Sample records for lander flight projects
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Robotic Lunar Landers for Science and Exploration
NASA Technical Reports Server (NTRS)
Chavers, D. G.; Cohen, B. A.; Bassler, J. A.; Hammond, M. S.; Harris, D. W.; Hill, L. A.; Eng, D.; Ballard, B. W.; Kubota, S. D.; Morse, B. J.;
2010-01-01
NASA Marshall Space Flight Center (MSFC) and The Johns Hopkins University Applied Physics Laboratory (APL) have been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. This paper describes some of the lunar lander concepts derived from these studies conducted by the MSFC/APL Robotic Lunar Lander Development Project team. In addition, the results to date of the lunar lander development risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing and combined GN&C and avionics testing will be addressed. The most visible elements of the risk reduction program are two autonomous lander flight test vehicles: a compressed air system with limited flight durations and a second version using hydrogen peroxide propellant to achieve significantly longer flight times and the ability to more fully exercise flight sensors and algorithms.
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NASA's International Lunar Network Anchor Nodes and Robotic Lunar Lander Project Update
NASA Technical Reports Server (NTRS)
Cohen, Barbara A.; Bassler, Julie A.; Ballard, Benjamin; Chavers, Greg; Eng, Doug S.; Hammond, Monica S.; Hill, Larry A.; Harris, Danny W.; Hollaway, Todd A.; Kubota, Sanae;
2010-01-01
NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory have been conducting mission studies and performing risk reduction activities for NASA's robotic lunar lander flight projects. Additional mission studies have been conducted to support other objectives of the lunar science and exploration community and extensive risk reduction design and testing has been performed to advance the design of the lander system and reduce development risk for flight projects.
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Robotic Lunar Lander Development Project Status
NASA Technical Reports Server (NTRS)
Hammond, Monica; Bassler, Julie; Morse, Brian
2010-01-01
This slide presentation reviews the status of the development of a robotic lunar lander. The goal of the project is to perform engineering tests and risk reduction activities to support the development of a small lunar lander for lunar surface science. This includes: (1) risk reduction for the flight of the robotic lander, (i.e., testing and analyzing various phase of the project); (2) the incremental development for the design of the robotic lander, which is to demonstrate autonomous, controlled descent and landing on airless bodies, and design of thruster configuration for 1/6th of the gravity of earth; (3) cold gas test article in flight demonstration testing; (4) warm gas testing of the robotic lander design; (5) develop and test landing algorithms; (6) validate the algorithms through analysis and test; and (7) tests of the flight propulsion system.
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Robotic Lunar Landers for Science and Exploration
NASA Technical Reports Server (NTRS)
Cohen, B. A.; Hill, L. A.; Bassler, J. A.; Chavers, D. G.; Hammond, M. S.; Harris, D. W.; Kirby, K. W.; Morse, B. J.; Mulac, B. D.; Reed, C. L. B.
2010-01-01
NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory has been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. In 2005, the Robotic Lunar Exploration Program Mission #2 (RLEP-2) was selected as a Exploration Systems Mission Directorate precursor robotic lunar lander mission to demonstrate precision landing and definitively determine if there was water ice at the lunar poles; however, this project was canceled. Since 2008, the team has been supporting NASA s Science Mission Directorate designing small lunar robotic landers for diverse science missions. The primary emphasis has been to establish anchor nodes of the International Lunar Network (ILN), a network of lunar science stations envisioned to be emplaced by multiple nations. This network would consist of multiple landers carrying instruments to address the geophysical characteristics and evolution of the moon. Additional mission studies have been conducted to support other objectives of the lunar science community and extensive risk reduction design and testing has been performed to advance the design of the lander system and reduce development risk for flight projects. This paper describes the current status of the robotic lunar mission studies that have been conducted by the MSFC/APL Robotic Lunar Lander Development team, including the ILN Anchor Nodes mission. In addition, the results to date of the lunar lander development risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing and combined GN&C and avionics testing will be addressed. The most visible elements of the risk reduction program are two autonomous lander test articles: a compressed air system with limited flight durations and a second version using hydrogen peroxide propellant to achieve significantly longer flight times and the ability to more fully exercise flight sensors and algorithms. Robotic Lunar Lander design and development will have significant feed-forward to other missions to the Moon and, indeed, to other airless bodies such as Mercury, asteroids, and Europa, to which similar science and exploration objectives are applicable.
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Robotic Lunar Landers For Science And Exploration
NASA Technical Reports Server (NTRS)
Cohen, B. A.; Bassler, J. A.; Morse, B. J.; Reed, C. L. B.
2010-01-01
NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory have been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. In 2005, the Robotic Lunar Exploration Program Mission #2 (RLEP-2) was selected as an ESMD precursor robotic lander mission to demonstrate precision landing and determine if there was water ice at the lunar poles; however, this project was canceled. Since 2008, the team has been supporting SMD designing small lunar robotic landers for science missions, primarily to establish anchor nodes of the International Lunar Network (ILN), a network of lunar geophysical nodes. Additional mission studies have been conducted to support other objectives of the lunar science community. This paper describes the current status of the MSFC/APL robotic lunar mission studies and risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing, combined GN&C and avionics testing, and two autonomous lander test articles.
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2013-12-10
CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the engine fires and the lander lifts off at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-10
CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the engine fires and the lander begins to lift off at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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Project Morpheus: Lessons Learned in Lander Technology Development
NASA Technical Reports Server (NTRS)
Olansen, Jon B.; Munday, Stephen R.; Mitchell, Jennifer D.
2013-01-01
NASA's Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing, that is designed to serve as a testbed for advanced spacecraft technologies. The lander vehicle, propelled by a LOX/Methane engine and sized to carry a 500kg payload to the lunar surface, provides a platform for bringing technologies from the laboratory into an integrated flight system at relatively low cost. Designed, developed, manufactured and operated in-house by engineers at Johnson Space Center, the initial flight test campaign began on-site at JSC less than one year after project start. After two years of testing, including two major upgrade periods, and recovery from a test crash that caused the loss of a vehicle, flight testing will evolve to executing autonomous flights simulating a 500m lunar approach trajectory, hazard avoidance maneuvers, and precision landing, incorporating the Autonomous Landing and Hazard Avoidance (ALHAT) sensor suite. These free-flights are conducted at a simulated planetary landscape built at Kennedy Space Center's Shuttle Landing Facility. The Morpheus Project represents a departure from recent NASA programs and projects that traditionally require longer development lifecycles and testing at remote, dedicated testing facilities. This paper expands on the project perspective that technologies offer promise, but capabilities offer solutions. It documents the integrated testing campaign, the infrastructure and testing facilities, and the technologies being evaluated in this testbed. The paper also describes the fast pace of the project, rapid prototyping, frequent testing, and lessons learned during this departure from the traditional engineering development process at NASA's Johnson Space Center.
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2013-12-10
CAPE CANAVERAL, Fla. – Preparations are underway to prepare the Project Morpheus prototype lander for its first free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-17
CAPE CANAVERAL, Fla. -- A technician prepares the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis
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2013-12-17
CAPE CANAVERAL, Fla. -- Preparations are underway to prepare the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis
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2013-12-17
CAPE CANAVERAL, Fla. -- Engineers and technicians prepare the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis
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2013-12-10
CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the lander’s engine fires at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-10
CAPE CANAVERAL, Fla. – Preparations are underway to prepare the Project Morpheus prototype lander for its first free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-17
CAPE CANAVERAL, Fla. -- A technician prepares the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis
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2013-12-10
CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the lander’s engine fires at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-17
CAPE CANAVERAL, Fla. -- Preparations are underway to prepare the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis
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2013-12-10
CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the lander’s engine fires at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-10
CAPE CANAVERAL, Fla. – Technicians and engineers prepare the Project Morpheus prototype lander for its first free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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Project Morpheus Main Engine Development and Preliminary Flight Testing
NASA Technical Reports Server (NTRS)
Morehead, Robert L.
2011-01-01
A LOX/Methane rocket engine was developed for a prototype terrestrial lander and then used to fly the lander at Johnson Space Center. The development path of this engine is outlined, including unique items such as variable acoustic damping and variable film cooling.
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NASA Technical Reports Server (NTRS)
Devolites, Jennifer L.; Olansen, Jon B.
2015-01-01
NASA's Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing that is designed to serve as a testbed for advanced spacecraft technologies. The lander vehicle, propelled by a Liquid Oxygen (LOX)/Methane engine and sized to carry a 500kg payload to the lunar surface, provides a platform for bringing technologies from the laboratory into an integrated flight system at relatively low cost. In 2012, Morpheus began integrating the Autonomous Landing and Hazard Avoidance Technology (ALHAT) sensors and software onto the vehicle in order to demonstrate safe, autonomous landing and hazard avoidance. From the beginning, one of goals for the Morpheus Project was to streamline agency processes and practices. The Morpheus project accepted a challenge to tailor the traditional NASA systems engineering approach in a way that would be appropriate for a lower cost, rapid prototype engineering effort, but retain the essence of the guiding principles. This paper describes the tailored project life cycle and systems engineering approach for the Morpheus project, including the processes, tools, and amount of rigor employed over the project's multiple lifecycles since the project began in fiscal year (FY) 2011.
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Morpheus Lander Testing Campaign
NASA Technical Reports Server (NTRS)
Hart, Jeremy J.; Mitchell, Jennifer D.
2011-01-01
NASA s Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing designed to serve as a testbed for advanced spacecraft technologies. The Morpheus vehicle has successfully performed a set of integrated vehicle test flights including hot-fire and tether tests, ultimately culminating in an un-tethered "free-flight" This development and testing campaign was conducted on-site at the Johnson Space Center (JSC), less than one year after project start. Designed, developed, manufactured and operated in-house by engineers at JSC, the Morpheus Project represents an unprecedented departure from recent NASA programs and projects that traditionally require longer development lifecycles and testing at remote, dedicated testing facilities. This paper documents the integrated testing campaign, including descriptions of test types (hot-fire, tether, and free-flight), test objectives, and the infrastructure of JSC testing facilities. A major focus of the paper will be the fast pace of the project, rapid prototyping, frequent testing, and lessons learned from this departure from the traditional engineering development process at NASA s Johnson Space Center.
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2012-07-19
CAPE CANAVERAL, Fla. - Just north of the Kennedy Space Center’s Shuttle Landing Facility, or SLF, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-16
CAPE CANAVERAL, Fla. –This panoramic view shows a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prot otype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. - Just north of the Kennedy Space Center’s Shuttle Landing Facility runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the launch platform for the Project Morpheus lander at the midfield point of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida. At the north end of the runway is a rock and crater-filled planetary scape built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the launch platform for the Project Morpheus lander at the midfield point of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida. At the north end of the runway is a rock and crater-filled planetary scape built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2013-12-04
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians prepare to load the Project Morpheus Prototype Lander with propellant at the launch platform located at the north end of the Shuttle Landing Facility. Morpheus is being prepared for a dress rehearsal of a tethered flight test. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-04
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians have loaded the Project Morpheus Prototype Lander with propellant at the launch platform located at the north end of the Shuttle Landing Facility. Morpheus is being prepared for a dress rehearsal of a tethered flight test. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-04
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander is attached to a tether at the launch platform located at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Morpheus is being prepared for a dress rehearsal of a tethered flight test. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the 15,000-foot long Shuttle Landing Facility at the Kennedy Space Center, Fla. At the north end of the runway, to the bottom, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s 15,000-foot long Shuttle Landing Facility. On the far left at the end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows a rock and crater-filled planetary scape that has been built at the north end of the Kennedy Space Center’s Shuttle Landing Facility. The site will allow engineers to test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway, in the upper right, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway, to the right, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the 15,000-foot long Shuttle Landing Facility at the Kennedy Space Center, Fla. At the north end of the runway, to the right, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. –This aerial view shows a rock and crater-filled planetary scape that has been built at the north end of the Kennedy Space Center’s Shuttle Landing Facility. The site will allow engineers to test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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Morpheus Alhat Integrated and Laser Test
2014-03-21
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for an automated landing and hazard avoidance technology, or ALHAT, and laser test at a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-14
CAPE CANAVERAL, Fla. – A flatbed truck carries the launch pad for the Project Morpheus prototype lander to a new location at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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Morpheus Alhat Integrated and Laser Test
2014-03-21
CAPE CANAVERAL, Fla. – Engineers run an automated landing and hazard avoidance technology, or ALHAT, and laser test on the Project Morpheus prototype lander at a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers assist as a crane lowers a portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers assist as a crane lowers a large portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2014-03-14
CAPE CANAVERAL, Fla. – A crane is used to lower the launch pad for the Project Morpheus prototype lander onto a new location at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad was moved to a different location to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers begin to reassemble the launch pad for the Project Morpheus prototype lander at a new location at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad was moved to a different location to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers attach a crane to part of the launch pad for the Project Morpheus prototype lander at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad will be moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - A forklift is used at the Kennedy Space Center in Florida to unload NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is inspected after unloading at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - Wheels are assembled for transporting NASA's Morpheus lander, a vertical test bed vehicle after its arrival at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is uncrated after unloading at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - A crane supports unloading of NASA's Morpheus lander, a vertical test bed vehicle, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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Mars Pathfinder mission operations concepts
NASA Technical Reports Server (NTRS)
Sturms, Francis M., Jr.; Dias, William C.; Nakata, Albert Y.; Tai, Wallace S.
1994-01-01
The Mars Pathfinder Project plans a December 1996 launch of a single spacecraft. After jettisoning a cruise stage, an entry body containing a lander and microrover will directly enter the Mars atmosphere and parachute to a hard landing near the sub-solar latitude of 15 degrees North in July 1997. Primary surface operations last for 30 days. Cost estimates for Pathfinder ground systems development and operations are not only lower in absolute dollars, but also are a lower percentage of total project costs than in past planetary missions. Operations teams will be smaller and fewer than typical flight projects. Operations scenarios have been developed early in the project and are being used to guide operations implementation and flight system design. Recovery of key engineering data from entry, descent, and landing is a top mission priority. These data will be recorded for playback after landing. Real-time tracking of a modified carrier signal through this phase can provide important insight into the spacecraft performance during entry, descent, and landing in the event recorded data is never recovered. Surface scenarios are dominated by microrover activity and lander imaging during 7 hours of the Mars day from 0700 to 1400 local solar time. Efficient uplink and downlink processes have been designed to command the lander and microrover each Mars day.
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Morpheus Vertical Test Bed Flight Testing
NASA Technical Reports Server (NTRS)
Hart, Jeremy; Devolites, Jennifer
2014-01-01
NASA's Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing, that is designed to serve as a testbed for advanced spacecraft technologies. The lander vehicle, propelled by a LOX/Methane engine and sized to carry a 500kg payload to the lunar surface, provides a platform for bringing technologies from the laboratory into an integrated flight system at relatively low cost. Morpheus onboard software is autonomous from ignition all the way through landing, and is designed to be capable of executing a variety of flight trajectories, with onboard fault checks and automatic contingency responses. The Morpheus 1.5A vehicle performed 26 integrated vehicle test flights including hot-fire tests, tethered tests, and two attempted freeflights between April 2011 and August 2012. The final flight of Morpheus 1.5A resulted in a loss of the vehicle. In September 2012, development began on the Morpheus 1.5B vehicle, which subsequently followed a similar test campaign culminating in free-flights at a simulated planetary landscape built at Kennedy Space Center's Shuttle Landing Facility. This paper describes the integrated test campaign, including successes and setbacks, and how the system design for handling faults and failures evolved over the course of the project.
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows the Shuttle Landing Facility’s air traffic control tower at the Kennedy Space Center in Florida. Just below the tower is the mid-field park site used for runway support vehicles. At the north end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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The MASSE Project: Applications of Biotechnology for Planetary Exploration
NASA Technical Reports Server (NTRS)
Lynch, Kennda; Steele, Andrew; Hedgecock, Jud; Wainwright, Norm; McKay, David S.; Maule, Jake; Schweitzer, Mary
2003-01-01
Automated life-detection experiments for solar system exploration have been previously. proposed and used onboard the. Viking, Mars lander,s, although. with ambiguous results. The recent advances in biotechnology such as biosensors, protein microarrays, and microfluidics alongside increased. knowledge in biomarker science have led to vastly improved sophistication and sensitivity for a new approach in life detection. The MASSE project has taken the challenge of integrating all of this knowledge into a new generation of interplanetary flight instrumentation for the main purpose.ot combining several mutually. confirming tests for life, organic/microbial contamination, prebiotic and abiotic chemicals into a small low powered instrument. Although the primary goal is interplanetary exploration, several terrestrial applications have become apparent specifically in point-of-care medical technology, bio-warfare, environmental sensing and microbial monitoring of manned space-flight vehicles.
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - Technicians secure connections for a crane which will be used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, arrives at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being moved out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-27
CAPE CANAVERAL, Fla. - A truck transporting NASA's Morpheus lander, a vertical test bed vehicle, arrives at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for unloading. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out from its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being moved out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out from its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-27
CAPE CANAVERAL, Fla. - A truck transporting NASA's Morpheus lander, a vertical test bed vehicle, heads towards the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for unloading. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-27
CAPE CANAVERAL, Fla. - Support equipment for NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-27
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-31
CAPE CANAVERAL, Fla. - Technicians set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-08-03
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, NASA Administrator Charles Bolden, left, joins Dr. Jon Olansen, Morpheus project manager, in the control room at the Shuttle Landing Facility for the first tethered flight of the Morpheus lander. After undergoing testing at Johnson Space Center in Houston for nearly a year, Morpheus arrived at Kennedy on July 27 to begin about three months of tests. A field, replete with boulders, rocks, slopes, craters and hazards to avoid, was created at the north end of Kennedy's runway to provide a realistic landscape for test flights of the lander. Morpheus utilizes autonomous landing and hazard avoidance technology, or ALHAT, to navigate to a safe landing site during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA's Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2012-08-03
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, NASA Administrator Charles Bolden joins Morpheus project manager Dr. Jon Olansen, pointing at monitor, in the control room at the Shuttle Landing Facility for the first tethered flight of the Morpheus lander. After undergoing testing at Johnson Space Center in Houston for nearly a year, Morpheus arrived at Kennedy on July 27 to begin about three months of tests. A field, replete with boulders, rocks, slopes, craters and hazards to avoid, was created at the north end of Kennedy's runway to provide a realistic landscape for test flights of the lander. Morpheus utilizes autonomous landing and hazard avoidance technology, or ALHAT, to navigate to a safe landing site during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA's Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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2013-08-30
CAPE CANAVERAL, Fla. - Workers install a flame deflector at the Shuttle Landing Facility, or SLF, at NASA's Kennedy Space Center in Florida for the Project Morpheus lander. The site is adjacent to a hazard field created to support the project at the north end of the SLF. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for a free flight at Kennedy later this year. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst obstacles during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html. Photo credit: NASA/Kim Shiflett
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Morpheus Alhat Integrated and Laser Test
2014-03-21
CAPE CANAVERAL, Fla. – A crane lowers the Project Morpheus prototype lander onto a launch pad at a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Engineers and technicians are preparing Morpheus for an automated landing and hazard avoidance technology, or ALHAT, and laser test at the new launch site. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus Alhat Integrated and Laser Test
2014-03-21
CAPE CANAVERAL, Fla. – Engineers and technicians wearing safety goggles, prepare the Project Morpheus prototype lander for an automated landing and hazard avoidance technology, or ALHAT, and laser test at a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers assist as a crane is used to lift a large portion of the launch pad for the Project Morpheus prototype lander onto a transporter at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad is being moved to a different location at the landing facility to support the next phase of flight testing. Morpheus completed its seventh free flight test on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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2014-03-14
CAPE CANAVERAL, Fla. – Construction workers monitor the progress as a crane is used to lift a portion of the launch pad for the Project Morpheus prototype lander at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The launch pad will be moved to a different location at the landing facility to support the next phase of flight testing. The seventh free flight test of Morpheus occurred on March 11. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces . The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Dimitri Gerondidakis
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NASA Technical Reports Server (NTRS)
Chavers, Greg
2015-01-01
Since 2006 NASA has been formulating robotic missions to the lunar surface through programs and projects like the Robotic Lunar Exploration Program, Lunar Precursor Robotic Program, and International Lunar Network. All of these were led by NASA Marshall Space Flight Center (MSFC). Due to funding shortfalls, the lunar missions associated with these efforts, the designs, were not completed. From 2010 to 2013, the Robotic Lunar Lander Development Activity was funded by the Science Mission Directorate (SMD) to develop technologies that would enable and enhance robotic lunar surface missions at lower costs. In 2013, a requirements-driven, low-cost robotic lunar lander concept was developed for the Resource Prospector Mission. Beginning in 2014, The Advanced Exploration Systems funded the lander team and established the MSFC, Johnson Space Center, Applied Physics Laboratory, and the Jet Propulsion Laboratory team with MSFC leading the project. The lander concept to place a 300-kg rover on the lunar surface has been described in the New Technology Report Case Number MFS-33238-1. A low-cost lander concept for placing a robotic payload on the lunar surface is shown in figures 1 and 2. The NASA lander team has developed several lander concepts using common hardware and software to allow the lander to be configured for a specific mission need. In addition, the team began to transition lander expertise to United States (U.S.) industry to encourage the commercialization of space, specifically the lunar surface. The Lunar Cargo Transportation and Landing by Soft Touchdown (CATALYST) initiative was started and the NASA lander team listed above is partnering with three competitively selected U.S. companies (Astrobotic, Masten Space Systems, and Moon Express) to develop, test, and operate their lunar landers.
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2012-07-19
CAPE CANAVERAL, Fla. – This aerial view shows a 50,000-square-foot hangar located on the Shuttle Landing Facility at the Kennedy Space Center, Fla., providing shelter and storage for NASA and non-NASA aircraft and maintenance operations. Adjacent to the hangar is an operations building housing personnel who support operations at the 15,000-foot long concrete runway. At the north end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander soars 800 feet above the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida on free flight test No. 15 at. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander soars 800 feet above the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida on free flight test No. 15 at. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander soars overhead during free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander soars 800 feet above the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida on free flight test No. 15. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander soars overhead during free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-01-21
CAPE CANAVERAL, Fla. – Technicians and engineers perform safing procedures on the Project Morpheus prototype lander after it touched down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. The lander successfully completed its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett
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Fast Paced, Low Cost Projects at MSFC
NASA Technical Reports Server (NTRS)
Watson-Morgan, Lisa; Clinton, Raymond
2012-01-01
What does an orbiting microsatellite, a robotic lander and a ruggedized camera and telescope have in common? They are all fast paced, low cost projects managed by Marshall Space Flight Center (MSFC) teamed with successful industry partners. MSFC has long been synonymous with human space flight large propulsion programs, engineering acumen and risk intolerance. However, there is a growing portfolio/product line within MSFC that focuses on these smaller, fast paced projects. While launching anything into space is expensive, using a managed risk posture, holding to schedule and keeping costs low by stopping at egood enough f were key elements to their success. Risk is defined as the possibility of loss or failure per Merriam Webster. The National Aeronautics and Space Administration (NASA) defines risk using procedural requirement 8705.4 and establishes eclasses f to discern the acceptable risk per a project. It states a Class D risk has a medium to significant risk of not achieving mission success. MSFC, along with industry partners, has created a niche in Class D efforts. How did the big, cautious MSFC succeed on these projects that embodied the antithesis of its heritage in human space flight? A key factor toward these successful projects was innovative industry partners such as Dynetics Corporation, University of Alabama in Huntsville (UAHuntsville), Johns Hopkins Applied Physics Laboratory (JHU APL), Teledyne Brown Engineering (TBE), Von Braun Center for Science and Innovation (VCSI), SAIC, and Jacobs. Fast Affordable Satellite Technology (FastSat HSV01) is a low earth orbit microsatellite that houses six instruments with the primary scientific objective of earth observation and technology demonstration. The team was comprised of Dynetics, UAHuntsvile, SAIC, Goddard Space Flight Center (GSFC) and VCSI with the United States Air Force Space Test Program as the customer. The team completed design, development, manufacturing, environmental test and integration in one year. FastSat HSV01 also deployed a Poly Picosatellite Orbital Deployer (PPOD) for a separate nano ]satellite class spacecraft (Cubesat: Nano Sail Demonstration) in partnership with Ames Research Center. The Robotic lunar lander is a MSFC JHU APL partnership that led to the development of a flexible architecture for landers to support robotic missions to a wide range of lunar and asteroid destinations. The team started with the goal of meeting NASA agency directives that led to the creation of a test bed focusing on GN&C and software to demonstrate the descent and landing on any airless body for the final 30 to 60 meters. The team created a complex technology demonstration as well as Guidance Control and Navigation (GN&C) algorithms providing autonomous control of the lander. The team uses a green propellant of 90% hydrogen peroxide and has completed 18 successful test flights. The International Space Station (ISS) SERVIR Environmental Research and Visualization System (ISERV) is a technology demonstration payload to assist the SERVIR project with environmental monitoring for disaster relief and humanitarian efforts. The ISERV project was a partnership with TBE. The ISERV payload consists of a commercial off the shelf camera, telescope, and MSFC developed power distribution box and interfaces on ISS with the Window Observational Research Facility in the US Lab. MSFC has identified three key areas that enabled the low cost mission success to include culture, partnering, and cost/schedule control. This paper will briefly discuss these three Class D efforts, FastSat HSV-01, the Robotic Lunar Lander and the ISERV camera system, the lessons learned, their successes and challenges.
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander is enveloped in a cloud of dust as it takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander is enveloped in a cloud of dust as it takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander is moved into position at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida in preparation for free flight test No. 15. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA/Jim Grossman
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander rises above a cloud of dust as it takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander is enveloped in a cloud of dust as it takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander comes to rest after a successful landing, capping free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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2014-12-15
CAPE CANAVERAL, Fla. – Engineers and technicians prepare NASA's Project Morpheus prototype lander for free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA/Jim Grossman
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2014-12-15
CAPE CANAVERAL, Fla. – NASA’s Project Morpheus prototype lander is enveloped in a cloud of dust as it takes off on free flight test No. 15 at the north end of the Shuttle Landing Facility at Kennedy Space Center in Florida. During the 97-second test, onboard autonomous landing and hazard avoidance technology sensors, or ALHAT, surveyed the hazard field for safe landing sites, then guided the lander forward and downward to a successful landing. For more information on Morpheus, visit: http://www.morpheuslander.jsc.nasa.gov. Photo credit: NASA
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Morpheus Campaign 2A Tether Test
2014-03-27
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is positioned near a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida for a tethered test. The test will be performed to verify the lander's recently installed autonomous landing and hazard avoidance technology, or ALHAT, sensors and integration system. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Glenn Benson
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2014-01-21
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander is transported to a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The prototype lander is being prepared for its fourth free flight test at Kennedy. Morpheus will launch from the ground over a flame trench and then descend and land on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Cory Huston
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2014-01-21
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander is being lifted by crane for positioning on a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The prototype lander is being prepared for its fourth free flight test at Kennedy. Morpheus will launch from the ground over a flame trench and then descend and land on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Cory Huston
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2014-03-05
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high and moves forward after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander ascends on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-03-05
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-01-21
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touches down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field after launching on its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett
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2014-03-05
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touches down in the automated landing and hazard avoidance technology, or ALHAT, hazard field after completing its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-01-21
CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touched down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field after launching on its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett
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Conceptual definition of a 50-100 kWe NEP system for planetary science missions
NASA Technical Reports Server (NTRS)
Friedlander, Alan
1993-01-01
The Phase 1 objective of this project is to assess the applicability of a common Nuclear Electric Propulsion (NEP) flight system of the 50-100 kWe power class to meet the advanced transportation requirements of a suite of planetary science (robotic) missions, accounting for differences in mission-specific payloads and delivery requirements. The candidate missions are as follows: (1) Comet Nucleus Sample Return; (2) Multiple Mainbelt Asteroid Rendezvous; (3) Jupiter Grand Tour (Galilean satellites and magnetosphere); (4) Uranus Orbiter/Probe (atmospheric entry and landers); (5) Neptune Orbiter/Probe (atmospheric entry and landers); and (6) Pluto-Charon Orbiter/Lander. The discussion is presented in vugraph form.
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2012-07-30
CAPE CANAVERAL, Fla. - Russell Romanella, director of Safety and Mission Assurance at NASA's Kennedy Space Center in Florida, right, is briefed on NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is being checked out by technicians and engineers in a building at the Shuttle Landing Facility, or SLF, at Kennedy. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - Russell Romanella, director of Safety and Mission Assurance at NASA's Kennedy Space Center in Florida, center, is briefed on NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is being checked out by technicians and engineers in a building at the Shuttle Landing Facility, or SLF, at Kennedy. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - Russell Romanella, director of Safety and Mission Assurance at NASA's Kennedy Space Center in Florida, right-center, is briefed on NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is being checked out by technicians and engineers in a building at the Shuttle Landing Facility, or SLF, at Kennedy. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - Russell Romanella, director of Safety and Mission Assurance at NASA's Kennedy Space Center in Florida, kneeling on the left, is briefed on NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is being checked out by technicians and engineers in a building at the Shuttle Landing Facility, or SLF, at Kennedy. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-07-30
CAPE CANAVERAL, Fla. - Russell Romanella, director of Safety and Mission Assurance at NASA's Kennedy Space Center in Florida, left, is briefed on NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is being checked out by technicians and engineers in a building at the Shuttle Landing Facility, or SLF, at Kennedy. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis
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2012-08-09
CAPE CANAVERAL, Fla. – At the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida, the Morpheus prototype lander begins to lift off of the ground during a free-flight test. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. Morpheus was manufactured and assembled at JSC and Armadillo Aerospace. Morpheus is large enough to carry 1,100 pounds of cargo to the moon – for example, a humanoid robot, a small rover, or a small laboratory to convert moon dust into oxygen. The primary focus of the test is to demonstrate an integrated propulsion and guidance, navigation and control system that can fly a lunar descent profile to exercise the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, safe landing sensors and closed-loop flight control. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA
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2014-12-11
CAPE CANAVERAL, Fla. – NASA Project Morpheus prototype lander is being lifted by crane during preparations for free flight test number 15 at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-10
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is being transported to the north end of the Shuttle Landing Facility for free flight test number 15 at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-10
CAPE CANAVERAL, Fla. – Engineers and technicians prepare NASA's Project Morpheus prototype lander for free flight test number 15 on a launch pad at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-11
CAPE CANAVERAL, Fla. – Engineers and technicians prepare NASA's Project Morpheus prototype lander for free flight test number 15 at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-11
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is prepared for transport to the north end of the Shuttle Landing Facility for free flight test number 15 at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-11
CAPE CANAVERAL, Fla. – Engineers and technicians prepare NASA's Project Morpheus prototype lander for free flight test number 15 at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-10
CAPE CANAVERAL, Fla. – NASA Project Morpheus prototype lander and support equipment are being transported to the north end of the Shuttle Landing Facility for free flight test number 15 at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2012-08-01
CAPE CANAVERAL, Fla. - At a hangar near the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, Chirold Epp, Johnson Space Center Project Manager for ALHAT, speaks to members of the media. In the background is the Morpheus prototype lander, which arrived at Kennedy on July 27. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2012-08-01
CAPE CANAVERAL, Fla. - At a hangar near the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, the Johnson Space Center Project Morpheus Manager Jon Olansen speaks to members of the media. In the foreground is the Morpheus prototype lander, which arrived at Kennedy on July 27. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2012-08-01
CAPE CANAVERAL, Fla. - At a hangar near the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, the Johnson Space Center Project Morpheus Manager Jon Olansen speaks to members of the media. In the background is the Morpheus prototype lander, which arrived at Kennedy on July 27. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2012-08-01
CAPE CANAVERAL, Fla. - At a hangar near the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, members of the media view the Morpheus prototype lander and speak with Morpheus managers. In front is Gregory Gaddis, Kennedy Project Morpheus/ALHAT site manager. To his left, are Jon Olansen, Johnson Space Center Project Morpheus manager and Chirold Epp, JSC ALHAT project manager. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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NASA's International Lunar Network Anchor Nodes and Robotic Lunar Lander Project Update
NASA Technical Reports Server (NTRS)
Morse, Brian J.; Reed, Cheryl L. B.; Kirby, Karen W.; Cohen, Barbara A.; Bassler, Julie A.; Harris, Danny W.; Chavers, D. Gregory
2010-01-01
In early 2008, NASA established the Lunar Quest Program, a new lunar science research program within NASA s Science Mission Directorate. The program included the establishment of the anchor nodes of the International Lunar Network (ILN), a network of lunar science stations envisioned to be emplaced by multiple nations. This paper describes the current status of the ILN Anchor Nodes mission development and the lander risk-reduction design and test activities implemented jointly by NASA s Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory. The lunar lander concepts developed by this team are applicable to multiple science missions, and this paper will describe a mission combining the functionality of an ILN node with an investigation of lunar polar volatiles.
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2014-01-21
CAPE CANAVERAL, Fla. – Technicians and engineers monitor the progress as the Project Morpheus prototype lander is lifted by crane for positioning on a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The prototype lander is being prepared for its fourth free flight test at Kennedy. Morpheus will launch from the ground over a flame trench and then descend and land on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Cory Huston
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2014-01-21
CAPE CANAVERAL, Fla. – Technicians monitor the progress as the Project Morpheus prototype lander is lifted by crane for positioning on a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The prototype lander is being prepared for its fourth free flight test at Kennedy. Morpheus will launch from the ground over a flame trench and then descend and land on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Cory Huston
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander soars high on its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander soars high on its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander soars high on its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - Technicians prepare the Project Morpheus prototype lander for its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - Engineers and technicians prepare the Project Morpheus prototype lander for its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander touches down in the automated landing and hazard avoidance technology, or ALHAT, hazard field after completing its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander soars high on its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - Preparations are underway to prepare the Project Morpheus prototype lander for its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander is transported to the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida for the seventh free flight test. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander begins to ascend on its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Mike Chambers
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander has been attached to a tether and is being raised from a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The tethered test includes lifting the lander 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander has been attached to a tether and is being prepared for a tether test on a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The tether test includes lifting the lander 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander is being prepared for placement on a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The lander will be prepared for a tethered test that includes lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2014-01-17
CAPE CANAVERAL, Fla. – Members of the news media view the Project Morpheus prototype lander inside a hangar near the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Speaking to the media, from left are Jon Olansen, Morpheus project manager at Johnson Space Center in Houston, and Greg Gaddis, the Kennedy Morpheus and ALHAT site manager. Morpheus successfully completed its third free flight test Jan. 16. The 57-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 187 feet, nearly doubling the target ascent velocity from the last test in December 2013. The lander flew forward, covering about 154 feet in 20 seconds before descending and landing within 11 inches of its target on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, a team of engineers and technicians assist as a tether is used to lower the Project Morpheus prototype lander onto a launch platform at the north end of the Shuttle Landing Facility. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, a team of engineers and technicians assist as a tether is used to move the Project Morpheus prototype lander to a launch platform at the north end of the Shuttle Landing Facility. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, technicians prepare the Project Morpheus prototype lander to be transported from a support building to a launch platform at the north end of the Shuttle Landing Facility. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, a team of engineers and technicians attaches a tether to the Project Morpheus prototype lander near the north end of the Shuttle Landing Facility. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for Morpheus’ tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, a convoy of vehicles accompanies the Project Morpheus prototype lander as it is transported to a launch platform at the north end of the Shuttle Landing Facility. Testing of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-03
CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander is prepared for its move from a support building to a launch platform at the north end of the Shuttle Landing Facility. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for a tether test near a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is positioned near a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida for a tether test. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – A technician prepares the Project Morpheus prototype lander for a tether test near a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Robotic Lunar Lander Development Status
NASA Technical Reports Server (NTRS)
Ballard, Benjamin; Cohen, Barbara A.; McGee, Timothy; Reed, Cheryl
2012-01-01
NASA Marshall Space Flight Center and John Hopkins University Applied Physics Laboratory have developed several mission concepts to place scientific and exploration payloads ranging from 10 kg to more than 200 kg on the surface of the moon. The mission concepts all use a small versatile lander that is capable of precision landing. The results to date of the lunar lander development risk reduction activities including high pressure propulsion system testing, structure and mechanism development and testing, and long cycle time battery testing will be addressed. The most visible elements of the risk reduction program are two fully autonomous lander flight test vehicles. The first utilized a high pressure cold gas system (Cold Gas Test Article) with limited flight durations while the subsequent test vehicle, known as the Warm Gas Test Article, utilizes hydrogen peroxide propellant resulting in significantly longer flight times and the ability to more fully exercise flight sensors and algorithms. The development of the Warm Gas Test Article is a system demonstration and was designed with similarity to an actual lunar lander including energy absorbing landing legs, pulsing thrusters, and flight-like software implementation. A set of outdoor flight tests to demonstrate the initial objectives of the WGTA program was completed in Nov. 2011, and will be discussed.
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NASA's Robotic Lunar Lander Development Program
NASA Technical Reports Server (NTRS)
Ballard, Benjamin W.; Reed, Cheryl L. B.; Artis, David; Cole, Tim; Eng, Doug S.; Kubota, Sanae; Lafferty, Paul; McGee, Timothy; Morese, Brian J.; Chavers, Gregory;
2012-01-01
NASA Marshall Space Flight Center and the Johns Hopkins University Applied Physics Laboratory have developed several mission concepts to place scientific and exploration payloads ranging from 10 kg to more than 200 kg on the surface of the moon. The mission concepts all use a small versatile lander that is capable of precision landing. The results to date of the lunar lander development risk reduction activities including high pressure propulsion system testing, structure and mechanism development and testing, and long cycle time battery testing will be addressed. The most visible elements of the risk reduction program are two fully autonomous lander flight test vehicles. The first utilized a high pressure cold gas system (Cold Gas Test Article) with limited flight durations while the subsequent test vehicle, known as the Warm Gas Test Article, utilizes hydrogen peroxide propellant resulting in significantly longer flight times and the ability to more fully exercise flight sensors and algorithms. The development of the Warm Gas Test Article is a system demonstration and was designed with similarity to an actual lunar lander including energy absorbing landing legs, pulsing thrusters, and flight-like software implementation. A set of outdoor flight tests to demonstrate the initial objectives of the WGTA program was completed in Nov. 2011, and will be discussed.
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2014-12-11
CAPE CANAVERAL, Fla. – Engineers and controllers in a mobile control room prepare for flight number 15 of NASA's Project Morpheus prototype lander at the north end of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-11
CAPE CANAVERAL, Fla. – Engineers and technicians prepare the launch pad for NASA's Project Morpheus prototype lander at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Morpheus is being prepared for free flight test number 15 at the SLF. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-10
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is being transported from a hangar at the Shuttle Landing Facility, or SLF, for free flight test number 15 at the north end of the SLF at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-10
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is being lowered by crane onto a launch pad at the north end of the Shuttle Landing Facility in preparation for free flight test number 15 at NASA’s Kennedy Space Center in Florida. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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2014-12-11
CAPE CANAVERAL, Fla. – Engineers and technicians prepare NASA's Project Morpheus prototype lander for free flight test number 15 on a launch pad at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Morpheus is being lowered by crane onto the launch pad. The lander will take off from the ground over a flame trench and use its autonomous landing and hazard avoidance technology, or ALHAT sensors, to survey the hazard field to determine safe landing sites. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Jim Grossmann
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Integration Testing of Space Flight Systems
NASA Technical Reports Server (NTRS)
Honeycutt, Timothy; Sowards, Stephanie
2008-01-01
Based on the previous success' of Multi-Element Integration Testing (MEITs) for the International Space Station Program, these type of integrated tests have also been planned for the Constellation Program: MEIT (1) CEV to ISS (emulated) (2) CEV to Lunar Lander/EDS (emulated) (3) Future: Lunar Surface Systems and Mars Missions Finite Element Integration Test (FEIT) (1) CEV/CLV (2) Lunar Lander/EDS/CaL V Integrated Verification Tests (IVT) (1) Performed as a subset of the FEITs during the flight tests and then performed for every flight after Full Operational Capability (FOC) has been obtained with the flight and ground Systems.
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - Engineers and technicians assist as a crane lowers the Project Morpheus prototype lander in preparation for its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the automated landing and hazard avoidance technology ALHAT hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - An engineer checks the Project Morpheus prototype lander after it landed in the automated landing and hazard avoidance technology, or ALHAT, hazard field, completing its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus 1C preps & post launch activities
2014-03-11
CAPE CANAVERAL, Fla. - The Project Morpheus prototype lander lifts off in the automated landing and hazard avoidance technology, or ALHAT, hazard field for its seventh free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 83-second test began at 3:41 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending to 580 feet, its highest to date. Morpheus then flew its fastest downrange trek at 30 mph, travelling farther than before, 837 feet. The lander performed a 42-foot divert to emulate a hazard avoidance maneuver before descending and touching down on Landing Site 2, at the northern landing pad inside the hazard field. Morpheus landed within one foot of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander has been attached to a tether and is being prepared for placement on a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The lander will be prepared for a tethered test that includes lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians and engineers assist as the Project Morpheus prototype lander is attached to a tether and lowered onto a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The lander will be prepared for a tethered test that includes lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, smoke fills the air as the Project Morpheus prototype lander’s engine fires during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet. The lander will maneuver backwards 10 feet, and then fly forward and descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander has been attached to a tether and is being lowered onto a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The lander will be prepared for a tethered test that includes lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett
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Viking lander spacecraft battery
NASA Technical Reports Server (NTRS)
Newell, D. R.
1976-01-01
The Viking Lander was the first spacecraft to fly a sterilized nickel-cadmium battery on a mission to explore the surface of a planet. The significant results of the battery development program from its inception through the design, manufacture, and test of the flight batteries which were flown on the two Lander spacecraft are documented. The flight performance during the early phase of the mission is also presented.
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Viking Lander spacecraft battery. Final report
DOE Office of Scientific and Technical Information (OSTI.GOV)
Newell, D.R.
1976-09-01
The Viking Lander was the first spacecraft to fly a sterilized nickel--cadmium battery on a mission to explore the surface of a planet. The significant results of the battery development program from its inception through the design, manufacture, and test of the flight batteries which were flown on the two Lander spacecraft are documented. The flight performance during the early phase of the mission is also presented.
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NASA Technical Reports Server (NTRS)
Hurlbert, Eric; Morehead, Robert; Melcher, John C.; Atwell, Matt
2016-01-01
An integrated liquid oxygen (LOx) and methane propulsion system where common propellants are fed to the reaction control system and main engines offers advantages in performance, simplicity, reliability, and reusability. LOx/Methane provides new capabilities to use propellants that are manufactured on the Mars surface for ascent return and to integrate with power and life support systems. The clean burning, non-toxic, high vapor pressure propellants provide significant advantages for reliable ignition in a space vacuum, and for reliable safing or purging of a space-based vehicle. The NASA Advanced Exploration Systems (AES) Morpheus lander demonstrated many of these key attributes as it completed over 65 tests including 15 flights through 2014. Morpheus is a prototype of LOx/Methane propellant lander vehicle with a fully integrated propulsion system. The Morpheus lander flight demonstrations led to the proposal to use LOx/Methane for a Discovery class mission, named Moon Aging Regolith Experiment (MARE) to land an in-situ science payload for Southwest Research Institute on the Lunar surface. Lox/Methane is extensible to human spacecraft for many transportation elements of a Mars architecture. This paper discusses LOx/Methane propulsion systems in regards to trade studies, the Morpheus project experience, the MARE NAVIS (NASA Autonomous Vehicle for In-situ Science) lander, and future possible applications. The paper also discusses technology research and development needs for Lox/Methane propulsion systems.
