Review of NASA's Planned Mars Program

NASA Technical Reports Server (NTRS)

1996-01-01

Contents include the following: Executive Summary; Introduction; Scientific Goals for the Exploration of Mars; Overview of Mars Surveyor and Others Mars Missions; Key Issues for NASA's Mars Exploration Program; and Assessment of the Scientific Potential of NASA's Mars Exploration Program.

Mars Trek: An Interactive Web Portal for Current and Future Missions to Mars

NASA Technical Reports Server (NTRS)

Law, E.; Day, B.

2017-01-01

NASA's Mars Trek (https://marstrek.jpl.nasa.gov) provides a web-based Portal and a suite of interactive visualization and analysis tools to enable mission planners, lunar scientists, and engineers to access mapped data products from past and current missions to Mars. During the past year, the capabilities and data served by Mars Trek have been significantly expanded beyond its original design as a public outreach tool. At the request of NASA's Science Mission Directorate and Human Exploration Operations Mission Directorate, Mars Trek's technology and capabilities are now being extended to support site selection and analysis activities for the first human missions to Mars.

Mars Trek: An Interactive Web Portal for Current and Future Missions to Mars

NASA Astrophysics Data System (ADS)

Law, E.; Day, B.

2017-09-01

NASA's Mars Trek (https://marstrek.jpl.nasa.gov) provides a web-based Portal and a suite of interactive visualization and analysis tools to enable mission planners, lunar scientists, and engineers to access mapped data products from past and current missions to Mars. During the past year, the capabilities and data served by Mars Trek have been significantly expanded beyond its original design as a public outreach tool. At the request of NASA's Science Mission Directorate and Human Exploration Operations Mission Directorate, Mars Trek's technology and capabilities are now being extended to support site selection and analysis activities for the first human missions to Mars.

Phoenix--the first Mars Scout mission.

PubMed

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.

Review of NASA's Planned Mars Program

NASA Technical Reports Server (NTRS)

1996-01-01

The exploration of Mars has long been a prime scientific objective of the U.S. planetary exploration program. Yet no U.S. spacecraft has successfully made measurements at Mars since the Viking missions of the late 1970s. Mars Observer, which was designed to conduct global observations from orbit, failed just before orbit insertion in 1993. The Russian spacecraft Phobos 2 did succeed in making some observations of the planet in 1989, but it was designed primarily to observe Phobos, the innermost satellite of Mars; the spacecraft failed 2 months after insertion into Mars orbit during the complex maneuvers required to rendezvous with the martian satellite. In fall 1996 NASA plans to launch Mars Pathfinder for a landing on the martian surface in mid-1997. This spacecraft is one of the first two missions in NASA's Discovery program that inaugurates a new style of planetary exploration in which missions are low-cost (less than $150 million) and have very focused science objectives. As can be seen in the comparative data presented in Box 1, this mission is considerably smaller in terms of cost, mass, and scope than NASA's previous Mars missions. NASA's FY 1995 budget initiated a continuing Mars exploration program, called Mars Surveyor, that involves multiple launches of spacecraft as small as or smaller than Mars Pathfinder to Mars over the next several launch opportunities, which recur roughly every 26 months. The first mission in the program, Mars Global Surveyor, set for launch late in 1996, is intended to accomplish many of the objectives of the failed Mars Observer. Like the Discovery program, Mars Surveyor is a continuing series of low-cost missions, each of which has highly focused science objectives. See Box 1 for comparative details of those Surveyor missions currently defined. Around the same time that the Mars Surveyor series was chosen as the centerpiece of NASA's solar system exploration program, the Committee on Planetary and Lunar Exploration (COMPLEX

NASA's Planetary Science Missions and Participations

NASA Astrophysics Data System (ADS)

Daou, Doris; Green, James L.

2017-04-01

NASA's Planetary Science Division (PSD) and space agencies around the world are collaborating on an extensive array of missions exploring our solar system. Planetary science missions are conducted by some of the most sophisticated robots ever built. International collaboration is an essential part of what we do. NASA has always encouraged international participation on our missions both strategic (ie: Mars 2020) and competitive (ie: Discovery and New Frontiers) and other Space Agencies have reciprocated and invited NASA investigators to participate in their missions. NASA PSD has partnerships with virtually every major space agency. For example, NASA has had a long and very fruitful collaboration with ESA. ESA has been involved in the Cassini mission and, currently, NASA funded scientists are involved in the Rosetta mission (3 full instruments, part of another), BepiColombo mission (1 instrument in the Italian Space Agency's instrument suite), and the Jupiter Icy Moon Explorer mission (1 instrument and parts of two others). In concert with ESA's Mars missions NASA has an instrument on the Mars Express mission, the orbit-ground communications package on the Trace Gas Orbiter (launched in March 2016) and part of the DLR/Mars Organic Molecule Analyzer instruments going onboard the ExoMars Rover (to be launched in 2018). NASA's Planetary Science Division has continuously provided its U.S. planetary science community with opportunities to include international participation on NASA missions too. For example, NASA's Discovery and New Frontiers Programs provide U.S. scientists the opportunity to assemble international teams and design exciting, focused planetary science investigations that would deepen the knowledge of our Solar System. The PSD put out an international call for instruments on the Mars 2020 mission. This procurement led to the selection of Spain and Norway scientist leading two instruments and French scientists providing a significant portion of another

The Mars Express/NASA Project at JPL

NASA Astrophysics Data System (ADS)

Thompson, T. W.; Horttor, R. L.; Acton, C. H., Jr.; Zamani, P.; Johnson, W. T. K.; Plaut, J. J.; Holmes, D. P.; No, S.; Asmar, S.; Goltz, G.

2006-03-01

The Mars Express/NASA Project at JPL supports much of the U.S. involvement in ESA's Mars Express mission. Mars Express has just completed its prime mission in late 2005 and has embarked on its first extended mission cycle.

A Reliable Service-Oriented Architecture for NASA's Mars Exploration Rover Mission

NASA Technical Reports Server (NTRS)

Mak, Ronald; Walton, Joan; Keely, Leslie; Hehner, Dennis; Chan, Louise

2005-01-01

The Collaborative Information Portal (CIP) was enterprise software developed jointly by the NASA Ames Research Center and the Jet Propulsion Laboratory (JPL) for NASA's highly successful Mars Exploration Rover (MER) mission. Both MER and CIP have performed far beyond their original expectations. Mission managers and engineers ran CIP inside the mission control room at JPL, and the scientists ran CIP in their laboratories, homes, and offices. All the users connected securely over the Internet. Since the mission ran on Mars time, CIP displayed the current time in various Mars and Earth time zones, and it presented staffing and event schedules with Martian time scales. Users could send and receive broadcast messages, and they could view and download data and image files generated by the rovers' instruments. CIP had a three-tiered, service-oriented architecture (SOA) based on industry standards, including J2EE and web services, and it integrated commercial off-the-shelf software. A user's interactions with the graphical interface of the CIP client application generated web services requests to the CIP middleware. The middleware accessed the back-end data repositories if necessary and returned results for these requests. The client application could make multiple service requests for a single user action and then present a composition of the results. This happened transparently, and many users did not even realize that they were connecting to a server. CIP performed well and was extremely reliable; it attained better than 99% uptime during the course of the mission. In this paper, we present overviews of the MER mission and of CIP. We show how CIP helped to fulfill some of the mission needs and how people used it. We discuss the criteria for choosing its architecture, and we describe how the developers made the software so reliable. CIP's reliability did not come about by chance, but was the result of several key design decisions. We conclude with some of the important

Mars curiosity mission

NASA Image and Video Library

2012-08-04

NASA welcomed hundreds of children and accompanying adults to its INFINITY visitor center on Aug. 4, offering Mars-related activities that focused attention on the space agency's Curiosity mission to the Red Planet. Among other attractions, 3-D images from Mars provided 'Wow!' glimpses of the Red Planet. In addition to the Mars activities, visitors were able to tour other space-related exhibits at the center.

Our Newest Mission to Mars on This Week @NASA – May 5, 2018

NASA Image and Video Library

2018-05-05

Our newest mission to Mars is on its way, Vice President Pence visits our Jet Propulsion Laboratory, and observing our planet’s ever-changing water cycle – a few of the stories to tell you about – This Week at NASA!

Micro-Pressure Sensors for Future Mars Missions

NASA Technical Reports Server (NTRS)

Catling, David C.

1996-01-01

The joint research interchange effort was directed at the following principal areas: u further development of NASA-Ames' Mars Micro-meteorology mission concept as a viable NASA space mission especially with regard to the science and instrument specifications u interaction with the flight team from NASA's New Millennium 'Deep-Space 2' (DS-2) mission with regard to selection and design of micro-pressure sensors for Mars u further development of micro-pressure sensors suitable for Mars The research work undertaken in the course of the Joint Research Interchange should be placed in the context of an ongoing planetary exploration objective to characterize the climate system on Mars. In particular, a network of small probes globally-distributed on the surface of the planet has often been cited as the only way to address this particular science goal. A team from NASA Ames has proposed such a mission called the Micrometeorology mission, or 'Micro-met' for short. Surface pressure data are all that are required, in principle, to calculate the Martian atmospheric circulation, provided that simultaneous orbital measurements of the atmosphere are also obtained. Consequently, in the proposed Micro-met mission a large number of landers would measure barometric pressure at various locations around Mars, each equipped with a micro-pressure sensor. Much of the time on the JRI was therefore spent working with the engineers and scientists concerned with Micro-met to develop this particular mission concept into a more realistic proposition.