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – Technicians watch as a crane lowers the Project Morpheus prototype lander onto a launch pad at a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Preparations are underway for a tether test. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – A crane lowers the Project Morpheus prototype lander onto a launch pad at a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Preparations are underway for a tether test. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – Engineers and technicians monitor the progress as a crane lifts the Project Morpheus prototype lander off the ground for a tether test near a new launch site at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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Morpheus Alhat Tether Test Preparations
2014-03-27
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is positioned near a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida for a tether test. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s automated landing and hazard avoidance technology, or ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. In the foreground of the photo is the ALHAT field. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Ben Smegelsky
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InSight Planetary Protection Status
NASA Astrophysics Data System (ADS)
Benardini, James; La Duc, Myron; Willis, Jason
The NASA Discovery Program’s next mission, Interior Exploration using Seismic Investigations, Geodesy and Heat Transport (InSIght), consists of a single spacecraft that will be launched aboard an Atlas V 401 rocket from Vandenberg Air Force Base (Space Launch Complex 3E) during the March 2016 timeframe. The overarching mission goal is to illuminate the fundamentals of formation and evolution of terrestrial planets by investigating the interior structure and processes of Mars. The flight system consists of a heritage cruise stage, aeroshell (heatshield and backshell), and Lander from the 2008 Phoenix mission. Included in the lander payload are various cameras, a seismometer, an auxiliary sensor suite to measure wind, temperature, and pressure, and a mole to penetrate the regolith (<5 meters) and assess the subsurface geothermal gradient of Mars. Being a Mars lander mission without life detection instruments, InSight has been designated a PP Category Iva mission. As such, planetary protection bioburden requirements apply which require microbial reduction procedures and biological burden reporting. The InSight project is current with required PP documentation, having completed an approved Planetary Protection Plan, Subsidiary PP Plans, and a PP Implementation Plan. The InSight mission’s early planetary protection campaign has commenced, coinciding with the fabrication and assembly of payload and flight system hardware and the baseline analysis of existing flight spares. A report on the status of InSight PP activities will be provided.
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NASA-STD-(I)-6016, Standard Materials and Processes Requirements for Spacecraft
NASA Technical Reports Server (NTRS)
Pedley, Michael; Griffin, Dennis
2006-01-01
This document is directed toward Materials and Processes (M&P) used in the design, fabrication, and testing of flight components for all NASA manned, unmanned, robotic, launch vehicle, lander, in-space and surface systems, and spacecraft program/project hardware elements. All flight hardware is covered by the M&P requirements of this document, including vendor designed, off-the-shelf, and vendor furnished items. Materials and processes used in interfacing ground support equipment (GSE); test equipment; hardware processing equipment; hardware packaging; and hardware shipment shall be controlled to prevent damage to or contamination of flight hardware.
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Project Morpheus: Morpheus 1.5A Lander Failure Investigation Results
NASA Technical Reports Server (NTRS)
Devolites, Jennifer L.; Olansen, Jon B.; Munday, Stephen R.
2013-01-01
On August 9, 2012 the Morpheus 1.5A vehicle crashed shortly after lift off from the Kennedy Space Center. The loss was limited to the vehicle itself which was pre-declared to be a test failure and not a mishap. The Morpheus project is demonstrating advanced technologies for in space and planetary surface vehicles including: autonomous flight control, landing site hazard identification and safe site selection, relative surface and hazard navigation, precision landing, modular reusable flight software, and high performance, non-toxic, cryogenic liquid Oxygen and liquid Methane integrated main engine and attitude control propulsion system. A comprehensive failure investigation isolated the fault to the Inertial Measurement Unit (IMU) data path to the flight computer. Several improvements have been identified and implemented for the 1.5B and 1.5C vehicles.
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Multibody Modeling and Simulation for the Mars Phoenix Lander Entry, Descent and Landing
NASA Technical Reports Server (NTRS)
Queen, Eric M.; Prince, Jill L.; Desai, Prasun N.
2008-01-01
A multi-body flight simulation for the Phoenix Mars Lander has been developed that includes high fidelity six degree-of-freedom rigid-body models for the parachute and lander system. The simulation provides attitude and rate history predictions of all bodies throughout the flight, as well as loads on each of the connecting lines. In so doing, a realistic behavior of the descending parachute/lander system dynamics can be simulated that allows assessment of the Phoenix descent performance and identification of potential sensitivities for landing. This simulation provides a complete end-to-end capability of modeling the entire entry, descent, and landing sequence for the mission. Time histories of the parachute and lander aerodynamic angles are presented. The response of the lander system to various wind models and wind shears is shown to be acceptable. Monte Carlo simulation results are also presented.
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The Tailoring of Traditional Systems Engineering for the Morpheus Project
NASA Technical Reports Server (NTRS)
Devolites, Jennifer L.; Hart, Jeremy J.
2013-01-01
NASA's Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing that is designed to serve as a testbed for advanced spacecraft technologies. The lander vehicle, propelled by a LOX/Methane engine and sized to carry a 500kg payload to the lunar surface, provides a platform for bringing technologies from the laboratory into an integrated flight system at relatively low cost. From the beginning, one of goals for the Morpheus Project was to streamline agency processes and practices. The Morpheus project accepted a challenge to tailor the traditional NASA systems engineering approach in a way that would be appropriate for a lower cost, rapid prototype engineering effort, but retain the essence of the guiding principles. The team has produced innovative ways to create an infrastructure and approach that would challenge existing systems engineering processes while still enabling successful implementation of the current Morpheus Project. This paper describes the tailored systems engineering approach for the Morpheus project, including the processes, tools, and amount of rigor employed over the project's multiple lifecycles since the project began in FY11. Lessons learned from these trials have the potential to be scaled up and improve efficiency on a larger projects or programs.
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander has been lifted by a tether and hovers above a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The lander’s engine begins firing for a tethered test that includes lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander’s engine begins to fire during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander is lifted 20 feet by crane, and will ascend another 10 feet, maneuver backwards 10 feet, and then fly forward and descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Project Morpheus prototype lander’s engine has completed its firing during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet, maneuvered backwards 10 feet, and then flew forward. It will descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, smoke fills the air as the Project Morpheus prototype lander’s engine fires during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet, maneuvered backwards 10 feet, and then flew forward. It will descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, smoke fills the air as the Project Morpheus prototype lander’s engine fires during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet, maneuvered backwards 10 feet, and then flew forward. It will descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, smoke fills the air as the Project Morpheus prototype lander’s engine fires during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet, maneuvered backwards 10 feet, and then flew forward. It will descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2013-12-06
CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, smoke fills the air as the Project Morpheus prototype lander’s engine fires during a tether test at the north end of the Shuttle Landing Facility. During the test, the lander was lifted 20 feet by crane, and then ascended another 10 feet, maneuvered backwards 10 feet, and then flew forward. It will descend to its original position, landing at the end of the tether onto a transportable launch platform. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2014-01-21
CAPE CANAVERAL, Fla. – Technicians monitor the progress as a crane lowers the Project Morpheus prototype for positioning on a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The prototype lander is being prepared for its fourth free flight test at Kennedy. Morpheus will launch from the ground over a flame trench and then descend and land on a dedicated pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Cory Huston
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Lander Propulsion Overview and Technology Requirements Discussion
NASA Technical Reports Server (NTRS)
Brown, Thomas M.
2007-01-01
This viewgraph presentation reviews the lunar lander propulsion requirements. It includes discussion on: Lander Project Overview, Project Evolution/Design Cycles, Lunar Architecture & Lander Reference Missions, Lander Concept Configurations, Descent and Ascent propulsion reviews, and a review of the technology requirements.
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2014-04-30
CAPE CANAVERAL, Fla. – A technician vents off the gas from the propellant lines of NASA's Project Morpheus prototype lander after it completed a free-flight test at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed autonomous landing and hazard avoidance technology, or ALHAT, sensors surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver. The lander descended and landed on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-04-30
CAPE CANAVERAL, Fla. – Technicians vent off the gas from the propellant lines of NASA's Project Morpheus prototype lander after it completed a free-flight test at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed autonomous landing and hazard avoidance technology, or ALHAT, sensors surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver. The lander descended and landed on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-04-30
CAPE CANAVERAL, Fla. – A technician vents off the gas from the propellant lines of NASA's Project Morpheus prototype lander after it landed from a free-flight test at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed autonomous landing and hazard avoidance technology, or ALHAT, sensors surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver. The lander descended and landed on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-04-30
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander touches down on the autonomous landing and hazard avoidance technology, or ALHAT, field after lifting off on a free-flight test from a new launch pad at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed ALHAT sensors, surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver. The lander descended and landed on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-04-30
CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander touches down on the autonomous landing and hazard avoidance technology, or ALHAT, field after lifting off on a free-flight test from a new launch pad at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed ALHAT sensors, surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver. The lander descended and landed on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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NASA Technical Reports Server (NTRS)
Hannan, Mike; Rickman, Doug; Chavers, Greg; Adam, Jason; Becker, Chris; Eliser, Joshua; Gunter, Dan; Kennedy, Logan; O'Leary, Patrick
2015-01-01
During 2011 a series of progressively more challenging flight tests of the Mighty Eagle autonomous terrestrial lander testbed were conducted primarily to validate the GNC system for a proposed lunar lander. With the successful completion of this GNC validation objective the opportunity existed to utilize the Mighty Eagle as a flying testbed for a variety of technologies. In 2012 an Autonomous Rendezvous and Capture (AR&C) algorithm was implemented in flight software and demonstrated in a series of flight tests. In 2012 a hazard avoidance system was developed and flight tested on the Mighty Eagle. Additionally, GNC algorithms from Moon Express and a MEMs IMU were tested in 2012. All of the testing described herein was above and beyond the original charter for the Mighty Eagle. In addition to being an excellent testbed for a wide variety of systems the Mighty Eagle also provided a great learning opportunity for many engineers and technicians to work a flight program.
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NASA Technical Reports Server (NTRS)
Wolf, M. B.
1981-01-01
The determination and removal of instrument signature from Viking Lander camera geometric data are described. All tests conducted as well as a listing of the final database (calibration constants) used to remove instrument signature from Viking Lander flight images are included. The theory of the geometric aberrations inherent in the Viking Lander camera is explored.
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COBALT: Development of a Platform to Flight Test Lander GN&C Technologies on Suborbital Rockets
NASA Technical Reports Server (NTRS)
Carson, John M., III; Seubert, Carl R.; Amzajerdian, Farzin; Bergh, Chuck; Kourchians, Ara; Restrepo, Carolina I.; Villapando, Carlos Y.; O'Neal, Travis V.; Robertson, Edward A.; Pierrottet, Diego;
2017-01-01
The NASA COBALT Project (CoOperative Blending of Autonomous Landing Technologies) is developing and integrating new precision-landing Guidance, Navigation and Control (GN&C) technologies, along with developing a terrestrial fight-test platform for Technology Readiness Level (TRL) maturation. The current technologies include a third- generation Navigation Doppler Lidar (NDL) sensor for ultra-precise velocity and line- of-site (LOS) range measurements, and the Lander Vision System (LVS) that provides passive-optical Terrain Relative Navigation (TRN) estimates of map-relative position. The COBALT platform is self contained and includes the NDL and LVS sensors, blending filter, a custom compute element, power unit, and communication system. The platform incorporates a structural frame that has been designed to integrate with the payload frame onboard the new Masten Xodiac vertical take-o, vertical landing (VTVL) terrestrial rocket vehicle. Ground integration and testing is underway, and terrestrial fight testing onboard Xodiac is planned for 2017 with two flight campaigns: one open-loop and one closed-loop.
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The Mars Sample Return Project
NASA Technical Reports Server (NTRS)
O'Neil, W. J.; Cazaux, C.
2000-01-01
The Mars Sample Return (MSR) Project is underway. A 2003 mission to be launched on a Delta III Class vehicle and a 2005 mission launched on an Ariane 5 will culminate in carefully selected Mars samples arriving on Earth in 2008. NASA is the lead agency and will provide the Mars landed elements, namely, landers, rovers, and Mars ascent vehicles (MAVs). The French Space Agency CNES is the largest international partner and will provide for the joint NASA/CNES 2005 Mission the Ariane 5 launch and the Earth Return Mars Orbiter that will capture the sample canisters from the Mars parking orbits the MAVs place them in. The sample canisters will be returned to Earth aboard the CNES Orbiter in the Earth Entry Vehicles provided by NASA. Other national space agencies are also expected to participate in substantial roles. Italy is planning to provide a drill that will operate from the Landers to provide subsurface samples. Other experiments in addition to the MSR payload will also be carried on the Landers. This paper will present the current status of the design of the MSR missions and flight articles. c 2000 American Institute of Aeronautics and Astronautics, Inc. Published by Elsevier Science Ltd.
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Synthetic Vision Displays for Planetary and Lunar Lander Vehicles
NASA Technical Reports Server (NTRS)
Arthur, Jarvis J., III; Prinzel, Lawrence J., III; Williams, Steven P.; Shelton, Kevin J.; Kramer, Lynda J.; Bailey, Randall E.; Norman, Robert M.
2008-01-01
Aviation research has demonstrated that Synthetic Vision (SV) technology can substantially enhance situation awareness, reduce pilot workload, improve aviation safety, and promote flight path control precision. SV, and related flight deck technologies are currently being extended for application in planetary exploration vehicles. SV, in particular, holds significant potential for many planetary missions since the SV presentation provides a computer-generated view for the flight crew of the terrain and other significant environmental characteristics independent of the outside visibility conditions, window locations, or vehicle attributes. SV allows unconstrained control of the computer-generated scene lighting, terrain coloring, and virtual camera angles which may provide invaluable visual cues to pilots/astronauts, not available from other vision technologies. In addition, important vehicle state information may be conformally displayed on the view such as forward and down velocities, altitude, and fuel remaining to enhance trajectory control and vehicle system status. The paper accompanies a conference demonstration that introduced a prototype NASA Synthetic Vision system for lunar lander spacecraft. The paper will describe technical challenges and potential solutions to SV applications for the lunar landing mission, including the requirements for high-resolution lunar terrain maps, accurate positioning and orientation, and lunar cockpit display concepts to support projected mission challenges.
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ALHAT COBALT: CoOperative Blending of Autonomous Landing Technology
NASA Technical Reports Server (NTRS)
Carson, John M.
2015-01-01
The COBALT project is a flight demonstration of two NASA ALHAT (Autonomous precision Landing and Hazard Avoidance Technology) capabilities that are key for future robotic or human landing GN&C (Guidance, Navigation and Control) systems. The COBALT payload integrates the Navigation Doppler Lidar (NDL) for ultraprecise velocity and range measurements with the Lander Vision System (LVS) for Terrain Relative Navigation (TRN) position estimates. Terrestrial flight tests of the COBALT payload in an open-loop and closed-loop GN&C configuration will be conducted onboard a commercial, rocket-propulsive Vertical Test Bed (VTB) at a test range in Mojave, CA.
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2013-12-06
CAPE CANAVERAL, Fla. – Inside a control room at NASA’s Kennedy Space Center in Florida, engineers monitor the progress as the Project Morpheus prototype lander is being prepared for a tether test on a transportable launch platform positioned at the north end of the Shuttle Landing Facility. The tethered test will include lifting it 20 feet by crane, ascending another 10 feet, maneuvering backwards 10 feet, and then flying forward and descending to its original position, landing at the end of the tether. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Daniel Casper
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2012-08-01
CAPE CANAVERAL, Fla. - At the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, field at the north end of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, members of the media view the hazard field and speak with Morpheus managers. At left, in the blue shirt is Gregory Gaddis, Kennedy Project Morpheus/ALHAT site manager. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus: Advancing Technologies for Human Exploration
NASA Technical Reports Server (NTRS)
Olansen, Jon B.; Munday, Stephen R.; Mitchell, Jennifer D.; Baine, Michael
2012-01-01
NASA's Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing. Designed to serve as a vertical testbed (VTB) for advanced spacecraft technologies, the vehicle provides a platform for bringing technologies from the laboratory into an integrated flight system at relatively low cost. This allows individual technologies to mature into capabilities that can be incorporated into human exploration missions. The Morpheus vehicle is propelled by a LOX/Methane engine and sized to carry a payload of 1100 lb to the lunar surface. In addition to VTB vehicles, the Project s major elements include ground support systems and an operations facility. Initial testing will demonstrate technologies used to perform autonomous hazard avoidance and precision landing on a lunar or other planetary surface. The Morpheus vehicle successfully performed a set of integrated vehicle test flights including hot-fire and tethered hover tests, leading up to un-tethered free-flights. The initial phase of this development and testing campaign is being conducted on-site at the Johnson Space Center (JSC), with the first fully integrated vehicle firing its engine less than one year after project initiation. Designed, developed, manufactured and operated in-house by engineers at JSC, the Morpheus Project represents an unprecedented departure from recent NASA programs that traditionally require longer, more expensive development lifecycles and testing at remote, dedicated testing facilities. Morpheus testing includes three major types of integrated tests. A hot-fire (HF) is a static vehicle test of the LOX/Methane propulsion system. Tether tests (TT) have the vehicle suspended above the ground using a crane, which allows testing of the propulsion and integrated Guidance, Navigation, and Control (GN&C) in hovering flight without the risk of a vehicle departure or crash. Morpheus free-flights (FF) test the complete Morpheus system without the additional safeguards provided during tether. A variety of free-flight trajectories are planned to incrementally build up to a fully functional Morpheus lander capable of flying planetary landing trajectories. In FY12, these tests will culminate with autonomous flights simulating a 1 km lunar approach trajectory, hazard avoidance maneuvers and precision landing in a prepared hazard field at the Kennedy Space Center (KSC). This paper describes Morpheus integrated testing campaign, infrastructure, and facilities, and the payloads being incorporated on the vehicle. The Project s fast pace, rapid prototyping, frequent testing, and lessons learned depart from traditional engineering development at JSC. The Morpheus team employs lean, agile development with a guiding belief that technologies offer promise, but capabilities offer solutions, achievable without astronomical costs and timelines.
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NASA-STD-6016 Standard Materials and Processes Requirements for Spacecraft
NASA Technical Reports Server (NTRS)
Hirsch, David B.
2009-01-01
The standards for materials and processes surrounding spacecraft are discussed. Presentation focused on minimum requirements for Materials and Processes (M&P) used in design, fabrication, and testing of flight components for NASA manned, unmanned, robotic, launch vehicle, lander, in-space and surface systems, and spacecraft program/project hardware elements.Included is information on flammability, offgassing, compatibility requirements, and processes; both metallic and non-metallic materials are mentioned.
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NASA Precision Landing Technologies Completes Initial Flight Tests on Vertical Testbed Rocket
2017-04-19
This 2-minute, 40-second video shows how over the past 5 weeks, NASA and Masten Space Systems teams have prepared for and conducted sub-orbital rocket flight tests of next-generation lander navigation technology through the CoOperative Blending of Autonomous Landing Technologies (COBALT) project. The COBALT payload was integrated onto Masten’s rocket, Xodiac. The Xodiac vehicle used the Global Positioning System (GPS) for navigation during this first campaign, which was intentional to verify and refine COBALT system performance. The joint teams conducted numerous ground verification tests, made modifications in the process, practiced and refined operations’ procedures, conducted three tether tests, and have now flown two successful free flights. This successful, collaborative campaign has provided the COBALT and Xodiac teams with the valuable performance data needed to refine the systems and prepare them for the second flight test campaign this summer when the COBALT system will navigate the Xodiac rocket to a precision landing. The technologies within COBALT provide a spacecraft with knowledge during entry, descent, and landing that enables it to precisely navigate and softly land close to surface locations that have been previously too risky to target with current capabilities. The technologies will enable future exploration destinations on Mars, the moon, Europa, and other planets and moons. The two primary navigation components within COBALT include the Langley Research Center’s Navigation Doppler Lidar, which provides ultra-precise velocity and line-of-sight range measurements, and Jet Propulsion Laboratory’s Lander Vision System (LVS), which provides navigation estimates relative to an existing surface map. The integrated system is being flight tested onboard a Masten suborbital rocket vehicle called Xodiac. The COBALT project is led by the Johnson Space Center, with funding provided through the Game Changing Development, Flight Opportunities program, and Advanced Exploration Systems programs. Based at NASA’s Armstrong Flight Research Center in Edwards, CA, the Flight Opportunities program funds technology development flight tests on commercial suborbital space providers of which Masten is a vendor. The program has previously tested the LVS on the Masten rocket and validated the technology for the Mars 2020 rover.
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2014-11-19
CAPE CANAVERAL, Fla. –NASA's Project Morpheus prototype lander is lifted by a crane in preparation for a tethered-flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. For the 40-second test, the lander will be hoisted 20 feet. The spacecraft will ascend an additional five feet and hover for five seconds. Morpheus then will perform a 5.6-foot ascent coupled with a 9.8-foot traverse, and hover for five more seconds before returning to the launch point. A number of changes have been made, primarily focused on autonomous landing and hazard avoidance technology ALHAT and moving the Doppler Lidar to the front of the forward liquid oxygen tank. The tether test was cut short due to Morpheus exceeding onboard abort rate limits. The vehicle was taken back to the hangar and data from the test is being studied. After review, managers will determine when a new test date will be set. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-11-19
CAPE CANAVERAL, Fla. –NASA's Project Morpheus prototype lander undergoes final preparations for a tethered-flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. For the 40-second test, the lander will be hoisted 20 feet. The spacecraft will ascend an additional five feet and hover for five seconds. Morpheus then will perform a 5.6-foot ascent coupled with a 9.8-foot traverse, and hover for five more seconds before returning to the launch point. A number of changes have been made, primarily focused on autonomous landing and hazard avoidance technology ALHAT and moving the Doppler Lidar to the front of the forward liquid oxygen tank. The tether test was cut short due to Morpheus exceeding onboard abort rate limits. The vehicle was taken back to the hangar and data from the test is being studied. After review, managers will determine when a new test date will be set. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2014-11-19
CAPE CANAVERAL, Fla. –NASA's Project Morpheus prototype lander is prepared for lifting by a crane in preparation for a tethered-flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. For the 40-second test, the lander will be hoisted 20 feet. The spacecraft will ascend an additional five feet and hover for five seconds. Morpheus then will perform a 5.6-foot ascent coupled with a 9.8-foot traverse, and hover for five more seconds before returning to the launch point. A number of changes have been made, primarily focused on autonomous landing and hazard avoidance technology ALHAT and moving the Doppler Lidar to the front of the forward liquid oxygen tank. The tether test was cut short due to Morpheus exceeding onboard abort rate limits. The vehicle was taken back to the hangar and data from the test is being studied. After review, managers will determine when a new test date will be set. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2012-08-01
CAPE CANAVERAL, Fla. - At the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, field at the north end of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, members of the media view the hazard field and speak with Morpheus managers. At far left, in the white shirt is Jon Olansen, Johnson Space Center Project Morpheus Manager. At left, in the blue shirt is Chirold Epp, JSC project manager for ALHAT. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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2012-08-01
CAPE CANAVERAL, Fla. - At the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, field at the north end of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida, members of the media view the hazard field and speak with Morpheus managers. In the white shirt is Jon Olansen, Johnson Space Center Project Morpheus Manager. Behind Olansen is Gregory Gaddis, Kennedy Project Morpheus/ALHAT site manager. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. The SLF will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus utilizes an autonomous landing and hazard avoidance technology, or ALHAT, payload that will allow it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Test of Lander Vision System for Mars 2020
2016-10-04
A prototype of the Lander Vision System for NASA Mars 2020 mission was tested in this Dec. 9, 2014, flight of a Masten Space Systems Xombie vehicle at Mojave Air and Space Port in California. http://photojournal.jpl.nasa.gov/catalog/PIA20848
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Mars Pathfinder Microrover- Implementing a Low Cost Planetary Mission Experiment
NASA Technical Reports Server (NTRS)
Matijevic, J.
1996-01-01
The Mars Pathfinder Microrover Flight Experiment (MFEX) is a NASA Office of Space Access and Technology (OSAT) flight experiment which has been delivered and integrated with the Mars Pathfinder (MPF) lander and spacecraft system. The total cost of the MFEX mission, including all subsystem design and development, test, integration with the MPF lander and operations on Mars has been capped at $25 M??is paper discusses the process and the implementation scheme which has resulted in the development of this first Mars rover.
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2014-04-30
CAPE CANAVERAL, Fla. – Engineers and technicians check NASA's Project Morpheus prototype lander after it touched down on a dedicated landing pad inside the autonomous landing and hazard avoidance technology, or ALHAT, hazard field at the north end of the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Morpheus launched on a free-flight test from a new launch pad at the north end of the landing facility. The 98-second test began at 1:57 p.m. EDT with the Morpheus lander launching from the ground over a flame trench and ascending more than 800 feet at a peak speed of 36 mph. The vehicle, with its recently installed ALHAT sensors, surveyed the hazard field to determine safe landing sites. Morpheus then flew forward and downward covering approximately 1300 feet while performing a 78-foot divert to simulate a hazard avoidance maneuver before landing on the dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett
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Morpheus 1.5A Lander Failure Investigation Results
NASA Technical Reports Server (NTRS)
Munday, Steve; Olansen, John
2013-01-01
On August 9th, 2012, the Morpheus 1.5 Vertical Testbed (VTB) crashed during Free Flight 2 (FF2) at KSC SLF, resulting in the loss of 1.5 VTB hardware. JSC/KSC Morpheus team immediately executed the pre-rehearsed Emergency Action Plan to protect personnel and property, so damage was limited to 1.5 VTB hardware. JSC/KSC Morpheus team secured data and mapped & recovered debris. Project had pre-declared loss of VTB to be a test failure, not a mishap.
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Grid resolution and solution convergence for Mars Pathfinder forebody
NASA Technical Reports Server (NTRS)
Nettelhorst, Heather L.; Mitcheltree, Robert A.
1994-01-01
As part of the Discovery Program, NASA Plans to launch a series of probes to Mars. The Mars Pathfinder project is the first of this series with a scheduled Mars arrival in July 1997. The entry vehicle will perform a direct entry into the atmosphere and deliver a lander to the surface. Predicting the entry vehicle's flight performance and designing the forebody heatshield requires knowledge of the expected aerothermodynamic environment. Much of this knowledge can be obtained through computational fluid dynamic (CFD) analysis.
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NASA Technical Reports Server (NTRS)
Rutishauser, David K.; Epp, Chirold; Robertson, Ed
2012-01-01
The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project is chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. The ALHAT System must be capable of identifying and avoiding surface hazards to enable a safe and accurate landing to within tens of meters of designated and certified landing sites anywhere on a planetary surface under any lighting conditions. Since its inception in 2006, the ALHAT Project has executed four field test campaigns to characterize and mature sensors and algorithms that support real-time hazard detection and global/local precision navigation for planetary landings. The driving objective for Government Fiscal Year 2012 (GFY2012) is to successfully demonstrate autonomous, real-time, closed loop operation of the ALHAT system in a realistic free flight scenario on Earth using the Morpheus lander developed at the Johnson Space Center (JSC). This goal represents an aggressive target consistent with a lean engineering culture of rapid prototyping and development. This culture is characterized by prioritizing early implementation to gain practical lessons learned and then building on this knowledge with subsequent prototyping design cycles of increasing complexity culminating in the implementation of the baseline design. This paper provides an overview of the ALHAT/Morpheus flight demonstration activities in GFY2012, including accomplishments, current status, results, and lessons learned. The ALHAT/Morpheus effort is also described in the context of a technology path in support of future crewed and robotic planetary exploration missions based upon the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN).
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Mars Pathfinder flight system integration and test.
NASA Astrophysics Data System (ADS)
Muirhead, B. K.
This paper describes the system integration and test experiences, problems and lessons learned during the assembly, test and launch operations (ATLO) phase of the Mars Pathfinder flight system scheduled to land on the surface of Mars on July 4, 1997. The Mars Pathfinder spacecraft consists of three spacecraft systems: cruise stage, entry vehicle and lander. The cruise stage carries the entry and lander vehicles to Mars and is jettisoned prior to entry. The entry vehicle, including aeroshell, parachute and deceleration rockets, protects the lander during the direct entry and reduces its velocity from 7.6 to 0 km/s in stages during the 5 min entry sequence. The lander's touchdown is softened by airbags which are retracted once stopped on the surface. The lander then uprights itself, opens up fully and begins surface operations including deploying its camera and rover. This paper overviews the system design and the results of the system integration and test activities, including the entry, descent and landing subsystem elements. System test experiences including science instruments, the microrover, Sojourner, and software are discussed. The final qualification of the entry, descent and landing subsystems during this period is also discussed.
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Synthetic and Enhanced Vision System for Altair Lunar Lander
NASA Technical Reports Server (NTRS)
Prinzell, Lawrence J., III; Kramer, Lynda J.; Norman, Robert M.; Arthur, Jarvis J., III; Williams, Steven P.; Shelton, Kevin J.; Bailey, Randall E.
2009-01-01
Past research has demonstrated the substantial potential of synthetic and enhanced vision (SV, EV) for aviation (e.g., Prinzel & Wickens, 2009). These augmented visual-based technologies have been shown to significantly enhance situation awareness, reduce workload, enhance aviation safety (e.g., reduced propensity for controlled flight -into-terrain accidents/incidents), and promote flight path control precision. The issues that drove the design and development of synthetic and enhanced vision have commonalities to other application domains; most notably, during entry, descent, and landing on the moon and other planetary surfaces. NASA has extended SV/EV technology for use in planetary exploration vehicles, such as the Altair Lunar Lander. This paper describes an Altair Lunar Lander SV/EV concept and associated research demonstrating the safety benefits of these technologies.
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The Lunar Lander "HabiTank" Concept
NASA Technical Reports Server (NTRS)
Kennedy, Kriss J.
2007-01-01
This paper will summarize the study that was conducted under the auspices of the National Aeronautics and Space Administration (NASA), lead by Johnson Space Center s Engineering Directorate in support of the Lunar Lander Preparatory Study (LLPS) as sponsored by the Constellation Program Office (CxPO), Advanced Projects Office (APO). The lunar lander conceptual design and analysis is intended to provide an understanding of requirements for human space exploration of the Moon using the Advanced Projects Office Pre-Lander Project Office selected "HabiTank" Lander concept. In addition, these analyses help identify system "drivers," or significant sources of cost, performance, risk, and schedule variation along with areas needing technology development. Recommendations, results, and conclusions in this paper do not reflect NASA policy or programmatic decisions. This paper is an executive summary of this study.
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Mission Plan for the Mars Surveyor 2001 Orbiter and Lander
NASA Technical Reports Server (NTRS)
Plaut, J. J.; Spencer, D. A.
1999-01-01
The Mars Surveyor 2001 Project consists of two missions to Mars, an Orbiter and a Lander, both to be launched in the spring of 2001 for October 2001 (Orbiter) and January 2002 (Lander) arrival at Mars. The Orbiter will support the Lander mission primarily as a communications relay system; the Lander will not have direct-to-Earth communications capability. Science data collected from the Orbiter will also be used to aid in the geologic interpretation of the landing site, along with data from past missions. Combining the Orbiter and Lander missions into a single Project has enabled the streamlining of many activities and an efficient use of personnel and other resources at the Jet Propulsion Laboratory and at the spacecraft contractor, Lockheed Martin Astronautics.
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Atmospheric Mining in the Outer Solar System: Outer Planet Orbital Transfer and Lander Analyses
NASA Technical Reports Server (NTRS)
Palaszewski, Bryan
2016-01-01
Atmospheric mining in the outer solar system has been investigated as a means of fuel production for high energy propulsion and power. Fusion fuels such as Helium 3 (3He) and deuterium can be wrested from the atmospheres of Uranus and Neptune and either returned to Earth or used in-situ for energy production. Helium 3 and deuterium were the primary gases of interest with hydrogen being the primary propellant for nuclear thermal solid core and gas core rocket-based atmospheric flight. A series of analyses were undertaken to investigate resource capturing aspects of atmospheric mining in the outer solar system. This included the gas capturing rate, storage options, and different methods of direct use of the captured gases. While capturing 3He, large amounts of hydrogen and 4He are produced. Analyses of orbital transfer vehicles (OTVs), landers, and the issues with in-situ resource utilization (ISRU) mining factories are included. Preliminary observations are presented on near-optimal selections of moon base orbital locations, OTV power levels, and OTV and lander rendezvous points. For analyses of round trip OTV flights from Uranus to Miranda or Titania, a 10-Megawatt electric (MWe) OTV power level and a 200-metric ton (MT) lander payload were selected based on a relative short OTV trip time and minimization of the number of lander flights. A similar optimum power level is suggested for OTVs flying from low orbit around Neptune to Thalassa or Triton. Several moon base sites at Uranus and Neptune and the OTV requirements to support them are also addressed.
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Atmospheric Mining in the Outer Solar System: Outer Planet Orbital Transfer and Lander Analyses
NASA Technical Reports Server (NTRS)
Palaszewski, Bryan
2016-01-01
Atmospheric mining in the outer solar system has been investigated as a means of fuel production for high energy propulsion and power. Fusion fuels such as Helium 3 (3He) and deuterium can be wrested from the atmospheres of Uranus and Neptune and either returned to Earth or used in-situ for energy production. Helium 3 and deuterium were the primary gases of interest with hydrogen being the primary propellant for nuclear thermal solid core and gas core rocket-based atmospheric flight. A series of analyses were undertaken to investigate resource capturing aspects of atmospheric mining in the outer solar system. This included the gas capturing rate, storage options, and different methods of direct use of the captured gases. While capturing 3He, large amounts of hydrogen and 4He are produced. Analyses of orbital transfer vehicles (OTVs), landers, and the issues with in-situ resource utilization (ISRU) mining factories are included. Preliminary observations are presented on near-optimal selections of moon base orbital locations, OTV power levels, and OTV and lander rendezvous points. For analyses of round trip OTV flights from Uranus to Miranda or Titania, a 10- Megawatt electric (MWe) OTV power level and a 200 metricton (MT) lander payload were selected based on a relative short OTV trip time and minimization of the number of lander flights. A similar optimum power level is suggested for OTVs flying from low orbit around Neptune to Thalassa or Triton. Several moon base sites at Uranus and Neptune and the OTV requirements to support them are also addressed.
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Federal Register 2010, 2011, 2012, 2013, 2014
2011-09-09
... Statement for the Lander Resource Management Plan Revision Project, Lander Field Office, Wyoming AGENCY... to the Lander Resource Management Plan Revision Project by any of the following methods: Web site... DEPARTMENT OF THE INTERIOR Bureau of Land Management [LLWYR0500.L16100000.DP0000. LXSS047K0000...
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Artemis: Results of the engineering feasibility study
NASA Technical Reports Server (NTRS)
1991-01-01
Information is given in viewgraph form for the Engineering Feasibility Study of the Artemis Project, a plan to establish a permanent base on the Moon. Topics covered include the Common Lunar Lander (CLL), lunar lander engineering study results, lunar lander trajectory analysis, lunar lander conceptual design and mass properties, the lunar lander communication subsystem design, and product assurance.
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MoonRIDERS: NASA and Hawaiis Innovative Lunar Surface Flight Experiment for Landing in Late 2017
NASA Technical Reports Server (NTRS)
Kelso, R. M.; Romo, R.; Mackey, P. J.; Phillips, J. R., III; Cox, R. E.; Hogue, M. D.; Calle, C. I.
2016-01-01
Recently, NASA Kennedy Space Center, Hawaii's state aerospace agency PISCES, and two Hawaii high schools Iolani and Kealakehe have come together in a unique collaboration called MoonRIDERS. This strategic partnership will allow Hawaii students to participate directly in sending a science experiment to the surface of the moon. The MoonRIDERS project started in the spring of 2014, with each institution responsible for its own project costs and activities. PISCES, given its legislative direction in advancing planetary surface systems, saw this collaboration as an important opportunity to inspire a young generation and encourage STEM (Science, Technology, Engineering, and Mathematics) learning. Under the guidance of PISCES and NASA, the students will be involved hands-on from start to finish in the engineering, testing, and validation of a space technology called the Electrodynamic Dust Shield (EDS). Dust is a critical issue for space exploration, as evidenced by the Apollo lunar missions and Mars rovers and landers. Dust creates a number of problems for humans and hardware, including inhalation, mechanical interference, wear and tear on spacesuits, inhibition of heat transfer on radiators, and reduced efficiency of solar panels. To address this, the EDS is designed to work on a variety of materials, and functions by generatingelectrodynamic fields to clear away the dust. The Google Lunar XPRIZE (GLXP), a space competition "designed to inspire pioneers to do robotic space transport on a budget," serves as a likely method for the MoonRIDERS to get their project to the moon. The EDS would potentially be flown as a hosted payload on a competitor's lander (still to be chosen). This briefing will provide an overview of the technology, the unique partnership, progress update and testing leading to this flight opportunity.
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NASA Technical Reports Server (NTRS)
Holden, Kritina; Sandor, A.; Thompson, S. G.; McCann, R. S.; Kaiser, M. K.; Begault, D. R.; Adelstein, B. D.; Beutter, B. R.; Stone, L. S.
2008-01-01
The goal of the Information Presentation Directed Research Project (DRP) is to address design questions related to the presentation of information to the crew on flight vehicles, surface landers and habitats, and during extra-vehicular activities (EVA). Designers of displays and controls for exploration missions must be prepared to select the text formats, label styles, alarms, electronic procedure designs, and cursor control devices that provide for optimal crew performance on exploration tasks. The major areas of work, or subtasks, within the Information Presentation DRP are: 1) Controls, 2) Displays, 3) Procedures, and 4) EVA Operations.
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Physics of Granular Materials: Investigations in Support of Astrobiology
NASA Technical Reports Server (NTRS)
Marshall, John R.
2002-01-01
This publication list is submitted as a summary of the work conducted under Cooperative Agreement 1120. The goal of the 1120 research was to study granular materials within a planetary, astrophysical, and astrobiological context. This involved research on the physical, mechanical and electrostatic properties of granular systems, as well as the examination of these materials with atomic force microscopy and x-ray analysis. Instruments for analyzing said materials in planetary environments were developed, including the MECA (Mars Environment Compatibility Assessment) experiment for the MSP '01 lander, the ECHOS/MATADOR experiment for the MSP '03 lander, an ISRU experiment for the '03 lander, and MiniLEAP technology. Flight experiments for microgravity (Space Station and Shuttle) have also been developed for the study of granular materials. As expressed in the publications, work on 1120 encompassed laboratory research, theoretical modeling, field experiments, and flight experiments: a series of successful new models were developed for understanding the behavior of triboelectrostatically charged granular masses, and 4 separate instruments were selected for space flight. No inventions or patents were generated by the research under this Agreement.
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An Atmospheric Guidance Algorithm Testbed for the Mars Surveyor Program 2001 Orbiter and Lander
NASA Technical Reports Server (NTRS)
Striepe, Scott A.; Queen, Eric M.; Powell, Richard W.; Braun, Robert D.; Cheatwood, F. McNeil; Aguirre, John T.; Sachi, Laura A.; Lyons, Daniel T.
1998-01-01
An Atmospheric Flight Team was formed by the Mars Surveyor Program '01 mission office to develop aerocapture and precision landing testbed simulations and candidate guidance algorithms. Three- and six-degree-of-freedom Mars atmospheric flight simulations have been developed for testing, evaluation, and analysis of candidate guidance algorithms for the Mars Surveyor Program 2001 Orbiter and Lander. These simulations are built around the Program to Optimize Simulated Trajectories. Subroutines were supplied by Atmospheric Flight Team members for modeling the Mars atmosphere, spacecraft control system, aeroshell aerodynamic characteristics, and other Mars 2001 mission specific models. This paper describes these models and their perturbations applied during Monte Carlo analyses to develop, test, and characterize candidate guidance algorithms.
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Viking 75 project: Viking lander system primary mission performance report
NASA Technical Reports Server (NTRS)
Cooley, C. G.
1977-01-01
Viking Lander hardware performance during launch, interplanetary cruise, Mars orbit insertion, preseparation, separation through landing, and the primary landed mission, with primary emphasis on Lander engineering and science hardware operations, the as-flown mission are described with respect to Lander system performance and anomalies during the various mission phases. The extended mission and predicted Lander performance is discussed along with a summary of Viking goals, mission plans, and description of the Lander, and its subsystem definitions.
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Operations and Autonomy of the Mars Pathfinder Microrover
NASA Technical Reports Server (NTRS)
Mishkin, A. H.; Morrison, J. C.; Nguyen, T. T.; Stone, H. W.; Cooper, B. K.
1998-01-01
The Microrover Flight Experiment (MFEX) is a NSAS OACT (Office of Advanced Concepts and Technology) flight experiment which, integrated with the Mars Pathfinder (MPF) lander and spacecraft system, landed on Mars on July 4, 1997.
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Wings of Man Neil Armstrong Documentary
2018-05-10
A narrated film documentary of Neil Armstrong, showing him in various aircraft, the Flight Research Center, lunar lander training vehicle (LLTV) at the Marshal Space Flight Center, Gemini VIII, in Apollo 11 and landing on the moon.
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Entry trajectory and atmosphere reconstruction methodologies for the Mars Exploration Rover mission
NASA Astrophysics Data System (ADS)
Desai, Prasun N.; Blanchard, Robert C.; Powell, Richard W.
2004-02-01
The Mars Exploration Rover (MER) mission will land two landers on the surface of Mars, arriving in January 2004. Both landers will deliver the rovers to the surface by decelerating with the aid of an aeroshell, a supersonic parachute, retro-rockets, and air bags for safely landing on the surface. The reconstruction of the MER descent trajectory and atmosphere profile will be performed for all the phases from hypersonic flight through landing. A description of multiple methodologies for the flight reconstruction is presented from simple parameter identification methods through a statistical Kalman filter approach.
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Red Dragon: Low-cost Access to the Surface of Mars using Commercial Capabilities
NASA Technical Reports Server (NTRS)
Karcz, John; Davis, S. M.; Aftosmis, M. J.; Allen, G. A.; Bakhtian, N. M.; Dyakonov, A. A.; Edquist, K. T.; Glass, B. J.; Gonzales, A. A.; Heldmann, J. L.;
2012-01-01
We will discuss the feasibility of using a minimally-modified variant of a SpaceX Dragon capsule as a low-cost, large-capacity, near-term, Mars lander for scientific and human-precursor missions. We have been evaluating such a Red Dragon platform as an option for a Discovery Program mission concept. A Red Dragon lander has the potential to be low cost primarily because it would be derived from a routinely-flying spacecraft. Dragon is being developed to ferry cargo and crew to and from the International Space Station (ISS). The cargo variant is currently undergoing test flights, which will be followed by standard ISS cargo missions and, eventually, crewed flights. The human variant, unlike other Earth-return vehicles, appears to also have most of the capabilities necessary to land on Mars. In particular, it has a set of high-thrust, throttleable, storable bi-propellant Super- Draco engines integrated directly into the capsule which are intended for launch abort and powered landings on Earth. These thrusters suggest the possibility of a parachute-free, fully-propulsive deceleration at Mars from supersonic speeds to the surface. Concepts for large, human-relevant landers (see, e.g., [1]) also often employ supersonic retro-propulsion; Red Dragon's entry, descent, and landing approach would scale to those landers. Further, SpaceX's Falcon Heavy launch vehicle, currently under development and expected to have its first flight in 2013, will be capable of sending Dragon on a trajectory to Mars. We will discuss our motivation for exploring a Red Dragon lander, the primary technical questions which determine its feasibility, and the current results of our analysis. In particular, we will examine entry, descent, and landing (EDL) in detail. We will describe the modifications to Dragon necessary for interplanetary cruise, EDL, and operations on the Martian surface.
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Life Support Systems for Lunar Landers
NASA Technical Reports Server (NTRS)
Anderson, Molly
2008-01-01
Engineers designing life support systems for NASA s next Lunar Landers face unique challenges. As with any vehicle that enables human spaceflight, the needs of the crew drive most of the lander requirements. The lander is also a key element of the architecture NASA will implement in the Constellation program. Many requirements, constraints, or optimization goals will be driven by interfaces with other projects, like the Crew Exploration Vehicle, the Lunar Surface Systems, and the Extravehicular Activity project. Other challenges in the life support system will be driven by the unique location of the vehicle in the environments encountered throughout the mission. This paper examines several topics that may be major design drivers for the lunar lander life support system. There are several functional requirements for the lander that may be different from previous vehicles or programs and recent experience. Some of the requirements or design drivers will change depending on the overall Lander configuration. While the configuration for a lander design is not fixed, designers can examine how these issues would impact their design and be prepared for the quick design iterations required to optimize a spacecraft.