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Randy Lillard, Program Executive for Technology Demonstration Missions of NASA's Space Technology Mission DIrectorate, speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Manned Mars mission accommodation: Sprint mission

NASA Technical Reports Server (NTRS)

Cirillo, William M.; Kaszubowski, Martin J.; Ayers, J. Kirk; Llewellyn, Charles P.; Weidman, Deene J.; Meredith, Barry D.

1988-01-01

The results of a study conducted at the NASA-LaRC to assess the impacts on the Phase 2 Space Station of Accommodating a Manned Mission to Mars are documented. In addition, several candidate transportation node configurations are presented to accommodate the assembly and verification of the Mars Mission vehicles. This study includes an identification of a life science research program that would need to be completed, on-orbit, prior to mission departure and an assessment of the necessary orbital technology development and demonstration program needed to accomplish the mission. Also included is an analysis of the configuration mass properties and a preliminary analysis of the Space Station control system sizing that would be required to control the station. Results of the study indicate the Phase 2 Space Station can support a manned mission to Mars with the addition of a supporting infrastructure that includes a propellant depot, assembly hangar, and a heavy lift launch vehicle to support the large launch requirements.

Anomaly Trends for Missions to Mars: Mars Global Surveyor and Mars Odyssey

NASA Technical Reports Server (NTRS)

Green, Nelson W.; Hoffman, Alan R.

2008-01-01

Conducted as a part of NASA Ultra-Reliability effort: Goal is to design for increased reliability in all NASA missions. Desire is to increase reliability by a factor of 10. Study provides a baseline for current technology. Analyzed anomalies for spacecraft orbiting Mars. Long lived spacecraft. Comparison with current rover missions and past orbiters. Looked for trends to assist design of future missions.

The Thermal Infrared Sensor onboard NASA's Mars 2020 Mission

NASA Astrophysics Data System (ADS)

Martinez, G.; Perez-Izquierdo, J.; Sebastian, E.; Ramos, M.; Bravo, A.; Mazo, M.; Rodriguez-Manfredi, J. A.

2017-12-01

NASA's Mars 2020 rover mission is scheduled for launch in July/August 2020 and will address key questions about the potential for life on Mars. The Mars Environmental Dynamics Analyzer (MEDA) is one of the seven instruments onboard the rover [1] and has been designed to assess the environmental conditions across the rover traverse. MEDA will extend the current record of in-situ meteorological measurements at the surface [2] to other locations on Mars. The Thermal InfraRed Sensor (TIRS) [3] is one of the six sensors comprising MEDA. TIRS will use three downward-looking channels to measure (1) the surface skin temperature (with high heritage from the Rover Environmental Monitoring Station onboard the Mars Science Laboratory mission [4]), (2) the upwelling thermal infrared radiation from the surface and (3) the reflected solar radiation at the surface, and two upward-looking channels to measure the (4) downwelling thermal infrared radiation at the surface and (5) the atmospheric temperature. In combination with other MEDA's sensors, TIRS will allow the quantification of the surface energy budget [5] and the determination of key geophysical properties of the terrain such as the albedo and thermal inertia with an unprecedented spatial resolution. Here we present a general description of the TIRS, with focus on its scientific requirements and results from field campaigns showing the performance of the different channels. References:[1] Rodríguez-Manfredi, J. A. et al. (2014), MEDA: An environmental and meteorological package for Mars 2020, LPSC, 45, 2837. [2] Martínez, G.M. et al. (2017), The Modern Near-Surface Martian Climate: A Review of In-situ Meteorological Data from Viking to Curiosity, Space Science Reviews, 1-44. [3] Pérez-Izquierdo, J. et al. (2017), The Thermal Infrared Sensor (TIRS) of the Mars Environmental Dynamics Analyzer (MEDA) Instrument onboard Mars 2020, IEEE. [4] Sebastián, E. et al. (2010), The Rover Environmental Monitoring Station Ground

NASA's Mars 2020 Rover Artist's Concept #1

NASA Image and Video Library

2017-05-23

This artist's concept depicts NASA's Mars 2020 rover on the surface of Mars. The mission takes the next step by not only seeking signs of habitable conditions on Mars in the ancient past, but also searching for signs of past microbial life itself. The Mars 2020 rover introduces a drill that can collect core samples of the most promising rocks and soils and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V 541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA21635

NASA Facts, The Viking Mission.

ERIC Educational Resources Information Center

National Aeronautics and Space Administration, Washington, DC. Educational Programs Div.