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NASA Astrophysics Data System (ADS)
Johnson, Michael
2015-04-01
iCubeSat, the Interplanetary CubeSat Workshop, is an annual technical workshop for researchers working on an exciting new standardised platform and opportunity for planetary and space scientists. The first workshop was held in 2012 at MIT, 2013 at Cornell, 2014 at Caltech with the 2015 workshop scheduled to take place on the 26-27th May 2015 at Imperial College London. Mission concepts and flight projects presented since 2012 have included orbiters and landers targeting asteroids, the moon, Mars, Venus, Saturn and their satellites to perform science traditionally reserved for flagship missions at a fraction of their cost. Some of the first missions proposed are currently being readied for flight in Europe, taking advantage of multiple ride share launch opportunities and technology providers. A review of these and other interplanetary CubeSat projects will be presented, covering details of their science objectives, instrument capabilities, technology, team composition, budget, funding sources, and the other programattic elements required to implement this potentially revolutionary new class of mission.
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NASA Astrophysics Data System (ADS)
Roback, Vincent E.; Amzajerdian, Farzin; Bulyshev, Alexander E.; Brewster, Paul F.; Barnes, Bruce W.
2016-05-01
For the first time, a 3-D imaging Flash Lidar instrument has been used in flight to scan a lunar-like hazard field, build a 3-D Digital Elevation Map (DEM), identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control system, help to guide the Morpheus autonomous, rocket-propelled, free-flying lander to that safe site on the hazard field. The flight tests served as the TRL 6 demo of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) system and included launch from NASA-Kennedy, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range. The ALHAT project developed a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The Flash Lidar is a second generation, compact, real-time, air-cooled instrument. Based upon extensive on-ground characterization at flight ranges, the Flash Lidar was shown to be capable of imaging hazards from a slant range of 1 km with an 8 cm range precision and a range accuracy better than 35 cm, both at 1-σ. The Flash Lidar identified landing hazards as small as 30 cm from the maximum slant range which Morpheus could achieve (450 m); however, under certain wind conditions it was susceptible to scintillation arising from air heated by the rocket engine and to pre-triggering on a dust cloud created during launch and transported down-range by wind.
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NASA Technical Reports Server (NTRS)
Roback, Vincent E.; Amzajerdian, Farzin; Bulyshev, Alexander E.; Brewster, Paul F.; Barnes, Bruce W.
2016-01-01
For the first time, a 3-D imaging Flash Lidar instrument has been used in flight to scan a lunar-like hazard field, build a 3-D Digital Elevation Map (DEM), identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control (GN&C) system, help to guide the Morpheus autonomous, rocket-propelled, free-flying lander to that safe site on the hazard field. The flight tests served as the TRL 6 demo of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) system and included launch from NASA-Kennedy, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range. The ALHAT project developed a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The Flash Lidar is a second generation, compact, real-time, air-cooled instrument. Based upon extensive on-ground characterization at flight ranges, the Flash Lidar was shown to be capable of imaging hazards from a slant range of 1 km with an 8 cm range precision and a range accuracy better than 35 cm, both at 1-delta. The Flash Lidar identified landing hazards as small as 30 cm from the maximum slant range which Morpheus could achieve (450 m); however, under certain wind conditions it was susceptible to scintillation arising from air heated by the rocket engine and to pre-triggering on a dust cloud created during launch and transported down-range by wind.
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Flight Testing of Terrain-Relative Navigation and Large-Divert Guidance on a VTVL Rocket
NASA Technical Reports Server (NTRS)
Trawny, Nikolas; Benito, Joel; Tweddle, Brent; Bergh, Charles F.; Khanoyan, Garen; Vaughan, Geoffrey M.; Zheng, Jason X.; Villalpando, Carlos Y.; Cheng, Yang; Scharf, Daniel P.;
2015-01-01
Since 2011, the Autonomous Descent and Ascent Powered-Flight Testbed (ADAPT) has been used to demonstrate advanced descent and landing technologies onboard the Masten Space Systems (MSS) Xombie vertical-takeoff, vertical-landing suborbital rocket. The current instantiation of ADAPT is a stand-alone payload comprising sensing and avionics for terrain-relative navigation and fuel-optimal onboard planning of large divert trajectories, thus providing complete pin-point landing capabilities needed for planetary landers. To this end, ADAPT combines two technologies developed at JPL, the Lander Vision System (LVS), and the Guidance for Fuel Optimal Large Diverts (G-FOLD) software. This paper describes the integration and testing of LVS and G-FOLD in the ADAPT payload, culminating in two successful free flight demonstrations on the Xombie vehicle conducted in December 2014.
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2012-08-09
CAPE CANAVERAL, Fla. – During a free-flight test of the Project Morpheus vehicle at the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida, the vehicle lifted off the ground and then experienced a hardware component failure, which prevented it from maintaining stable flight. Engineers are looking into the test data and the agency will release information as it becomes available. Failures such as these were anticipated prior to the test, and are part of the development process for any complex spaceflight hardware. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. Morpheus was manufactured and assembled at JSC and Armadillo Aerospace. Morpheus is large enough to carry 1,100 pounds of cargo to the moon – for example, a humanoid robot, a small rover, or a small laboratory to convert moon dust into oxygen. The primary focus of the test is to demonstrate an integrated propulsion and guidance, navigation and control system that can fly a lunar descent profile to exercise the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, safe landing sensors and closed-loop flight control. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA
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Mars Smart Lander Parachute Simulation Model
NASA Technical Reports Server (NTRS)
Queen, Eric M.; Raiszadeh, Ben
2002-01-01
A multi-body flight simulation for the Mars Smart Lander has been developed that includes six degree-of-freedom rigid-body models for both the supersonically-deployed and subsonically-deployed parachutes. This simulation is designed to be incorporated into a larger simulation of the entire entry, descent and landing (EDL) sequence. The complete end-to-end simulation will provide attitude history predictions of all bodies throughout the flight as well as loads on each of the connecting lines. Other issues such as recontact with jettisoned elements (heat shield, back shield, parachute mortar covers, etc.), design of parachute and attachment points, and desirable line properties can also be addressed readily using this simulation.
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Resource Prospector Propulsion System Cold Flow Testing
NASA Technical Reports Server (NTRS)
Williams, Hunter; Holt, Kim; Addona, Brad; Trinh, Huu
2015-01-01
Resource Prospector (RP) is a NASA mission being led by NASA Ames Research Center with current plans to deliver a scientific payload package aboard a rover to the lunar surface. As part of an early risk reduction activity, Marshall Space Flight Center (MSFC) and Johnson Space Flight Center (JSC) have jointly developed a government-version concept of a lunar lander for the mission. The spacecraft consists of two parts, the lander and the rover which carries the scientific instruments. The lander holds the rover during launch, cruise, and landing on the surface. Following terminal descent and landing the lander portion of the spacecraft become dormant after the rover embarks on the science mission. The lander will be equipped with a propulsion system for lunar descent and landing, as well as trajectory correction and attitude control maneuvers during transit to the moon. Hypergolic propellants monomethyl hydrazine and nitrogen tetroxide will be used to fuel sixteen 70-lbf descent thrusters and twelve 5-lbf attitude control thrusters. A total of four metal-diaphragm tanks, two per propellant, will be used along with a high-pressure composite-overwrapped pressure vessel for the helium pressurant gas. Many of the major propulsion system components are heritage missile hardware obtained by NASA from the Air Force. In parallel with the flight system design activities, a simulated propulsion system based on flight drawings was built for conducting a series of water flow tests to characterize the transient fluid flow of the propulsion system feed lines and to verify the critical operation modes such as system priming, waterhammer, and crucial mission duty cycles. The primary objective of the cold flow testing was to simulate the RP propulsion system fluid flow operation through water flow testing and to obtain data for anchoring analytical models. The models will be used to predict the transient and steady state flow behaviors in the actual flight operations. All design and build efforts, including the analytical modeling, have been performed. The cold flow testing of the propulsion system was set up and conducted at a NASA MSFC test facility. All testing was completed in the summer of 2014, and this paper documents the results of that testing and the associated fluid system modeling efforts.
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The mosaics of Mars: As seen by the Viking Lander cameras
NASA Technical Reports Server (NTRS)
Levinthal, E. C.; Jones, K. L.
1980-01-01
The mosaics and derivative products produced from many individual high resolution images acquired by the Viking Lander Camera Systems are described: A morning and afternoon mosaic for both cameras at the Lander 1 Chryse Planitia site, and a morning, noon, and afternoon camera pair at Utopia Planitia, the Lander 11 site. The derived products include special geometric projections of the mosaic data sets, polar stereographic (donut), stereoscopic, and orthographic. Contour maps and vertical profiles of the topography were overlaid on the mosaics from which they were derived. Sets of stereo pairs were extracted and enlarged from stereoscopic projections of the mosaics.
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2012-02-17
Apollo Capsule/Lunar Lander: The goal of Project Apollo was to land man on the moon and return them safely to the Earth. The Apollo spacecraft consisted of a command module serving as the crew’s quarters and flight control section and the lunar module, carrying two crewmembers to the surface of the moon. The first Apollo spacecraft to land on the moon was Apollo 11 on July 20, 1969. The program concluded with Apollo 17 in December 1972 after putting 27 men into lunar orbit and 12 of them on the surface of the moon. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA
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Lunar lander ground support system
NASA Technical Reports Server (NTRS)
1991-01-01
This year's project, like the previous Aerospace Group's project, involves a lunar transportation system. The basic time line will be the years 2010-2030 and will be referred to as a second generation system, as lunar bases would be present. The project design completed this year is referred to as the Lunar Lander Ground Support System (LLGSS). The area chosen for analysis encompasses a great number of vehicles and personnel. The design of certain elements of the overall lunar mission are complete projects in themselves. For this reason the project chosen for the Senior Aerospace Design is the design of specific servicing vehicles and additions or modifications to existing vehicles for the area of concern involving servicing and maintenance of the lunar lander while on the surface.
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Self-unloading, unmanned, reusable lunar lander project
NASA Technical Reports Server (NTRS)
Cowan, Kevin; Lewis, Ron; Mislinski, Philip; Rivers, Donna; Smith, Solar; Vasicek, Clifford; Verona, Matt
1991-01-01
A payload delivery system will be required to support the buildup and operation of a manned lunar base. In response, a self-unloading, unmanned, reusable lunar lander was conceptually designed. The lander will deliver a 7000 kg payload, with the same dimensions as a space station logistics module, from low lunar orbit to any location on the surface of the moon. The technical aspects of the design is introduced as well as the management structure and project cost.
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Planetary Lake Lander - A Robotic Sentinel to Monitor a Remote Lake
NASA Technical Reports Server (NTRS)
Pedersen, Liam; Smith, Trey; Lee, Susan; Cabrol, Nathalie; Rose, Kevin
2012-01-01
The Planetary Lake Lander Project is studying the impact of rapid deglaciation at a high altitude alpine lake in the Andes, where disrupted environmental, physical, chemical, and biological cycles result in newly emerging natural patterns. The solar powered Lake Lander robot is designed to monitor the lake system and characterize both baseline characteristics and impacts of disturbance events such as storms and landslides. Lake Lander must use an onboard adaptive science-on-the-fly approach to return relevant data about these events to mission control without exceeding limited energy and bandwidth resources. Lake Lander carries weather sensors, cameras and a sonde that is winched up and down the water column to monitor temperature, dissolved oxygen, turbidity and other water quality parameters. Data from Lake Lander is returned via satellite and distributed to an international team of scientists via web-based ground data systems. Here, we describe the Lake Lander Project scientific goals, hardware design, ground data systems, and preliminary data from 2011. The adaptive science-on-the-fly system will be described in future papers.
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NASA Technical Reports Server (NTRS)
2008-01-01
The robotic arm on NASA's Phoenix Mars Lander slid a rock out of the way during the mission's 117th Martian day (Sept. 22, 2008) to gain access to soil that had been underneath the rock.The lander's Surface Stereo Imager took the two images for this stereo view later the same day, showing the rock, called 'Headless,' after the arm pushed it about 40 centimeters (16 inches) from its previous location. 'The rock ended up exactly where we intended it to,' said Matt Robinson of NASA's Jet Propulsion Laboratory, robotic arm flight software lead for the Phoenix team. The arm had enlarged the trench near Headless two days earlier in preparation for sliding the rock into the trench. The trench was dug to about 3 centimeters (1.2 inches) deep. The ground surface between the rock's prior position and the lip of the trench had a slope of about 3 degrees downward toward the trench. Headless is about the size and shape of a VHS videotape. The Phoenix science team sought to move the rock in order to study the soil and the depth to subsurface ice underneath where the rock had been. This image was taken at about 12:30 p.m., local solar time on Mars. The view is to the north northeast of the lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by JPL, Pasadena, Calif. Spacecraft development was by Lockheed Martin Space Systems, Denver. -
Flight Reconstruction of the Mars Pathfinder Disk-Gap-Band Parachute Drag Coefficient
NASA Technical Reports Server (NTRS)
Desai, Prasun; Schofield, John T.; Lisano, Michael E.
2003-01-01
On July 4, 1997, the Mars Pathfinder (MPF) mission successfully landed on Mars. The entry, descent, and landing (EDL) scenario employed the use of a Disk-Gap-Band parachute design to decelerate the Lander. Flight reconstruction of the entry using MPF flight accelerometer data revealed that the MPF parachute decelerated faster than predicted. In the summer of 2003, the Mars Exploration Rover (MER) mission will send two Landers to the surface of Mars arriving in January 2004. The MER mission utilizes a similar EDL scenario and parachute design as that employed by MPF. As a result, characterizing the degree of underperformance of the MPF parachute system is critical for the MER EDL trajectory design. This paper provides an overview of the methodology utilized to estimate the MPF parachute drag coefficient as experienced on Mars.
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Brake Failure from Residual Magnetism in the Mars Exploration Rover Lander Petal Actuator
NASA Technical Reports Server (NTRS)
Jandura, Louise
2004-01-01
In January 2004, two Mars Exploration Rover spacecraft arrived at Mars. Each safely delivered an identical rover to the Martian surface in a tetrahedral lander encased in airbags. Upon landing, the airbags deflated and three Lander Petal Actuators opened the three deployable Lander side petals enabling the rover to exit the Lander. Approximately nine weeks prior to the scheduled launch of the first spacecraft, one of these mission-critical Lander Petal Actuators exhibited a brake stuck-open failure during its final flight stow at Kennedy Space Center. Residual magnetism was the definitive conclusion from the failure investigation. Although residual magnetism was recognized as an issue in the design, the lack of an appropriately specified lower bound on brake drop-out voltage inhibited the discovery of this problem earlier in the program. In addition, the brakes had more unit-to-unit variation in drop-out voltage than expected, likely due to a larger than expected variation in the magnetic properties of the 15-5 PH stainless steel brake plates. Failure analysis and subsequent rework of two other Lander Petal Actuators with marginal brakes was completed in three weeks, causing no impact to the launch date.
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NASA Technical Reports Server (NTRS)
Edquist, Karl T.
2006-01-01
Comparisons are made between the LAURA Navier-Stokes code and Viking Lander Capsule hypersonic aerodynamics data from ground and flight measurements. Wind tunnel data are available for a 3.48 percent scale model at Mach 6 and a 2.75 percent scale model at Mach 10.35, both under perfect gas air conditions. Viking Lander 1 aerodynamics flight data also exist from on-board instrumentation for velocities between 2900 and 4400 m/sec (Mach 14 to 23.3). LAURA flowfield solutions are obtained for the geometry as tested or flown, including sting effects at tunnel conditions and finite-rate chemistry effects in flight. Using the flight vehicle center-of-gravity location (trim angle approx. equals -11.1 deg), the computed trim angle at tunnel conditions is within 0.31 degrees of the angle derived from Mach 6 data and 0.13 degrees from the Mach 10.35 trim angle. LAURA Mach 6 trim lift and drag force coefficients are within 2 percent of measured data, and computed trim lift-to-drag ratio is within 4 percent of the data. Computed trim lift and drag force coefficients at Mach 10.35 are within 5 percent and 3 percent, respectively, of wind tunnel data. Computed trim lift-to-drag ratio is within 2 percent of the Mach 10.35 data. Using the nominal density profile and center-of-gravity location, LAURA trim angle at flight conditions is within 0.5 degrees of the total angle measured from on-board instrumentation. LAURA trim lift and drag force coefficients at flight conditions are within 7 and 5 percent, respectively, of the flight data. Computed trim lift-to-drag ratio is within 4 percent of the data. Computed aerodynamics sensitivities to center-of-gravity location, atmospheric density, and grid refinement are generally small. The results will enable a better estimate of aerodynamics uncertainties for future Mars entry vehicles where non-zero angle-of-attack is required.
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NASA Technical Reports Server (NTRS)
Blanchard, R. C.; Walberg, G. D.
1980-01-01
Results of an investigation to determine the full scale drag coefficient in the high speed, low density regime of the Viking lander capsule 1 entry vehicle are presented. The principal flight data used in the study were from onboard pressure, mass spectrometer, and accelerometer instrumentation. The hypersonic continuum flow drag coefficient was unambiguously obtained from pressure and accelerometer data; the free molecule flow drag coefficient was indirectly estimated from accelerometer and mass spectrometer data; the slip flow drag coefficient variation was obtained from an appropriate scaling of existing experimental sphere data. Comparison of the flight derived drag hypersonic continuum flow regime except for Reynolds numbers from 1000 to 100,000, for which an unaccountable difference between flight and ground test data of about 8% existed. The flight derived drag coefficients in the free molecule flow regime were considerably larger than those previously calculated with classical theory. The general character of the previously determined temperature profile was not changed appreciably by the results of this investigation; however, a slightly more symmetrical temperature variation at the highest altitudes was obtained.
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Design and Analysis of Morpheus Lander Flight Control System
NASA Technical Reports Server (NTRS)
Jang, Jiann-Woei; Yang, Lee; Fritz, Mathew; Nguyen, Louis H.; Johnson, Wyatt R.; Hart, Jeremy J.
2014-01-01
The Morpheus Lander is a vertical takeoff and landing test bed vehicle developed to demonstrate the system performance of the Guidance, Navigation and Control (GN&C) system capability for the integrated autonomous landing and hazard avoidance system hardware and software. The Morpheus flight control system design must be robust to various mission profiles. This paper presents a design methodology for employing numerical optimization to develop the Morpheus flight control system. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics and propellant slosh. Under the assumption that the Morpheus time-varying dynamics and control system can be frozen over a short period of time, the flight controllers are designed to stabilize all selected frozen-time control systems in the presence of parametric uncertainty. Both control gains in the inner attitude control loop and guidance gains in the outer position control loop are designed to maximize the vehicle performance while ensuring robustness. The flight control system designs provided herein have been demonstrated to provide stable control systems in both Draper Ares Stability Analysis Tool (ASAT) and the NASA/JSC Trick-based Morpheus time domain simulation.
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NASA Technical Reports Server (NTRS)
Klem, Mark D.; Smith, Timothy D.
2008-01-01
The Propulsion and Cryogenics Advanced Development (PCAD) Project in the Exploration Technology Development Program is developing technologies as risk mitigation for Orion and the Lunar Lander. An integrated main and reaction control propulsion system has been identified as a candidate for the Lunar Lander Ascent Module. The propellants used in this integrated system are Liquid Oxygen (LOX)/Liquid Methane (LCH4) propellants. A deep throttle pump fed Liquid Oxygen (LOX)/Liquid Hydrogen (LH2) engine system has been identified for the Lunar Lander Descent Vehicle. The propellant combination and architecture of these propulsion systems are novel and would require risk reduction prior to detailed design and development. The PCAD Project addresses the technology requirements to obtain relevant and necessary test data to further the technology maturity of propulsion hardware utilizing these propellants. This plan and achievements to date will be presented.
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SIIOS in Alaska - Testing an `In-Vault' Option for a Europa Lander Seismometer.
NASA Astrophysics Data System (ADS)
Bray, V. J.; Weber, R. C.; DellaGiustina, D. N.; Bailey, H.; Schmerr, N. C.; Pettit, E. C.; Dahl, P.; Albert, D.; Avenson, B.; Byrne, S.; Siegler, M.; Bland, M. T.; Patterson, G. W.; Selznick, S.
2017-12-01
The surface environment of Europa within the radiation-heavy jovian system, poses extreme technical challenges for potential landed missions. The need for radiation shielding and protection from the cold requires instruments to be housed within a thermally insulated and radiation protected `vault'. Unfortunately, this is non-ideal for seismometers as instrument-to-surface coupling is an important factor in the quality of returned data. Delivering a seismic package to an icy world would therefore benefit from the development of a cold-tolerant, radiation-hardened sensor that can survive outside of a protective vault. If such an instrument package were not technologically mature enough, or if lander safety considerations prevent deployment on lander legs, an in-vault location is still a viable option. For such a case, a better understanding of the transmission of seismic signals received through the lander legs is necessary for interpretation of the received signals. The performance, mass, and volume of the `Seismometer to investigate ice and ocean structure' (SIIOS) already meet or exceed flight requirements identified in lander studies for the icy moon Europa. We are testing this flight-candidate in several configurations around and within a lander mock-up, assuming a 1x1 meter vault with extended legs. We compare the received signals from a SIIOS device on the ice with those received by an identical sensor directly above it in the `vault'. We also compare the data from these single-point receivers to that received by two short base-line arrays - A 4-point "in-vault" array and another 4-point array arranged at the ice surface at the base of the lander legs. Our field-testing is performed at Gulkana Glacier, Alaska. The summer melt season provides kilometer-scale regions of coexisting ice, water, and silicate material, thereby providing seismic contrasts analogous to the ice-water layers and possible sub-surface lakes expected at Europa. We demonstrate the sensitivity of SIIOS to detect a variety of passive and active sources from both on-ice and lander-mounted locations, and compare the accuracy of ice-water boundary identification and event location from each configuration.
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Results of the first Seismometer to Investigate Ice and Ocean Structure (SIIOS) Analogue Mission
NASA Astrophysics Data System (ADS)
Della-Giustina, Daniella; Bray, Veronica; "Hop" Bailey, Samuel; Pettit, Erin; Schmerr, Nicholas; Dahl, Peter; Avenson, Brad; Byrne, Shane; SIIOS Team
2017-10-01
The icy moons of Europa and Enceladus are thought to have global subsurface oceans in contact with mineral-rich interiors, likely providing the ingredients needed for life as we know it. The possibility of life forming in the ocean or in melt pockets, relies on the presence of a source of energy and chemistry for biological molecule formation. A thick, stagnant ice crust would likely prevent transfer of oxidants from the surface to the water, halting the development of life. The ice thickness and structure is therefore one of the most important and controversial topics in astrobiology.The best way to access an icy moon’s interior structure is with a lander-based seismometer. Our team has identified a commercial-off-the-shelf device as a flight-candidate for operation in the extreme environment of the icy moons. Based on estimates of Europan seismicity, the flight candidate device is sensitive enough to detect the ice-water boundary and pockets of liquid within the ice. Its low mass and low power enables deployment of multiple seismometers in a short-baseline array on a lander. The performance, mass, and volume of this device meet or exceed flight requirements identified in lander studies making a field test of these seismometers highly representative of a flight unit developed for an Ocean Worlds mission.We report the results of the first field campaign for the SIIOS Analogue Mission Program (AMP), which has evaluates the performance of the flight candidate seismometer in Ocean World terrestrial analogue environments. In particular, the first SIIOS AMP field exercise is performed at Gulkana Glacier, Alaska. During the summer melt season Gulkana provides kilometer-scale regions of coexisting ice, water, and silicate material, thereby providing areas with the desired analogue seismic contrasts. During this first mission, we have demonstrated device sensitivity to the detection of seismicity from high frequency (> 50 Hz) active and passive sources, the depth of ice-water boundaries, and to the ice properties using a short-baseline (1 m2) seismic array and a “lander-mounted” single station seismometer.
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2012-08-09
CAPE CANAVERAL, Fla. – During a free-flight test of the Project Morpheus vehicle at the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida, the vehicle lifted off the ground and then experienced a hardware component failure, which prevented it from maintaining stable flight. No one was injured and the resulting fire was extinguished by Kennedy fire personnel. Engineers are looking into the test data and the agency will release information as it becomes available. Failures such as these were anticipated prior to the test, and are part of the development process for any complex spaceflight hardware. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. Morpheus was manufactured and assembled at JSC and Armadillo Aerospace. Morpheus is large enough to carry 1,100 pounds of cargo to the moon – for example, a humanoid robot, a small rover, or a small laboratory to convert moon dust into oxygen. The primary focus of the test is to demonstrate an integrated propulsion and guidance, navigation and control system that can fly a lunar descent profile to exercise the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, safe landing sensors and closed-loop flight control. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA
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2012-08-09
CAPE CANAVERAL, Fla. – During a free-flight test of the Project Morpheus vehicle at the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida, the vehicle lifted off the ground and then experienced a hardware component failure, which prevented it from maintaining stable flight. No one was injured and the resulting fire was extinguished by Kennedy fire personnel. Engineers are looking into the test data and the agency will release information as it becomes available. Failures such as these were anticipated prior to the test, and are part of the development process for any complex spaceflight hardware. Testing of the prototype lander had been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free-flight test at Kennedy Space Center. Morpheus was manufactured and assembled at JSC and Armadillo Aerospace. Morpheus is large enough to carry 1,100 pounds of cargo to the moon – for example, a humanoid robot, a small rover, or a small laboratory to convert moon dust into oxygen. The primary focus of the test is to demonstrate an integrated propulsion and guidance, navigation and control system that can fly a lunar descent profile to exercise the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, safe landing sensors and closed-loop flight control. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA
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Crew systems and architectural considerations for first lunar surface return missions
NASA Astrophysics Data System (ADS)
Winisdoerffer, F.; Ximenes, S.
1992-08-01
The design requirements for the habitability of the pressurized volumes of a typical first manned lander are presented. Attention is given to providing dual habitation/exploration services (EVA/IVA), supporting the separation of the surface/flight functions, allowing growth potential based on site characteristics, and in situ resources utilization. Lunar lander conceptual diagrams are provided for the basic system architecture, automatic cargo delivery, the piloted crew module, and the pressurized volumes.
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Lean Development with the Morpheus Simulation Software
NASA Technical Reports Server (NTRS)
Brogley, Aaron C.
2013-01-01
The Morpheus project is an autonomous robotic testbed currently in development at NASA's Johnson Space Center (JSC) with support from other centers. Its primary objectives are to test new 'green' fuel propulsion systems and to demonstrate the capability of the Autonomous Lander Hazard Avoidance Technology (ALHAT) sensor, provided by the Jet Propulsion Laboratory (JPL) on a lunar landing trajectory. If successful, these technologies and lessons learned from the Morpheus testing cycle may be incorporated into a landing descent vehicle used on the moon, an asteroid, or Mars. In an effort to reduce development costs and cycle time, the project employs lean development engineering practices in its development of flight and simulation software. The Morpheus simulation makes use of existing software packages where possible to reduce the development time. The development and testing of flight software occurs primarily through the frequent test operation of the vehicle and incrementally increasing the scope of the test. With rapid development cycles, risk of loss of the vehicle and loss of the mission are possible, but efficient progress in development would not be possible without that risk.
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Rock Moved by Mars Lander Arm, Stereo View
NASA Technical Reports Server (NTRS)
2008-01-01
The robotic arm on NASA's Phoenix Mars Lander slid a rock out of the way during the mission's 117th Martian day (Sept. 22, 2008) to gain access to soil that had been underneath the rock.The lander's Surface Stereo Imager took the two images for this stereo view later the same day, showing the rock, called 'Headless,' after the arm pushed it about 40 centimeters (16 inches) from its previous location. 'The rock ended up exactly where we intended it to,' said Matt Robinson of NASA's Jet Propulsion Laboratory, robotic arm flight software lead for the Phoenix team. The arm had enlarged the trench near Headless two days earlier in preparation for sliding the rock into the trench. The trench was dug to about 3 centimeters (1.2 inches) deep. The ground surface between the rock's prior position and the lip of the trench had a slope of about 3 degrees downward toward the trench. Headless is about the size and shape of a VHS videotape. The Phoenix science team sought to move the rock in order to study the soil and the depth to subsurface ice underneath where the rock had been. This left-eye and right-eye images for this stereo view were taken at about 12:30 p.m., local solar time on Mars. The scene appears three-dimensional when seen through blue-red glasses.The view is to the north northeast of the lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by JPL, Pasadena, Calif. Spacecraft development was by Lockheed Martin Space Systems, Denver. -
Phoenix Lander on Mars with Surrounding Terrain, Vertical Projection
NASA Technical Reports Server (NTRS)
2008-01-01
This view is a vertical projection that combines more than 500 exposures taken by the Surface Stereo Imager camera on NASA's Mars Phoenix Lander and projects them as if looking down from above. The black circle on the spacecraft is where the camera itself is mounted on the lander, out of view in images taken by the camera. North is toward the top of the image. The height of the lander's meteorology mast, extending toward the southwest, appears exaggerated because that mast is taller than the camera mast. This view in approximately true color covers an area about 30 meters by 30 meters (about 100 feet by 100 feet). The landing site is at 68.22 degrees north latitude, 234.25 degrees east longitude on Mars. The ground surface around the lander has polygonal patterning similar to patterns in permafrost areas on Earth. This view comprises more than 100 different Stereo Surface Imager pointings, with images taken through three different filters at each pointing. The images were taken throughout the period from the 13th Martian day, or sol, after landing to the 47th sol (June 5 through July 12, 2008). The lander's Robotic Arm is cut off in this mosaic view because component images were taken when the arm was out of the frame. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Lunar scout: A Project Artemis proposal
NASA Technical Reports Server (NTRS)
1992-01-01
The results of a student project to design a lunar lander in the context of a specifically defined mission are presented. The Lunar Scout will be launched from Cape Canaveral, Florida onboard a Delta II launch vehicle. The Delta II will carry the lander and its payload to a 1367 km orbit. Once it reaches that altitude, a STAR 48A solid rocket motor will kick the spacecraft into a lunar trajectory. After burnout of the lunar insertion motor, it will be jettisoned from the spacecraft. The flight from the earth to the moon will take approximately 106.4 hours. During this time the battery, which was fully charged prior to launch, will provide all power to the spacecraft. Every hour, the spacecraft will use its sun sensors and star trackers to update its position, maintain some stabilization and relay it back to earth using the dipole antennas. At the start of its lunar trajectory, the spacecraft will fire one of its 1.5 N thrusters to spin in at a very small rate. The main reason for this is to prevent one side of the spacecraft from overheating in the sun. When the spacecraft nears the moon, it will orient itself for the main retro burn. At an altitude of 200 km, a 4400 N bipropellant liquid thruster will ignite to slow the spacecraft. During the burn, the radar altimeter will be turned on to guide the spacecraft. The main retro rocket will slow the lander to 10 m/s at an approximate altitude of 40 km above the moon. From there, the space craft will use four 4.5 N hydrazine vertical thrusters and 1.5 N horizontal thrusters to guide the spacecraft to a soft landing. Once on the ground, the lander will shutoff the radar and attitude control systems. After the debris from the impact has settled, the six solar panels will be deployed to begin recharging the batteries and to power up the payload. The feedhorn antenna will then rotate to fix itself on the earth. Once it moves, it will stay in that position for the spacecraft's lifetime. The payload will then be activated to begin the lunar mission.
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Lunar scout: A Project Artemis proposal
NASA Astrophysics Data System (ADS)
The results of a student project to design a lunar lander in the context of a specifically defined mission are presented. The Lunar Scout will be launched from Cape Canaveral, Florida onboard a Delta II launch vehicle. The Delta II will carry the lander and its payload to a 1367 km orbit. Once it reaches that altitude, a STAR 48A solid rocket motor will kick the spacecraft into a lunar trajectory. After burnout of the lunar insertion motor, it will be jettisoned from the spacecraft. The flight from the earth to the moon will take approximately 106.4 hours. During this time the battery, which was fully charged prior to launch, will provide all power to the spacecraft. Every hour, the spacecraft will use its sun sensors and star trackers to update its position, maintain some stabilization and relay it back to earth using the dipole antennas. At the start of its lunar trajectory, the spacecraft will fire one of its 1.5 N thrusters to spin in at a very small rate. The main reason for this is to prevent one side of the spacecraft from overheating in the sun. When the spacecraft nears the moon, it will orient itself for the main retro burn. At an altitude of 200 km, a 4400 N bipropellant liquid thruster will ignite to slow the spacecraft. During the burn, the radar altimeter will be turned on to guide the spacecraft. The main retro rocket will slow the lander to 10 m/s at an approximate altitude of 40 km above the moon. From there, the space craft will use four 4.5 N hydrazine vertical thrusters and 1.5 N horizontal thrusters to guide the spacecraft to a soft landing. Once on the ground, the lander will shutoff the radar and attitude control systems. After the debris from the impact has settled, the six solar panels will be deployed to begin recharging the batteries and to power up the payload. The feedhorn antenna will then rotate to fix itself on the earth.
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1998-10-01
KENNEDY SPACE CENTER, FLA. -- At the Shuttle Landing Facility, the Mars Polar Lander is loaded onto a truck after its flight aboard an Air Force C-17 cargo plane that carried it from the Lockheed Martin Astronautics plant in Denver, CO. The lander is being transported to the Spacecraft Assembly and Encapsulation Facility-2(SAEF-2) in the KSC Industrial Area for testing, including a functional test of the science instruments and the basic spacecraft subsystems. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars Polar Lander spacecraft is planned for launch from Cape Canaveral Air Station aboard a Delta II rocket on Jan. 3, 1999
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Robotic Lunar Landers for Science and Exploration
NASA Technical Reports Server (NTRS)
Cohen, Barbara A.
2012-01-01
The MSFC/APL Robotic Lunar Landing Project (RLLDP) team has developed lander concepts encompassing a range of mission types and payloads for science, exploration, and technology demonstration missions: (1) Developed experience and expertise in lander systems, (2) incorporated lessons learned from previous efforts to improve the fidelity of mission concepts, analysis tools, and test beds Mature small and medium lander designs concepts have been developed: (1) Share largely a common design architecture. (2) Flexible for a large number of mission and payload options. High risk development areas have been successfully addressed Landers could be selected for a mission with much of the concept formulation phase work already complete
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Enabling technologies for Chinese Mars lander guidance system
NASA Astrophysics Data System (ADS)
Jiang, Xiuqiang; Li, Shuang
2017-04-01
Chinese first Mars exploration activity, orbiting landing and roaming collaborative mission, has been programmed and started. As a key technology, Mars lander guidance system is intended to serve atmospheric entry, descent and landing (EDL) phases. This paper is to report the formation process of enabling technology road map for Chinese Mars lander guidance system. First, two scenarios of the first-stage of the Chinese Mars exploration project are disclosed in detail. Second, mission challenges and engineering needs of EDL guidance, navigation, and control (GNC) are presented systematically for Chinese Mars exploration program. Third, some useful related technologies developed in China's current aerospace projects are pertinently summarized, especially on entry guidance, parachute descent, autonomous hazard avoidance and safe landing. Finally, an enabling technology road map of Chinese Mars lander guidance is given through technological inheriting and improving.
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A Mars airplane. [for Mars environment surveys
NASA Technical Reports Server (NTRS)
Clarke, V. C.; Kerem, A.; Lewis, R.
1979-01-01
An airplane specifically designed for Mars flight is described, emphasizing its conceivable role as an aerial surveyor for visual imaging, gamma-ray and IR reflectance spectroscopy, studies of atmospheric composition and dynamics, and gravity-field, magnetic-field, and electromagnetic sounding. Possible imaging systems and surveying tasks are considered, along with a plausible mission scenario for a fleet of 12 airplanes, which would be taken to Mars in squadrons of four by three Shuttle/IUS Twin Stage/spacecraft carriers. A basic configuration closely resembling that of a competition glider is examined, and four types of airplane are discussed: hydrazine-powered cruisers and landers and electrically powered cruisers and landers. Attention is given to navigation, guidance, and control avionics, vehicle weight, the use of composite materials for the wing, and flight testing on earth.
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Morpheus Lander Roll Control System and Wind Modeling
NASA Technical Reports Server (NTRS)
Gambone, Elisabeth A.
2014-01-01
The Morpheus prototype lander is a testbed capable of vertical takeoff and landing developed by NASA Johnson Space Center to assess advanced space technologies. Morpheus completed a series of flight tests at Kennedy Space Center to demonstrate autonomous landing and hazard avoidance for future exploration missions. As a prototype vehicle being tested in Earth's atmosphere, Morpheus requires a robust roll control system to counteract aerodynamic forces. This paper describes the control algorithm designed that commands jet firing and delay times based on roll orientation. Design, analysis, and testing are supported using a high fidelity, 6 degree-of-freedom simulation of vehicle dynamics. This paper also details the wind profiles generated using historical wind data, which are necessary to validate the roll control system in the simulation environment. In preparation for Morpheus testing, the wind model was expanded to create day-of-flight wind profiles based on data delivered by Kennedy Space Center. After the test campaign, a comparison of flight and simulation performance was completed to provide additional model validation.
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Lunar lander stage requirements based on the Civil Needs Data Base
NASA Technical Reports Server (NTRS)
Mulqueen, John A.
1992-01-01
This paper examines the lunar lander stages that will be necessary for the future exploration and development of the Moon. Lunar lander stage sizing is discussed based on the projected lunar payloads listed in the Civil Needs Data Base. Factors that will influence the lander stage design are identified and discussed. Some of these factors are (1) lunar orbiting and lunar surface lander bases; (2) implications of direct landing trajectories and landing from a parking orbit; (3) implications of landing site and parking orbit; (4) implications of landing site and parking orbit selection; (5) the use of expendable and reusable lander stages; and (6) the descent/ascent trajectories. Data relating the lunar lander stage design requirements to each of the above factors and others are presented in parametric form. These data will provide useful design data that will be applicable to future mission model modifications and design studies.
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Mars In-Situ Propellant Production Precursor (MIP) Flight Demonstration Project: Overview
NASA Technical Reports Server (NTRS)
Kaplan, D. I.; Ratliff, J. E.; Baird, R. S.; Sanders, G. B.; Johnson, K. R.; Karlmann, P. B.; Juanero, K. J.; Baraona, C. R.; Landis, G. A.; Jenkins, P. P.;
1999-01-01
Strategic planning for human missions of exploration to Mars has conclusively identified in-situ propellant production (ISPP) as an enabling technology. A team of scientists and engineers from NASA's Johnson Space Center, Jet Propulsion Laboratory, and Lewis Research Center is preparing the MARS ISPP PRECURSOR (MIP) Flight Demonstration. The objectives of MIP are to characterize the performance of processes and hardware which are important to ISPP concepts and to demonstrate how these processes and hardware interact with the Mars environment. Operating this hardware in the actual Mars environment is extremely important due to both uncertainties in our knowledge of the Mars environment as well as because of conditions that cannot be adequately simulated on Earth. The MIP Flight Demonstration is a payload onboard the MARS SURVEYOR Lander and will be launched in April 2001. MIP will be the first hardware to utilize the indigenous resources of a planet or moon. Its successful operation will pave the way for future robotic and human missions to rely on propellants produced using Martian resources as feedstock.
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Mars In-Situ Propellant Production Precursor (MIP) Flight Demonstration Project: Overview
NASA Technical Reports Server (NTRS)
Kaplan, D. I.; Ratliff, J. E.; Sanders, G. B.; Johnson, K. R.; Karlmann, P. B.; Juanero, K. J.; Barona, C. R.; Landis, G. A.; Jenkins, P. P.; Scheiman, D. A.
1999-01-01
Strategic planning for human missions of exploration to Mars has conclusively identified in-situ propellant production (ISPP) as an enabling technology. A team of scientists and engineers from NASA's Johnson Space Center, Jet Propulsion Laboratory, and Lewis Research Center is preparing the MARS ISPP Precursors (MIP) Flight Demonstration. The objectives of MIP are to characterize the performance of processes and hardware which are important to ISPP concepts and to demonstrate how these processes and hardware interact with the Mars environment. Operating this hardware in the actual Mars environment is extremely important due to both uncertainties in our knowledge of the Mars environment as well as because of conditions that cannot be adequately simulated on Earth. The MIP Flight Demonstration is a payload onboard the MARS SURVEYOR Lander and will be launched in April 2001. MIP will be the first hardware to utilize the indigenous resources of a planet or moon. Its successful operation will pave the way for future robotic and human missions to rely on propellants produced using Martian resources as feedstock.
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Navigation Strategy for the Mars 2001 Lander Mission
NASA Technical Reports Server (NTRS)
Mase, Robert A.; Spencer, David A.; Smith, John C.; Braun, Robert D.
2000-01-01
The Mars Surveyor Program (MSP) is an ongoing series of missions designed to robotically study, map and search for signs of life on the planet Mars. The MSP 2001 project will advance the effort by sending an orbiter, a lander and a rover to the red planet in the 2001 opportunity. Each vehicle will carry a science payload that will Investigate the Martian environment on both a global and on a local scale. Although this mission will not directly search for signs of life, or cache samples to be returned to Earth, it will demonstrate certain enabling technologies that will be utilized by the future Mars Sample Return missions. One technology that is needed for the Sample Return mission is the capability to place a vehicle on the surface within several kilometers of the targeted landing site. The MSP'01 Lander will take the first major step towards this type of precision landing at Mars. Significant reduction of the landed footprint will be achieved through two technology advances. The first, and most dramatic, is hypersonic aeromaneuvering; the second is improved approach navigation. As a result, the guided entry will produce in a footprint that is only tens of kilometers, which is an order of magnitude improvement over the Pathfinder and Mars Polar Lander ballistic entries. This reduction will significantly enhance scientific return by enabling the potential selection of otherwise unreachable landing sites with unique geologic interest and public appeal. A landed footprint reduction from hundreds to tens of kilometers is also a milestone on the path towards human exploration of Mars, where the desire is to place multiple vehicles within several hundred meters of the planned landing site. Hypersonic aeromaneuvering is an extension of the atmospheric flight goals of the previous landed missions, Pathfinder and Mars Polar Lander (MPL), that utilizes aerodynamic lift and an autonomous guidance algorithm while in the upper atmosphere. The onboard guidance algorithm will control the direction of the lift vector, via bank angle modulation, to keep the vehicle on the desired trajectory. While numerous autonomous guidance algorithms have been developed for use during hypersonic flight at Earth, this will be the first flight of an autonomously directed lifting entry vehicle at Mars. However, without sufficient control and knowledge of the atmospheric entry conditions, the guidance algorithm will not perform effectively. The goal of the interplanetary navigation strategy is to deliver the spacecraft to the desired entry condition with sufficient accuracy and knowledge to enable satisfactory guidance algorithm performance. Specifically, the entry flight path angle must not exceed 0.27 deg. to a 3 sigma confidence level. Entry errors will contribute directly to the size of the landed footprint and the most significant component is entry flight path angle. The size of the entry corridor is limited on the shallow side by integrated heating constraints, and on the steep side by deceleration (g-load) and terminal descent propellant. In order to meet this tight constraint it is necessary to place a targeting maneuver seven hours prior to the time of entry. At this time the trajectory knowledge will be quite accurate, and the effects of maneuver execution errors will be small. The drawback is that entry accuracy is dependent on the success of this final late maneuver. Because propulsive maneuvers are critical events, it is desirable to minimize their occurrence and provide the flight team with as much response time as possible in the event of a spacecraft fault. A mission critical maneuver at Entry - 7 hours does not provide much fault tolerance, and it is desirable to provide a strategy that minimizes reliance on this maneuver. This paper will focus on the Improvements in interplanetary navigation that will decrease entry errors and will reduce the landed footprint, even in the absence of aeromaneuvering. The easiest to take advantage of are Improvements In the knowledge of the Mars ephemeris and gravity field due to the MGS and MSP'98 missions. Improvements In data collection and reduction techniques such as "precislon ranging' and near-simultaneous tracking will also be utilized. In addition to precise trajectory control, a robust strategy for communications and flight operations must also be demonstrated. The result Is a navigation and communications strategy on approach that utilizes optimal maneuver placement to take advantage of trajectory knowledge, minimizes risk for the flight operations team, is responsive to spacecraft hardware limitations, and achieves the entry corridor. The MSP2001 mission Is managed at JPL under the auspices of the Mars Exploration Directorate. The spacecraft flight elements are built and managed by Lockheed-Martin Astronautics in Denver, Colorado.
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NASA Technical Reports Server (NTRS)
Timmerman, Paul J.; Surampudi, Subbarao
2000-01-01
A viewgraph presentation outlines the Jet Propulsion Laboratory (JPL) flight programs, including past, present and future missions targeting Solar System exploration. Details, including launch dates and batteries used, are given for Deep Space 1 (Asteroid Rendezvous), Deep Space 2 (Mars Penetrator), Mars Global Surveyor, Mars Surveyor '98, Stardust, Europa Orbiter, Mars Surveyor 2001, Mars 2003 Lander and Rover, and Genesis (Solar Dust Return). Earth science projects are also outlined: Active Cavity Radiometer Irradiance Monitor (ARIMSAT), Ocean Topography Experiment (TOPEX/Poseidon), Jason-1 (TOPEX follow-on), and QuikScat/Seawinds (Ocean Winds Tracking). The status, background, and plans are given for several batteries: (1) 2.5 inch common pressure vessel (CPV), (2) 3.5 inch CPV, (3) Ni-H2, and (4) Li-Ion.
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NASA Technical Reports Server (NTRS)
1991-01-01
Project UM-Haul is the preliminary design of a reusable lunar transportation vehicle that travels between a lunar parking orbit and the lunar surface. This vehicle is an indispensible link in the overall task of establishing a lunar base as defined by the NASA Space Exploration Initiative. The response to this need consists of two independent vehicles: a lander and an unloader. The system can navigate and unload itself with a minimum amount of human intervention. The design addresses structural analysis, propulsion, power, controls, communications, payload handling and orbital operations. The Lander has the capacity to decend from low lunar orbit (LLO) to the lunar surface carrying a 7000 kg payload, plus the unloader, plus propellant for ascent to LLO. The Lander employs the Unloader by way of a motorized ramp. The Unloader is a terrain vehicle capable of carrying cargoes of 8,500 kg mass and employs a lift system to lower payloads to the ground. The system can perform ten missions before requiring major servicing.
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Lunar transit telescope lander design
NASA Technical Reports Server (NTRS)
Omar, Husam A.
1991-01-01
The Program Development group at NASA's Marshall Space Flight Center has been involved in studying the feasibility of placing a 16 meter telescope on the lunar surface to scan the skies using visible/ Ultraviolet/ Infrared light frequencies. The precursor telescope is now called the TRANSIT LUNAR TELESCOPE (LTT). The Program Development Group at Marshall Space Flight Center has been given the task of developing the basic concepts and providing a feasibility study on building such a telescope. The telescope should be simple with minimum weight and volume to fit into one of the available launch vehicles. The preliminary launch date is set for 2005. A study was done to determine the launch vehicle to be used to deliver the telescope to the lunar surface. The TITAN IV/Centaur system was chosen. The engineering challenge was to design the largest possible telescope to fit into the TITAN IV/Centaur launch system. The telescope will be comprised of the primary, secondary and tertiary mirrors and their supporting system in addition to the lander that will land the telescope on the lunar surface and will also serve as the telescope's base. The lunar lander should be designed integrally with the telescope in order to minimize its weight, thus allowing more weight for the telescope and its support components. The objective of this study were to design a lander that meets all the constraints of the launching system. The basic constraints of the TITAN IV/Centaur system are given.
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Lunar transit telescope lander design
NASA Technical Reports Server (NTRS)
Omar, Husam A.
1992-01-01
The Program Development group at NASA's Marshall Space Flight Center has been involved in studying the feasibility of placing a 16 meter telescope on the lunar surface to scan the skies using visible/ Ultraviolet/ Infrared light frequencies. The precursor telescope is now called the TRANSIT LUNAR TELESCOPE (LTT). The Program Development Group at Marshall Space Flight Center has been given the task of developing the basic concepts and providing a feasibility study on building such a telescope. The telescope should be simple with minimum weight and volume to fit into one of the available launch vehicles. The preliminary launch date is set for 2005. A study was done to determine the launch vehicle to be used to deliver the telescope to the lunar surface. The TITAN IV/Centaur system was chosen. The engineering challenge was to design the largest possible telescope to fit into the TITAN IV/Centaur launch system. The telescope will be comprised of the primary, secondary and tertiary mirrors and their supporting system in addition to the lander that will land the telescope on the lunar surface and will also serve as the telescope's base. The lunar lander should be designed integrally with the telescope in order to minimize its weight, thus allowing more weight for the telescope and its support components. The objective of this study were to design a lander that meets all the constraints of the launching system. The basic constraints of the TITAN IV/Centaur system are given.
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Progress of the Mars Array Technology Experiment (MATE) on the 2001 Lander
NASA Technical Reports Server (NTRS)
Scheiman, David A.; Baraona, Cosmo; Wilt, Dave; Jenkins, Phil; Krasowski, Michael; Greer, Lawrence; Lekki, John; Spina, Daniel; Landis, Geoff
2005-01-01
NASA is planning missions to Mars every two years until 2010, these missions will rely on solar power. Sunlight on the surface of Mars is altered by airborne dust and fluctuates from day to day. The MATE flight experiment was designed to evaluate solar cell performance and will fly on the Mars 2001 surveyor Lander as part of the Mars In-Situ Propellant Production Precursor (MIP) package. MATE will measure several solar cell technologies and characterize the Martian environment's solar power. This will be done by measuring full IV curvers on solar cells, direct and global insolation, temperature, and spectral content. The lander is scheduled to launch in April 2001 and arrive on Mars in January of 2002. The site location has not been identified but will be near the equator, is a powered landing, and is baselined for 90 sols. The intent of this paper is to provide a brief overview of the MATE experiment and progress to date. The MATE Development Unit (DU) hardware has been built and has completed testing, work is beginning in the Qualification Unit which will start testing later this year, Flight Hardware is to be delivered next spring.
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Self-unloading, reusable, lunar lander project
NASA Technical Reports Server (NTRS)
Arseculeratne, Ruwan; Cavazos, Melissa; Euker, John; Ghavidel, Fred; Hinkel, Todd J.; Hitzfelder, John; Leitner, Jesse; Nevik, James; Paynter, Scott; Zolondek, Allen
1990-01-01
In the early 21st century, NASA will return to the Moon and establish a permanent base. To achieve this goal safely and economically, B&T Engineering has designed an unmanned, reusable, self-unloading lunar lander. The lander is designed to deliver 15,000 kg payloads from an orbit transfer vehicle (OTV) in a low lunar polar orbit and an altitude of 200 km to any location on the lunar surface.
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Power System Trade Studies for the Lunar Surface Access Module
NASA Technical Reports Server (NTRS)
Kohout, Lisa, L.
2008-01-01
A Lunar Lander Preparatory Study (LLPS) was undertaken for NASA's Lunar Lander Pre-Project in 2006 to explore a wide breadth of conceptual lunar lander designs. Civil servant teams from nearly every NASA center responded with dozens of innovative designs that addressed one or more specific lander technical challenges. Although none of the conceptual lander designs sought to solve every technical design issue, each added significantly to the technical database available to the Lunar Lander Project Office as it began operations in 2007. As part of the LLPS, a first order analysis was performed to identify candidate power systems for the ascent and descent stages of the Lunar Surface Access Module (LSAM). A power profile by mission phase was established based on LSAM subsystem power requirements. Using this power profile, battery and fuel cell systems were modeled to determine overall mass and volume. Fuel cell systems were chosen for both the descent and ascent stages due to their low mass. While fuel cells looked promising based on these initial results, several areas have been identified for further investigation in subsequent studies, including the identification and incorporation of peak power requirements into the analysis, refinement of the fuel cell models to improve fidelity and incorporate ongoing technology developments, and broadening the study to include solar power.
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COBALT: A GN&C Payload for Testing ALHAT Capabilities in Closed-Loop Terrestrial Rocket Flights
NASA Technical Reports Server (NTRS)
Carson, John M., III; Amzajerdian, Farzin; Hines, Glenn D.; O'Neal, Travis V.; Robertson, Edward A.; Seubert, Carl; Trawny, Nikolas
2016-01-01
The COBALT (CoOperative Blending of Autonomous Landing Technology) payload is being developed within NASA as a risk reduction activity to mature, integrate and test ALHAT (Autonomous precision Landing and Hazard Avoidance Technology) systems targeted for infusion into near-term robotic and future human space flight missions. The initial COBALT payload instantiation is integrating the third-generation ALHAT Navigation Doppler Lidar (NDL) sensor, for ultra high-precision velocity plus range measurements, with the passive-optical Lander Vision System (LVS) that provides Terrain Relative Navigation (TRN) global-position estimates. The COBALT payload will be integrated onboard a rocket-propulsive terrestrial testbed and will provide precise navigation estimates and guidance planning during two flight test campaigns in 2017 (one open-loop and closed- loop). The NDL is targeting performance capabilities desired for future Mars and Moon Entry, Descent and Landing (EDL). The LVS is already baselined for TRN on the Mars 2020 robotic lander mission. The COBALT platform will provide NASA with a new risk-reduction capability to test integrated EDL Guidance, Navigation and Control (GN&C) components in closed-loop flight demonstrations prior to the actual mission EDL.
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Flight Analysis of an Autonomously Navigated Experimental Lander for High Altitude Recovery
NASA Technical Reports Server (NTRS)
Chin, Jeffrey; Niehaus, Justin; Goodenow, Debra; Dunker, Storm; Montague, David
2016-01-01
First steps have been taken to qualify a family of parafoil systems capable of increasing the survivability and reusability of high-altitude balloon payloads. The research is motivated by the common risk facing balloon payloads where expensive flight hardware can often land in inaccessible areas that make them difficult or impossible to recover. The Autonomously Navigated Experimental Lander (ANGEL) flight test introduced a commercial Guided Parachute Aerial Delivery System (GPADS) to a previously untested environment at 108,000ft MSL to determine its high-altitude survivability and capabilities. Following release, ANGEL descended under a drogue until approximately 25,000ft, at which point the drogue was jettisoned and the main parachute was deployed, commencing navigation. Multiple data acquisition platforms were used to characterize the return-to-point technology performance and help determine its suitability for returning future scientific payloads ranging from 180 to 10,000lbs to safer and more convenient landing locations. This report describes the test vehicle design, and summarizes the captured sensor data. Various post-flight analyses are used to quantify the system's performance, gondola load data, and serve as a reference point for subsequent missions.
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Flight Analysis of an Autonomously Navigated Experimental Lander
NASA Technical Reports Server (NTRS)
Chin, Jeffrey; Niehaus, Justin; Goodenow, Debra; Dunker, Storm; Montague, David
2016-01-01
First steps have been taken to qualify a family of parafoil systems capable of increasing the survivability and reusability of high-altitude balloon payloads. The research is motivated by the common risk facing balloon payloads where expensive flight hardware can often land in inaccessible areas that make them difficult or impossible to recover. The Autonomously Navigated Experimental Lander (ANGEL) flight test introduced a commercial Guided Parachute Aerial Delivery System (GPADS) to a previously untested environment at 108,000 feet Mean Sea Level (MSL) to determine its high-altitude survivability and capabilities. Following release, ANGEL descended under a drogue until approximately 25,000 feet, at which point the drogue was jettisoned and the main parachute was deployed, commencing navigation. Multiple data acquisition platforms were used to characterize the return-to-point technology performance and help determine its suitability for returning future scientific payloads ranging from 180 to 10,000 pounds to safer and more convenient landing locations. This report describes the test vehicle design, and summarizes the captured sensor data. Various post-flight analyses are used to quantify the systems performance, gondola load data, and serve as a reference point for subsequent missions.
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The Vikings are coming. [landing site selection and experiments
NASA Technical Reports Server (NTRS)
Spitzer, C. R.
1976-01-01
The exploration of Mars with the aid of the two Viking landers is discussed. The probable landing date for Viking Lander 1 will be July 4, 1976, and for Lander 2 September 4, 1976. The criteria used in selecting the landing site are considered along with the procedure to be employed in the final approach of the lander to the planet and the touchdown. A description is given of the studies to be conducted by the lander, taking into account the search for life and the collection of meteorological and seismological data. Attention is also given to technical data concerning the spacecraft, details regarding the software, and the ground facilities on earth which are used for the Viking project.
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Constellation Program Mission Operations Project Office Status and Support Philosophy
NASA Technical Reports Server (NTRS)
Smith, Ernest; Webb, Dennis
2007-01-01
The Constellation Program Mission Operations Project Office (CxP MOP) at Johnson Space Center in Houston Texas is preparing to support the CxP mission operations objectives for the CEV/Orion flights, the Lunar Lander, and and Lunar surface operations. Initially the CEV will provide access to the International Space Station, then progress to the Lunar missions. Initial CEV mission operations support will be conceptually similar to the Apollo missions, and we have set a challenge to support the CEV mission with 50% of the mission operations support currently required for Shuttle missions. Therefore, we are assessing more efficient way to organize the support and new technologies which will enhance our operations support. This paper will address the status of our preparation for these CxP missions, our philosophical approach to CxP operations support, and some of the technologies we are assessing to streamline our mission operations infrastructure.
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An Evaluation of Ultra-High Pressure Regulator for Robotic Lunar Landing Spacecraft
NASA Technical Reports Server (NTRS)
Burnside, Christopher; Trinh, Huu; Pedersen, Kevin
2011-01-01
The Robotic Lunar Lander Development (RLLD) Project Office at NASA Marshall Space Flight Center (MSFC) has studied several lunar surface science mission concepts. These missions focus on spacecraft carrying multiple science instruments and power systems that will allow extended operations on the lunar surface. Initial trade studies of launch vehicle options for these mission concepts indicate that the spacecraft design will be significantly mass-constrained. To minimize mass and facilitate efficient packaging, the notional propulsion system for these landers has a baseline of an ultra-high pressure (10,000 psig) helium pressurization system that has been used on Defense missiles. The qualified regulator is capable of short duration use; however, the hardware has not been previously tested at NASA spacecraft requirements with longer duration. Hence, technical risks exist in using this missile-based propulsion component for spacecraft applications. A 10,000-psig helium pressure regulator test activity is being carried out as part of risk reduction testing for MSFC RLLD project. The goal of the test activity is to assess the feasibility of commercial off-the-shelf ultra-high pressure regulator by testing with a representative flight mission profile. Slam-start, gas blowdown, water expulsion, lock-up, and leak tests are also performed on the regulator to assess performance under various operating conditions. The preliminary test results indicated that the regulator can regulate helium to a stable outlet pressure of 740 psig within the +/- 5% tolerance band and maintain a lock-up pressure less than +5% for all tests conducted. Numerous leak tests demonstrated leakage less than 10-3 standard cubic centimeters per second (SCCS) for internal seat leakage at lock-up and less than10-5 SCCS for external leakage through the regulator ambient reference cavity. The successful tests have shown the potential for 10,000 psig helium systems in NASA spacecraft and have reduced risk associated with hardware availability and hardware ability to meet RLL mission requirements.
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Lunar Surface Access Module Descent Engine Turbopump Technology: Detailed Design
NASA Technical Reports Server (NTRS)
Alvarez, Erika; Forbes, John C.; Thornton, Randall J.
2010-01-01
The need for a high specific impulse LOX/LH2 pump-fed lunar lander engine has been established by NASA for the new lunar exploration architecture. Studies indicate that a 4-engine cluster in the thrust range of 9,000-lbf each is a candidate configuration for the main propulsion of the manned lunar lander vehicle. The lander descent engine will be required to perform multiple burns including the powered descent onto the lunar surface. In order to achieve the wide range of thrust required, the engines must be capable of throttling approximately 10:1. Working under internal research and development funding, NASA Marshall Space Flight Center (MSFC) has been conducting the development of a 9,000-lbf LOX/LH2 lunar lander descent engine technology testbed. This paper highlights the detailed design and analysis efforts to develop the lander engine Fuel Turbopump (FTP) whose operating speeds range from 30,000-rpm to 100,000-rpm. The capability of the FTP to operate across this wide range of speeds imposes several structural and dynamic challenges, and the small size of the FTP creates scaling and manufacturing challenges that are also addressed in this paper.
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Lunar Surface Access Module Descent Engine Turbopump Technology: Detailed Design
NASA Technical Reports Server (NTRS)
Alarez, Erika; Thornton, Randall J.; Forbes, John C.
2008-01-01
The need for a high specific impulse LOX/LH2 pump-fed lunar lander engine has been established by NASA for the new lunar exploration architecture. Studies indicate that a 4-engine cluster in the thrust range of 9,000-lbf each is a candidate configuration for the main propulsion of the manned lunar lander vehicle. The lander descent engine will be required to perform minor mid-course corrections, a Lunar Orbit Insertion (LOI) burn, a de-orbit burn, and the powered descent onto the lunar surface. In order to achieve the wide range of thrust required, the engines must be capable of throttling approximately 10:1. Working under internal research and development funding, NASA Marshall Space Flight Center (MSFC) has been conducting the development of a 9,000-lbf LOX/LH2 lunar lander descent engine testbed. This paper highlights the detailed design and analysis efforts to develop the lander engine Fuel Turbopump (FTP) whose operating speeds range from 30,000-rpm to 100,000-rpm. The capability of the FTP to operate across this wide range of speeds imposes several structural and dynamic challenges, and the small size of the FTP creates scaling and manufacturing challenges that are also addressed in this paper.
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Development of a Mars Surface Imager
NASA Technical Reports Server (NTRS)
Squyres, Steve W.
1994-01-01
The Mars Surface Imager (MSI) is a multispectral, stereoscopic, panoramic imager that allows imaging of the full scene around a Mars lander from the lander body to the zenith. It has two functional components: panoramic imaging and sky imaging. In the most recent version of the MSI, called PIDDP-cam, a very long multi-line color CCD, an innovative high-performance drive system, and a state-of-the-art wavelet image compression code have been integrated into a single package. The requirements for the flight version of the MSI and the current design are presented.
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Spaceship Discovery's Crew and Cargo Lander Module Designs for Human Exploration of Mars
NASA Astrophysics Data System (ADS)
Benton, Mark G.
2008-01-01
The Spaceship Discovery design was first presented at STAIF 2006. This conceptual design space vehicle architecture for human solar system exploration includes two types of Mars exploration lander modules: A piloted crew lander, designated Lander Module 2 (LM2), and an autonomous cargo lander, designated Lander Module 3 (LM3). The LM2 and LM3 designs were first presented at AIAA Space 2007. The LM2 and LM3 concepts have recently been extensively redesigned. The specific objective of this paper is to present these revised designs. The LM2 and LM3 landers are based on a common design that can be configured to carry either crew or cargo. They utilize a combination of aerodynamic reentry, parachutes, and propulsive braking to decelerate from orbital velocity to a soft landing. The LM2 crew lander provides two-way transportation for a nominal three-person crew between Mars orbit and the surface, and provides life support for a 30-day contingency mission. It contains an ascent section to return the crew to orbit after completion of surface operations. The LM3 cargo lander provides one-way, autonomous transportation of cargo from Mars orbit to the surface and can be configured to carry a mix of consumables and equipment, or equipment only. Lander service life and endurance is based on the Spaceship Discovery conjunction-class Design Reference Mission 2. The LM3 is designed to extend the surface stay for three crew members in an LM2 crew lander such that two sets of crew and cargo landers enable human exploration of the surface for the bulk of the 454 day wait time at Mars, in two shifts of three crew members each. Design requirements, mission profiles, mass properties, performance data, and configuration layouts are presented for the LM2 crew and LM3 cargo landers. These lander designs are a proposed solution to the problem of safely transporting a human crew from Mars orbit to the surface, sustaining them for extended periods of time on the surface, and returning them safely to orbit. They are based on reliable and proven technology and build on an extensive heritage of successful unmanned probes. Safety, redundancy, and abort and rescue capabilities are stressed in the design and operations concepts. The designs share many common features, hardware, subsystems, and flight control modes to reduce development cost.
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Resource Prospector Lander: Architecture and Trade Studies
NASA Technical Reports Server (NTRS)
Moore, Josh; Calvert, Derek; Frady, Greg; Chavers, Greg; Wayne, Andrew; Hull, Patrick; Lowery, Eric; Farmer, Jeff; Trinh, Huu; Rojdev, Kristina;
2014-01-01
NASA's Resource Prospector (RP) is a multi-center and multi-institution collaborative project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and is approximately 10 days. The RP vehicle comprises three elements: the Lander, the Rover, and the Payload. The Payload is housed on the Rover and the Rover is on top of the Lander. The focus of this paper is on the Lander element for the RP vehicle. The design of the Lander was requirements driven and focused on a low-cost approach. To arrive at the final configuration, several trade studies were conducted. Of those trade studies, there were six primary trade studies that were instrumental in determining the final design. This paper will discuss each of these trades in further detail and show how these trades led to the final architecture of the RP Lander.
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Low-cost unmanned lunar lander
NASA Technical Reports Server (NTRS)
Daniel, Walter K.
1992-01-01
Two student groups designed unmanned landers to deliver 200 kilogram payloads to the lunar surface. Payloads could include astronomical telescopes, small lunar rovers, and experiments related to future human exploration. Requirements include the use of existing hardware where possible, use of a medium-class launch vehicle, an unobstructed view of the sky for the payload, and access to the lunar surface for the payload. The projects were modeled after Artemis, a project that the NASA Office of Exploration is pursuing with a planned first launch in 1996. The Lunar Scout design uses a Delta 2 launch vehicle with a Star 48 motor for insertion into the trans-lunar trajectory. During the transfer, the solar panels will be folded inward and the spacecraft will be powered by rechargeable nickel-cadmium batteries. The lander will use a combination of a solid rocket motor and hydrazine thrusters for the descent to the lunar surface. The solar arrays will be deployed after landing. The lander will provide power for operations to the payload during the lunar day; batteries will provide 'stay-alive' power during the lunar night. A horn antenna on the lander will provide communications between the payload and the earth.
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NASA Propulsion Concept Studies and Risk Reduction Activities for Resource Prospector Lander
NASA Technical Reports Server (NTRS)
Trinh, Huu P.; Williams, Hunter; Burnside, Chris
2015-01-01
The trade study has led to the selection of propulsion concept with the lowest cost and net lowest risk -Government-owned, flight qualified components -Meet mission requirements although the configuration is not optimized. Risk reduction activities have provided an opportunity -Implement design improvements while development with the early-test approach. -Gain knowledge on the operation and identify operation limit -Data to anchor analytical models for future flight designs; The propulsion system cold flow tests series have provided valuable data for future design. -The pressure surge from the system priming and waterhammer within component operation limits. -Enable to optimize the ullage volume to reduce the propellant tank mass; RS-34 hot fire tests have successfully demonstrated of using the engines for the RP mission -No degradation of performance due to extended storage life of the hardware. -Enable to operate the engine for RP flight mission scenarios, outside of the qualification regime. -Provide extended data for the thermal and GNC designs. Significant progress has been made on NASA propulsion concept design and risk reductions for Resource Prospector lander.
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COBALT CoOperative Blending of Autonomous Landing Technology
NASA Technical Reports Server (NTRS)
Carson, John M. III; Restrepo, Carolina I.; Robertson, Edward A.; Seubert, Carl R.; Amzajerdian, Farzin
2016-01-01
COBALT is a terrestrial test platform for development and maturation of GN&C (Guidance, Navigation and Control) technologies for PL&HA (Precision Landing and Hazard Avoidance). The project is developing a third generation, Langley Navigation Doppler Lidar (NDL) for ultra-precise velocity and range measurements, which will be integrated and tested with the JPL Lander Vision System (LVS) for Terrain Relative Navigation (TRN) position estimates. These technologies together provide navigation that enables controlled precision landing. The COBALT hardware will be integrated in 2017 into the GN&C subsystem of the Xodiac rocket-propulsive Vertical Test Bed (VTB) developed by Masten Space Systems (MSS), and two terrestrial flight campaigns will be conducted: one open-loop (i.e., passive) and one closed-loop (i.e., active).
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Environmental Assurance Program for the Phoenix Mars Mission
NASA Technical Reports Server (NTRS)
Man, Kin F.; Natour, Maher C.; Hoffman, Alan R.
2008-01-01
The Phoenix Mars mission involves delivering a stationary science lander on to the surface of Mars in the polar region within the latitude band 65 deg N to 72 deg N. Its primary objective is to perform in-situ and remote sensing investigations that will characterize the chemistry of the materials at the local surface, subsurface, and atmosphere. The Phoenix spacecraft was launched on August 4, 2007 and will arrive at Mars in May 2008. The lander includes a suite of seven (7) science instruments. This mission is baselined for up to 90 sols (Martian days) of digging, sampling, and analysis. Operating at the Mars polar region creates a challenging environment for the Phoenix landed subsystems and instruments with Mars surface temperature extremes between -120 deg C to 25 deg C and diurnal thermal cycling in excess of 145 deg C. Some engineering and science hardware inside the lander were qualification tested up to 80 deg C to account for self heating. Furthermore, many of the hardware for this mission were inherited from earlier missions: the lander from the Mars Surveyor Program 2001 (MSP'01) and instruments from the MSP'01 and the Mars Polar Lander. Ensuring all the hardware was properly qualified and flight acceptance tested to meet the environments for this mission required defining and implementing an environmental assurance program that included a detailed heritage review coupled with tailored flight acceptance testing. A heritage review process with defined acceptance success criteria was developed and is presented in this paper together with the lessons learned in its implementation. This paper also provides a detailed description of the environmental assurance program of the Phoenix Mars mission. This program includes assembly/subsystem and system level testing in the areas of dynamics, thermal, and electromagnetic compatibility, as well as venting/pressure, dust, radiation, and meteoroid analyses to meet the challenging environment of this mission.
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Experiences with operations and autonomy of the Mars Pathfinder Microrover.
NASA Astrophysics Data System (ADS)
Mishkin, A. H.; Morrison, J. C.; Nguyen, T. T.; Stone, H. W.; Cooper, B. K.; Wilcox, B. H.
The Microrover Flight Experiment (MFEX) is a NASA OACT (Office of Advanced Concepts and Technology) flight experiment which, integrated with the Mars Pathfinder (MPF) lander and spacecraft system, landed on Mars on July 4, 1997. In the succeeding 30 sols (1 sol = 1 Martian day), the Sojourner microrover accomplished all of its primary and extended mission objectives. After completion of the originally planned extended mission, MFEX continued to conduct a series of technology experiments, deploy its alpha proton X-ray spectrometer (APXS) on rocks and soil, and image both terrain features and the lander. This mission was conducted under the constraints of a once-per-sol opportunity for command and telemetry transmissions between the lander and Earth operators. As such, the MFEX rover was required to carry out its mission, including terrain navigation and contingency response, under supervised autonomous control. For example, goal locations were specified daily by human operators; the rover then safely traversed to these locations. During traverses, the rover autonomously detected and avoided rock, slope, and drop-off hazards, changing its path as needed before turning back towards its goal. This capability to operate in an unmodeled environment, choosing actions in response to sensor input to accomplish requested objectives, is unique among robotic space missions to date.
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The Moon is a Planet Too: Lunar Science and Robotic Exploration
NASA Technical Reports Server (NTRS)
Cohen, Barbara
2008-01-01
The first decades of the 21st century will be marked by major lunar science and exploration activities. The Moon is a witness to 4.5 billion years of solar system history, recording that history more completely and more clearly than any other planetary body. Lunar science encompasses early planetary evolution and differentiation, lava eruptions and fire fountains, impact scars throughout time, and billions of years of volatile input. I will cover the main outstanding issues in lunar science today and the most intriguing scientific opportunities made possible by renewed robotic and human lunar exploration. Barbara is a planetary scientist at NASA s Marshall Space Flight Center. She studies meteorites from the Moon, Mars and asteroids and has been to Antarctica twice to hunt for them. Barbara also works on the Mars Exploration Rovers Spirit and Opportunity and has an asteroid named after her. She is currently helping the Lunar Precursor Robotics Program on the Lunar Mapping and Modeling Project, a project tasked by the Exploration System Mission Directorate (ESMD) to develop maps and tools of the Moon to benefit the Constellation Program lunar planning. She is also supporting the Science Mission Directorate s (SMD) lunar flight projects line at Marshall as the co-chair of the Science Definition Team for NASA s next robotic landers, which will be nodes of the International Lunar Network, providing geophysical information about the Moon s interior structure and composition.
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Optimal Terminal Descent Guidance Logic to Achieve a Soft Lunar Touchdown
NASA Technical Reports Server (NTRS)
Lee, Allan Y.
2011-01-01
Altair Lunar Lander is the linchpin in the Constellation Program for human return to the Moon. In the 2010design reference mission, Altair is to be delivered to low Earth orbit by the Ares V heavy lift launch vehicle, and after subsequent docking with Orion in LEO, the Altair/Orion stack is delivered through trans-lunar injection (TLI). The Altair/Orion stack separates from the Ares V Earth departure stage shortly after TLI and continues the flight to the Moon as a single stack. Fig. 1 depicts one version of the Altair lunar lander.
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ROSETTA lander Philae: Touch-down reconstruction
NASA Astrophysics Data System (ADS)
Roll, Reinhard; Witte, Lars
2016-06-01
The landing of the ROSETTA-mission lander Philae on November 12th 2014 on Comet 67 P/Churyumov-Gerasimenko was planned as a descent with passive landing and anchoring by harpoons at touch-down. Actually the lander was not fixed at touch-down to the ground due to failing harpoons. The lander internal damper was actuated at touch-down for 42.6 mm with a speed of 0.08 m/s while the lander touch-down speed was 1 m/s. The kinetic energy before touch-down was 50 J, 45 J were dissipated by the lander internal damper and by ground penetration at touch-down, and 5 J kinetic energy are left after touch-down (0.325 m/s speed). Most kinetic energy was dissipated by ground penetration (41 J) while only 4 J are dissipated by the lander internal damper. Based on these data, a value for a constant compressive soil-strength of between 1.55 kPa and 1.8 kPa is calculated. This paper focuses on the reconstruction of the touch-down at Agilkia over a period of around 20 s from first ground contact to lift-off again. After rebound Philae left a strange pattern on ground documented by the OSIRIS Narrow Angle Camera (NAC). The analysis shows, that the touch-down was not just a simple damped reflection on the surface. Instead the lander had repeated contacts with the surface over a period of about 20 s±10 s. This paper discusses scenarios for the reconstruction of the landing sequence based on the data available and on computer simulations. Simulations are performed with a dedicated mechanical multi-body model of the lander, which was validated previously in numerous ground tests. The SIMPACK simulation software was used, including the option to set forces at the feet to the ground. The outgoing velocity vector is mostly influenced by the timing of the ground contact of the different feet. It turns out that ground friction during damping has strong impact on the lander outgoing velocity, on its rotation, and on its nutation. After the end of damping, the attitude of the lander can be strongly changed by the additional ground contacts even with the flywheel still running inside the lander. The simulation shows that the outbound velocity vector and the lander rotation were formed immediately at touch-down during the first 1.5 s. The outbound velocity vector is found to be formed by the ground slope and the lander damping characteristic, especially the nearly horizontal flight out.
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Testing Phoenix Mars Lander Parachute in Idaho
NASA Technical Reports Server (NTRS)
2008-01-01
NASA's Phoenix Mars Lander will parachute for nearly three minutes as it descends through the Martian atmosphere on May 25, 2008. Extensive preparations for that crucial period included this drop test near Boise, Idaho, in October 2006. The parachute used for the Phoenix mission is similar to ones used by NASA's Viking landers in 1976. It is a 'disk-gap-band' type of parachute, referring to two fabric components -- a central disk and a cylindrical band -- separated by a gap. Although the Phoenix parachute has a smaller diameter (11.8 meters or 39 feet) than the parachute for the 2007 Mars Pathfinder landing (12.7 meters or 42 feet), its Viking configuration results in slightly larger drag area. The smaller physical size allows for a stronger system because, given the same mass and volume restrictions, a smaller parachute can be built using higher strength components. The Phoenix parachute is approximately 1.5 times stronger than Pathfinder's. Testing shows that it is nearly two times stronger than the maximum opening force expected during its use at Mars. Engineers used a dart-like weight for the drop testing in Idaho. On the Phoenix spacecraft, the parachute is attached the the backshell. The backshell is the upper portion of a capsule around the lander during the flight from Earth to Mars and protects Phoenix during the initial portion of the descent through Mars' atmosphere. Phoenix will deploy its parachute at about 12.6 kilometers (7.8 miles) in altitude and at a velocity of 1.7 times the speed of sound. A mortar on the spacecraft fires to deploy the parachute, propelling it away from the backshell into the supersonic flow. The mortar design for Phoenix is essentially the same as Pathfinder's. The parachute and mortar are collectively called the 'parachute decelerator system.' Pioneer Aerospace, South Windsor, Conn., produced this system for Phoenix. The same company provided the parachute decelerator systems for Pathfinder, Mars Polar Lander, Spirit, and Opportunity, ensuring that lessons learned from past programs were incorporated into the Phoenix system. During the first 25 seconds of the three-minute period when Phoenix descends on its parachute, the spacecraft will cast away its heat shield and extend its three legs. About 43 seconds before reaching the surface of Mars, the lander will shed the parachute by separating from the backshell. The lander will begin firing its descent thrusters half a second after the separation from the backshell and continue using them until touchdown. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
The design of a common lunar lander
NASA Technical Reports Server (NTRS)
Driggers, Dan; Hearrell, Sean; Key, Kevin; Le, Brian; Love, Glen; Mcmullen, Rob; Messec, Scott; Ruhnke, Jim
1991-01-01
The Austin Cynthesis Corporation was formed to respond to a Request for Proposal for the design of a Common Lunar Lander (CLL) capable of carrying lightweight (less than 500 kg), unspecified payload to the moon. This Final Design Report Document includes information on the requirements for the design project; the ideas proposed as solutions to the design problem; the work which has been completed in support of the design effort; justifications, validations, and verifications of decisions made during the project; and suggestions for future work to be done in support of the project. A project schedule, including current status of the items included on the schedule, as well as cost and management summaries is also included.
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Altair Lunar Lander Development Status: Enabling Human Lunar Exploration
NASA Technical Reports Server (NTRS)
Laurini, Kathleen C.; Connolly, John F.
2009-01-01
As a critical part of the NASA Constellation Program lunar transportation architecture, the Altair lunar lander will return humans to the moon and enable a sustained program of lunar exploration. The Altair is to deliver up to four crew to the surface of the moon and return them to low lunar orbit at the completion of their mission. Altair will also be used to deliver large cargo elements to the lunar surface, enabling the buildup of an outpost. The Altair Project initialized its design using a minimum functionality approach that identified critical functionality required to meet a minimum set of Altair requirements. The Altair team then performed several analysis cycles using risk-informed design to selectively add back components and functionality to increase the vehicles safety and reliability. The analysis cycle results were captured in a reference Altair design. This design was reviewed at the Constellation Lunar Capabilities Concept Review, a Mission Concept Review, where key driving requirements were confirmed and the Altair Project was given authorization to begin Phase A project formulation. A key objective of Phase A is to revisit the Altair vehicle configuration, to better optimize it to complete its broad range of crew and cargo delivery missions. Industry was invited to partner with NASA early in the design to provide their insights regarding Altair configuration and key engineering challenges. A blended NASA-industry team will continue to refine the lander configuration and mature the vehicle design over the next few years. This paper will update the international community on the status of the Altair Project as it addresses the challenges of project formulation, including optimizing a vehicle configuration based on the work of the NASA Altair Project team, industry inputs and the plans going forward in designing the Altair lunar lander.
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An Altair Overview: Designing a Lunar Lander for 21st Century Human Space Exploration
NASA Technical Reports Server (NTRS)
Brown, Kendall K.; Connolly, John F.
2012-01-01
Altair, the lunar lander element of NASA's Constellation program, was conducted in a different design environment than many other NASA projects of similar scope. Because of this relatively unique approach, there are a number of significant success stories that should be considered during the development of any future lunar landers or human spacecraft. This paper is divided into two separate themes; the first is the approach used during the conceptual design studies, including the systematic analysis cycles and the decision making process associated with each: and the second is a summary of the resulting lessons learned that were compiled after looking back at the lifetime of the Project. Altair was terminated before entering Phase B of its design, and was often criticized for being a very heavy and very large vehicle. While there was specific rationale for all of the decisions that led up to that configuration, future design cycles were specifically planned to re-address the mass challenge. Had the project continued, the deliberate, stepwise design process would have converged on an optimized lander design that balanced mass, risk, cost and capabilities. Some of the specific items that will be addressed in this paper include project development strategy, organizational approach and team dynamics, risk-informed design process, mission architecture constraints, mission key driving requirements, model-based systems engineering process, configuration studies, contingency considerations, subsystem overviews and key trade studies. The paper will conclude with a summary of the lessons identified during the Altair project and make suggestions for application to future studies.
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TMBM: Tethered Micro-Balloons on Mars
NASA Technical Reports Server (NTRS)
Sims, M. H.; Greeley, R.; Cutts, J. A.; Yavrouian, A. H.; Murbach, M.
2000-01-01
The use of balloons/aerobots on Mars has been under consideration for many years. Concepts include deployment during entry into the atmosphere from a carrier spacecraft, deployment from a lander, use of super-pressurized systems for long duration flights, 'hot-air' systems, etc. Principal advantages include the ability to obtain high-resolution data of the surface because balloons provide a low-altitude platform which moves relatively slowly. Work conducted within the last few years has removed many of the technical difficulties encountered in deployment and operation of balloons/aerobots on Mars. The concept proposed here (a tethered balloon released from a lander) uses a relatively simple approach which would enable aspects of Martian balloons to be tested while providing useful and potentially unique science results. Tethered Micro-Balloons on Mars (TMBM) would be carried to Mars on board a future lander as a stand-alone experiment having a total mass of one to two kilograms. It would consist of a helium balloon of up to 50 cubic meters that is inflated after landing and initially tethered to the lander. Its primary instrumentation would be a camera that would be carried to an altitude of up to tens of meters above the surface. Imaging data would be transmitted to the lander for inclusion in the mission data stream. The tether would be released in stages allowing different resolutions and coverage. In addition during this staged release a lander camera system may observe the motion of the balloon at various heights above he lander. Under some scenarios upon completion of the primary phase of TMBM operations, the tether would be cut, allowing TMBM to drift away from the landing site, during which images would be taken along the ground.
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A Hybrid FPGA/Tilera Compute Element for Autonomous Hazard Detection and Navigation
NASA Technical Reports Server (NTRS)
Villalpando, Carlos Y.; Werner, Robert A.; Carson, John M., III; Khanoyan, Garen; Stern, Ryan A.; Trawny, Nikolas
2013-01-01
To increase safety for future missions landing on other planetary or lunar bodies, the Autonomous Landing and Hazard Avoidance Technology (ALHAT) program is developing an integrated sensor for autonomous surface analysis and hazard determination. The ALHAT Hazard Detection System (HDS) consists of a Flash LIDAR for measuring the topography of the landing site, a gimbal to scan across the terrain, and an Inertial Measurement Unit (IMU), along with terrain analysis algorithms to identify the landing site and the local hazards. An FPGA and Manycore processor system was developed to interface all the devices in the HDS, to provide high-resolution timing to accurately measure system state, and to run the surface analysis algorithms quickly and efficiently. In this paper, we will describe how we integrated COTS components such as an FPGA evaluation board, a TILExpress64, and multi-threaded/multi-core aware software to build the HDS Compute Element (HDSCE). The ALHAT program is also working with the NASA Morpheus Project and has integrated the HDS as a sensor on the Morpheus Lander. This paper will also describe how the HDS is integrated with the Morpheus lander and the results of the initial test flights with the HDS installed. We will also describe future improvements to the HDSCE.
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A hybrid FPGA/Tilera compute element for autonomous hazard detection and navigation
NASA Astrophysics Data System (ADS)
Villalpando, C. Y.; Werner, R. A.; Carson, J. M.; Khanoyan, G.; Stern, R. A.; Trawny, N.
To increase safety for future missions landing on other planetary or lunar bodies, the Autonomous Landing and Hazard Avoidance Technology (ALHAT) program is developing an integrated sensor for autonomous surface analysis and hazard determination. The ALHAT Hazard Detection System (HDS) consists of a Flash LIDAR for measuring the topography of the landing site, a gimbal to scan across the terrain, and an Inertial Measurement Unit (IMU), along with terrain analysis algorithms to identify the landing site and the local hazards. An FPGA and Manycore processor system was developed to interface all the devices in the HDS, to provide high-resolution timing to accurately measure system state, and to run the surface analysis algorithms quickly and efficiently. In this paper, we will describe how we integrated COTS components such as an FPGA evaluation board, a TILExpress64, and multi-threaded/multi-core aware software to build the HDS Compute Element (HDSCE). The ALHAT program is also working with the NASA Morpheus Project and has integrated the HDS as a sensor on the Morpheus Lander. This paper will also describe how the HDS is integrated with the Morpheus lander and the results of the initial test flights with the HDS installed. We will also describe future improvements to the HDSCE.
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In Brief: NASA's Phoenix spacecraft lands on Mars
NASA Astrophysics Data System (ADS)
Showstack, Randy; Kumar, Mohi
2008-06-01
After a 9.5-month, 679-million-kilometer flight from Florida, NASA's Phoenix spacecraft made a soft landing in Vastitas Borealis in Mars's northern polar region on 25 May. The lander, whose camera already has returned some spectacular images, is on a 3-month mission to examine the area and dig into the soil of this site-chosen for its likelihood of having frozen water near the surface-and analyze samples. In addition to a robotic arm and robotic arm camera, the lander's instruments include a surface stereo imager; thermal and evolved-gas analyzer; microscopy, electrochemistry, and conductivity analyzer; and a meteorological station that is tracking daily weather and seasonal changes.
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NASA Technical Reports Server (NTRS)
Haskin, Larry A.
2000-01-01
This summary is the final report of work on two-year grant. Our objectives for this project were (1) to demonstrate that Raman spectroscopy is an excellent method for determining mineralogy on the surface of the Moon, Mars, and other planetary bodies; (2) to construct a prototype of a small Raman spectrometer of the kind we suggest could be used on a lander or rover; and (3) to test the ability of that spectrometer to identify minerals and quantify mineral proportions in lunar materials and complex Martian analog materials, and to identify organic matter in planetary surface materials, all under roughly simulated field conditions. These goals have been met. The principal accomplishments of this PIDDP project have been the following: selection for flight; construction of a breadboard Raman probe; throughput confirmation of the breadboard Raman probe; selection of a laser; a breadboard spectrograph based on our PIDDP design; and overall result.
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CxP Wireless DFI Summary Presentation for OTI Flight Test Working Group
NASA Technical Reports Server (NTRS)
Arteaga, Ricardo A.
2009-01-01
This slide presentation reviews the wireless instrumentation architecture needed for the Alatir Lunar Lander, Ares I, Ares V, and the Block II Orion Crew Exploration Vehicle (CEV). It includes information about the Wireless DFI system, mission planning, and the technology roadmap.
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2003-02-24
KENNEDY SPACE CENTER, FLA. -- The cruise stage, aeroshell and lander for the Mars Exploration Rover-1 mission and the MER-2 rover arrive at KSC. The same flight hardware for the MER-2 rover arrived Jan. 27; however, the MER-2 rover is scheduled to arrive at KSC in March. While at KSC, each of the two rovers, the aeroshells and the landers will undergo a full mission simulation. All of these flight elements will then be integrated together. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers will be identical to each other, but will land at different regions of Mars. Launch of the MER-1 is scheduled for May 30. MER-2 will follow June 25.
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LANDER program manual: A lunar ascent and descent simulation
NASA Technical Reports Server (NTRS)
1988-01-01
LANDER is a computer program used to predict the trajectory and flight performance of a spacecraft ascending or descending between a low lunar orbit of 15 to 500 nautical miles (nm) and the lunar surface. It is a three degree-of-freedom simulation which is used to analyze the translational motion of the vehicle during descent. Attitude dynamics and rotational motion are not considered. The program can be used to simulate either an ascent from the Moon or a descent to the Moon. For an ascent, the spacecraft is initialized at the lunar surface and accelerates vertically away from the ground at full thrust. When the local velocity becomes 30 ft/s, the vehicle turns downrange with a pitch-over maneuver and proceeds to fly a gravity turn until Main Engine Cutoff (MECO). The spacecraft then coasts until it reaches the requested holding orbit where it performs an orbital insertion burn. During a descent simulation, the lander begins in the holding orbit and performs a deorbit burn. It then coasts to pericynthion, where it reignites its engines and begins a gravity turn descent. When the local horizontal velocity becomes zero, the lander pitches up to a vertical orientation and begins to hover in search of a landing site. The lander hovers for a period of time specified by the user, and then lands.
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Mars Lander/Rover vehicle development: An advanced space design project for USRA and NASA/OAST
NASA Technical Reports Server (NTRS)
1987-01-01
The accomplishments of the Utah State University (USU) Mars Lander/Rover (MLR) design class during the Winter Quarter are delineated and explained. Environment and trajectory, ground systems, balloon system, and payload system are described. Results from this effort will provide a valid and useful basis for further studies of Mars exploratory vehicles.
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NASA Technical Reports Server (NTRS)
Roback, V. Eric; Pierrottet, Diego F.; Amzajerdian, Farzin; Barnes, Bruce W.; Bulyshev, Alexander E.; Hines, Glenn D.; Petway, Larry B.; Brewster, Paul F.; Kempton, Kevin S.
2015-01-01
For the first time, a suite of three lidar sensors have been used in flight to scan a lunar-like hazard field, identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control (GN&C) system, help to guide the Morpheus autonomous, rocket-propelled, free-flying lander to that safe site on the hazard field. The lidar sensors and GN&C system are part of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) project which has been seeking to develop a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The 3-D imaging Flash Lidar is a second generation, compact, real-time, aircooled instrument developed from a number of components from industry and NASA and is used as part of the ALHAT Hazard Detection System (HDS) to scan the hazard field and build a 3-D Digital Elevation Map (DEM) in near-real time for identifying safe sites. The Flash Lidar is capable of identifying a 30 cm hazard from a slant range of 1 km with its 8 cm range precision (1-s). The Flash Lidar is also used in Hazard Relative Navigation (HRN) to provide position updates down to a 250m slant range to the ALHAT navigation filter as it guides Morpheus to the safe site. The Navigation Doppler Lidar (NDL) system has been developed within NASA to provide velocity measurements with an accuracy of 0.2 cm/sec and range measurements with an accuracy of 17 cm both from a maximum range of 2,200 m to a minimum range of several meters above the ground. The NDLâ€"TM"s measurements are fed into the ALHAT navigation filter to provide lander guidance to the safe site. The Laser Altimeter (LA), also developed within NASA, provides range measurements with an accuracy of 5 cm from a maximum operational range of 30 km down to 1 m and, being a separate sensor from the Flash Lidar, can provide range along a separate vector. The LA measurements are also fed into the ALHAT navigation filter to provide lander guidance to the safe site. The flight tests served as the culmination of the TRL 6 journey for the ALHAT system and included launch from a pad situated at the NASA-Kennedy Space Center Shuttle Landing Facility (SLF) runway, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range just off the North end of the runway. The tests both confirmed the expected performance and also revealed several challenges present in the flight-like environment which will feed into future TRL advancement of the sensors. Guidance provided by the ALHAT system was impeded in portions of the trajectory and intermittent near the end of the trajectory due to optical effects arising from air heated by the rocket engine. The Flash Lidar identified hazards as small as 30 cm from the maximum slant range of 450 m which Morpheus could provide; however, it was occasionally susceptible to an increase in range noise due to scintillation arising from air heated by the Morpheus rocket engine which entered its Field-of-View (FOV). The Flash Lidar was also susceptible to pre-triggering, during the HRN phase, on a dust cloud created during launch and transported down-range by the wind. The NDL provided velocity and range measurements to the expected accuracy levels yet it was also susceptible to signal degradation due to air heated by the rocket engine. The LA, operating with a degraded transmitter laser, also showed signal attenuation over a few seconds at a specific phase of the flight due to the heat plume generated by the rocket engine.
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Solar Panel Buffeted by Wind at Phoenix Site
NASA Technical Reports Server (NTRS)
2008-01-01
Winds were strong enough to cause about a half a centimeter (.19 inch) of motion of a solar panel on NASA's Phoenix Mars lander when the lander's Surface Stereo Imager took this picture on Aug. 31, 2008, during the 96th Martian day since landing. The lander's telltale wind gauge has been indicating wind speeds of about 4 meters per second (9 miles per hour) during late mornings at the site. These conditions were anticipated and the wind is not expected to do any harm to the lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
NASA Technical Reports Server (NTRS)
Soffen, G. A.
1977-01-01
The Viking project launched two unmanned spacecraft to Mars in 1975 for scientific exploration with special emphasis on the search for life. Each spacecraft consisted of an orbiter and a lander. The landing sites were finally selected after the spacecraft were in orbit. Thirteen investigations were performed: three mapping experiments from the orbiter, one atmospheric investigation during the lander entry phase, eight experiments on the surface of the planet, and one using the spacecraft radio and radar systems. The experiments on the surface dealt principally with biology, chemistry, geology, and meteorology. Seventy-eight scientists have participated in the 13 teams performing these experiments. This paper is a summary of the project and an introduction to the articles that follow.
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Valuation of Real Options as Competitive Prototyping in System Development
2014-07-01
Brealey & Meyers, 2000; Dixit & Pindyck, 1994; Kulatilaka, 1995; Lander, 1997; Lander & Pinches, 1998; McDonald, 2006; Quigg, 1993; Teisberg, 1995...Brennan & Trigeorgis, 2000; Dixit & Pindyck, 1994; Kemna, 1993; Miller & Lessard, 2000; Trigeorgis, 1995). Examples include valuation of options to... Dixit , A. K., & Pindyck, R. S. (1994). Investment under uncertainty. NJ: Princeton University Press. Ford, D. N., & Bhargav, S. (2006, Spring). Project
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NASA Technical Reports Server (NTRS)
Trinh, Huu P.
2015-01-01
NASA's exploration roadmap is focused on developing technologies and performing precursor missions to advance the state of the art for eventual human missions to Mars. One of the key components of this roadmap is various robotic missions to Near-Earth Objects, the Moon, and Mars to fill in some of the strategic knowledge gaps. The Resource Prospector (RP) project is one of these robotic precursor activities in the roadmap. RP is a multi-center and multi-institution project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and is approximately 10 days, assuming a five day direct Earth to Moon transfer. Because of the mission cost constraint, a trade study of the propulsion concepts was conducted with a focus on available low-cost hardware for reducing cost in development, while technical risk, system mass, and technology advancement requirements were also taken into consideration. The propulsion system for the lander is composed of a braking stage providing a high thrust to match the lander's velocity with the lunar surface and a lander stage performing the final lunar descent. For the braking stage, liquid oxygen (LOX) and liquid methane (LCH4) propulsion systems, derived from the Morpheus experimental lander, and storable bi-propellant systems, including the 4th stage Peacekeeper (PK) propulsion components and Space Shuttle orbital maneuvering engine (OME), and a solid motor were considered for the study. For the lander stage, the trade study included miniaturized Divert Attitude Control System (DACS) thrusters (Missile Defense Agency (MDA) heritage), their enhanced thruster versions, ISE-100 and ISE-5, and commercial-off-the-shelf (COTS) hardware. The lowest cost configuration of using the solid motor and the PK components while meeting the requirements was selected. The reference concept of the lander is shown in Figure 1. In the current reference configuration, the solid stage is the primary provider of delta-V. It will generate 15,000-lbf of thrust with a single burn of 80's seconds. The lander stage is a bi-propellant, pressure-regulated, pulsing liquid propulsion system to perform all other functions.
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NASA Technical Reports Server (NTRS)
Powell, Richard W.
1998-01-01
This paper describes the development and evaluation of a numerical roll reversal predictor-corrector guidance algorithm for the atmospheric flight portion of the Mars Surveyor Program 2001 Orbiter and Lander missions. The Lander mission utilizes direct entry and has a demanding requirement to deploy its parachute within 10 km of the target deployment point. The Orbiter mission utilizes aerocapture to achieve a precise captured orbit with a single atmospheric pass. Detailed descriptions of these predictor-corrector algorithms are given. Also, results of three and six degree-of-freedom Monte Carlo simulations which include navigation, aerodynamics, mass properties and atmospheric density uncertainties are presented.
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Cobalt: Development and Maturation of GN&C Technologies for Precision Landing
NASA Technical Reports Server (NTRS)
Carson, John M.; Restrepo, Carolina; Seubert, Carl; Amzajerdian, Farzin
2016-01-01
The CoOperative Blending of Autonomous Landing Technologies (COBALT) instrument is a terrestrial test platform for development and maturation of guidance, navigation and control (GN&C) technologies for precision landing. The project is developing a third-generation Langley Research Center (LaRC) navigation doppler lidar (NDL) for ultra-precise velocity and range measurements, which will be integrated and tested with the Jet Propulsion Laboratory (JPL) lander vision system (LVS) for terrain relative navigation (TRN) position estimates. These technologies together provide precise navigation knowledge that is critical for a controlled and precise touchdown. The COBALT hardware will be integrated in 2017 into the GN&C subsystem of the Xodiac rocket-propulsive vertical test bed (VTB) developed by Masten Space Systems, and two terrestrial flight campaigns will be conducted: one open-loop (i.e., passive) and one closed-loop (i.e., active).
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MARS PATHFINDER PYRO SYSTEMS SWITCHING ACTIVITY
NASA Technical Reports Server (NTRS)
1996-01-01
The Mars Pathfinder lander is subjected to a electrical and functional tests of its pyrotechic petal deployer system by Jet Propulsion Laboratory (JPL) engineers and technicians in KSC's Spacecraft Assembly and Encapsulation Facility (SAEF-2). In the background is the Pathfinder cruise stage, which the lander will be mated to once its functional tests are complete. The lander will remain attached to this stage during its six-to-seven-month journey to Mars. When the lander touches down on the surface of Mars next year, the pyrotechnic system will deploy its three petals open like a flower and allow the Sojourner autonomous rover to explore the Martian surface. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2, the beginning of a 24-day launch period. JPL is managing the Mars Pathfinder project for NASA.
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NASA Technical Reports Server (NTRS)
2007-01-01
NASA's Viking Project found a place in history when it became the first mission to land a spacecraft successfully on the surface of another planet and return both imaging and non-imaging data over an extended time period. Two identical spacecraft, each consisting of a lander and an orbiter, were built. Each orbiter-lander pair flew together and entered Mars orbit; the landers then separated and descended to the planet's surface. The Viking 1 Lander touched down on the western slope of Chryse Planitia (the Plains of Gold) on July 20, 1976, while the Viking 2 lander settled down at Utopia Planitia on September 3, 1976. Besides taking photographs and collecting other science data on the Martian surface, the two landers conducted three biology experiments designed to look for possible signs of life. These experiments discovered unexpected and enigmatic chemical activity in the Martian soil, but provided no clear evidence for the presence of living microorganisms in soil near the landing sites. According to scientists, Mars is self-sterilizing. They believe the combination of solar ultraviolet radiation that saturates the surface, the extreme dryness of the soil and the oxidizing nature of the soil chemistry prevent the formation of living organisms in the Martian soil. The Viking mission was planned to continue for 90 days after landing. Each orbiter and lander operated far beyond its design lifetime. Viking Orbiter 1 functioned until July 25, 1978, while Viking Orbiter 2 continued for four years and 1,489 orbits of Mars, concluding its mission August 7, 1980. Because of the variations in available sunlight, both landers were powered by radioisotope thermoelectric generators -- devices that create electricity from heat given off by the natural decay of plutonium. That power source allowed long-term science investigations that otherwise would not have been possible. The last data from Viking Lander 2 arrived at Earth on April 11, 1980. Viking Lander 1 made its final transmission to Earth November 11, 1982. -
Altair Descent and Ascent Reference Trajectory Design and Initial Dispersion Analyses
NASA Technical Reports Server (NTRS)
Kos, Larry D.; Polsgrove, Tara T.; Sostaric, Ronald r.; Braden, Ellen M.; Sullivan, Jacob J.; Lee, Thanh T.
2010-01-01
The Altair Lunar Lander is the linchpin in the Constellation Program (CxP) for human return to the Moon. Altair is delivered to low Earth orbit (LEO) by the Ares V heavy lift launch vehicle, and after subsequent docking with Orion in LEO, the Altair/Orion stack is delivered through translunar injection (TLI). The Altair/Orion stack separating from the Earth departure stage (EDS) shortly after TLI and continues the flight to the Moon as a single stack. Altair performs the lunar orbit insertion (LOI) maneuver, targeting a 100-km circular orbit. This orbit will be a polar orbit for missions landing near the lunar South Pole. After spending nearly 24 hours in low lunar orbit (LLO), the lander undocks from Orion and performs a series of small maneuvers to set up for descending to the lunar surface. This descent begins with a small deorbit insertion (DOI) maneuver, putting the lander on an orbit that has a perilune of 15.24 km (50,000 ft), the altitude where the actual powered descent initiation (PDI) commences. At liftoff from Earth, Altair has a mass of 45 metric tons (mt). However after LOI (without Orion attached), the lander mass is slightly less than 33 mt at PDI. The lander currently has a single descent module main engine, with TBD lb(sub f) thrust (TBD N), providing a thrust-to-weight ratio of approximately TBD Earth g's at PDI. LDAC-3 (Lander design and analysis cycle #3) is the most recently closed design sizing and mass properties iteration. Upgrades for loss of crew (LDAC-2) and loss of mission (LDAC-3) have been incorporated into the lander baseline design (and its Master Equipment List). Also, recently, Altair has been working requirements analyses (LRAC-1). All nominal data here are from the LDAC-3 analysis cycle. All dispersions results here are from LRAC-1 analyses.
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NASA Technical Reports Server (NTRS)
2008-01-01
The Surface Stereo Imager on NASA's Mars Phoenix Lander acquired this view of the textured plain near the lander at about 11 a.m. local Mars solar time during the mission's 124th Martian day, or sol (Sept. 29, 2008). The image was taken through an infrared filter. The brighter patches are dustier than darker areas of the surface. The last signal from the lander came on Nov. 2, 2008. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Systems Engineering and Reusable Avionics
NASA Technical Reports Server (NTRS)
Conrad, James M.; Murphy, Gloria
2010-01-01
One concept for future space flights is to construct building blocks for a wide variety of avionics systems. Once a unit has served its original purpose, it can be removed from the original vehicle and reused in a similar or dissimilar function, depending on the function blocks the unit contains. For example: Once a lunar lander has reached the moon's surface, an engine controller for the Lunar Decent Module would be removed and used for a lunar rover motor control unit or for a Environmental Control Unit for a Lunar Habitat. This senior design project included the investigation of a wide range of functions of space vehicles and possible uses. Specifically, this includes: (1) Determining and specifying the basic functioning blocks of space vehicles. (2) Building and demonstrating a concept model. (3) Showing high reliability is maintained. The specific implementation of this senior design project included a large project team made up of Systems, Electrical, Computer, and Mechanical Engineers/Technologists. The efforts were made up of several sub-groups that each worked on a part of the entire project. The large size and complexity made this project one of the more difficult to manage and advise. Typical projects only have 3-4 students, but this project had 10 students from five different disciplines. This paper describes the difference of this large project compared to typical projects, and the challenges encountered. It also describes how the systems engineering approach was successfully implemented so that the students were able to meet nearly all of the project requirements.
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Propulsive Maneuver Design for the 2007 Mars Phoenix Lander Mission
NASA Technical Reports Server (NTRS)
Raofi, Behzad; Bhat, Ramachandra S.; Helfrich, Cliff
2008-01-01
On May 25, 2008, the Mars Phoenix Lander (PHX) successfully landed in the northern planes of Mars in order to continue and complement NASA's "follow the water" theme as its predecessor Mars missions, such as Mars Odyssey (ODY) and Mars Exploration Rovers, have done in recent years. Instruments on the lander, through a robotic arm able to deliver soil samples to the deck, will perform in-situ and remote-sensing investigations to characterize the chemistry of materials at the local surface, subsurface, and atmosphere. Lander instruments will also identify the potential history of key indicator elements of significance to the biological potential of Mars, including potential organics within any accessible water ice. Precise trajectory control and targeting were necessary in order to achieve the accurate atmospheric entry conditions required for arriving at the desired landing site. The challenge for the trajectory control maneuver design was to meet or exceed these requirements in the presence of spacecraft limitations as well as other mission constraints. This paper describes the strategies used, including the specialized targeting specifically developed for PHX, in order to design and successfully execute the propulsive maneuvers that delivered the spacecraft to its targeted landing site while satisfying the planetary protection requirements in the presence of flight system constraints.
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System Analysis Applied to Autonomy: Application to Human-Rated Lunar/Mars Landers
NASA Technical Reports Server (NTRS)
Young, Larry A.
2006-01-01
System analysis is an essential technical discipline for the modern design of spacecraft and their associated missions. Specifically, system analysis is a powerful aid in identifying and prioritizing the required technologies needed for mission and/or vehicle development efforts. Maturation of intelligent systems technologies, and their incorporation into spacecraft systems, are dictating the development of new analysis tools, and incorporation of such tools into existing system analysis methodologies, in order to fully capture the trade-offs of autonomy on vehicle and mission success. A "system analysis of autonomy" methodology will be outlined and applied to a set of notional human-rated lunar/Mars lander missions toward answering these questions: 1. what is the optimum level of vehicle autonomy and intelligence required? and 2. what are the specific attributes of an autonomous system implementation essential for a given surface lander mission/application in order to maximize mission success? Future human-rated lunar/Mars landers, though nominally under the control of their crew, will, nonetheless, be highly automated systems. These automated systems will range from mission/flight control functions, to vehicle health monitoring and prognostication, to life-support and other "housekeeping" functions. The optimum degree of autonomy afforded to these spacecraft systems/functions has profound implications from an exploration system architecture standpoint.
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Navigation Challenges of the Mars Phoenix Lander Mission
NASA Technical Reports Server (NTRS)
Portock, Brian M.; Kruizinga, Gerhard; Bonfiglio, Eugene; Raofi, Behzad; Ryne, Mark
2008-01-01
The Mars Phoenix Lander mission was launched on August 4th, 2007. To land safely at the desired landing location on the Mars surface, the spacecraft trajectory had to be controlled to a set of stringent atmospheric entry and landing conditions. The landing location needed to be controlled to an elliptical area with dimensions of 100km by 20km. The two corresponding critical components of the atmospheric entry conditions are the entry flight path angle (target: -13.0 deg +/-0.21 deg) and the entry time (within +/-30 seconds). The purpose of this paper is to describe the navigation strategies used to overcome the challenges posed during spacecraft operations, which included an attitude control thruster calibration campaign, a trajectory control strategy, and a trajectory reconstruction strategy. Overcoming the navigation challenges resulted in final Mars atmospheric entry conditions just 0.007 deg off in entry flight path angle and 14.9 sec early in entry time. These entry dispersions in addition to the entry, descent, and landing trajectory dispersion through the atmosphere, lead to a final landing location just 7 km away from the desired landing target.
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2003-02-24
KENNEDY SPACE CENTER, FLA. -- The cruise stage, aeroshell and lander for the Mars Exploration Rover-1 mission and the MER-2 rover arrive at KSC's Multi-Payload Processing Facility. The same flight hardware for the MER-2 rover arrived Jan. 27; however, the MER-2 rover is scheduled to arrive at KSC in March. While at KSC, each of the two rovers, the aeroshells and the landers will undergo a full mission simulation. All of these flight elements will then be integrated together. After spin balance testing, each spacecraft will be mated to a solid propellant upper stage booster that will propel the spacecraft out of Earth orbit. Approximately 10 days before launch they will be transported to the launch pad for mating with their respective Boeing Delta II rockets. The rovers will serve as robotic geologists to seek answers about the evolution of Mars, particularly for a history of water. The rovers will be identical to each other, but will land at different regions of Mars. Launch of the MER-1 is scheduled for May 30. MER-2 will follow June 25.
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Phoenix Robotic Arm's Workspace After 90 Sols
NASA Technical Reports Server (NTRS)
2008-01-01
During the first 90 Martian days, or sols, after its May 25, 2008, landing on an arctic plain of Mars, NASA's Phoenix Mars Lander dug several trenches in the workspace reachable with the lander's robotic arm. The lander's Surface Stereo Imager camera recorded this view of the workspace on Sol 90, early afternoon local Mars time (overnight Aug. 25 to Aug. 26, 2008). The shadow of the the camera itself, atop its mast, is just left of the center of the image and roughly a third of a meter (one foot) wide. The workspace is on the north side of the lander. The trench just to the right of center is called 'Neverland.' The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
MARS PATHFINDER CAMERA TEST IN SAEF-2
NASA Technical Reports Server (NTRS)
1996-01-01
Jet Propulsion Laboratory (JPL) workers conduct a systems test of the Mars Pathfinder imager, installed atop the Pathfinder lander (with JPL insignia). The imager is the white cyclindrical structure close to the worker's gloved hand. At left is the small rover that will be deployed from the lander to explore the Martian surface. The rover is mounted on one of three petals that will be attached to the lander. The two-pronged mast extending upward from the lander is for the low-gain antenna. The imager is mounted on a mast that will be extended after the lander touches down on Mars, affording a better view of the area. The imager is a camera that will transmit images of the Martian surface as well as the trail left by the rover, helping researchers to better understand the composition of the soil. It also is equipped with selectable filters for gathering data about the atmosphere of the Red Planet. JPL manages the Mars Pathfinder project for NASA. The journey to Mars is scheduled to begin with liftoff Dec. 2 aboard a Delta II expendable launch vehicle.
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The development of sine vibration test requirements for Viking lander capsule components
NASA Technical Reports Server (NTRS)
Barrett, S.
1974-01-01
In connection with the Viking project for exploring the planet Mars, two identical spacecraft, each consisting of an orbiter and a lander, will be launched in the third quarter of 1975. Upon arrival at the planet, the Viking lander will separate from the Viking orbiter and descend to a soft landing at a selected site on the Mars surface. It was decided to perform a sine vibration test on the Viking spacecraft, in its launch configuration, to qualify it for the booster-induced transient-dynamic environment. It is shown that component-level testing is a cost- and schedule-effective prerequisite to the system-level, sine-vibration test sequences.
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Types of rocks exposed at the Viking landing sites
DOE Office of Scientific and Technical Information (OSTI.GOV)
Guinness, E.; Arvidson, R.; Dale-Bannister, M.
1985-01-01
Spectral estimates derived from Viking Lander multispectral images have been used to investigate the types of rocks exposed at both landing sites, and to infer whether the rocks are primary igneous rocks or weathering products. These analyses should aid interpretations of spectra to be returned from the Visual and Infrared Mapping Spectrometer on the upcoming Mars Observer Mission. A series of gray surfaces on the Landers were used to check the accuracy of the camera preflight calibrations. Results indicate that the pre-flight calibrations for the three color channels are probably correct for all cameras but camera 2 on Lander 1.more » The calibration for the infrared channels appears to have changed, although the cause is not known. For this paper, only the color channels were used to derive data for rocks. Rocks at both sites exhibit a variety of reflectance values. For example, reflectance estimates for two rocks in the blue (0.4-0.5 microns), green (0.5-0.6 microns), and red (0.6-0.75 microns) channels are 0.16, 0.23, and 0.33 and 0.12, 0.19, 0.37 at a phase angle of 20 degrees. These values have been compared with laboratory reflectance spectra of analog materials and telescopic spectra of Mars, both convolved to the Lander bandpasses. Lander values for some rocks are similar to earth based observations of martian dark regions and with certain mafic igneous rocks thinly coated with amorphous ferric-oxide rich weathering products. These results are consistent with previous interpretations.« less
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Mars Telecommunications Orbiter, Artist's Concept
NASA Technical Reports Server (NTRS)
2005-01-01
This illustration depicts a concept for NASA's Mars Telecommunications Orbiter in flight around Mars. The orbiter is in development to be the first spacecraft with a primary function of providing communication links while orbiting a foreign planet. The project's plans call for launch in September 2009, arrival at Mars in August 2010 and a mission of six to 10 years while in orbit. Mars Telecommunication Orbiter would serve as the Mars hub for an interplanetery Internet, greatly increasing the information payoff from other future Mars missions. The mission is designed to orbit Mars more than 10 times farther from the planet than orbiters dedicated primarily to science. The high-orbit design minimizes the time that Mars itself blocks the orbiter from communicating with Earth and maximizes the time that the orbiter is above the horizon -- thus capable of communications relay -- for rovers and stationary landers on Mars' surface. -
The Deep Impact Network Experiment Operations Center
NASA Technical Reports Server (NTRS)
Torgerson, J. Leigh; Clare, Loren; Wang, Shin-Ywan
2009-01-01
Delay/Disruption Tolerant Networking (DTN) promises solutions in solving space communications challenges arising from disconnections as orbiters lose line-of-sight with landers, long propagation delays over interplanetary links, and other phenomena. DTN has been identified as the basis for the future NASA space communications network backbone, and international standardization is progressing through both the Consultative Committee for Space Data Systems (CCSDS) and the Internet Engineering Task Force (IETF). JPL has developed an implementation of the DTN architecture, called the Interplanetary Overlay Network (ION). ION is specifically implemented for space use, including design for use in a real-time operating system environment and high processing efficiency. In order to raise the Technology Readiness Level of ION, the first deep space flight demonstration of DTN is underway, using the Deep Impact (DI) spacecraft. Called the Deep Impact Network (DINET), operations are planned for Fall 2008. An essential component of the DINET project is the Experiment Operations Center (EOC), which will generate and receive the test communications traffic as well as "out-of-DTN band" command and control of the DTN experiment, store DTN flight test information in a database, provide display systems for monitoring DTN operations status and statistics (e.g., bundle throughput), and support query and analyses of the data collected. This paper describes the DINET EOC and its value in the DTN flight experiment and potential for further DTN testing.
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Mars Lander/Rover vehicle development: An advanced space design project for USRA and NASA/OAST
NASA Technical Reports Server (NTRS)
1987-01-01
The results of the studies on one particular part of the Mars Lander/Rover (MLR) system are contained: the Balloon Rover. This component vehicle was selected for further research and design because of the lack of technical literature on this subject, as compared to surface rover technology. Landing site selection; balloon system development and deployment; optics and communications; and the payload power supply are described.
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NASA Technical Reports Server (NTRS)
Otte, Neil E.; Lyles, Garry; Reuter, James L.; Davis, Daniel J.
2008-01-01
Fielding an integrated launch vehicle system entails many challenges, not the least of which is the fact that it has been over 30 years since the United States has developed a human-rated vehicle - the venerable Space Shuttle. Over time, whole generations of rocket scientists have passed through the aerospace community without the opportunity to perform such exacting, demanding, and rewarding work. However, with almost 50 years of experience leading the design, development, and end-to-end systems engineering and integration of complex launch vehicles, the National Aeronautics and Space Administration's (NASA's) Marshall Space Flight Center offers the in-house talent - both junior- and senior-level personnel - to shape a new national asset to meet the requirements for safe, reliable, and affordable space exploration solutions. The technical personnel are housed primarily in Marshall's Engineering Directorate and are matrixed into the programs and projects that reside at the rocket center. Fortunately, many Apollo-era and Shuttle engineers, as well as those who gained valuable hands-on experience in the 1990s by conducting technology demonstrator projects such as the Delta-Clipper Experimental Advanced, X-33, X-34, and X-37, as well as the short-lived Orbital Space Plane, work closely with industry partners to advance the nation's strategic capability for human access to space. The Ares Projects Office, resident at Marshall, is managing the design and development of America's new space fleet, including the Ares I, which will loft the Orion crew capsule for its first test flight in the 2013 timeframe, as well as the heavy-lift Ares V, which will round out the capability to leave low-Earth orbit once again, when it delivers the Altair lunar lander to orbit late next decade. This paper provides information about the approach to integrating the Ares I stack and designing the upper stage in house, using unique facilities and an expert workforce to revitalize the nation's space exploration resources.
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CECE: A Deep Throttling Demonstrator Cryogenic Engine for NASA's Lunar Lander
NASA Technical Reports Server (NTRS)
Giuliano, Victor J.; Leonard, Timothy G.; Adamski, Walter M.; Kim, Tony S.
2007-01-01
As one of the first technology development programs awarded under NASA's Vision for Space Exploration, the Pratt & Whitney Rocketdyne (PWR) Deep Throttling, Common Extensible Cryogenic Engine (CECE) program was selected by NASA in November 2004 to begin technology development and demonstration toward a deep throttling, cryogenic Lunar Lander engine for use across multiple human and robotic lunar exploration mission segments with extensibility to Mars. The CECE program leverages the maturity and previous investment of a flight-proven hydrogen/oxygen expander cycle engine, the RL10, to develop and demonstrate an unprecedented combination of reliability, safety, durability, throttlability, and restart capabilities in a high-energy, cryogenic engine. NASA Marshall Space Flight Center and NASA Glenn Research Center personnel were integral design and analysis team members throughout the requirements assessment, propellant studies and the deep throttling demonstrator elements of the program. The testbed selected for the initial deep throttling demonstration phase of this program was a minimally modified RL10 engine, allowing for maximum current production engine commonality and extensibility with minimum program cost. In just nine months from technical program start, CECE Demonstrator No. 1 engine testing in April/May 2006 at PWR's E06 test stand successfully demonstrated in excess of 10:1 throttling of the hydrogen/oxygen expander cycle engine. This test provided an early demonstration of a viable, enabling cryogenic propulsion concept with invaluable system-level technology data acquisition toward design and development risk mitigation for both the subsequent CECE Demonstrator No. 2 program and to the future Lunar Lander Design, Development, Test and Evaluation effort.
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Constellation Overview: Ares V Solar System Science Workshop
NASA Technical Reports Server (NTRS)
Horack, John M.
2008-01-01
Presentation topics include: what is NASA's mission, why the Moon next, options for Moon landings, NASA's exploration roadmap, building on a foundation of proven technologies - launch vehicle comparisons, Ares nationwide team, Ares I elements, vehicle integration accomplishments, Aires I-X test flight, Ares I-X accomplishments, Orion crew exploration vehicle, Altair lunar lander, and Ares V elements.
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Altair Lunar Lander Development Status: Enabling Lunar Exploration
NASA Technical Reports Server (NTRS)
Laurini, Kathleen C.; Connolly, John F.
2009-01-01
As a critical part of the NASA Constellation Program lunar transportation architecture, the Altair lunar lander will return humans to the moon and enable a sustained program of lunar exploration. The Altair is to deliver up to four crew to the surface of the moon and return them to low lunar orbit at the completion of their mission. Altair will also be used to deliver large cargo elements to the lunar surface, enabling the buildup of an outpost. The Altair Project initialized its design using a "minimum functionality" approach that identified critical functionality required to meet a minimum set of Altair requirements. The Altair team then performed several analysis cycles using risk-informed design to selectively add back components and functionality to increase the vehicle's safety and reliability. The analysis cycle results were captured in a reference Altair design. This design was reviewed at the Constellation Lunar Capabilities Concept Review, a Mission Concept Review, where key driving requirements were confirmed and the Altair Project was given authorization to began Phase A project formulation. A key objective of Phase A is to revisit the Altair vehicle configuration, to better optimize it to complete its broad range of crew and cargo delivery missions. Industry was invited to partner with NASA early in the design to provide their insights regarding Altair configuration and key engineering challenges. NASA intends to continue to seek industry involvement in project formulation activities. This paper will update the international coimmunity on the status of the Altair Project as it addresses the challenges of project formulation, including optinuzing a vehicle configuration based on the work of the NASA Altair Project team, industry inputs and the plans going forward in designing the Altair lunar lander.
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Phoenix Animation Looking North
NASA Technical Reports Server (NTRS)
2008-01-01
[figure removed for brevity, see original site] Click on image for animation This animation is a series of images, taken by NASA's Phoenix Mars Lander's Surface Stereo Imager, combined into a panoramic view looking north from the lander. The area depicted is beyond the immediate workspace of the lander and shows a system of polygons and troughs that connect with the ones Phoenix will be investigating in depth. The images were taken on sol 14 (June 8, 2008) or the 14th Martian day after landing. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Extended duration lunar lander
NASA Technical Reports Server (NTRS)
Babic, Nikola; Carter, Matt; Cosper, Donna; Garza, David; Gonzalez, Eloy; Goodine, David; Hirst, Edward; Li, Ray; Lindsey, Martin; Ng, Tony
1993-01-01
Selenium Technologies has been conducting preliminary design work on a manned lunar lander for use in NASA's First Lunar Outpost (FLO) program. The resulting lander is designed to carry a crew of four astronauts to a prepositioned habitat on the lunar surface, remain on the lunar surface for up to 45 days while the crew is living in the habitat, then return the crew to earth via direct reentry and land recovery. Should the need arise, the crew can manually guide the lander to a safe lunar landing site, and live in the lander for up to ten days on the surface. Also, an abort to earth is available during any segment of the mission. The main propulsion system consists of a cluster of four modified Pratt and Whitney RL10 rocket engines that use liquid methane (LCH4) and liquid oxygen (LOX). Four engines are used to provide redundancy and a satisfactory engine out capability. Differences between the new propulsion system and the original system include slightly smaller engine size and lower thrust per engine, although specific impulse remains the same despite the smaller size. Concerns over nozzle ground clearance and engine reliability, as well as more information from Pratt and Whitney, brought about this change. The power system consists of a combination of regenerative fuel cells and solar arrays. While the lander is in flight to or from the moon, or during the lunar night, fuel cells provide all electrical power. During the lunar day, solar arrays are deployed to provide electrical power for the lander as well as electrolyzers, which separate some water back into hydrogen and oxygen for later use by the fuel cells. Total storage requirements for oxygen, hydrogen, and water are 61 kg, 551 kg, and 360 kg, respectively. The lander is a stage-and-a-half design with descent propellant, cargo, and landing gear contained in the descent stage, and the main propulsion system, ascent propellant, and crew module contained in the ascent stage. The primary structure for both stages is a truss, to which all tanks and components are attached. The crew module is a conical shape similar to that of the Apollo Command Module, but significantly larger with a height and maximum diameter of six meters.
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Concept study for a Venus Lander Mission to Analyze Atmospheric and Surface Composition
NASA Astrophysics Data System (ADS)
Kumar, K.; Banks, M. E.; Benecchi, S. D.; Bradley, B. K.; Budney, C. J.; Clark, G. B.; Corbin, B. A.; James, P. B.; O'Brien, R. C.; Rivera-Valentin, E. G.; Saltman, A.; Schmerr, N. C.; Seubert, C. R.; Siles, J. V.; Stickle, A. M.; Stockton, A. M.; Taylor, C.; Zanetti, M.; JPL Team X
2011-12-01
We present a concept-level study of a New Frontiers class, Venus lander mission that was developed during Session 1 of NASA's 2011 Planetary Science Summer School, hosted by Team X at JPL. Venus is often termed Earth's sister planet, yet they have evolved in strikingly different ways. Venus' surface and atmosphere dynamics, and their complex interaction are poorly constrained. A lander mission to Venus would enable us to address a multitude of outstanding questions regarding the geological evolution of the Venusian atmosphere and crust. Our proposed mission concept, VenUs Lander for Composition ANalysis (VULCAN), is a two-component mission, consisting of a lander and a carrier spacecraft functioning as relay to transmit data to Earth. The total mission duration is 150 days, with primary science obtained during a 1-hour descent through the atmosphere and a 2-hour residence on the Venusian surface. In the atmosphere, the lander will provide new data on atmospheric evolution by measuring dominant and trace gas abundances, light stable isotopes, and noble gas isotopes with a neutral mass spectrometer. It will make important meteorological observations of mid-lower atmospheric dynamics with pressure and temperature sensors and obtain unprecedented, detailed imagery of surface geomorphology and properties with a descent Near-IR/VIS camera. A nepholometer will provide new constraints on the sizes of suspended particulate matter within the lower atmosphere. On the surface, the lander will quantitatively investigate the chemical and mineralogical evolution of the Venusian crust with a LIBS-Raman spectrometer. Planetary differentiation processes recorded in heavy elements will be evaluated using a gamma-ray spectrometer. The lander will also provide the first stereo images for evaluating the geomorphologic/volcanic evolution of the Venusian surface, as well as panoramic views of the sample site using multiple filters, and detailed images of unconsolidated material and rock textures from a microscopic imager. Our mission proposal will enable the construction of a unique Venus test facility that will attract a new generation of scientists to Venus science. With emphasis on flight heritage, we demonstrate our cost basis and risk mitigation strategies to ensure that the VULCAN mission can be conducted within the requirements and constraints of the New Frontiers Program.
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NASA Astrophysics Data System (ADS)
Fantino, E.; Grassi, M.; Pasolini, P.; Causa, F.; Molfese, C.; Aurigemma, R.; Cimminiello, N.; de la Torre, D.; Dell'Aversana, P.; Esposito, F.; Gramiccia, L.; Paudice, F.; Punzo, F.; Roma, I.; Savino, R.; Zuppardi, G.
2017-08-01
The Small Mars System is a proposed mission to Mars. Funded by the European Space Agency, the project has successfully completed Phase 0. The contractor is ALI S.c.a.r.l., and the study team includes the University of Naples ;Federico II;, the Astronomical Observatory of Capodimonte and the Space Studies Institute of Catalonia. The objectives of the mission are both technological and scientific, and will be achieved by delivering a small Mars lander carrying a dust particle analyser and an aerial drone. The former shall perform in situ measurements of the size distribution and abundance of dust particles suspended in the Martian atmosphere, whereas the latter shall demonstrate low-altitude flight in the rarefied planetary environment. The mission-enabling technology is an innovative umbrella-like heat shield, known as IRENE, developed and patented by ALI. The mission is also a technological demonstration of the shield in the upper atmosphere of Mars. The core characteristics of SMS are the low cost (120 M€) and the small size (320 kg of wet mass at launch, 110 kg at landing), features which stand out with respect to previous Mars landers. To comply with them is extremely challenging at all levels, and sets strict requirements on the choice of the materials, the sizing of payloads and subsystems, their arrangement inside the spacecraft and the launcher's selection. In this contribution, the mission and system concept and design are illustrated and discussed. Special emphasis is given to the innovative features and to the challenges faced in the development of the work.
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), JPL workers mount a Mars microprobe onto the Mars Polar Lander. Two microprobes will hitchhike on the lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), JPL workers prepare to mount a Mars microprobe onto the Mars Polar Lander. Two microprobes will hitchhike on the lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), the two Mars microprobes are shown mounted on opposite sides of the Mars Polar Lander. The two microprobes and the lander are scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), a JPL worker carries a Mars microprobe to the Mars Polar Lander at left. Two microprobes will hitchhike on the lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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Eifel field operation campaign supporting Moon Mars and NEO exploration
NASA Astrophysics Data System (ADS)
Kamps, Oscar; Foing, Bernard H.; Offringa, Marloes
2016-07-01
As follow-up on the 2009 Eifel field campaign new field tests with our ExoGeoLab lander were conducted in November 2015 and February 2016. The two phase campaign was used to test the usability of a mock-up lander as test bench for experiments and its remote control in a Moon, Mars analogue environment. In a real mission such a lander could be used in a robotic or manned mission as scientific tool for scientists on Earth to do preliminary study on in-situ collected rocks. This could be useful for example for a sample return mission where scientists on Earth can determine if sample is interesting enough for a more detailed study. The prototype lander is one of the components of the ExoGeoLab project from ESA and ILEWG. Several student projects have prepared the lander for a geological field campaign in lunar and Martian analogue terrain. The lander can be divided in three sections which are used to store several components of the lander. The lower compartment can be used to store a rover or used as laboratory. The middle compartment is used for the lander computer(s), spectrometers and the associated cables. The top plate is used for a telescope which in our case is used to observe the environment around the lander and to guide astronauts during their EVA. As closest volcanic are there is chosen to do the Eifel area, Germany. Several stages of volcanism from Devon till Quaternary resulted in a variation of rocks which is analogue to volcanic rocks from Moon, Mars and other near Earth objects. Several topics we would like to test were pre-defined. Functional tests and demo were performed at European astronaut centre prior to the campaign. The latest updates with respect to the remote control were tested. The pressurised transport vehicle was equipped as remote base for (scientific) support during the campaign. The new instrument set-up were tested and some spectra were measured on collected rocks. The telescope was used to study the environment around the lander, selecting sites of interest for EVA, and as support for astronauts on both safety as science. From this campaign some lessons were learned and are points of improvement for future campaigns. One of the most important is to make the whole lander more robust. Several times some systems were not working correctly and someone had to repair. To make it more self-contained a stable cable system and power supply is needed. The new set-up of the spectrometer and sample holder seemed to work fine with the sun as illumination source. For future campaigns there should be a good artificial source as alternative or complement for solar illumination. The telescope provided a good image with a lot of details of the volcanic ash stratigraphy, but we have experienced the importance for a wider view to have a better understanding of the context of the telescope view. An alternative for an ad-hoc network is preferred. Four computers and two networks seemed to interfere which made it impossible to use systems on the lander at the same time. With the share screen function there was some delay in controlling the computer. Next campaign we would like to have the remote support separated from the field location so the people which have to support astronauts have no understanding of the area. Acknowledgment: We would like to thank people from ESTEC , EAC, and DLR for their support during the campaign.
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Synergistic Development, Test, and Qualification Approaches for the Ares I and V Launch Vehicles
NASA Technical Reports Server (NTRS)
Cockrell, Charles E.; Taylor, James L.; Patterson, Alan; Stephens, Samuel E.; Tuma, Margaret; Bartolotta, Paul; Huetter, Uwe; Kaderback, Don; Goggin, David
2009-01-01
The U.S. National Aeronautics and Space Administration (NASA) initiated plans to develop the Ares I and Ares V launch vehicles in 2005 to meet the mission objectives for future human exploration of space. Ares I is designed to provide the capability to deliver the Orion crew exploration vehicle (CEV) to low-Earth orbit (LEO), either for docking to the International Space Station (ISS) or docking with an Earth departure stage (EDS) and lunar lander for transit to the Moon. Ares V provides the heavy-lift capability to deliver the EDS and lunar lander to orbit. An integrated test plan was developed for Ares I that includes un-crewed flight validation testing and ground testing to qualify structural components and propulsion systems prior to operational deployment. The overall test program also includes a single development test flight conducted prior to the Ares I critical design review (CDR). Since the Ares V concept was formulated to maximize hardware commonality between the Ares V and Ares I launch vehicles, initial test planning for Ares V has considered the extensibility of test approaches and facilities from Ares I. The Ares V test plan was part of a successful mission concept review (MCR) in 2008.
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The Effects of Synthetic and Enhanced Vision Technologies for Lunar Landings
NASA Technical Reports Server (NTRS)
Kramer, Lynda J.; Norman, Robert M.; Prinzel, Lawrence J., III; Bailey, Randall E.; Arthur, Jarvis J., III; Shelton, Kevin J.; Williams, Steven P.
2009-01-01
Eight pilots participated as test subjects in a fixed-based simulation experiment to evaluate advanced vision display technologies such as Enhanced Vision (EV) and Synthetic Vision (SV) for providing terrain imagery on flight displays in a Lunar Lander Vehicle. Subjects were asked to fly 20 approaches to the Apollo 15 lunar landing site with four different display concepts - Baseline (symbology only with no terrain imagery), EV only (terrain imagery from Forward Looking Infra Red, or FLIR, and LIght Detection and Ranging, or LIDAR, sensors), SV only (terrain imagery from onboard database), and Fused EV and SV concepts. As expected, manual landing performance was excellent (within a meter of landing site center) and not affected by the inclusion of EV or SV terrain imagery on the Lunar Lander flight displays. Subjective ratings revealed significant situation awareness improvements with the concepts employing EV and/or SV terrain imagery compared to the Baseline condition that had no terrain imagery. In addition, display concepts employing EV imagery (compared to the SV and Baseline concepts which had none) were significantly better for pilot detection of intentional but unannounced navigation failures since this imagery provided an intuitive and obvious visual methodology to monitor the validity of the navigation solution.
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Low Cost Precision Lander for Lunar Exploration
NASA Astrophysics Data System (ADS)
Hoppa, G. V.; Head, J. N.; Gardner, T. G.; Seybold, K. G.
2004-12-01
For 60 years the US Defense Department has invested heavily in producing small, low mass, precision-guided vehicles. The technologies matured under these programs include terrain-aided navigation, closed loop terminal guidance algorithms, robust autopilots, high thrust-to-weight propulsion, autonomous mission management software, sensors, and data fusion. These technologies will aid NASA in addressing New Millennium Science and Technology goals as well as the requirements flowing from the Moon to Mars vision articulated in January 2004. Establishing and resupplying a long-term lunar presence will require automated landing precision not yet demonstrated. Precision landing will increase safety and assure mission success. In our lander design, science instruments amount to 10 kg, 16% of the lander vehicle mass. This compares favorably with 7% for Mars Pathfinder and less than 15% for Surveyor. The mission design relies on a cruise stage for navigation and TCMs for the lander's flight to the moon. The landing sequence begins with a solid motor burn to reduce the vehicle speed to 300-450 m/s. At this point the lander is about 2 minutes from touchdown and has 600 to 700 m/s delta-v capability. This allows for about 10 km of vehicle divert during terminal descent. This concept of operations closely mimics missile operational protocol used for decades: the vehicle remains inert, then must execute its mission flawlessly on a moment's notice. The vehicle design uses a propulsion system derived from heritage MDA programs. A redesigned truss provides hard points for landing gear, electronics, power supply, and science instruments. A radar altimeter and a Digital Scene Matching Area Correlator (DSMAC) provide data for the terminal guidance algorithms. This approach leverages the billions of dollars DoD has invested in these technologies, to land useful science payloads precisely on the lunar surface at relatively low cost.
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A Wet Chemistry Laboratory Cell
NASA Technical Reports Server (NTRS)
2008-01-01
This picture of NASA's Phoenix Mars Lander's Wet Chemistry Laboratory (WCL) cell is labeled with components responsible for mixing Martian soil with water from Earth, adding chemicals and measuring the solution chemistry. WCL is part of the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA) instrument suite on board the Phoenix lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.
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Propulsion engineering study for small-scale Mars missions
DOE Office of Scientific and Technical Information (OSTI.GOV)
Whitehead, J.
1995-09-12
Rocket propulsion options for small-scale Mars missions are presented and compared, particularly for the terminal landing maneuver and for sample return. Mars landing has a low propulsive {Delta}v requirement on a {approximately}1-minute time scale, but at a high acceleration. High thrust/weight liquid rocket technologies, or advanced pulse-capable solids, developed during the past decade for missile defense, are therefore more appropriate for small Mars landers than are conventional space propulsion technologies. The advanced liquid systems are characterize by compact lightweight thrusters having high chamber pressures and short lifetimes. Blowdown or regulated pressure-fed operation can satisfy the Mars landing requirement, but hardwaremore » mass can be reduced by using pumps. Aggressive terminal landing propulsion designs can enable post-landing hop maneuvers for some surface mobility. The Mars sample return mission requires a small high performance launcher having either solid motors or miniature pump-fed engines. Terminal propulsion for 100 kg Mars landers is within the realm of flight-proven thruster designs, but custom tankage is desirable. Landers on a 10 kg scale also are feasible, using technology that has been demonstrated but not previously flown in space. The number of sources and the selection of components are extremely limited on this smallest scale, so some customized hardware is required. A key characteristic of kilogram-scale propulsion is that gas jets are much lighter than liquid thrusters for reaction control. The mass and volume of tanks for inert gas can be eliminated by systems which generate gas as needed from a liquid or a solid, but these have virtually no space flight history. Mars return propulsion is a major engineering challenge; earth launch is the only previously-solved propulsion problem requiring similar or greater performance.« less
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Remote X-Ray Diffraction and X-Ray Fluorescence Analysis on Planetary Surfaces
NASA Technical Reports Server (NTRS)
Blake, David F.; DeVincenzi, D. (Technical Monitor)
1999-01-01
The legacy of planetary X-ray Diffraction (XRD) and X-ray Fluorescence (XRF) began in 1960 when W. Parish proposed an XRD instrument for deployment on the moon. The instrument was built and flight qualified, but the Lunar XRD program was cancelled shortly before the first human landing in 1969. XRF chemical data have been collected in situ by surface landers on Mars (Viking 1 & 2, Pathfinder) and Venus (Venera 13 & 14). These highly successful experiments provide critical constraints on our current understanding of surface processes and planetary evolution. However, the mineralogy, which is more critical to planetary surface science than simple chemical analysis, will remain unknown or will at best be imprecisely constrained until X-ray diffraction (XRD) data are collected. Recent progress in X-ray detector technology allows the consideration of simultaneous XRD (mineralogic analysis) and high-precision XRF (elemental analysis) in systems miniaturized to the point where they can be mounted on fixed landers or small robotic rovers. There is a variety of potential targets for XRD/XRF equipped landers within the solar system, the most compelling of which are the poles of the moon, the southern highlands of Mars and Europa.
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Resource Prospector Mission Animation (June 2018)
2018-05-30
Expanding human presence beyond low-Earth orbit will require the maximum possible use of local materials, so-called in-situ resources (ISRU). The Moon presents a unique destination to conduct robotic investigations that advance ISRU capabilities, as well as providing significant exploration and science value. This video animation shows one mission concept under study by NASA called Resource Prospector (RP), an ISRU prospecting and technology demonstration mission. RP would scan the surface and sub-surface terrain, and demonstrate extraction of hydrogen and oxygen from lunar regolith to validate one possible ISRU approach. As NASA plans a series of progressive robotic missions to the lunar surface, the agency is considering a variety of approaches to evolve progressively larger landers leading to an eventual human lander capability. Part of this expanded lunar campaign includes early flight of select instruments from Resource Prospector to the Moon.
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NASA Technical Reports Server (NTRS)
2002-01-01
[figure removed for brevity, see original site] This portion of a daytime IR image covers the Viking 2 landing site (shown with the X). The second landing on Mars took place September 3, 1976 in Utopia Planitia. The exact location of Lander 2 is not as well established as Lander 1 because there were no clearly identifiable features in the lander images as there were for the site of Lander 1. The Utopia landing site region contains pedestal craters, shallow swales and gentle ridges. The crater Goldstone was named in honor of the Tracking Station in the desert of California. The two Viking Landers operated for over 6 years (nearly four martian years) after landing. This one band IR (band 9 at 12.6 microns) image shows bright and dark textures, which are primarily due to differences in the abundance of rocks on the surface. The relatively cool (dark) regions during the day are rocky or indurated materials, fine sand and dust are warmer (bright). Many of the temperature variations are due to slope effects, with sun-facing slopes warmer than shaded slopes. The dark rings around several of the craters are due to the presence of rocky (cool) material ejected from the crater. These rocks are well below the resolution of any existing Mars camera, but THEMIS can detect the temperature variations they produce. Daytime temperature variations are produced by a combination of topographic (solar heating) and thermophysical (thermal inertia and albedo) effects. Due to topographic heating the surface morphologies seen in THEMIS daytime IR images are similar to those seen in previous imagery and MOLA topography.Note: this THEMIS visual image has not been radiometrically nor geometrically calibrated for this preliminary release. An empirical correction has been performed to remove instrumental effects. A linear shift has been applied in the cross-track and down-track direction to approximate spacecraft and planetary motion. Fully calibrated and geometrically projected images will be released through the Planetary Data System in accordance with Project policies at a later time.NASA's Jet Propulsion Laboratory manages the 2001 Mars Odyssey mission for NASA's Office of Space Science, Washington, D.C. The Thermal Emission Imaging System (THEMIS) was developed by Arizona State University, Tempe, in collaboration with Raytheon Santa Barbara Remote Sensing. The THEMIS investigation is led by Dr. Philip Christensen at Arizona State University. Lockheed Martin Astronautics, Denver, is the prime contractor for the Odyssey project, and developed and built the orbiter. Mission operations are conducted jointly from Lockheed Martin and from JPL, a division of the California Institute of Technology in Pasadena. -
2014-05-21
CAPE CANAVERAL, Fla. – Jon Olansen, Morpheus project manager, speaks to members of the media inside a facility near the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Behind Olansen is the Project Morpheus prototype lander. Project Morpheus tests NASA’s autonomous landing and hazard avoidance technology, or ALHAT, sensors and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-05-21
CAPE CANAVERAL, Fla. – Jon Olansen, Morpheus project manager, speaks to members of the media inside a facility near the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Behind Olansen is the Project Morpheus prototype lander. Project Morpheus tests NASA’s autonomous landing and hazard avoidance technology, or ALHAT, sensors and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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2014-05-21
CAPE CANAVERAL, Fla. – Chirold Epp, the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, project manager, speaks to members of the media inside a facility near the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. Behind Epp is the Project Morpheus prototype lander. Project Morpheus tests NASA’s ALHAT sensors and an engine that runs on liquid oxygen and methane, which are green propellants. These new capabilities could be used in future efforts to deliver cargo to planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin
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Space Launch System Co-Manifested Payload Options for Habitation
NASA Technical Reports Server (NTRS)
Smitherman, David
2015-01-01
The Space Launch System (SLS) has a co-manifested payload capability that will grow over time as the launch vehicle matures and planned upgrades are implemented. The final configuration is planned to be capable of inserting a payload greater than 10 metric tons (mt) into a trans-lunar injection trajectory along with the crew in the Orion capsule and its service module. The co-manifested payload is located below the Orion and its service module in a 10 m high fairing similar to the way the Saturn launch vehicle carried the lunar lander below the Apollo command and service modules. Various approaches that utilize this comanifested payload capability to build up infrastructure in deep space have been explored in support of future asteroid, lunar, and Mars mission scenarios. This paper reports on the findings of the Advanced Concepts Office study team at NASA Marshall Space Flight Center (MSFC) working with the Advanced Exploration Systems Program on the Exploration Augmentation Module Project. It includes some of the possible options for habitation in the co-manifested payload volume of the SLS. Findings include a set of module designs that can be developed in 10 mt increments to support these co-manifested payload missions along with a comparison of this approach to a large-module payload flight configuration for the SLS.
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Mars MetNet Mission - Martian Atmospheric Observational Post Network
NASA Astrophysics Data System (ADS)
Haukka, Harri; Harri, Ari-Matti; Aleksashkin, Sergey; Arruego, Ignacio; Schmidt, Walter; Genzer, Maria; Vazquez, Luis; Siikonen, Timo; Palin, Matti
2016-10-01
A new kind of planetary exploration mission for Mars is under development in collaboration between the Finnish Meteorological Institute (FMI), Lavochkin Association (LA), Space Research Institute (IKI) and Institutio Nacional de Tecnica Aerospacial (INTA). The Mars MetNet mission is based on a new semi-hard landing vehicle called MetNet Lander (MNL).The scientific payload of the Mars MetNet Precursor mission is divided into three categories: Atmospheric instruments, Optical devices and Composition and structure devices. Each of the payload instruments will provide significant insights in to the Martian atmospheric behavior.The key technologies of the MetNet Lander have been qualified and the electrical qualification model (EQM) of the payload bay has been built and successfully tested.Full Qualification Model (QM) of the MetNet landing unit with the Precursor Mission payload is currently under functional tests. In the near future the QM unit will be exposed to environmental tests with qualification levels including vibrations, thermal balance, thermal cycling and mechanical impact shock. One complete flight unit of the entry, descent and landing systems (EDLS) has been manufactured and tested with acceptance levels. Another flight-like EDLS has been exposed to most of the qualification tests, and hence it may be used for flight after refurbishments. Accordingly two flight-capable EDLS systems exist. The eventual goal is to create a network of atmospheric observational posts around the Martian surface. The next step in the MetNet Precursor Mission is the demonstration of the technical robustness and scientific capabilities of the MetNet type of landing vehicle. Definition of the Precursor Mission and discussions on launch opportunities are currently under way. The baseline program development funding exists for the next five years. Flight unit manufacture of the payload bay takes about 18 months, and it will be commenced after the Precursor Mission has been defined.
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NASA Technical Reports Server (NTRS)
2008-01-01
This image shows bluish-white frost seen on the Martian surface near NASA's Phoenix Mars Lander. The image was taken by the lander's Surface Stereo Imager on the 131st Martian day, or sol, of the mission (Oct. 7, 2008). Frost is expected to continue to appear in images as fall, then winter approach Mars' northern plains. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
2012-06-25
A frame grab from a mounted video camera on the E-3 Test Stand at Stennis Space Center documents testing of the new Project Morpheus engine. The new liquid methane, liquid oxygen engine will power the Morpheus prototype lander, which could one day evolve to carry cargo safely to the moon, asteroids or Mars surfaces.
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An Evaluation of a High Pressure Regulator for NASA's Robotic Lunar Lander Spacecraft
NASA Technical Reports Server (NTRS)
Burnside, Christopher G.; Trinh, Huu P.; Pedersen, Kevin W.
2013-01-01
The Robotic Lunar Lander (RLL) development project office at NASA Marshall Space Flight Center is currently studying several lunar surface science mission concepts. The focus is on spacecraft carrying multiple science instruments and power systems that will allow extended operations on the lunar surface or other air-less bodies in the solar system. Initial trade studies of launch vehicle options indicate the spacecraft will be significantly mass and volume constrained. Because of the investment by the DOD in low mass, highly volume efficient components, NASA has investigated the potential integration of some of these technologies in space science applications. A 10,000 psig helium pressure regulator test activity has been conducted as part of the overall risk reduction testing for the RLL spacecraft. The regulator was subjected to typical NASA acceptance testing to assess the regulator response to the expected RLL mission requirements. The test results show the regulator can supply helium at a stable outlet pressure of 740 psig within a +/- 5% tolerance band and maintain a lock-up pressure less than the +5% above nominal outlet pressure for all tests conducted. Numerous leak tests demonstrated leakage less than 10-3 standard cubic centimeters per second (SCCS) for the internal seat leakage at lock-up and less than 10-5 SCCS for external leakage through the regulator body. The successful test has shown the potential for 10,000 psig helium systems in NASA spacecraft and has reduced risk associated with hardware availability and hardware ability to meet RLL mission requirements.
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Dig Hazard Assessment Using a Stereo Pair of Cameras
NASA Technical Reports Server (NTRS)
Rankin, Arturo L.; Trebi-Ollennu, Ashitey
2012-01-01
This software evaluates the terrain within reach of a lander s robotic arm for dig hazards using a stereo pair of cameras that are part of the lander s sensor system. A relative level of risk is calculated for a set of dig sectors. There are two versions of this software; one is designed to run onboard a lander as part of the flight software, and the other runs on a PC under Linux as a ground tool that produces the same results generated on the lander, given stereo images acquired by the lander and downlinked to Earth. Onboard dig hazard assessment is accomplished by executing a workspace panorama command sequence. This sequence acquires a set of stereo pairs of images of the terrain the arm can reach, generates a set of candidate dig sectors, and assesses the dig hazard of each candidate dig sector. The 3D perimeter points of candidate dig sectors are generated using configurable parameters. A 3D reconstruction of the terrain in front of the lander is generated using a set of stereo images acquired from the mast cameras. The 3D reconstruction is used to evaluate the dig goodness of each candidate dig sector based on a set of eight metrics. The eight metrics are: 1. The maximum change in elevation in each sector, 2. The elevation standard deviation in each sector, 3. The forward tilt of each sector with respect to the payload frame, 4. The side tilt of each sector with respect to the payload frame, 5. The maximum size of missing data regions in each sector, 6. The percentage of a sector that has missing data, 7. The roughness of each sector, and 8. Monochrome intensity standard deviation of each sector. Each of the eight metrics forms a goodness image layer where the goodness value of each sector ranges from 0 to 1. Goodness values of 0 and 1 correspond to high and low risk, respectively. For each dig sector, the eight goodness values are merged by selecting the lowest one. Including the merged goodness image layer, there are nine goodness image layers for each stereo pair of mast images.
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Real-Time Hazard Detection and Avoidance Demonstration for a Planetary Lander
NASA Technical Reports Server (NTRS)
Epp, Chirold D.; Robertson, Edward A.; Carson, John M., III
2014-01-01
The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project is chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. In addition to precision landing close to a pre-mission defined landing location, the ALHAT System must be capable of autonomously identifying and avoiding surface hazards in real-time to enable a safe landing under any lighting conditions. This paper provides an overview of the recent results of the ALHAT closed loop hazard detection and avoidance flight demonstrations on the Morpheus Vertical Testbed (VTB) at the Kennedy Space Center, including results and lessons learned. This effort is also described in the context of a technology path in support of future crewed and robotic planetary exploration missions based upon the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN).
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NASA Technical Reports Server (NTRS)
Tran, Sarah Diem
2015-01-01
This project stems from the Exploration, Research, and Technology Directorate (UB) Projects Division, and one of their main initiatives is the "Journey to Mars". Landing on the surface of Mars which is millions of miles away is an incredibly large challenge. The terrain is covered in boulders, deep canyons, volcanic mountains, and spotted with sand dunes. The robotic lander is a kind of spacecraft with multiple purposes. One purpose is to be the protective shell for the Martian rover and absorb the impact from the landing forces; another purpose is to be a place where the rovers can come back to, actively communicate with, and recharge their batteries from. Rovers have been instrumental to the Journey to Mars initiative. They have been performing key research on the terrain of the red planet, trying to unlock the mysteries of the land for over a decade. The rovers that will need charging will not all have the same kind of internal battery either. RASSOR batteries may differ from the PbAC batteries inside Red Rover's chassis. NASA has invested heavily in the exploration of the surface of Mars. A driving force behind further exploration is the need for a more efficient operation of Martian rovers. One way is to reduce the weight as much as possible to reduce power consumption given the same mission parameters. In order to reduce the mass of the rovers, power generation, communication, and sample analysis systems currently onboard Martian rovers can be moved to a stationary lander deck. Positioning these systems from the rover to the Lander deck allows a taskforce of smaller, lighter rovers to perform the same tasks currently performed by or planned for larger rovers. A major task in transferring these systems to a stationary lander deck is ensuring that power can be transferred to the rovers.
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Combined Instrumentation Package COMARS+ for the ExoMars Schiaparelli Lander
NASA Astrophysics Data System (ADS)
Gülhan, Ali; Thiele, Thomas; Siebe, Frank; Kronen, Rolf
2018-02-01
In order to measure aerothermal parameters on the back cover of the ExoMars Schiaparelli lander the instrumentation package COMARS+ was developed by DLR. Consisting of three combined aerothermal sensors, one broadband radiometer sensor and an electronic box the payload provides important data for future missions. The aerothermal sensors called COMARS combine four discrete sensors measuring static pressure, total heat flux, temperature and radiative heat flux at two specific spectral bands. The infrared radiation in a broadband spectral range is measured by the separate broadband radiometer sensor. The electronic box of the payload is used for amplification, conditioning and multiplexing of the sensor signals. The design of the payload was mainly carried out using numerical tools including structural analyses, to simulate the main mechanical loads which occur during launch and stage separation, and thermal analyses to simulate the temperature environment during cruise phase and Mars entry. To validate the design an extensive qualification test campaign was conducted on a set of qualification models. The tests included vibration and shock tests to simulate launch loads and stage separation shocks. Thermal tests under vacuum condition were performed to simulate the thermal environment of the capsule during the different flight phases. Furthermore electromagnetic compatibility tests were conducted to check that the payload is compatible with the electromagnetic environment of the capsule and does not emit electromagnetic energy that could cause electromagnetic interference in other devices. For the sensor heads located on the ExoMars back cover radiation tests were carried out to verify their radiation hardness. Finally the bioburden reduction process was demonstrated on the qualification hardware to show the compliance with the planetary protection requirements. To test the actual heat flux, pressure and infrared radiation measurement under representative conditions, aerothermal tests were performed in an arc-heated wind tunnel facility. After all qualification tests were passed successfully, the acceptance test campaign for the flight hardware at acceptance level included the same tests than the qualification campaign except shock, radiation hardness and aerothermal tests. After passing all acceptance tests, the COMARS+ flight hardware was integrated into the Schiaparelli capsule in January 2015 at the ExoMars integration site at Thales Alenia Space in Turin. Although the landing of Schiaparelli failed, resulting in the loss of most COMARS+ flight data because they were stored on the lander, some data points were directly transmitted to the orbiter at low sampling rate during the entry phase. These data indicate that all COMARS+ sensors delivered useful data until parachute deployment with the exception of the plasma black-out phase. Since measured structure and sensor housing temperatures are far below predicted pre-flight values, a new calibration using COMARS+ spare sensors at temperatures below 0 °C is necessary.
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NASA Technical Reports Server (NTRS)
Dwyer Cianciolo, Alicia; Powell, Richard W.
2017-01-01
Precision landing on Mars is a challenge. All Mars lander missions prior to the 2012 Mars Science Laboratory (MSL) had landing location uncertainty ellipses on the order of hundreds of kilometers. Sending humans to the surface of Mars will likely require multiple landers delivered in close proximity, which will in turn require orders of magnitude improvement in landing accuracy. MSL was the first Mars mission to use an Apollo-derived bank angle guidance to reduce the size of the landing ellipse. It utilized commanded bank angle magnitude to control total range and bank angle reversals to control cross range. A shortcoming of this bank angle guidance is that the open loop phase of flight created by use of bank reversals increases targeting errors. This paper presents a comparison of entry, descent and landing performance for a vehicle with a low lift-to-drag ratio using both bank angle control and an alternative guidance called Direct Force Control (DFC). DFC eliminates the open loop flight errors by directly controlling two forces independently, lift and side force. This permits independent control of down range and cross range. Performance results, evaluated using the Program to Optimize Simulated Trajectories (POST2), including propellant use and landing accuracy, are presented.
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SIIOS in Alaska: Testing an "In-Vault" Option for a Europa Lander Seismometer Experiment
NASA Technical Reports Server (NTRS)
Bray, Veronica J.; Weber, Renee C.; DellaGiustina, Daniella N.; Bailey, S. H. (Hop); Schmerr, Nicholas C.; Pettit, Erin C.; Avenson, Brad; Marusiak, Angela G.; Dahl, Peter; Carr, Christina;
2017-01-01
The icy moons of Europa and Enceladus are thought to have global subsurface oceans in contact with mineral-rich silicate interiors, likely providing the three ingredients needed for life as we know it: liquid water, essential chemicals, and a source of energy. The possibility of life forming in their subsurface oceans relies in part on transfer of oxidants from the irradiated ice surface to the sheltered ocean below. Constraining the mechanisms and location of material exchange between the ice surface, the ice shell, and the subsurface ocean, however, is not possible without knowledge of ice thickness and liquid water depths. In a future lander-based experiment seismic measurements will be a key geophysical tool for obtaining this critical knowledge. The Seismometer to Investigate Ice and Ocean Structure (SIIOS) field-tests flight-ready technologies and develops the analytical methods necessary to make a seismic study of Europa and Enceladus a reality. We have been performing small-array seismology with a flight-candidate sensor in analog environments that exploit passive sources. Determining the depth to a subsurface ocean and any intermediate bodies of water is a priority for Ocean Worlds missions as it allows assessment of the habitability of these worlds and provides vital information for evaluating the spacecraft technologies required to access their oceans.
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Testing Conducted for Lithium-Ion Cell and Battery Verification
NASA Technical Reports Server (NTRS)
Reid, Concha M.; Miller, Thomas B.; Manzo, Michelle A.
2004-01-01
The NASA Glenn Research Center has been conducting in-house testing in support of NASA's Lithium-Ion Cell Verification Test Program, which is evaluating the performance of lithium-ion cells and batteries for NASA mission operations. The test program is supported by NASA's Office of Aerospace Technology under the NASA Aerospace Flight Battery Systems Program, which serves to bridge the gap between the development of technology advances and the realization of these advances into mission applications. During fiscal year 2003, much of the in-house testing effort focused on the evaluation of a flight battery originally intended for use on the Mars Surveyor Program 2001 Lander. Results of this testing will be compared with the results for similar batteries being tested at the Jet Propulsion Laboratory, the Air Force Research Laboratory, and the Naval Research Laboratory. Ultimately, this work will be used to validate lithium-ion battery technology for future space missions. The Mars Surveyor Program 2001 Lander battery was characterized at several different voltages and temperatures before life-cycle testing was begun. During characterization, the battery displayed excellent capacity and efficiency characteristics across a range of temperatures and charge/discharge conditions. Currently, the battery is undergoing lifecycle testing at 0 C and 40-percent depth of discharge under low-Earth-orbit (LEO) conditions.
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COBALT Flight Demonstrations Fuse Technologies
2017-06-07
This 5-minute, 50-second video shows how the CoOperative Blending of Autonomous Landing Technologies (COBALT) system pairs new landing sensor technologies that promise to yield the highest precision navigation solution ever tested for NASA space landing applications. The technologies included a navigation doppler lidar (NDL), which provides ultra-precise velocity and line-of-sight range measurements, and the Lander Vision System (LVS), which provides terrain-relative navigation. Through flight campaigns conducted in March and April 2017 aboard Masten Space Systems' Xodiac, a rocket-powered vertical takeoff, vertical landing (VTVL) platform, the COBALT system was flight tested to collect sensor performance data for NDL and LVS and to check the integration and communication between COBALT and the rocket. The flight tests provided excellent performance data for both sensors, as well as valuable information on the integrated performance with the rocket that will be used for subsequent COBALT modifications prior to follow-on flight tests. Based at NASA’s Armstrong Flight Research Center in Edwards, CA, the Flight Opportunities program funds technology development flight tests on commercial suborbital space providers of which Masten is a vendor. The program has previously tested the LVS on the Masten rocket and validated the technology for the Mars 2020 rover.
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Product Assurance Targeted to Meet Mission Objectives
NASA Technical Reports Server (NTRS)
Mclaughlin, Diane
1991-01-01
Topics concerning the Common Lunar Lander for the Space Exploration Initiative are covered and include the following: product assurance tools and supports; project goals; and product assurance structured for optimal payback.
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2014-11-03
CAPE CANAVERAL, Fla. - Greg C. Shavers, Lander Technology director at Marshall Space Flight Center in Alabama, speaks to members of the media during an event to announce the agency's Lunar Cargo Transportation and Landing by Soft Touchdown, or Lunar CATALYST, initiative and introduced one of the partners, Moon Express Inc. of Moffett Field, California. The event took place at Kennedy's automated landing and hazard avoidance technology, or ALHAT, hazard field at the north end of the Shuttle Landing Facility. Moon Express is developing a lander with capabilities that will enable delivery of payloads to the surface of the moon, as well as new science and exploration missions of interest to NASA and scientific and academic communities. Moon Express will base its activities at Kennedy and utilize the Morpheus ALHAT field and a hangar nearby for CATALYST testing. The Advanced Exploration Systems Division of NASA's Human Exploration and Operations Mission Directorate manages Lunar CATALYST. Photo credit: NASA/Ben Smegelsky
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2014-11-03
Greg C. Shavers, Lander Technology director at Marshall Space Flight Center in Alabama, speaks to members of the media during an event to announce the agency's Lunar Cargo Transportation and Landing by Soft Touchdown, or Lunar CATALYST, initiative and introduced one of the partners, Moon Express Inc. of Moffett Field, California. The event took place at Kennedy's automated landing and hazard avoidance technology, or ALHAT, hazard field at the north end of the Shuttle Landing Facility. Moon Express is developing a lander with capabilities that will enable delivery of payloads to the surface of the moon, as well as new science and exploration missions of interest to NASA and scientific and academic communities. Moon Express will base its activities at Kennedy and utilize the Morpheus ALHAT field and a hangar nearby for CATALYST testing. The Advanced Exploration Systems Division of NASA's Human Exploration and Operations Mission Directorate manages Lunar CATALYST.
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Viking Mars lander 1975 dynamic test model/orbiter developmental test model forced vibration test
NASA Technical Reports Server (NTRS)
Fortenberry, J.; Brownlee, G. R.
1974-01-01
The Viking Mars Lander 1975 dynamic test model and orbiter developmental test model were subjected to forced vibration sine tests. Flight acceptance (FA) and type approval (TA) test levels were applied to the spacecraft structure in a longitudinal test configuration using a 133,440-N (30,000-lb) force shaker. Testing in the two lateral axes (X, Y) was performed at lower levels using four 667-N (150-lb) force shakers. Forced vibration qualification (TA) test levels were successfully imposed on the spacecraft at frequencies down to 10 Hz. Measured responses showed the same character as analytical predictions, and correlation was reasonably good. Because of control system test tolerances, orbiter primary structure generally did not reach the design load limits attained in earlier static testing. A post-test examination of critical orbiter structure disclosed no apparent damage to the structure as a result of the test environment.
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Hybrid Heat Pipes for Lunar and Martian Surface and High Heat Flux Space Applications
NASA Technical Reports Server (NTRS)
Ababneh, Mohammed T.; Tarau, Calin; Anderson, William G.; Farmer, Jeffery T.; Alvarez-Hernandez, Angel R.
2016-01-01
Novel hybrid wick heat pipes are developed to operate against gravity on planetary surfaces, operate in space carrying power over long distances and act as thermosyphons on the planetary surface for Lunar and Martian landers and rovers. These hybrid heat pipes will be capable of operating at the higher heat flux requirements expected in NASA's future spacecraft and on the next generation of polar rovers and equatorial landers. In addition, the sintered evaporator wicks mitigate the start-up problems in vertical gravity aided heat pipes because of large number of nucleation sites in wicks which will allow easy boiling initiation. ACT, NASA Marshall Space Flight Center, and NASA Johnson Space Center, are working together on the Advanced Passive Thermal experiment (APTx) to test and validate the operation of a hybrid wick VCHP with warm reservoir and HiK"TM" plates in microgravity environment on the ISS.
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NASA Technical Reports Server (NTRS)
Roback, Vincent E.; Pierrottet, Diego F.; Amzajerdian, Farzin; Barnes, Bruce W.; Hines, Glenn D.; Petway, Larry B.; Brewster, Paul F.; Kempton, Kevin S.; Bulyshev, Alexander E.
2015-01-01
For the first time, a suite of three lidar sensors have been used in flight to scan a lunar-like hazard field, identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control (GN&C) system, guide the Morpheus autonomous, rocket-propelled, free-flying test bed to a safe landing on the hazard field. The lidar sensors and GN&C system are part of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) project which has been seeking to develop a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The 3-D imaging flash lidar is a second generation, compact, real-time, air-cooled instrument developed from a number of cutting-edge components from industry and NASA and is used as part of the ALHAT Hazard Detection System (HDS) to scan the hazard field and build a 3-D Digital Elevation Map (DEM) in near-real time for identifying safe sites. The flash lidar is capable of identifying a 30 cm hazard from a slant range of 1 km with its 8 cm range precision at 1 sigma. The flash lidar is also used in Hazard Relative Navigation (HRN) to provide position updates down to a 250m slant range to the ALHAT navigation filter as it guides Morpheus to the safe site. The Doppler Lidar system has been developed within NASA to provide velocity measurements with an accuracy of 0.2 cm/sec and range measurements with an accuracy of 17 cm both from a maximum range of 2,200 m to a minimum range of several meters above the ground. The Doppler Lidar's measurements are fed into the ALHAT navigation filter to provide lander guidance to the safe site. The Laser Altimeter, also developed within NASA, provides range measurements with an accuracy of 5 cm from a maximum operational range of 30 km down to 1 m and, being a separate sensor from the flash lidar, can provide range along a separate vector. The Laser Altimeter measurements are also fed into the ALHAT navigation filter to provide lander guidance to the safe site. The flight tests served as the culmination of the TRL 6 journey for the lidar suite and included launch from a pad situated at the NASA-Kennedy Space Center Shuttle Landing Facility (SLF) runway, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range just off the North end of the runway. The tests both confirmed the expected performance and also revealed several challenges present in the flight-like environment which will feed into future TRL advancement of the sensors. The flash lidar identified hazards as small as 30 cm from the maximum slant range of 450 m which Morpheus could provide, however, it was occasionally susceptible to an increase in range noise due to heated air from the Morpheus rocket plume which entered its Field-of-View (FOV). The flash lidar was also susceptible to pre-triggering on dust during the HRN phase which was created during launch and transported by the wind. The Doppler Lidar provided velocity and range measurements to the expected accuracy levels yet it was also susceptible to signal degradation due to air heated by the rocket engine. The Laser Altimeter, operating with a degraded transmitter laser, also showed signal attenuation over a few seconds at a specific phase of the flight due to the heat plume generated by the rocket engine.
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Aeroshell for Mars Science Laboratory
NASA Technical Reports Server (NTRS)
2008-01-01
This image from July 2008 shows the aeroshell for NASA's Mars Science Laboratory while it was being worked on by spacecraft technicians at Lockheed Martin Space Systems Company near Denver. This hardware was delivered in early fall of 2008 to NASA's Jet Propulsion Laboratory, Pasadena, Calif., where the Mars Science Laboratory spacecraft is being assembled and tested. The aeroshell encapsulates the mission's rover and descent stage during the journey from Earth to Mars and shields them from the intense heat of friction with that upper atmosphere during the initial portion of descent. The aeroshell has two main parts: the backshell, which is on top in this image and during the descent, and the heat shield, on the bottom. The heat shield in this image is an engineering unit for testing. The heat shield to be used in flight will be substituted later. The heat shield has a diameter of about 15 feet. For comparison, the heat shields for NASA's Mars Exploraton Rovers Spirit and Opportunity were 8.5 feet and the heat shields for the Apollo capsules that protected astronauts returning to Earth from the moon were just under 13 feet. In addition to protecting the Mars Science Laboratory rover, the backshell provides structural support for the descent stage's parachute and sky crane, a system that will lower the rover to a soft landing on the surface of Mars. The backshell for the Mars Science Laboratory is made of an aluminum honeycomb structure sandwiched between graphite-epoxy face sheets. It is covered with a thermal protection system composed of a cork/silicone super light ablator material that originated with the Viking landers of the 1970s. This ablator material has been used on the heat shields of all NASA Mars landers in the past, but this mission is the first Mars mission using it on the backshell. The heat shield for Mars Science Laboratory's flight will use tiles made of phenolic impregnated carbon ablator. The engineering unit in this image does not have the tiles. JPL, a division of the California Institute of Technology, manages the Mars Science Laboratory Project for the NASA Science Mission Directorate, Washington. -
Flexible Graphene-based Energy Storage Devices for Space Application Project
NASA Technical Reports Server (NTRS)
Calle, Carlos I.
2014-01-01
Develop prototype graphene-based reversible energy storage devices that are flexible, thin, lightweight, durable, and that can be easily attached to spacesuits, rovers, landers, and equipment used in space.
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Animation of Panorama of Phoenix's Solar Panel and Robotic Arm
NASA Technical Reports Server (NTRS)
2008-01-01
[figure removed for brevity, see original site] Click on image for animation This is an animation of panorama images of NASA's Phoenix Mars Lander's solar panel and the lander's Robotic Arm with a sample in the scoop. The image was taken just before the sample was delivered to the Optical Microscope. The images making up this animation were taken by the lander's Surface Stereo Imager looking west during Phoenix's Sol 16 (June 10, 2008), or the 16th Martian day after landing. This view is a part of the 'mission success' panorama that will show the whole landing site in color. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
1998-11-10
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), the Mars Polar Lander is prepared to receive a number of microprobes being added to the spacecraft. Scheduled to be launched on Jan. 3, 1999, the solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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Deepest Trenching at Phoenix Site on Mars
NASA Technical Reports Server (NTRS)
2008-01-01
NASA's Phoenix Mars Lander widened the deepest trench it has excavated, dubbed 'Stone Soup,' (in the lower half of this image) to collect a sample from about 18 centimeters (7 inches) below the surface for analysis by the lander's wet chemistry laboratory. Phoenix's Surface Stereo Imager took this image on Sol 95 (Aug. 30, 2008), the 95th Martian day since landing. For scale, the rock to the right of the Stone Soup trench is about 15 centimeters (6 inches) across. The lander's robotic arm scooped up a sample from the left half of the trench for delivery the following sol to the wet chemistry laboratory. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
NASA Technical Reports Server (NTRS)
2008-01-01
The Phoenix Mars Lander's Surface Stereo Imager took this image of the spacecraft's crumpled heat shield on Sept. 16, 2008, the 111th Martian day of the mission. The 2-1/2 meter (about 8-1/2 feet) heat shield landed southeast of Phoenix, about halfway between the spacecraft and its backshell/parachute. The backshell/parachute touched ground 300 meters (1,000 ft) to the south of the lander. The dark area to the right of the heat shield is the 'bounce mark' it made on impact with the Red Planet. This image is the highest-resolution image that will likely be taken by the lander, and is part of the 1,500-image 'Happily Ever After' panorama. The Phoenix mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is led by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Apollo Video Photogrammetry Estimation of Plume Impingement Effects
NASA Technical Reports Server (NTRS)
Immer, Christopher; Lane, John; Metzger, Philip; Clements, Sandra
2008-01-01
Each of the six Apollo mission landers touched down at unique sites on the lunar surface. Aside from the Apollo 12 landing site located 180 meters from the Surveyor III lander, plume impingement effects on ground hardware during the landings were largely not an issue. The Constellation Project's planned return to the moon requires numerous landings at the same site. Since the top few centimeters are loosely packed regolith, plume impingement from the lander ejects the granular material at high velocities. With high vacuum conditions on the moon (10 (exp -14) to 10 (epx -12) torr), motion of all particles is completely ballistic. Estimates from damage to the Surveyor III show that the ejected regolith particles to be anywhere 400 m/s to 2500 m/s. It is imperative to understand the physics of plume impingement to safely design landing sites for the Constellation Program.
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Orbiter, Flyby and Lander Mission Concepts for Investigating Europa's Habitability
NASA Astrophysics Data System (ADS)
Prockter, L. M.
2012-04-01
Coauthors: R. T. Pappalardo (1), F. Bagenal (2), A. C. Barr (3), B. G. Bills (1), D. L. Blaney (1), D. D. Blankenship (4), W. Brinckerhoff (5), J. E. P. Connerney (5), K. Hand (1), T. Hoehler (6), W. Kurth (7), M. McGrath (8), M. Mellon (9), J. M. Moore (6), D. A. Senske (1), E. Shock (10), D. E. Smith (11), T. Gavin (1), G. Garner (1), T. Magner (12), B. C. Cooke (1), R. Crum (1), V. Mallder (12), L. Adams (12), K. Klaasen (1), G. W. Patterson (12), and S. D. Vance (1); 1: Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA; 2: University of Colorado, Boulder, CO, USA; 3: Brown University, Providence, RI, USA; 4: University of Texas Institute for Geophysics, Austin, TX, USA; 5: NASA Goddard Space Flight Center, Greenbelt, MD, USA; 6: NASA Ames Research Center, Mountain View, CA, USA; 7: University of Iowa, Iowa City, IA, USA; 8: NASA Marshall Space Flight Center, Huntsville, AL, USA; 9: Southwest Research Institute, Boulder, CO, USA; 10: Arizona State University, Tempe, AZ, USA; 11: Massachusetts Institute of Technology, Cambridge, MA, USA; 12: Johns Hopkins University Applied Physics Laboratory, Laurel, MD, USA. Introduction: Assessment of Europa's habitability requires understanding whether the satellite possesses the three "ingredients" for life: water, chemistry, and energy. The National Research Council's Planetary Decadal Survey [1] placed an extremely high priority on Europa science but noted that the budget profile for the Jupiter Europa Orbiter (JEO) mission concept [2] is incompatible with NASA's projected planetary science budget. Thus, in April 2011, NASA enlisted a small Europa Science Definition Team (ESDT) to consider Europa mission options that might be more feasible over the next decade from a programmatic perspective. The ESDT has studied three Europa mission concepts: a Europa orbiter, a Europa multiple-flyby mission, and a Europa lander. These share an overarching goal: Explore Europa to investigate its habitability. Each of the three mission options would address this goal in different and complementary ways, and each has high science value of its own, independent of the others. Each mission concept traces geophysical, compositional, and/or geological investigations that are best addressed by that specific platform. Investigations best addressed through near-continuous global data sets that are obtained under relatively uniform conditions could be undertaken by the orbiter; investigations that are more focused on characterization of local regions could be accomplished by a spacecraft making multiple flybys from Jupiter orbit; and measurements that are most effective from the surface could be addressed by a lander. Although there is overlap in the science objectives of these three mission concepts, each stands alone as a viable Europa mission concept.
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The ROSETTA PHILAE Lander damping mechanism as probe for the Comet soil strength.
NASA Astrophysics Data System (ADS)
Roll, R.
2015-10-01
The ROSETTA Lander is equipped with an one axis damping mechanism to dissipate kinetic energy during the touch down. This damping is necessary to avoid damages to the Lander by a hard landing shock and more important to avoid re-bouncing from ground with high velocity. The damping mechanism works best for perpendicular impact, which means the velocity vector is parallel to the damper axis and all three feet touch the ground at the same time. That is usually not the case. Part of the impact energy can be transferred into rotational energy at ground contact if the impact is not perpendicular. This energy will lift up the Lander from the ground if the harpoons and the hold down thruster fail, as happen in mission. The damping mechanism itself is an electrical generator, driven by a spindle inside a telescopic tube. This tube was extended in mission for landing by 200mm. A maximum damping length of 140mm would be usually required to compensate a landing velocity of 1m/s, if the impact happens perpendicular on hard ground. After landing the potentiometer of the telescopic tube reading shows a total damping length of only 42,5mm. The damping mechanism and the overall mechanical behavior of the Lander at touch down are well tested and characterized and transferred to a multi-body computer model. The incoming and outgoing flightpath of PHILAE allow via computer-simulation the reconstruction of the touch down. It turns out, that the outgoing flight direction is dominated by the local ground slope and that the damping length is strongly dependent on the soil strength. Damping of soft comet ground must be included to fit the damping length measured. Scenario variations of the various feet contact with different local surface features (stone or regolith) and of different soil models finally lead to a restricted range for the soil strength at the touch down area.
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Recent Projects in the KSC Applied Physics Lab
NASA Technical Reports Server (NTRS)
Starr, Stanley
2013-01-01
Topics include: Shuttle heritage; ISRU /RESOLVE: a) Payload for Lunar Lander/Rover on Polar Areas of Moon. b) Avionics/Software. New Technologies for Exploration: a) Radiation Shielding work. b) Cooperative Tractor Beams.
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The Viking parachute qualification test technique.
NASA Technical Reports Server (NTRS)
Raper, J. L.; Lundstrom, R. R.; Michel, F. C.
1973-01-01
The parachute system for NASA's Viking '75 Mars lander was flight qualified in four high-altitude flight tests at the White Sands Missile range (WSMR). A balloon system lifted a full-scale simulated Viking spacecraft to an altitude where a varying number of rocket motors were used to propel the high drag, lifting test vehicle to test conditions which would simulate the range of entry conditions expected at Mars. A ground-commanded cold gas pointing system located on the balloon system provided powered vehicle azimuth control to insure that the flight trajectory remained within the WSMR boundaries. A unique ground-based computer-radar system was employed to monitor inflight performance of the powered vehicle and insure that command ignition of the parachute mortar occurred at the required test conditions of Mach number and dynamic pressure. Performance data were obtained from cameras, telemetry, and radar.
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Development of an Audio Microphone for the Mars Surveyor 98 Lander
NASA Astrophysics Data System (ADS)
Delory, G. T.; Luhmann, J. G.; Curtis, D. W.; Friedman, L. D.; Primbsch, J. H.; Mozer, F. S.
1998-01-01
In December 1999, the next Mars Surveyor Lander will bring the first microphone to the surface of Mars. The Mars Microphone represents a joint effort between the Planetary Society and the University of California at Berkeley Space Sciences Laboratory and is riding on the lander as part of the LIDAR instrument package provided by the Russian Academy of Sciences in Moscow. The inclusion of a microphone on the Mars Surveyor Lander represents a unique opportunity to sample for the first time the acoustic environment on the surface, including both natural and lander-generated sounds. Sounds produced by martian meteorology are among the signals to be recorded, including wind and impacts of sand particles on the instrument. Photographs from the Viking orbiters as well as Pathfinder images show evidence of small tornado-like vortices that may be acoustically detected, along with noise generated by static discharges possible during sandstorms. Lander-generated sounds that will be measured include the motion and digging of the lander arm as it gathers soil samples for analysis. Along with these scientific objectives, the Mars Microphone represents a powerful tool for public outreach by providing sound samples on the Internet recorded during the mission. The addition of audio capability to the lander brings us one step closer to a true virtual presence on the Mars surface by complementing the visual capabilities of the Mars Surveyor cameras. The Mars Microphone is contained in a 5 x 5 x 1 cm box, weighs less than 50 g, and uses 0.1 W of power during its most active times. The microphone used is a standard hearing-aid electret. The sound sampling and processing system relies on an RSC-164 speech processor chip, which performs 8-bit A/ D sampling and sound compression. An onboard flight program enables several modes for the instrument, including varying sample ranges of 5 kHz and 20 kHz, and a selectable gain setting with 64x dynamic range. The device automatically triggers on the loudest sound during a collection period for storage in an internal flash memory. Data returned by the lander consist of a compressed time-series acoustic waveform, between 2 and 10 s long, depending on the sample rate. In addition to the discrete waveform. capture, the instrument continuously records the mean power in each of six frequency bands in order to provide an average characterization of the martian acoustic environment. Once the data are retrieved from the telemetry, the compressed time series is expanded into a standard PC-compatible WAV file for analysis, which will include representation in spectral format using FFTs for quantitative characterization of the sound data. The WAV files will be used to share the data with the public via the Internet. The Mars Microphone will thus fulfill a dual role on the Mars Surveyor mission, one as a possible precursor to a more sophisticated acoustic instrument on future landers. and one as a mechanism to increase public awareness of efforts to explore and understand the martian climate and planetary history.
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Planetary cubesats - mission architectures
NASA Astrophysics Data System (ADS)
Bousquet, Pierre W.; Ulamec, Stephan; Jaumann, Ralf; Vane, Gregg; Baker, John; Clark, Pamela; Komarek, Tomas; Lebreton, Jean-Pierre; Yano, Hajime
2016-07-01
Miniaturisation of technologies over the last decade has made cubesats a valid solution for deep space missions. For example, a spectacular set 13 cubesats will be delivered in 2018 to a high lunar orbit within the frame of SLS' first flight, referred to as Exploration Mission-1 (EM-1). Each of them will perform autonomously valuable scientific or technological investigations. Other situations are encountered, such as the auxiliary landers / rovers and autonomous camera that will be carried in 2018 to asteroid 1993 JU3 by JAXA's Hayabusas 2 probe, and will provide complementary scientific return to their mothership. In this case, cubesats depend on a larger spacecraft for deployment and other resources, such as telecommunication relay or propulsion. For both situations, we will describe in this paper how cubesats can be used as remote observatories (such as NEO detection missions), as technology demonstrators, and how they can perform or contribute to all steps in the Deep Space exploration sequence: Measurements during Deep Space cruise, Body Fly-bies, Body Orbiters, Atmospheric probes (Jupiter probe, Venus atmospheric probes, ..), Static Landers, Mobile landers (such as balloons, wheeled rovers, small body rovers, drones, penetrators, floating devices, …), Sample Return. We will elaborate on mission architectures for the most promising concepts where cubesat size devices offer an advantage in terms of affordability, feasibility, and increase of scientific return.
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SESAME/CASSE listening to the insertion of the MUPUS PEN at Abydos site, 67P/Churyumov-Gerasimenko
NASA Astrophysics Data System (ADS)
Knapmeyer, M.; Fischer, H.-H.; Knollenberg, J.; Seidensticker, K. J.; Thiel, K.; Arnold, W.; Faber, C.; Möhlmann, D.
2015-10-01
SESAME is a suite of three instruments (the Comet Acoustic Surface Sounding Experiment CASSE, the Dust Impact Monitor DIM, and the electrical Permittivity Probe PP) that have sensors and transmitters distributed all over the Philae lander, but share common electronics for commanding and processing. SESAME is conducted by a consortium of DLR, the Max Planck Institute for Solar System Research (Göttingen), and the Finnish Meteorological Institute (Helsinki, [1]). The Multi-Purpose Sensor MUPUS, run also by DLR, combines a thermal conductivity and heat flow experiment with a mechanical properties experiment associated with the anchoring harpoons of the lander ([2]). It was recognized early in the preparation of both the SESAME and MUPUS experiments that the hammering mechanism of the latter, which drives the thermal probe into the ground, might as well serve as source of elastic waves for the CASSE experiment. To support the CASSE experiment, the MUPUS flight software provides information on its hammering process in a shared memory of the lander data management system. CASSE listening to the MUPUS PEN hammer mechanism proved to be the first active seismic experiment conducted on a celestial body other than Earth since the Lunar Seismic Profiling Experiment, which was carried out on the Moon by the Apollo 17 astronauts in 1972 (e.g. [3]).
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On Release of Microbe-Laden Particles from Mars Landers
NASA Technical Reports Server (NTRS)
Bellan, Josette; Harstad, Kenneth
2006-01-01
A paper presents a study in which rates of release of small particles from Mars lander spacecraft into the Martian atmosphere were estimated from first principles. Because such particles can consist of, or be laden with, terrestrial microbes, the study was undertaken to understand their potential for biological contamination of Mars. The study included taking account of forces and energies involved in adhesion of particles and of three mechanisms of dislodgement of particles from the surface of a Mars lander: wind shear, wind-driven impingement of suspended dust, and impingement of wind-driven local saltating sand particles. Wind shear was determined to be effective in dislodging only particles larger than about 10 microns and would probably be of limited interest because such large particles could be removed by pre-flight cleaning of the spacecraft, and their number on the launched spacecraft would thus be relatively small. Dislodgement by wind-driven dust was found to be characterized by an adhesion half-life of the order of 10,000 years judged to be too long to be of concern. Dislodgement by saltating sand particles, including skirts of dust devils, was found to be of potential importance, depending on the sizes of the spacecraft-attached particles and characteristics of both Mars sand-particle and spacecraft surfaces.
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NASA Technical Reports Server (NTRS)
1973-01-01
NASA will launch two spacecraft to Mars in 1975 to soft-land on the surface and test for signs of life. After confirming the site data from orbit, each of the spacecraft will separate into two parts, an orbiter and a lander. Together they will conduct scientific studies of the Martian atmosphere and surface. The lander's instruments will collect data for transmission to earth, direct or via the orbiter, including panoramic, stereo color pictures of its immediate surroundings, molecular organic and inorganic analyses of the soil, and atmospheric, meteorological, magnetic, and seismic characteristics. It will also make measurements of the atmosphere as it descends to the surface.
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Color Image of Phoenix Lander on Mars Surface
NASA Technical Reports Server (NTRS)
2008-01-01
This is an enhanced-color image from Mars Reconnaissance Orbiter's High Resolution Imaging Science Experiment (HiRISE) camera. It shows the Phoenix lander with its solar panels deployed on the Mars surface. The spacecraft appears more blue than it would in reality. The blue/green and red filters on the HiRISE camera were used to make this picture. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Mars Surface near Viking Lander 1 Footpad
NASA Technical Reports Server (NTRS)
2008-01-01
This image, which has been flipped horizontally, was taken by Viking Lander 1 on August 1, 1976, 12 sols after landing. Much like images that have returned from Phoenix, the soil beneath Viking 1 has been exposed due to exhaust from thruster engines during descent. This is visible to the right of the struts of Viking's surface-sampler arm housing, seen on the left. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Phoenix Carries Soil to Wet Chemistry Lab
NASA Technical Reports Server (NTRS)
2008-01-01
This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Robotic Arm scoop positioned over the Wet Chemistry Lab delivery funnel on Sol 29, the 29th Martian day after landing, or June 24, 2008. The soil will be delivered to the instrument on Sol 30. This image has been enhanced to brighten the scene. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Radiator Study for Stationary Lunar Landers
NASA Technical Reports Server (NTRS)
OConnor, Brian; Abel, Elisabeth
2010-01-01
This paper provides an overview of a study to identify, select and evaluate potential heat rejection radiators for application to small, low power, stationary lunar landers. While this study supported risk mitigation activities related to the International Lunar Network project, the radiator concepts and performance assessments are applicable to a wide range of lunar lander applications. The radiator concepts identified and evaluated in this study were aimed at providing reliable heat rejection for landers that might be subjected to hot lunar noon conditions at the equator. As a part of the study, a literature search of lunar radiators was performed from which many radiator designs were developed. These designs were compared in a trade study and two of the most promising were used to develop six concepts. These six radiator concepts went through a more detailed thermal analysis using Thermal Desktop. The analysis considered heat rejection capability, and sensitivity to many factors such as dust deposition, latitude, life, and topographical features like landing on a hill, on a rock, or in a hole/crater. From the result of the analysis, two radiator concepts were selected for recommendation: a flat horizontal plate with a dust cover and a stacked vertical radiator with parabolic reflectors and a one degree tilting mechanism.
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NASA Astrophysics Data System (ADS)
Linley, T. D.; Lavaleye, M.; Maiorano, P.; Bergman, M.; Capezzuto, F.; Cousins, N. J.; D'Onghia, G.; Duineveld, G.; Shields, M. A.; Sion, L.; Tursi, A.; Priede, I. G.
2017-11-01
Autonomous photographic landers are a low-impact survey method for the assessment of mobile fauna in situations where methods such as trawling are not feasible or ethical. Three institutions collaborated through the CoralFISH project, each using differing lander systems, to assess the effects of cold-water corals on fish diversity and density. The Biogenic Reef Ichthyofauna Lander (BRIL, Oceanlab), Autonomous Lander for Biological Experiments (ALBEX, NIOZ) and the Marine Environment MOnitoring system (MEMO, CoNISMa) were deployed in four CoralFISH European study regions covering the Arctic, NE Atlantic and Mediterranean, namely Northern Norway (275-310 m depth), Belgica Mound Province (686-1025 m depth), the Bay of Biscay (623-936 m depth), and Santa Maria di Leuca (547-670 m depth). A total of 33 deployments were carried out in the different regions. Both the time of first arrival (Tarr) and the maximum observed number of fish (MaxN) were standardised between the different lander systems and compared between coral and reference stations as indicators of local fish density. Fish reached significantly higher MaxN at the coral stations than at the reference stations. Fish were also found to have significantly lower Tarr in the coral areas in data obtained from the BRIL and MEMO landers. All data indicated that fish abundance is higher within the coral areas. Fish species diversity was higher within the coral areas of Atlantic Ocean while in Northern Norway and Santa Maria di Leuca coral areas, diversity was similar at coral and reference stations but a single dominant species (Brosme brosme and Conger conger respectively) showed much higher density within the coral areas. Indicating that, while cold-water coral reefs have a positive effect on fish diversity and/or abundance, this effect varies across Europe's reefs.
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Status of the French Mars Exploration Program
NASA Astrophysics Data System (ADS)
Bonneville, R.; Counil, J.-L.; Rocard, F.
2002-01-01
The French Mars exploration initiative named PREMIER (Programme de Retour d'Echantillons Martiens et Installation d'Expériences en Réseau) is a long term, multiform co- operative program including as its two main components : - the development with a consortium of European partners (Finland, Germany, Belgium) and the deployment of a network of 4 small Mars ground stations for performing geophysical measurements (NetLander project) ; - a participation to the future Mars Sample Return mission (MSR) in cooperation with NASA including the development and the operation of the orbiter vehicle of this mission. Its additional elements are : - instrument contributions to ESA's Mars Express mission ; - payload contributions to the orbiters and landers &rovers of the future missions to Mars, and especially to NASA's "smart lander" mission dedicated to in situ investigations. This program wants to ensure the complementarity between its three poles : (i) global investigations from the orbit, (ii) landed science with both network science (NetLanders) and in situ investigations, and (iii) sample return. A major step in the PREMIER program will be the 2007 orbiter mission ; this precursor vehicle developed by CNES and launched by Ariane 5 in September 2007 will first deliver the 4 NetLanders at Mars and then will be inserted in Mars orbit. This orbiter will perform technological tests aiming at preparing the future Mars Sample Return mission, it will ensure a telecommunication relay function for the NetLanders and it will be used for an additional orbital science mission. While the NetLanders will study the internal structure of Mars and its climate, with the goal to operate a full Martian year, the primary objectives of the orbital science mission will be complementary of those of the NetLanders, with an emphasis on the study of the Martian atmosphere. In a first phase, the orbiter will be on a 500 km x 500 km circular, near polar, Sun-synchronous orbit around 12 am local time, which is optimal for the NetLander relay. In a second phase, the orbit will be lowered around 350 km for the benefit of the orbital science. A very low periapsis phase (170 km x 1000 km) is foreseen for some experiments. The nominal mission will end in September 2011, with the hope of an extended mission beyond this date.
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Development of a miniature scanning electron microscope for in-flight analysis of comet dust
NASA Technical Reports Server (NTRS)
Conley, J. M.; Bradley, J. G.; Giffin, C. E.; Albee, A. L.; Tomassian, A. D.
1983-01-01
A description is presented of an instrument which was developed with the original goal of being flown on the International Comet Mission, scheduled for a 1985 launch. The Scanning Electron Microscope and Particle Analyzer (SEMPA) electron miniprobe is a miniaturized electrostatically focused electron microscope and energy dispersive X-ray analyzer for in-flight analysis of comet dust particles. It was designed to be flown on board a comet rendezvous spacecraft. Other potential applications are related to asteroid rendezvous and planetary lander missions. According to the development objectives, SEMPA miniprobe is to have the capability for imaging and elemental analysis of particles in the size range of 0.25 microns and larger.
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NASA Technical Reports Server (NTRS)
Schroeder, C.; Klingelhoefer, G; Morris, R. V.; Yen, A. S.; Renz, F.; Graff, T. G.
2016-01-01
The miniaturized Moessbauer spectrometer MIMOS II is an off-the-shelf instrument with proven flight heritage. It has been successfully deployed during NASA’s Mars Exploration Rover (MER) mission and was on-board the UK-led Beagle 2 Mars lander and the Russian Phobos-Grunt sample return mission. A Moessbauer spectrometer has been suggested for ASTEX, a DLR Near-Earth Asteroid (NEA) mission study, and the potential payload to be hosted by the Asteroid Redirect Mission (ARM). Here we make the case for in situ asteroid characterization with Moessbauer spectroscopy on the ARM employing one of three available fully-qualified flight-spare Moessbauer instruments.
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NASA Technical Reports Server (NTRS)
Epp, Chirold D.; Robertson, Edward A.; Ruthishauser, David K.
2013-01-01
The Autonomous Landing and Hazard Avoidance Technology (ALHAT) Project was chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with real-time terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. The ALHAT System must be capable of identifying and avoiding surface hazards to enable a safe and accurate landing to within tens of meters of designated and certified landing sites anywhere on a planetary surface under any lighting conditions. This is accomplished with the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN). The NASA plan for the ALHAT technology is to perform the TRL6 closed loop demonstration on the Morpheus Vertical Test Bed (VTB). The first Morpheus vehicle was lost in August of 2012 during free-flight testing at Kennedy Space Center (KSC), so the decision was made to perform a helicopter test of the integrated ALHAT System with the Morpheus avionics over the ALHAT planetary hazard field at KSC. The KSC helicopter tests included flight profiles approximating planetary approaches, with the entire ALHAT system interfaced with all appropriate Morpheus subsystems and operated in real-time. During these helicopter flights, the ALHAT system imaged the simulated lunar terrain constructed in FY2012 to support ALHAT/Morpheus testing at KSC. To the best of our knowledge, this represents the highest fidelity testing of a system of this kind to date. During this helicopter testing, two new Morpheus landers were under construction at the Johnson Space Center to support the objective of an integrated ALHAT/Morpheus free-flight demonstration. This paper provides an overview of this helicopter flight test activity, including results and lessons learned, and also provides an overview of recent integrated testing of ALHAT on the second Morpheus vehicle.
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NASA Technical Reports Server (NTRS)
Rutishauser, David; Epp, Chirold; Robertson, Edward
2013-01-01
The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project was chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with real-time terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. The ALHAT System must be capable of identifying and avoiding surface hazards to enable a safe and accurate landing to within tens of meters of designated and certified landing sites anywhere on a planetary surface under any lighting conditions. This is accomplished with the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN). The NASA plan for the ALHAT technology is to perform the TRL6 closed loop demonstration on the Morpheus Vertical Test Bed (VTB). The first Morpheus vehicle was lost in August of 2012 during free-flight testing at Kennedy Space Center (KSC), so the decision was made to perform a helicopter test of the integrated ALHAT System with the Morpheus avionics over the ALHAT planetary hazard field at KSC. The KSC helicopter tests included flight profiles approximating planetary approaches, with the entire ALHAT system interfaced with all appropriate Morpheus subsystems and operated in real-time. During these helicopter flights, the ALHAT system imaged the simulated lunar terrain constructed in FY2012 to support ALHAT/Morpheus testing at KSC. To the best of our knowledge, this represents the highest fidelity testing of a system of this kind to date. During this helicopter testing, two new Morpheus landers were under construction at the Johnson Space Center to support the objective of an integrated ALHAT/Morpheus free-flight demonstration. This paper provides an overview of this helicopter flight test activity, including results and lessons learned, and also provides an overview of recent integrated testing of ALHAT on the second Morpheus vehicle.
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The Camera of the MASCOT Asteroid Lander on Board Hayabusa 2
NASA Astrophysics Data System (ADS)
Jaumann, R.; Schmitz, N.; Koncz, A.; Michaelis, H.; Schroeder, S. E.; Mottola, S.; Trauthan, F.; Hoffmann, H.; Roatsch, T.; Jobs, D.; Kachlicki, J.; Pforte, B.; Terzer, R.; Tschentscher, M.; Weisse, S.; Mueller, U.; Perez-Prieto, L.; Broll, B.; Kruselburger, A.; Ho, T.-M.; Biele, J.; Ulamec, S.; Krause, C.; Grott, M.; Bibring, J.-P.; Watanabe, S.; Sugita, S.; Okada, T.; Yoshikawa, M.; Yabuta, H.
2017-07-01
The MASCOT Camera (MasCam) is part of the Mobile Asteroid Surface Scout (MASCOT) lander's science payload. MASCOT has been launched to asteroid (162173) Ryugu onboard JAXA's Hayabusa 2 asteroid sample return mission on Dec 3rd, 2014. It is scheduled to arrive at Ryugu in 2018, and return samples to Earth by 2020. MasCam was designed and built by DLR's Institute of Planetary Research, together with Airbus-DS Germany. The scientific goals of the MasCam investigation are to provide ground truth for the orbiter's remote sensing observations, provide context for measurements by the other lander instruments (radiometer, spectrometer and magnetometer), the orbiter sampling experiment, and characterize the geological context, compositional variations and physical properties of the surface (e.g. rock and regolith particle size distributions). During daytime, clear filter images will be acquired. During night, illumination of the dark surface is performed by an LED array, equipped with 4×36 monochromatic light-emitting diodes (LEDs) working in four spectral bands. Color imaging will allow the identification of spectrally distinct surface units. Continued imaging during the surface mission phase and the acquisition of image series at different sun angles over the course of an asteroid day will contribute to the physical characterization of the surface and also allow the investigation of time-dependent processes and to determine the photometric properties of the regolith. The MasCam observations, combined with the MASCOT hyperspectral microscope (MMEGA) and radiometer (MARA) thermal observations, will cover a wide range of observational scales and serve as a strong tie point between Hayabusa 2's remote-sensing scales (103-10^{-3} m) and sample scales (10^{-3}-10^{-6} m). The descent sequence and the close-up images will reveal the surface features over a broad range of scales, allowing an assessment of the surface's diversity and close the gap between the orbital observations and those made by the in-situ measurements. The MasCam is mounted inside the lander slightly tilted, such that the center of its 54.8° square field-of-view is directed towards the surface at an angle of 22° with respect to the surface plane. This is to ensure that both the surface close to the lander and the horizon are observable. The camera optics is designed according to the Scheimpflug principle, thus that the entire scene along the camera's depth of field (150 mm to infinity) is in focus. The camera utilizes a 1024×1024 pixel CMOS sensor sensitive in the 400-1000 nm wavelength range, peaking at 600-700 nm. Together with the f-16 optics, this yields a nominal ground resolution of 150 micron/px at 150 mm distance (diffraction limited). The camera flight model has undergone standard radiometric and geometric calibration both at the component and system (lander) level. MasCam relies on the use of wavelet compression to maximize data return within stringent mission downlink limits. All calibration and flight data products will be generated and archived in the Planetary Data System in PDS image format.
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Space Launch System Co-Manifested Payload Options for Habitation
NASA Technical Reports Server (NTRS)
Smitherman, David
2015-01-01
The Space Launch System (SLS) has a co-manifested payload capability that will grow over time as the rocket matures and planned upgrades are implemented. The final configuration is planned to be capable of inserting a payload greater than 10 metric tons (mt) into a trans-lunar injection trajectory along with the crew in the Orion capsule and the service module. The co-manifested payload is located below the Orion and its service module in a 10-meter high fairing similar to the way the Saturn launch vehicle carried the lunar lander below the Apollo command and service modules. A variety of approaches have been explored that utilizes this co-manifested payload capability to build up infrastructure in deep space in support of future asteroid, lunar, and Mars mission scenarios. This paper is a report on the findings from the Advanced Concepts Office study team at the NASA Marshall Space Flight Center, working with the Advanced Exploration Systems Program on the Exploration Augmentation Module Project. It includes some of the possible options for habitation in the co-manifested payload volume on SLS. Findings include module designs that can be developed in 10mt increments to support these missions, including overall conceptual layouts, mass properties, and approaches for integration into various scenarios for near-term support of deep space habitat research and technology development, support to asteroid exploration, and long range support for Mars transfer flights.
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Landing Site Dispersion Analysis and Statistical Assessment for the Mars Phoenix Lander
NASA Technical Reports Server (NTRS)
Bonfiglio, Eugene P.; Adams, Douglas; Craig, Lynn; Spencer, David A.; Strauss, William; Seelos, Frank P.; Seelos, Kimberly D.; Arvidson, Ray; Heet, Tabatha
2008-01-01
The Mars Phoenix Lander launched on August 4, 2007 and successfully landed on Mars 10 months later on May 25, 2008. Landing ellipse predicts and hazard maps were key in selecting safe surface targets for Phoenix. Hazard maps were based on terrain slopes, geomorphology maps and automated rock counts of MRO's High Resolution Imaging Science Experiment (HiRISE) images. The expected landing dispersion which led to the selection of Phoenix's surface target is discussed as well as the actual landing dispersion predicts determined during operations in the weeks, days, and hours before landing. A statistical assessment of these dispersions is performed, comparing the actual landing-safety probabilities to criteria levied by the project. Also discussed are applications for this statistical analysis which were used by the Phoenix project. These include using the statistical analysis used to verify the effectiveness of a pre-planned maneuver menu and calculating the probability of future maneuvers.
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Red Dragon drill missions to Mars
NASA Astrophysics Data System (ADS)
Heldmann, Jennifer L.; Stoker, Carol R.; Gonzales, Andrew; McKay, Christopher P.; Davila, Alfonso; Glass, Brian J.; Lemke, Larry L.; Paulsen, Gale; Willson, David; Zacny, Kris
2017-12-01
We present the concept of using a variant of a Space Exploration Technologies Corporation (SpaceX) Dragon space capsule as a low-cost, large-capacity, near-term, Mars lander (dubbed ;Red Dragon;) for scientific and human precursor missions. SpaceX initially designed the Dragon capsule for flight near Earth, and Dragon has successfully flown many times to low-Earth orbit (LEO) and successfully returned the Dragon spacecraft to Earth. Here we present capsule hardware modifications that are required to enable flight to Mars and operations on the martian surface. We discuss the use of the Dragon system to support NASA Discovery class missions to Mars and focus in particular on Dragon's applications for drilling missions. We find that a Red Dragon platform is well suited for missions capable of drilling deeper on Mars (at least 2 m) than has been accomplished to date due to its ability to land in a powered controlled mode, accommodate a long drill string, and provide payload space for sample processing and analysis. We show that a Red Dragon drill lander could conduct surface missions at three possible targets including the ice-cemented ground at the Phoenix landing site (68 °N), the subsurface ice discovered near the Viking 2 (49 °N) site by fresh impact craters, and the dark sedimentary subsurface material at the Curiosity site (4.5 °S).
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NASA Technical Reports Server (NTRS)
Horvath, Thomas J.; OConnell, Tod F.; Cheatwood, F. McNeil; Prabhu, Ramadas K.; Alter, Stephen J.
2002-01-01
Aerodynamic wind-tunnel screening tests were conducted on a 0.029 scale model of a proposed Mars Surveyor 2001 Precision Lander (70 deg half angle spherically blunted cone with a conical afterbody). The primary experimental objective was to determine the effectiveness of a single flap to trim the vehicle at incidence during a lifting hypersonic planetary entry. The laminar force and moment data, presented in the form of coefficients, and shock patterns from schlieren photography were obtained in the NASA Langley Aerothermodynamic Laboratory for post-normal shock Reynolds numbers (based on forebody diameter) ranging from 2,637 to 92,350, angles of attack ranging from 0 tip to 23 degrees at 0 and 2 degree sideslip, and normal-shock density ratios of 5 and 12. Based upon the proposed entry trajectory of the 2001 Lander, the blunt body heavy gas tests in CF, simulate a Mach number of approximately 12 based upon a normal shock density ratio of 12 in flight at Mars. The results from this experimental study suggest that when traditional means of providing aerodynamic trim for this class of planetary entry vehicle are not possible (e.g. offset c.g.), a single flap can provide similar aerodynamic performance. An assessment of blunt body aerodynamic effects attributed to a real gas were obtained by synergistic testing in Mach 6 ideal-air at a comparable Reynolds number. From an aerodynamic perspective, an appropriately sized flap was found to provide sufficient trim capability at the desired L/D for precision landing. Inviscid hypersonic flow computations using an unstructured grid were made to provide a quick assessment of the Lander aerodynamics. Navier-Stokes computational predictions were found to be in very good agreement with experimental measurement.
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Resource Prospector Propulsion Cold Flow Test
NASA Technical Reports Server (NTRS)
Williams, Hunter; Pederson, Kevin; Dervan, Melanie; Holt, Kimberly; Jernigan, Frankie; Trinh, Huu; Flores, Sam
2014-01-01
For the past year, NASA Marshall Space Flight Center and Johnson Space Center have been working on a government version of a lunar lander design for the Resource Prospector Mission. A propulsion cold flow test system, representing an early flight design of the propulsion system, has been fabricated. The primary objective of the cold flow test is to simulate the Resource Prospector propulsion system operation through water flow testing and obtain data for anchoring analytical models. This effort will also provide an opportunity to develop a propulsion system mockup to examine hardware integration to a flight structure. This paper will report the work progress of the propulsion cold flow test system development and test preparation. At the time this paper is written, the initial waterhammer testing is underway. The initial assessment of the test data suggests that the results are as expected and have a similar trend with the pretest prediction. The test results will be reported in a future conference.
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Overview of Proposed ISRU Technology Development
NASA Technical Reports Server (NTRS)
Linne, Diane; Sanders, Jerry; Starr, Stan; Suzuki, Nantel; O'Malley, Terry
2016-01-01
ISRU involves any hardware or operation that harnesses and utilizes in-situ resources (natural and discarded) to create products and services for robotic and human exploration: Assessment of physical, mineral chemical, and volatile water resources, terrain, geology, and environment (orbital and local). Production of replacement parts, complex products, machines, and integrated systems from feedstock derived from one or more processed resources. Civil engineering, infrastructure emplacement, and structure construction using materials produced from in situ resources. Radiation shields, landing pads, roads, berms, habitats, etc. Generation and storage of electrical, thermal, and chemical energy with in situ derived materials. Solar arrays, thermal wadis, chemical batteries, etc. ISRU is a disruptive capability: Enables more affordable exploration than todays paradigm. Allows more sustainable architectures to be developed. Understand the ripple effect in the other Exploration Elements: MAV: propellant selection, higher rendezvous altitude (higher DV capable with ISRU propellants). EDL: significantly reduces required landed mass. Life Support: reduce amount of ECLSS closure, reduce trash mass carried through propulsive maneuvers. Power: ISRU drives electrical requirements, reactant and regeneration for fuel cells for landers, rovers, and habitat backup. Every Exploration Element except ISRU has some flight heritage (power, propulsion, habitats, landers, life support, etc.) ISRU will require a flight demonstration mission on Mars before it will be included in the critical path. Mission needs to be concluded at least 10 years before first human landed mission to ensure lessons learned can be incorporated into final design. ISRU Formulation team has generated a (still incomplete) list of over 75 technical questions on more than 40 components and subsystems that need to be answered before the right ISRU system will be ready for this flight demo.
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Earthly Considerations on Mars
NASA Technical Reports Server (NTRS)
Shaw, Robert J.
2003-01-01
When it came time to contact my research subjects on the Orbiter and Lander projects, I made it clear that I wasn't interested in finger pointing and I wasn't looking to blame anyone for failures. I explained that I was studying the strategic design of each project, i. e., the grouping, linking and alignment of the project. I wanted to look at the political environment to see how the goals and interests of stakeholders affected the outcomes, and I wanted to understand the working culture of each project.
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NASA Technical Reports Server (NTRS)
Shields, W. E.
1973-01-01
Tests were conducted to provide flight conditions for qualifying the Viking Decelerator System in a simulated Mars environment. A balloon launched decelerator test (BLDT) vehicle which has an external shape similar to the actual Mars Viking Lander Capsule was used so that the decelerator would be deployed in the wake of a blunt body. An effort was made to simulate the BLDT vehicle flights from the time they were dropped from the balloon, through decelerator deployment, until stable decelerator conditions were reached. The procedure used to simulate these flights using the Statistical Trajectory Estimation Program (STEP) is discussed. Using primarily ground-based position radar and vehicle onboard rate gyro and accelerometer data, the STEP produces a minimum variance solution of the vehicle trajectory and calculates vehicle attitude histories. Using film from cameras in the vehicle along with a computer program, attitude histories for portions of the flight before and after decelerator deployment were calculated independent of the STEP simulation. With the assumption that the vehicle motions derived from camera data are accurate, a comparison reveals that STEP was able to simulate vehicle motions for all flights both before and after decelerator deployment.
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Surface Stereo Imager on Mars, Side View
NASA Technical Reports Server (NTRS)
2008-01-01
This image is a view of NASA's Phoenix Mars Lander's Surface Stereo Imager (SSI) as seen by the lander's Robotic Arm Camera. This image was taken on the afternoon of the 116th Martian day, or sol, of the mission (September 22, 2008). The mast-mounted SSI, which provided the images used in the 360 degree panoramic view of Phoenix's landing site, is about 4 inches tall and 8 inches long. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Nighttime Clouds in Martian Arctic (Accelerated Movie)
NASA Technical Reports Server (NTRS)
2008-01-01
An angry looking sky is captured in a movie clip consisting of 10 frames taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander. The clip accelerates the motion. The images were take around 3 a.m. local solar time at the Phoenix site during Sol 95 (Aug. 30), the 95th Martian day since landing. The swirling clouds may be moving generally in a westward direction over the lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Overview of the Altair Lunar Lander Thermal Control System Design
NASA Technical Reports Server (NTRS)
Stephan, Ryan A.
2010-01-01
NASA's Constellation Program has been developed to successfully return humans to the Lunar surface by 2020. The Constellation Program includes several different project offices including Altair, which is the next generation Lunar Lander. The planned Altair missions are very different than the Lunar missions accomplished during the Apollo era. These differences have resulted in a significantly different thermal control system architecture. The current paper will summarize the Altair mission architecture and the various operational phases. In addition, the derived thermal requirements will be presented. The paper will conclude with a brief description of the thermal control system designed to meet these unique and challenging thermal requirements.
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Phoenix Makes an Impression on Mars
NASA Technical Reports Server (NTRS)
2008-01-01
This view from the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the first impression dubbed Yeti and looking like a wide footprint -- made on the Martian soil by the Robotic Arm scoop on Sol 6, the sixth Martian day of the mission, (May 31, 2008). Touching the ground is the first step toward scooping up soil and ice and delivering the samples to the lander's experiments. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Overview of LIDS Docking Seals Development
NASA Technical Reports Server (NTRS)
Dunlap, Pat; Steinetz, Bruce; Daniels, Chris
2008-01-01
NASA is developing a new docking system to support future space exploration missions to low-Earth orbit, the Moon, and Mars. This mechanism, called the Low Impact Docking System (LIDS), is designed to connect pressurized space vehicles and structures including the Crew Exploration Vehicle, International Space Station, and lunar lander. NASA Glenn Research Center (GRC) is playing a key role in developing the main interface seal for this new docking system. These seals will be approximately 147 cm (58 in.) in diameter. GRC is evaluating the performance of candidate seal designs under simulated operating conditions at both sub-scale and full-scale levels. GRC is ultimately responsible for delivering flight hardware seals to NASA Johnson Space Center around 2013 for integration into LIDS flight units.
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), Chris Voorhees (front) watches while Satish Krishnan (back) places a Mars microprobe on a workstand. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-10
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), Satish Krishnan (right) from the Jet Propulsion Laboratory places a Mars microprobe on a workstand. In the background, Chris Voorhees watches. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), Chris Voorhees (left) and Satish Krishnan (right), from the Jet Propulsion Laboratory, remove the second Mars microprobe from a drum. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-10
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), Chris Voorhees and Satish Krishnan from the Jet Propulsion Laboratory remove a microprobe which will hitchhike on the Mars Polar Lander. Scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket, the solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), a JPL worker checks the Mars microprobe. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-12
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), two JPL workers measure a Mars microprobe. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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Sample Handling in Extreme Environments
NASA Technical Reports Server (NTRS)
Avellar, Louisa; Badescu, Mircea; Sherrit, Stewart; Bar-Cohen, Yoseph
2013-01-01
Harsh environments, such as that on Venus, preclude the use of existing equipment for functions that involve interaction with the environment. The operating limitations of current high temperature electronics are well below the actual temperature and pressure found on Venus (460 deg C and 92 atm), so proposed lander configurations typically include a pressure vessel where the science instruments are kept at Earth-like temperature and pressure (25 deg C and 1 atm). The purpose of this project was to develop and demonstrate a method for sample transfer from an external drill to internal science instruments for a lander on Venus. The initial concepts were string and pneumatically driven systems; and the latter system was selected for its ability to deliver samples at very high speed. The pneumatic system was conceived to be driven by the pressure difference between the Venusian atmosphere and the inside of the lander. The pneumatic transfer of a small capsule was demonstrated, and velocity data was collected from the lab experiment. The sample transfer system was modeled using CAD software and prototyped using 3D printing. General structural and thermal analyses were performed to approximate the proposed system's mass and effects on the temperature and pressure inside of the lander. Additionally, a sampler breadboard for use on Titan was tested and functionality problems were resolved.
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Altair Lander Life Support: Design Analysis Cycles 4 and 5
NASA Technical Reports Server (NTRS)
Anderson, Molly; Curley, Su; Rotter, Henry; Stambaugh, Imelda; Yagoda, Evan
2011-01-01
Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.
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Altair Lander Life Support: Design Analysis Cycles 4 and 5
NASA Technical Reports Server (NTRS)
Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan
2010-01-01
Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.
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Aerial radiometric and magnetic survey: Lander National Topographic Map, Wyoming
DOE Office of Scientific and Technical Information (OSTI.GOV)
Not Available
1979-01-01
The results of analyses of the airborne gamma radiation and total magnetic field survey flown for the region identified as the Lander National Topographic Map NK12-6 are presented. The airborne data gathered are reduced by ground computer facilities to yield profile plots of the basic uranium, thorium and potassium equivalent gamma radiation intensities, ratios of these intensities, aircraft altitude above the earth's surface, total gamma ray and earth's magnetic field intensity, correlated as a function of geologic units. The distribution of data within each geologic unit, for all surveyed map lines and tie lines, has been calculated and is included.more » Two sets of profiled data for each line are included, with one set displaying the above-cited data. The second set includes only flight line magnetic field, temperature, pressure, altitude data plus magnetic field data as measured at a base station. A general description of the area, including descriptions of the various geologic units and the corresponding airborne data, is included also.« less
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The Mars climate for a photovoltaic system operation
NASA Technical Reports Server (NTRS)
Appelbaum, Joseph; Flood, Dennis J.
1989-01-01
Detailed information on the climatic conditions on Mars are very desirable for the design of photovoltaic systems for establishing outposts on the Martian surface. The distribution of solar insolation (global, direct and diffuse) and ambient temperature is addressed. This data are given at the Viking lander's locations and can also be used, to a first approximation, for other latitudes. The insolation data is based on measured optical depth of the Martian atmosphere derived from images taken of the sun with a special diode on the Viking cameras; and computation based on multiple wavelength and multiple scattering of the solar radiation. The ambient temperature (diurnal and yearly distribution) is based on direct measurements with a thermocouple at 1.6 m above the ground at the Viking lander locations. The insolation and ambient temperature information are short term data. New information about Mars may be forthcoming in the future from new analysis of previously collected data or from future flight missions. The Mars climate data for photovoltaic system operation will thus be updated accordingly.
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InSight Cruise Stage and Lander in Assembly
2015-05-27
Spacecraft specialists in a clean room at Lockheed Martin Space Systems, Denver, are working on NASA's InSight spacecraft in this January 2015 scene from the mission's assembly and testing phase. At center is the cruise stage, which will serve multiple functions during the flight from Earth to Mars. In the background is the InSight lander. InSight, for Interior Exploration Using Seismic Investigations, Geodesy and Heat Transport, will investigate the deep interior of Mars to gain information about how rocky planets, including Earth, formed and evolved. The mission is scheduled for launch from California in March 2016 and landing on Mars in September 2016. Note: After thorough examination, NASA managers have decided to suspend the planned March 2016 launch of the Interior Exploration using Seismic Investigations Geodesy and Heat Transport (InSight) mission. The decision follows unsuccessful attempts to repair a leak in a section of the prime instrument in the science payload. http://photojournal.jpl.nasa.gov/catalog/PIA19403
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Optimization of a Lunar Pallet Lander Reinforcement Structure Using a Genetic Algorithm
NASA Technical Reports Server (NTRS)
Burt, Adam O.; Hull, Patrick V.
2014-01-01
This paper presents a design automation process using optimization via a genetic algorithm to design the conceptual structure of a Lunar Pallet Lander. The goal is to determine a design that will have the primary natural frequencies at or above a target value as well as minimize the total mass. Several iterations of the process are presented. First, a concept optimization is performed to determine what class of structure would produce suitable candidate designs. From this a stiffened sheet metal approach was selected leading to optimization of beam placement through generating a two-dimensional mesh and varying the physical location of reinforcing beams. Finally, the design space is reformulated as a binary problem using 1-dimensional beam elements to truncate the design space to allow faster convergence and additional mechanical failure criteria to be included in the optimization responses. Results are presented for each design space configuration. The final flight design was derived from these results.
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Precise Image-Based Motion Estimation for Autonomous Small Body Exploration
NASA Technical Reports Server (NTRS)
Johnson, Andrew Edie; Matthies, Larry H.
2000-01-01
We have developed and tested a software algorithm that enables onboard autonomous motion estimation near small bodies using descent camera imagery and laser altimetry. Through simulation and testing, we have shown that visual feature tracking can decrease uncertainty in spacecraft motion to a level that makes landing on small, irregularly shaped, bodies feasible. Possible future work will include qualification of the algorithm as a flight experiment for the Deep Space 4/Champollion comet lander mission currently under study at the Jet Propulsion Laboratory.
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NASA Technical Reports Server (NTRS)
Schroder, Christian; Klingelhofer, Gostar; Morris, Richard V.; Yen, Albert S.; Renz, Franz; Graff, Trevor G.
2016-01-01
The miniaturized Mossbauer spectrometer MIMOS II is an off-the-shelf instrument, which has been successfully deployed during NASA's Mars Exploration Rover (MER) mission and was on-board the ESA/UK Beagle 2 Mars lander and the Russian Phobos-Grunt sample return mission. We propose to use a fully-qualified flight-spare MIMOS II instrument available from these missions for in situ asteroid characterization with the Asteroid Redirect Robotic Mission (ARRM).
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Exploration Life Support Technology Development for Lunar Missions
NASA Technical Reports Server (NTRS)
Ewert, Michael K.; Barta, Daniel J.; McQuillan, Jeffrey
2009-01-01
Exploration Life Support (ELS) is one of NASA's Exploration Technology Development Projects. ELS plans, coordinates and implements the development of new life support technologies for human exploration missions as outlined in NASA's Vision for Space Exploration. ELS technology development currently supports three major projects of the Constellation Program - the Orion Crew Exploration Vehicle (CEV), the Altair Lunar Lander and Lunar Surface Systems. ELS content includes Air Revitalization Systems (ARS), Water Recovery Systems (WRS), Waste Management Systems (WMS), Habitation Engineering, Systems Integration, Modeling and Analysis (SIMA), and Validation and Testing. The primary goal of the ELS project is to provide different technology options to Constellation which fill gaps or provide substantial improvements over the state-of-the-art in life support systems. Since the Constellation missions are so challenging, mass, power, and volume must be reduced from Space Shuttle and Space Station technologies. Systems engineering analysis also optimizes the overall architecture by considering all interfaces with the life support system and potential for reduction or reuse of resources. For long duration missions, technologies which aid in closure of air and water loops with increased reliability are essential as well as techniques to minimize or deal with waste. The ELS project utilizes in-house efforts at five NASA centers, aerospace industry contracts, Small Business Innovative Research contracts and other means to develop advanced life support technologies. Testing, analysis and reduced gravity flight experiments are also conducted at the NASA field centers. This paper gives a current status of technologies under development by ELS and relates them to the Constellation customers who will eventually use them.
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Low Cost Precision Lander for Lunar Exploration
NASA Astrophysics Data System (ADS)
Head, J. N.; Gardner, T. G.; Hoppa, G. V.; Seybold, K. G.
2004-12-01
For 60 years the US Defense Department has invested heavily in producing small, low mass, precision guided vehicles. The technologies matured under these programs include terrain-aided navigation, closed loop terminal guidance algorithms, robust autopilots, high thrust-to-weight propulsion, autonomous mission management software, sensors, and data fusion. These technologies will aid NASA in addressing New Millennium Science and Technology goals as well as the requirements flowing from the Vision articulated in January 2004. Establishing and resupplying a long term lunar presence will require automated landing precision not yet demonstrated. Precision landing will increase safety and assure mission success. In the DOD world, such technologies are used routinely and reliably. Hence, it is timely to generate a point design for a precise planetary lander useful for lunar exploration. In this design science instruments amount to 10 kg, 16% of the lander vehicle mass. This compares favorably with 7% for Mars Pathfinder and less than 15% for Surveyor. The mission design flies the lander in an inert configuration to the moon, relying on a cruise stage for navigation and TCMs. The lander activates about a minute before impact. A solid booster reduces the vehicle speed to 300-450 m/s. The lander is now about 2 minutes from touchdown and has 600 to 700 m/s delta-v capability, allowing for about 10 km of vehicle divert during terminal descent. This concept of operations is chosen because it closely mimics missile operational timelines used for decades: the vehicle remains inert in a challenging environment, then must execute its mission flawlessly on a moment's notice. The vehicle design consists of a re-plumbed propulsion system, using propellant tanks and thrusters from exoatmospheric programs. A redesigned truss provides hard points for landing gear, electronics, power supply, and science instruments. A radar altimeter and a Digital Scene Matching Area Correlator (DSMAC) provide data for the terminal guidance algorithms. DSMAC acquires high-resolution images for real-time correlation with a reference map. This system provides ownship position with a resolution comparable to the map. Since the DSMAC can sample at 1.5 mrad, any imaging acquired below 70 km altitude will surpass the resolution available from previous missions. DSMAC has a mode where image data are compressed and downlinked. This capability could be used to downlink live images during terminal guidance. Approximately 500 kbitps telemetry would be required to provide the first live descent imaging sequence since Ranger. This would provide unique geologic context imaging for the landing site. The development path to produce such a vehicle is that used to develop missiles. First, a pathfinder vehicle is designed and built as a test bed for hardware integration including science instruments. Second, a hover test vehicle would be built. Equipped with mass mockups for the science payload, the vehicle would otherwise be an exact copy of the flight vehicle. The hover vehicle would be flown on earth to demonstrate the proper function and integration of the propulsion system, autopilots, navigation algorithms, and guidance sensors. There is sufficient delta-v in the proposed design to take off from the ground, fly a ballistic arc to over 100 m altitude, then guide to a precision soft landing. Once the vehicle has flown safely on earth, then the validated design would be used to produce the flight vehicle. Since this leverages the billions of dollars DOD has invested in these technologies, it should be possible to land useful science payloads precisely on the lunar surface at relatively low cost.
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Delivery to the Wet Chemistry Laboratory
NASA Technical Reports Server (NTRS)
2008-01-01
This portion of a picture acquired by NASA's Phoenix Mars Lander's Robotic Arm Camera documents the delivery of soil to one of four Wet Chemistry Laboratory (WCL) cells on the 30th Martian day, or sol, of the mission. Approximately one cubic centimeter of this soil was then introduced into the cell and mixed with water for chemical analysis. WCL is part of the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA) instrument suite on board the Phoenix lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
NASA Technical Reports Server (NTRS)
2008-01-01
Three locations to the right of the test dig area are identified for the first samples to be delivered to the Thermal and Evolved Gas Analyzer (TEGA), the Wet Chemistry Lab (WCL), and the Optical Microscope (OM) on NASA's Phoenix Mars Lander. These sampling areas are informally labeled 'Baby Bear', 'Mama Bear', and 'Papa Bear' respectively. This image was taken on the seventh day of the Mars mission, or Sol 7 (June 1, 2008) by the Surface Stereo Imager aboard NASA's Phoenix Mars Lander. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Altair Lander Life Support: Requirement Analysis Cycles 1 and 2
NASA Technical Reports Server (NTRS)
Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan
2009-01-01
Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally-functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair s life support system.
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Altair Lander Life Support: Requirements Analysis Cycles 1 and 2
NASA Technical Reports Server (NTRS)
Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan
2010-01-01
Life support systems are a critical part of human exploration beyond low earth orbit. NASA's Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally -functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper'. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair's life support system.
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Moon-Mars simulation campaign in volcanic Eifel: Remote science support and sample analysis
NASA Astrophysics Data System (ADS)
Offringa, Marloes; Foing, Bernard H.; Kamps, Oscar
2016-07-01
Moon-Mars analogue missions using a mock-up lander that is part of the ESA/ILEWG ExoGeoLab project were conducted during Eifel field campaigns in 2009, 2015 and 2016 (Foing et al., 2010). In the last EuroMoonMars2016 campaign the lander was used to conduct reconnaissance experiments and in situ geological scientific analysis of samples, with a payload that mainly consisted of a telescope and a UV-VIS reflectance spectrometer. The aim of the campaign was to exhibit possibilities for the ExoGeoLab lander to perform remotely controlled experiments and test its applicability in the field by simulating the interaction with astronauts. The Eifel region in Germany where the experiments with the ExoGeoLab lander were conducted is a Moon-Mars analogue due to its geological setting and volcanic rock composition. The research conducted by analysis equipment on the lander could function in support of Moon-Mars sample return missions, by providing preliminary insight into characteristics of the analyzed samples. The set-up of the prototype lander was that of a telescope with camera and solar power equipment deployed on the top, the UV-VIS reflectance spectrometer together with computers and a sample webcam were situated in the middle compartment and to the side a sample analysis test bench was attached, attainable by astronauts from outside the lander. An alternative light source that illuminated the samples in case of insufficient daylight was placed on top of the lander and functioned on solar power. The telescope, teleoperated from a nearby stationed pressurized transport vehicle that functioned as a base control center, attained an overview of the sampling area and assisted the astronauts in their initial scouting pursuits. Locations of suitable sampling sites based on these obtained images were communicated to the astronauts, before being acquired during a simulated EVA. Sampled rocks and soils were remotely analyzed by the base control center, while the astronauts assisted by placing the samples onto the sample holder and adjusting test bench settings in order to obtain spectra. After analysis the collected samples were documented and stored by the astronauts, before returning to the base. Points of improvement for the EuroMoonMars2016 analog campaign are the remote control of the computers using an established network between the base and the lander. During following missions the computers should preferably be operated over a larger distance without interference. In the bottom compartment of the lander a rover is stored that in future campaigns could replace astronaut functions by collecting and returning samples, as well as performing adjustments to the analysis test bench by using a remotely controlled robotic arm. Acknowledgements: we thank Dominic Doyle for ESTEC optical lab support, Aidan Cowley (EAC) and Matthias Sperl (DLR) for support discussions, and collaborators from EuroMoonMars Eifel 2015-16 campaign team.
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Phoenix--the first Mars Scout mission.
Shotwell, Robert
2005-01-01
NASA has initiated the first of a new series of missions to augment the current Mars Program. In addition to the systematic series of planned, directed missions currently comprising the Mars Program plan, NASA has started a series of Mars Scout missions that are low cost, price fixed, Principal [correction of Principle] Investigator-led projects. These missions are intended to provide an avenue for rapid response to discoveries made as a result of the primary Mars missions, as well as allow more risky technologies and approaches to be applied in the investigation of Mars. The first in this new series is the Phoenix mission which was selected as part of a highly competitive process. Phoenix will use the Mars 2001 Lander that was discontinued in 2000 and apply a new set of science objectives and mission objectives and will validate this soft lander architecture for future applications. This paper will provide an overview of both the Program and the Project. c2005 Elsevier Ltd. All rights reserved.
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NASA Technical Reports Server (NTRS)
Martin, J. S., Jr.; Sibbers, C. W.
1972-01-01
Description of the Viking Project, a current effort to explore Mars using two unmanned spacecraft, consisting of an orbiter and lander each, during the 1975-1976 opportunity. The experiments on the surface will deal principally with biology, geology, and meteorology. If life is discovered on Mars, the dramatic find would greatly expand the field of exobiology and lead to a remarkable opportunity to study life that may be similar or different from our own.
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Project UM-HAUL: A self-unloading reusable lunar lander
NASA Technical Reports Server (NTRS)
1991-01-01
The establishment of a lunar base is technologically and financially challenging. Given the necessary resources and political support, it can be done. In addition to the geopolitical obstacles, however, there are logistical problems involved in establishing such bases that can only be overcome with the acquisition of a significant transportation and communications network in the Earth-Moon spatial region. Considering the significant number of payloads that will be required in this process, the mass-specific cost of launching these payloads, and the added risk and cost of human presence in space, it is clearly desirable to automate major parts of such an operation. One very costly and time-consuming factor in this picture is the delivery of payloads to the Moon. Foreseeable payloads would include atmospheric modules, inflatable habitat kits, energy and oxygen plant elements, ground vehicles, laboratory modules, crew supplies, etc. The duration of high-risk human presence on the Moon could be greatly reduced if all such payloads were delivered to the prospective base site in advance of crew arrival. In this view, the idea of a 'Self-Unloading Reusable Lunar Lander' (SURLL) arises naturally. The general scenario depicts the lander being brought to low lunar orbit (LLO) from Earth atop a generic Orbital Transfer Vehicle (OTV). From LLO, the lander shuttles payloads down to the lunar surface, where, by means of some resident, detachable unloading device, it deploys the payloads and returns to orbit. The general goal is for the system to perform with maximum payload capability, automation, and reliability, while also minimizing environmental hazards, servicing needs, and mission costs. Our response to this demand is UM-HAUL, or the UnManned Heavy pAyload Unloader and Lander. The complete study includes a system description, along with a preliminary cost analysis and a design status assessment.
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Project UM-HAUL: A self-unloading reusable lunar lander
NASA Astrophysics Data System (ADS)
The establishment of a lunar base is technologically and financially challenging. Given the necessary resources and political support, it can be done. In addition to the geopolitical obstacles, however, there are logistical problems involved in establishing such bases that can only be overcome with the acquisition of a significant transportation and communications network in the Earth-Moon spatial region. Considering the significant number of payloads that will be required in this process, the mass-specific cost of launching these payloads, and the added risk and cost of human presence in space, it is clearly desirable to automate major parts of such an operation. One very costly and time-consuming factor in this picture is the delivery of payloads to the Moon. Foreseeable payloads would include atmospheric modules, inflatable habitat kits, energy and oxygen plant elements, ground vehicles, laboratory modules, crew supplies, etc. The duration of high-risk human presence on the Moon could be greatly reduced if all such payloads were delivered to the prospective base site in advance of crew arrival. In this view, the idea of a 'Self-Unloading Reusable Lunar Lander' (SURLL) arises naturally. The general scenario depicts the lander being brought to low lunar orbit (LLO) from Earth atop a generic Orbital Transfer Vehicle (OTV). From LLO, the lander shuttles payloads down to the lunar surface, where, by means of some resident, detachable unloading device, it deploys the payloads and returns to orbit. The general goal is for the system to perform with maximum payload capability, automation, and reliability, while also minimizing environmental hazards, servicing needs, and mission costs. Our response to this demand is UM-HAUL, or the UnManned Heavy pAyload Unloader and Lander. The complete study includes a system description, along with a preliminary cost analysis and a design status assessment.
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Using virtual reality for science mission planning: A Mars Pathfinder case
NASA Technical Reports Server (NTRS)
Kim, Jacqueline H.; Weidner, Richard J.; Sacks, Allan L.
1994-01-01
NASA's Mars Pathfinder Project requires a Ground Data System (GDS) that supports both engineering and scientific payloads with reduced mission operations staffing, and short planning schedules. Also, successful surface operation of the lander camera requires efficient mission planning and accurate pointing of the camera. To meet these challenges, a new software strategy that integrates virtual reality technology with existing navigational ancillary information and image processing capabilities. The result is an interactive workstation based applications software that provides a high resolution, 3-dimensial, stereo display of Mars as if it were viewed through the lander camera. The design, implementation strategy and parametric specification phases for the development of this software were completed, and the prototype tested. When completed, the software will allow scientists and mission planners to access simulated and actual scenes of Mars' surface. The perspective from the lander camera will enable scientists to plan activities more accurately and completely. The application will also support the sequence and command generation process and will allow testing and verification of camera pointing commands via simulation.
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1998-11-10
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), workers from the Jet Propulsion Laboratory open the drums containing the Mars microprobes that will hitchhike on the Mars Polar Lander. From left, they are Satish Krishnan, Charles Cruzan, Chris Voorhees and Arden Acord. Scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket, the solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millennium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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1998-11-10
KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), Tandy Bianco, with Lockheed Martin, and Satish Krishnan (foreground) and Chris Voorhees (behind him), from the Jet Propulsion Laboratory, observe a Mars microprobe on the workstand. Two microprobes will hitchhike on the Mars Polar Lander, scheduled to be launched Jan. 3, 1999, aboard a Delta II rocket. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars microprobes, called Deep Space 2, are part of NASA's New Millelnnium Program. They will complement the climate-related scientific focus of the lander by demonstrating an advanced, rugged microlaser system for detecting subsurface water. Such data on polar subsurface water, in the form of ice, should help put limits on scientific projections for the global abundance of water on Mars
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Martian Soil Ready for Robotic Laboratory Analysis
NASA Technical Reports Server (NTRS)
2008-01-01
NASA's Phoenix Mars Lander scooped up this Martian soil on the mission's 11th Martian day, or sol, after landing (June 5, 2008) as the first soil sample for delivery to the laboratory on the lander deck. The material includes a light-toned clod possibly from crusted surface of the ground, similar in appearance to clods observed near a foot of the lander. This approximately true-color view of the contents of the scoop on the Robotic Arm comes from combining separate images taken by the Robotic Arm Camera on Sol 11, using illumination by red, green and blue light-emitting diodes on the camera. The scoop loaded with this sample was poised over an open sample-delivery door of Thermal and Evolved-Gas Analyzer at the end of Sol 11, ready to be dumped into the instrument on the next sol. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Passive range estimation for rotorcraft low-altitude flight
NASA Technical Reports Server (NTRS)
Sridhar, B.; Suorsa, R.; Hussien, B.
1991-01-01
The automation of rotorcraft low-altitude flight presents challenging problems in control, computer vision and image understanding. A critical element in this problem is the ability to detect and locate obstacles, using on-board sensors, and modify the nominal trajectory. This requirement is also necessary for the safe landing of an autonomous lander on Mars. This paper examines some of the issues in the location of objects using a sequence of images from a passive sensor, and describes a Kalman filter approach to estimate the range to obstacles. The Kalman filter is also used to track features in the images leading to a significant reduction of search effort in the feature extraction step of the algorithm. The method can compute range for both straight line and curvilinear motion of the sensor. A laboratory experiment was designed to acquire a sequence of images along with sensor motion parameters under conditions similar to helicopter flight. Range estimation results using this imagery are presented.
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The Mars In-Situ-Propellant-Production Precursor (MIP) Flight Demonstration
NASA Technical Reports Server (NTRS)
Kaplan, D. I.; Ratliff, J. E.; Baird, R. S.; Sanders, G. B.; Johnson, K. R.; Karlmann, P. B.; Baraona, C. R.; Landis, G. A.; Jenkins, P. P.; Scheiman, D. A.
1999-01-01
Strategic planning for human missions of exploration to Mars has conclusively identified insitu propellant production (ISPP) as an enabling technology. A team of scientists and engineers from NASA's Johnson Space Center, Jet Propulsion Laboratory, and Glenn Research Center is preparing the MARS ISPP PRECURSOR (MIP) Flight Demonstration. The objectives of MIP are to characterize the performance of processes and hardware that are important to ISPP concepts and to demonstrate how these processes and hardware interact with the Mars environment. Operating this hardware in the actual Mars environment is extremely important due to (1) uncertainties in our knowledge of the Mars environment, and (2) conditions that cannot be adequately simulated on Earth. The MIP Flight Demonstration is a payload onboard the MARS SURVEYOR Lander and will be launched in April 2001. MIP will be the first hardware to utilize the indigenous resources of a planet or moon. Its successful operation will pave the way for future robotic and human missions to rely on propellants produced using Martian resources as feedstock.
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Mars Sample Return and Flight Test of a Small Bimodal Nuclear Rocket and ISRU Plant
NASA Technical Reports Server (NTRS)
George, Jeffrey A.; Wolinsky, Jason J.; Bilyeu, Michael B.; Scott, John H.
2014-01-01
A combined Nuclear Thermal Rocket (NTR) flight test and Mars Sample Return mission (MSR) is explored as a means of "jump-starting" NTR development. Development of a small-scale engine with relevant fuel and performance could more affordably and quickly "pathfind" the way to larger scale engines. A flight test with subsequent inflight postirradiation evaluation may also be more affordable and expedient compared to ground testing and associated facilities and approvals. Mission trades and a reference scenario based upon a single expendable launch vehicle (ELV) are discussed. A novel "single stack" spacecraft/lander/ascent vehicle concept is described configured around a "top-mounted" downward firing NTR, reusable common tank, and "bottom-mount" bus, payload and landing gear. Requirements for a hypothetical NTR engine are described that would be capable of direct thermal propulsion with either hydrogen or methane propellant, and modest electrical power generation during cruise and Mars surface insitu resource utilization (ISRU) propellant production.
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NASA Technical Reports Server (NTRS)
Prabhu, Ramadas K.; Sutton, Kenneth (Technical Monitor)
2001-01-01
This report documents the results of a study conducted to compute the inviscid longitudinal aerodynamic characteristics of three aeroshell configurations of the proposed '07 Mars lander. This was done in support of the activity to design a smart lander for the proposed '07 Mars mission. In addition to the three configurations with tabs designated as the shelf, the canted, and the Ames, the baseline configuration (without tab) was also studied. The unstructured grid inviscid CFD software FELISA was used, and the longitudinal aerodynamic characteristics of the four configurations were computed for Mach number of 2.3, 2.7, 3.5, and 4.5, and for an angle of attack range of -4 to 20 degrees. Wind tunnel tests had been conducted on scale models of these four configurations in the Unitary Plan Wind Tunnel, NASA Langley Research Center. Present computational results are compared with the data from these tests. Some differences are noticed between the two results, particularly at the lower Mach numbers. These differences are attributed to the pressures acting on the aft body. Most of the present computations were done on the forebody only. Additional computations were done on the full body (forebody and afterbody) for the baseline and the Shelf configurations. Results of some computations done (to simulate flight conditions) with the Mars gas option and with an effective gamma are also included.
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Mars 1994/1996: The French navigation tasks
NASA Technical Reports Server (NTRS)
Bonneau, Frederic; Bernard, Jacques; Delobette, Damien
1993-01-01
In the fall of 1994, Russia will launch a spacecraft to Mars. France is involved in many scientific experiments which are onboard the spacecraft, as PI or CI. Some days before the Mars orbit insertion maneuver, two small stations and two penetrators will be injected into an entry trajectory. They will carry out for at least six months in situ analysis on the Martian surface. Two years later, a second spacecraft will be launched. It will carry the French balloon and a small rover. The scientific data of these landers will be relayed to earth via the spacecraft. However, during the first 20 days of their mission, Mars Observer will be used. To this end, a Mars balloon relay will be used, which will receive the data from the landers and store them into the memory of the Mars Observer camera. The spacecraft will also be used to localize the landers with the help of relative one-way Doppler measurements. An international cooperative is set up for this process, including JPS, Russian ballistic centers (Babakine, Institute of Applied Mathematics, Moscow Flight Control Center), and CNES Toulouse. Another task dedicated to the space mathematics division of CNES is to support the French scientists to prepare their telecommands and to analyze their telemetry. This second part is integrated into the French ground segment created for the Mars 94/96 mission. This paper describes the method used in CNES for the localization process, the support provided to the scientists, and the links for the data exchange.
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French Participation in Mars Sample Return (and MARS Exploration)
NASA Astrophysics Data System (ADS)
Counil, Jean-Louis
2000-10-01
This presentation focused on high level contribution to the first MARS Sample Return mission. It further discusses leadership of the European Netlander project, Payload Instruments on the ESA-mission MARS-Express, Contribution to US Micro-missions, Instruments on Landers (PALOMA, Ma-FLUX), and Co-Is.
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Crater Morphology in the Phoenix Landing Ellipse: Insights Into Net Erosion and Ice Table Depth
NASA Technical Reports Server (NTRS)
Noe Dobrea, E. Z.; Stoker, C. R.; McKay, C. P.; Davila, A. F.; Krco, M.
2015-01-01
Icebreaker [1] is a Discovery class mission being developed for future flight opportunities. Under this mission concept, the Icebreaker payload is carried on a stationary lander, and lands in the same landing ellipse as Phoenix. Samples are acquired from the subsurface using a drilling system that penetrates into materials which may include loose or cemented soil, icy soil, pure ice, rocks, or mixtures of these. To avoid the complexity of mating additional strings, the drill is single-string, limiting it to a total length of 1 m.
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(abstract) Scaling Nominal Solar Cell Impedances for Array Design
NASA Technical Reports Server (NTRS)
Mueller, Robert L; Wallace, Matthew T.; Iles, Peter
1994-01-01
This paper discusses a task the objective of which is to characterize solar cell array AC impedance and develop scaling rules for impedance characterization of large arrays by testing single solar cells and small arrays. This effort is aimed at formulating a methodology for estimating the AC impedance of the Mars Pathfinder (MPF) cruise and lander solar arrays based upon testing single cells and small solar cell arrays and to create a basis for design of a single shunt limiter for MPF power control of flight solar arrays having very different inpedances.
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The Viking mortar - Design, development, and flight qualification.
NASA Technical Reports Server (NTRS)
Brecht, J. P.; Pleasants, J. E.; Mehring, R. D.
1973-01-01
Approximately 25,400 ft above the local surface of Mars, a radar height sensor fires the Viking mortar, which ejects a 53-ft D sub o disk-gap-band (DGB) parachute. The parachute decelerates and stabilizes the Viking lander sufficiently for the terminal engine system to take over and effect a soft landing. The general design and environmental requirements for the mortar system are presented; various illustrations of the mortar components and how the mortar system functions also are presented. Primary emphasis is placed on manufacturing, developing, and qualification testing of the mortar system.
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Conductivity Probe Inserted in Martian Soil, Sol 46
NASA Technical Reports Server (NTRS)
2008-01-01
This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Thermal and Electrical Conductivity Probe (TECP), at the end of the Robotic Arm, on the 46th Martian day, or sol, of the mission (July 11, 2008). The TECP is inserted at a site called Vestri, which was monitored several times over the course of the mission. The probe's measurements at this site yielded evidence that water was exchanged, daily and seasonally, between the soil and atmosphere. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Entry Vehicle Control System Design for the Mars Smart Lander
NASA Technical Reports Server (NTRS)
Calhoun, Philip C.; Queen, Eric M.
2002-01-01
The NASA Langley Research Center, in cooperation with the Jet Propulsion Laboratory, participated in a preliminary design study of the Entry, Descent and Landing phase for the Mars Smart Lander Project. This concept utilizes advances in Guidance, Navigation and Control technology to significantly reduce uncertainty in the vehicle landed location on the Mars surface. A candidate entry vehicle controller based on the Reaction Control System controller for the Apollo Lunar Excursion Module digital autopilot is proposed for use in the entry vehicle attitude control. A slight modification to the phase plane controller is used to reduce jet-firing chattering while maintaining good control response for the Martian entry probe application. The controller performance is demonstrated in a six-degree-of-freedom simulation with representative aerodynamics.
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Dark Skies and Clouds Move in at Phoenix site
NASA Technical Reports Server (NTRS)
2008-01-01
Clouds of dust and ice swirl past the Surface Stereo Imager (SSI) camera on NASA's Phoenix Mars Lander in a series of images taken on the 132nd Martian day of the mission (Oct. 7, 2008). The images show the increase in storm activity and potential for snowfall. The solar powered spacecraft was disabled by decreased light from heavy dust storms in the area a few weeks later. The last communication heard from the lander occurred on Nov. 2, 2008. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
Phoenix Again Carries Soil to Wet Chemistry Lab
NASA Technical Reports Server (NTRS)
2008-01-01
This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Robotic Arm scoop positioned over the Wet Chemistry Lab Cell 1 delivery funnel on Sol 41, the 42nd Martian day after landing, or July 6, 2008, after a soil sample was delivered to the instrument. The instrument's Cell 1 is second one from the foreground of the image. The first cell, Cell 0, received a soil sample two weeks earlier. This image has been enhanced to brighten the scene. The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
NASA Technical Reports Server (NTRS)
2008-01-01
The Robotic Arm Camera on NASA's Phoenix Mars Lander took this image on Oct. 18, 2008, during the 142nd Martian day, or sol, since landing. The flat patch in the center of the image has the informal name 'Holy Cow,' based on researchers' reaction when they saw the initial image of it only a few days after the May 25, 2008 landing. Researchers first saw this flat patch in an image taken by the Robotic Arm Camera on May 30, the fifth Martian day of the mission. The Phoenix mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver. -
NASA Astrophysics Data System (ADS)
Golombek, M. P.
1996-09-01
The Mars Pathfinder mission is a Discovery class mission that will place a small lander and rover on the surface of Mars on July 4, 1997. The Pathfinder flight system is a single small lander, packaged within an aeroshell and back cover with a back-pack-style cruise stage. The vehicle will be launched, fly independently to Mars, and enter the atmosphere directly on approach behind the aeroshell. The vehicle is slowed by a parachute and 3 small solid rockets before landing on inflated airbags. Petals of a small tetrahedron shaped lander open up, to right the vehicle. The lander is solar powered with batteries and will operate on the surface for up to a year, downlinking data on a high-gain antenna. Pathfinder will be the first mission to use a rover, with 3 imagers and an alpha proton X-ray spectrometer, to characterize the rocks and soils in a landing area over hundreds of square meters on Mars, which will provide a calibration point or "ground truth" for orbital remote sensing observations. The rover (includes a series of technology experiments), the instruments (including a stereo multispectral surface imager on a pop up mast and an atmospheric structure instrument-surface meteorology package) and the telemetry system will allow investigations of: the surface morphology and geology at meter scale, the petrology and geochemistry of rocks and soils, the magnetic properties of dust, soil mechanics and properties, a variety of atmospheric investigations and the rotational and orbital dynamics of Mars. Landing downstream from the mouth of a giant catastrophic outflow channel, Ares Vallis, offers the potential of identifying and analyzing a wide variety of crustal materials, from the ancient heavily cratered terrain, intermediate-aged ridged plains and reworked channel deposits, thus allowing first-order scientific investigations of the early differentiation and evolution of the crust, the development of weathering products and early environments and conditions on Mars.
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Nano Icy Moons Propellant Harvester
NASA Technical Reports Server (NTRS)
VanWoerkom, Michael (Principal Investigator)
2017-01-01
As one of just a few bodies identified in the solar system with a liquid ocean, Europa has become a top priority in the search for life outside of Earth. However, cost estimates for exploring Europa have been prohibitively expensive, with estimates of a NASA Flagship class orbiter and lander approaching $5 billion. ExoTerra's NIMPH offers an affordable solution that can not only land, but return a sample from the surface to Earth. NIMPH combines solar electric propulsion (SEP) technologies being developed for the asteroid redirect mission and microsatellite electronics to reduce the cost of a full sample return mission below $500 million. A key to achieving this order-of-magnitude cost reduction is minimizing the initial mass of the system. The cost of any mission is directly proportional to its mass. By keeping the mission within the constraints of an Atlas V 551 launch vehicle versus an SLS, we can significantly reduce launch costs. To achieve this we reduce the landed mass of the sample return lander, which is the largest multiplier of mission mass, and shrink propellant mass through high efficiency SEP and gravity assists. The NIMPH projects first step in reducing landed mass focuses on development of a micro-In Situ Resource Utilization (micro-ISRU) system. ISRU allows us to minimize landed mass of a sample return mission by converting local ice into propellants. The project reduces the ISRU system to a CubeSat-scale package that weighs just 1.74 kg and consumes just 242 W of power. We estimate that use of this ISRU vs. an identical micro-lander without ISRU reduces fuel mass by 45 kg. As the dry mass of the lander grows for larger missions, these savings scale exponentially. Taking full advantage of the micro-ISRU system requires the development of a micro-liquid oxygen-liquid hydrogen engine. The micro-liquid oxygen-liquid hydrogen engine is tailored for the mission by scaling it to match the scale of the micro-lander and the low gravity of the target moon. We also tailor the engine for a near stoichiometric mixture ratio of 7.5. Most high-performance liquid oxygen-liquid hydrogen engines inject extra liquid hydrogen to lower the average molecular weight of the exhaust, which improves specific impulse. However, this extra liquid hydroden requires additional power and processing time on the surface for the ISRU to create. This increases mission cost, and on missions within high radiation environments such as Europa, increases radiation shielding mass. The resulting engine weighs just 1.36 kg and produces 71.5 newton of thrust at 364 s specific impulse. Finally, the mission reduces landed mass by taking advantage of the SEP modules solar power to beam energy to the surface using a collimated laser. This allows us to replace an 45 kg MMRTG with a 2.5 kg resonant array. By using the combination of ISRU, a liquid oxygen-liquid hydrogen engine, and beamed power, we reduce the initial mass of the lander to just 51.5 kg. When combined with an SEP module to ferry the lander to Europa the initial mission mass is just 6397 kg - low enough to be placed on an Earth escape trajectory using an Atlas V 551 launch vehicle. By comparison, we estimate a duplicate lander using an MMRTG and semi-storable propellants such as liquid oxygen-methane would result in an order of magnitude increase in initial lander mass to 445 kg. Attempting to perform the trajectory with a 450 s liquid oxygen-liquid hydrogen engine would increase initial mass to approximately 135,000 kg. Using an Atlas V 1 U.S. Dollar per kg rate to Earth escape value of $27.7k per kg, just the launch savings are over $3.5 billion.
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A lander mission to probe subglacial water on Saturn's moon Enceladus for life
NASA Astrophysics Data System (ADS)
Konstantinidis, Konstantinos; Flores Martinez, Claudio L.; Dachwald, Bernd; Ohndorf, Andreas; Dykta, Paul; Bowitz, Pascal; Rudolph, Martin; Digel, Ilya; Kowalski, Julia; Voigt, Konstantin; Förstner, Roger
2015-01-01
The plumes discovered by the Cassini mission emanating from the south pole of Saturn's moon Enceladus and the unique chemistry found in them have fueled speculations that Enceladus may harbor life. The presumed aquiferous fractures from which the plumes emanate would make a prime target in the search for extraterrestrial life and would be more easily accessible than the moon's subglacial ocean. A lander mission that is equipped with a subsurface maneuverable ice melting probe will be most suitable to assess the existence of life on Enceladus. A lander would have to land at a safe distance away from a plume source and melt its way to the inner wall of the fracture to analyze the plume subsurface liquids before potential biosignatures are degraded or destroyed by exposure to the vacuum of space. A possible approach for the in situ detection of biosignatures in such samples can be based on the hypothesis of universal evolutionary convergence, meaning that the independent and repeated emergence of life and certain adaptive traits is wide-spread throughout the cosmos. We thus present a hypothetical evolutionary trajectory leading towards the emergence of methanogenic chemoautotrophic microorganisms as the baseline for putative biological complexity on Enceladus. To detect their presence, several instruments are proposed that may be taken aboard a future subglacial melting probe. The "Enceladus Explorer" (EnEx) project funded by the German Space Administration (DLR), aims to develop a terrestrial navigation system for a subglacial research probe and eventually test it under realistic conditions in Antarctica using the EnEx-IceMole, a novel maneuverable subsurface ice melting probe for clean sampling and in situ analysis of ice and subglacial liquids. As part of the EnEx project, an initial concept study is foreseen for a lander mission to Enceladus to deploy the IceMole near one of the active water plumes on the moon's South-Polar Terrain, where it will search for signatures of life. The general mission concept is to place the Lander at a safe distance from an active plume. The IceMole would then be deployed to melt its way through the ice crust to an aquiferous fracture at a depth of 100 m or more for an in situ examination for the presence of microorganisms. The driving requirement for the mission is the high energy demand by the IceMole to melt through the cold Enceladan ices. This requirement is met by a nuclear reactor providing 5 kW of electrical power. The nuclear reactor and the IceMole are placed on a pallet lander platform. An Orbiter element is also foreseen, with the main function of acting as a communications relay between Lander and Earth. After launch, the Lander and Orbiter will perform the interplanetary transfer to Saturn together, using the on-board nuclear reactor to power electric thrusters. After Saturn orbit insertion, the Combined Spacecraft will continue using Nuclear Electric Propulsion to reach the orbit of Enceladus. After orbit insertion at Enceladus, the Orbiter will perform a detailed reconnaissance of the South-Polar Terrain. At the end of the reconnaissance phase, the Lander will separate from the Orbiter and an autonomously guided landing sequence will place it near one of the active vapor plumes. Once landed, the IceMole will be deployed and start melting through the ice, while navigating around hazards and towards a target subglacial aquiferous fracture. An initial estimation of the mission's cost is given, as well as recommendations on the further development of enabling technologies. The planetary protection challenges posed by such a mission are also addressed.
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Completion of the Viking Labeled Release experiment on Mars
NASA Technical Reports Server (NTRS)
Levin, G. V.; Straat, P. A.
1979-01-01
The final Labeled Release (LR) cycle on each Viking lander tested a surface sample that had been stored for several months at approximately 10 C prior to the onset of the active sequence. At each lander site, activity was strongly diminished. This thermal sensitivity of the active agent on the surface of Mars is consistent with a biological explanation of the LR experiment. At the end of one of these cycles, the incubation mixture was heated to 50 C to release any radioactive gas trapped in the sample matrix. The results suggest that more than one carbon substrate is involved in the LR reaction on Mars. The thermal data from the stored samples, coupled with data from previous cycles, have formed the basis for evaluation of the thermal decomposition of the Mars active agent. The slope of the resulting Arrhenius plot has been used to test the fit of other flight data and to calculate the activation energy for thermal decomposition of the Mars agent. The results and their interpretation still leave unresolved the question of whether the Mars LR data were generated by biological or chemical activity.
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Completion of the Viking labeled release experiment on Mars.
Levin, G V; Straat, P A
1979-12-01
The final Labeled Release (LR) cycle on each Viking lander tested a surface sample that had been stored for several months at approximately 10 degrees C prior to the onset of the active sequence. At each lander site, activity was strongly diminished. This thermal sensitivity of the active agent on the surface of Mars is consistent with a biological explanation of the LR experiment. At the end of one of these cycles, the incubation mixture was heated to 50 degrees C to release any radioactive gas trapped in the sample matrix. The results suggest that more than one carbon substrate is involved in the LR reaction on Mars. The thermal data from the stored samples, coupled with data from previous cycles, have formed the basis for evaluation of the thermal decomposition of the Mars active agent. The slope of the resulting Arrhenius plot has been used to test the fit of other flight data and to calculate the activation energy for thermal decomposition of the Mars agent. The results and their interpretation still leave unresolved the question of whether the Mars LR data were generated by biological or chemical activity.
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A Light-Weight Inflatable Hypersonic Drag Device for Planetary Entry
NASA Technical Reports Server (NTRS)
McRonald, Angus D.
2000-01-01
The author has analyzed the use of a light-weight inflatable hypersonic drag device, called a ballute, for flight in planetary atmospheres, for entry, aerocapture, and aerobraking. Studies to date include Mars, Venus, Earth, Saturn, Titan, Neptune and Pluto, and data on a Pluto lander and a Mars orbiter will be presented to illustrate the concept. The main advantage of using a ballute is that aero, deceleration and heating in atmospheric entry occurs at much smaller atmospheric density with a ballute than without it. For example, if a ballute has a diameter 10 times as large as the spacecraft, for unchanged total mass, entry speed and entry angle,the atmospheric density at peak convective heating is reduced by a factor of 100, reducing the heating by a factor of 10 for the spacecraft and a factor of 30 for the ballute. Consequently the entry payload (lander, orbiter, etc) is subject to much less heating, requires a much reduced thermal. protection system (possibly only an MLI blanket), and the spacecraft design is therefore relatively unchanged from its vacuum counterpart. The heat flux on the ballute is small enough to be radiated at temperatures below 800 K or so. Also, the heating may be reduced further because the ballute enters at a more shallow angle, even allowing for the increased delivery angle error. Added advantages are less mass ratio of entry system to total entry mass, and freedom from the low-density and transonic instability problems that conventional rigid entry bodies suffer, since the vehicle attitude is determined by the ballute, usually released at continuum conditions (hypersonic for an orbiter, and subsonic for a lander). Also, for a lander the range from entry to touchdown is less, offering a smaller footprint. The ballute derives an entry corridor for aerocapture by entering on a path that would lead to landing, and releasing the ballute adaptively, responding to measured deceleration, at a speed computed to achieve the desired orbiter exit conditions. For a lander an accurate landing point could be achieved by providing the lander with a small gliding capacity, using the large potential energy available from being subsonic at high altitude. Alternatively the ballute can be retained to act as a parachute or soft-landing device, or to float the payload as a buoyant aerobot. As expected, the ballute has smaller size for relatively small entry speeds, such as for Mars and Titan, or for the extensive atmosphere of a low-gravity planet such as Pluto. Details of a ballute to place a small Mars orbiter and a small Pluto lander will be given to illustrate the concept. The author will discuss presently available ballute materials and a development program of aerodynamic tests and materials that would be required for ballutes to achieve their full potential.
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Simulated Reentry Heating by Torching
NASA Technical Reports Server (NTRS)
Harvey, Gale A.
2008-01-01
The two first order reentry heating parameters are peak heating flux (W/cm2) and peak heat load (kJ/cm2). Peak heating flux (and deceleration, gs) is higher for a ballistic reentry and peak heat load is higher for a lifting reentry. Manned vehicle reentries are generally lifting reentries at nominal 1-5 gs so that personnel will not be crushed by high deceleration force. A few off-nominal manned reentries have experienced 8 or more gs with corresponding high heating flux (but below nominal heat load). The Shuttle Orbiter reentries provide about an order of magnitude difference in peak heating flux at mid-bottom (TPS tiles, approximately 6 W/cm2 or 5 BTU/ft2- sec) and leading edge (RCC, approximately 60 W/cm2 or 50 BTU/ft2- sec). Orion lunar return and Mars sample lander are of the same order of magnitude as orbiter leading edge peak heat loads. Flight temperature measurements are available for some orbiter TPS tile and RCC locations. Return-to-Flight on-orbit tile-repair-candidate-material-heating performance was evaluated by matching propane torch heating of candidate-materials temperatures at several depths to orbiter TPS tile flight-temperatures. Char and ash characteristics, heat expansion, and temperature histories at several depths of the cure-in-place ablator were some of the TPS repair material performance characteristics measured. The final char surface was above the initial surface for the primary candidate (silicone based) material, in contrast to a receded surface for the Apollo-type ablative heat shield material. Candidate TPS materials for Orion CEV (LEO and lunar return), and for Mars sample lander are now being evaluated. Torching of a candidate ablator material, PICA, was performed to match the ablation experienced by the STARDUST PICA heat shield. Torching showed that the carbon fiberform skeleton in a sample of PICA was inhomogeneous in that sample, and allowed measurements (of the clumps and voids) of the inhomogeneity. Additional reentry heating-performance characterizations of high temperature insulation materials were performed.
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Benthic long-term Observatories based on Lander Technology
NASA Astrophysics Data System (ADS)
Linke, P.; Pfannkuche, O.; Sommer, S.; Gubsch, S.; Gust, G.
2003-04-01
Landers are autonomous carrier systems for a wide range of scientific applications. The GEOMAR Lander System is based on a tripod-shaped platform for various scientific payloads to monitor, measure and experiment at the deep sea floor. These landers can be deployed using hybrid fibre optical or coaxial cables with a special launching device or in the conventional free falling mode. The launcher enables accurate positioning on meter scale, soft deployment and rapid disconnection of lander and launcher by an electric release. The bi-directional video and data telemetry provides on line video transmission, power supply and surface control of various relay functions. Within the collaborative project LOTUS novel long-term observatories have been developed and integrated into the GEOMAR Lander System. An overview of the recent developments is presented. Two new observatories are presented in detail to study the temporal variability of physico-chemical and biogeochemical mechanisms, flux- and turnover rates related to the decomposition and formation of near surface gas hydrates embedded in their original sedimentary matrix. With the Biogeochemical Observatory, BIGO, the temporal variability of the biologically facilitated methane turnover in the sediment and fluxes across the sediment water interface is studied in two mesocosms. Inside the mesocosms the oxygen content can be maintained by a chemostat. The in situ flow regime is measured outside the mesocosms and is reproduced within the chamber with an intelligent stirring system. This approach represents a major step in the development of benthic chambers from stationary to dynamic systems. The Fluid-Flux Observatory (FLUFO) measures the different types of fluid fluxes at the benthic boundary layer of sediments overlying near surface gas hydrates and monitors relevant environmental parameters as temperature, pressure and near bottom currents. FLUFO consists of two chamber units. Both units separate the gas phase from the aqueous phase and measure their individual contribution to the total fluid flux. Whereas the first (reference) chamber measures the aqueous flux without obtaining information about their direction, the second (FLUFO) chamber measures the aqueous flux including the direction discriminating between outward flow, stagnation and inward flow.
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A Dual Launch Robotic and Human Lunar Mission Architecture
NASA Technical Reports Server (NTRS)
Jones, David L.; Mulqueen, Jack; Percy, Tom; Griffin, Brand; Smitherman, David
2010-01-01
This paper describes a comprehensive lunar exploration architecture developed by Marshall Space Flight Center's Advanced Concepts Office that features a science-based surface exploration strategy and a transportation architecture that uses two launches of a heavy lift launch vehicle to deliver human and robotic mission systems to the moon. The principal advantage of the dual launch lunar mission strategy is the reduced cost and risk resulting from the development of just one launch vehicle system. The dual launch lunar mission architecture may also enhance opportunities for commercial and international partnerships by using expendable launch vehicle services for robotic missions or development of surface exploration elements. Furthermore, this architecture is particularly suited to the integration of robotic and human exploration to maximize science return. For surface operations, an innovative dual-mode rover is presented that is capable of performing robotic science exploration as well as transporting human crew conducting surface exploration. The dual-mode rover can be deployed to the lunar surface to perform precursor science activities, collect samples, scout potential crew landing sites, and meet the crew at a designated landing site. With this approach, the crew is able to evaluate the robotically collected samples to select the best samples for return to Earth to maximize the scientific value. The rovers can continue robotic exploration after the crew leaves the lunar surface. The transportation system for the dual launch mission architecture uses a lunar-orbit-rendezvous strategy. Two heavy lift launch vehicles depart from Earth within a six hour period to transport the lunar lander and crew elements separately to lunar orbit. In lunar orbit, the crew transfer vehicle docks with the lander and the crew boards the lander for descent to the surface. After the surface mission, the crew returns to the orbiting transfer vehicle for the return to the Earth. This paper describes a complete transportation architecture including the analysis of transportation element options and sensitivities including: transportation element mass to surface landed mass; lander propellant options; and mission crew size. Based on this analysis, initial design concepts for the launch vehicle, crew module and lunar lander are presented. The paper also describes how the dual launch lunar mission architecture would fit into a more general overarching human space exploration philosophy that would allow expanded application of mission transportation elements for missions beyond the Earth-moon realm.
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Cooperative Lander-Surface/Aerial Microflyer Missions for Mars Exploration
NASA Technical Reports Server (NTRS)
Thakoor, Sarita; Lay, Norman; Hine, Butler; Zornetzer, Steven
2004-01-01
Concepts are being investigated for exploratory missions to Mars based on Bioinspired Engineering of Exploration Systems (BEES), which is a guiding principle of this effort to develop biomorphic explorers. The novelty lies in the use of a robust telecom architecture for mission data return, utilizing multiple local relays (including the lander itself as a local relay and the explorers in the dual role of a local relay) to enable ranges 10 to 1,000 km and downlink of color imagery. As illustrated in Figure 1, multiple microflyers that can be both surface or aerially launched are envisioned in shepherding, metamorphic, and imaging roles. These microflyers imbibe key bio-inspired principles in their flight control, navigation, and visual search operations. Honey-bee inspired algorithms utilizing visual cues to perform autonomous navigation operations such as terrain following will be utilized. The instrument suite will consist of a panoramic imager and polarization imager specifically optimized to detect ice and water. For microflyers, particularly at small sizes, bio-inspired solutions appear to offer better alternate solutions than conventional engineered approaches. This investigation addresses a wide range of interrelated issues, including desired scientific data, sizes, rates, and communication ranges that can be accomplished in alternative mission scenarios. The mission illustrated in Figure 1 offers the most robust telecom architecture and the longest range for exploration with two landers being available as main local relays in addition to an ephemeral aerial probe local relay. The shepherding or metamorphic plane are in their dual role as local relays and image data collection/storage nodes. Appropriate placement of the landing site for the scout lander with respect to the main mission lander can allow coverage of extremely large ranges and enable exhaustive survey of the area of interest. In particular, this mission could help with the path planning and risk mitigation in the traverse of the long-distance surface explorer/rover. The basic requirements of design and operation of BEES to implement the scenarios are discussed. Terrestrial applications of such concepts include distributed aerial/surface measurements of meteorological events, i.e., storm watch, seismic monitoring, reconnaissance, biological chemical sensing, search and rescue, surveillance, autonomous security/ protection agents, and/or delivery and lateral distribution of agents (sensors, surface/subsurface crawlers, clean-up agents). Figure 2 illustrates an Earth demonstration that is in development, and its implementation will illustrate the value of these biomorphic mission concepts.