Presented is one of a series of publications of National Aeronautics and Space Administration (NASA) facts about the exploration of Mars. The Viking mission to Mars, consisting of two unmanned NASA spacecraft launched in August and September, 1975, is described. A description of the spacecraft and their paths is given. A diagram identifying the…

Human Mars Missions: Cost Driven Architecture Assessments

NASA Technical Reports Server (NTRS)

Donahue, Benjamin

1998-01-01

This report investigates various methods of reducing the cost in space transportation systems for human Mars missions. The reference mission for this task is a mission currently under study at NASA. called the Mars Design Reference Mission, characterized by In-Situ propellant production at Mars. This study mainly consists of comparative evaluations to the reference mission with a view to selecting strategies that would reduce the cost of the Mars program as a whole. One of the objectives is to understand the implications of certain Mars architectures, mission modes, vehicle configurations, and potentials for vehicle reusability. The evaluations start with year 2011-2014 conjunction missions which were characterized by their abort-to-the-surface mission abort philosophy. Variations within this mission architecture, as well as outside the set to other architectures (not predicated on an abort to surface philosophy) were evaluated. Specific emphasis has been placed on identifying and assessing overall mission risk. Impacts that Mars mission vehicles might place upon the Space Station, if it were to be used as an assembly or operations base, were also discussed. Because of the short duration of this study only on a few propulsion elements were addressed (nuclear thermal, cryogenic oxygen-hydrogen, cryogenic oxygen-methane, and aerocapture). Primary ground rules and assumptions were taken from NASA material used in Marshall Space Flight Center's own assessment done in 1997.

Life sciences interests in Mars missions

NASA Technical Reports Server (NTRS)

Rummel, John D.; Griffiths, Lynn D.

1989-01-01

NASA's Space Life Sciences research permeates plans for Mars missions and the rationale for the exploration of the planet. The Space Life Sciences program has three major roles in Mars mission studies: providing enabling technology for piloted missions, conducting scientific exploration related to the origin and evolution of life, and protecting space crews from the adverse physiological effects of space flight. This paper presents a rationale for exploration and some of the issues, tradeoffs, and visions being addressed in the Space Life Sciences program in preparation for Mars missions.

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Randy Lillard, Program Executive for Technology Demonstration Missions of NASA's Space Technology Mission DIrectorate, speaks about the upcoming Low-Density Supersonic Decelerator demonstration during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Anomaly Trends for Missions to Mars: Mars Global Surveyor and Mars Odyssey

NASA Technical Reports Server (NTRS)

Green, Nelson W.; Hoffman, Alan R.

2008-01-01

The long term flight operations of the Mars Global Surveyor and Mars Odyssey spacecraft give us an excellent chance to examine the operations of two long lived spacecraft in orbit around Mars during overlapping time periods. This study examined the anomalies for each mission maintained for NASA at the Jet Propulsion Laboratory. By examining the anomalies each mission encountered during their multiyear missions, trends were identified related to when anomalies occurred during each mission, the types of anomalies encountered, and corrective actions taken to mitigate the effects of the anomalies. As has been discovered in previous studies the numbers of anomalies directly correlate with mission activity and show a decreasing trend with elapsed mission time. Trend analysis also identified a heavy emphasis on software as the source or solution to anomalies for both missions.

Comparing NASA and ESA Cost Estimating Methods for Human Missions to Mars

NASA Technical Reports Server (NTRS)

Hunt, Charles D.; vanPelt, Michel O.

2004-01-01

To compare working methodologies between the cost engineering functions in NASA Marshall Space Flight Center (MSFC) and ESA European Space Research and Technology Centre (ESTEC), as well as to set-up cost engineering capabilities for future manned Mars projects and other studies which involve similar subsystem technologies in MSFC and ESTEC, a demonstration cost estimate exercise was organized. This exercise was a direct way of enhancing not only cooperation between agencies but also both agencies commitment to credible cost analyses. Cost engineers in MSFC and ESTEC independently prepared life-cycle cost estimates for a reference human Mars project and subsequently compared the results and estimate methods in detail. As a non-sensitive, public domain reference case for human Mars projects, the Mars Direct concept was chosen. In this paper the results of the exercise are shown; the differences and similarities in estimate methodologies, philosophies, and databases between MSFC and ESTEC, as well as the estimate results for the Mars Direct concept. The most significant differences are explained and possible estimate improvements identified. In addition, the Mars Direct plan and the extensive cost breakdown structure jointly set-up by MSFC and ESTEC for this concept are presented. It was found that NASA applied estimate models mainly based on historic Apollo and Space Shuttle cost data, taking into account the changes in technology since then. ESA used models mostly based on European satellite and launcher cost data, taking into account the higher equipment and testing standards for human space flight. Most of NASA's and ESA s estimates for the Mars Direct case are comparable, but there are some important, consistent differences in the estimates for: 1) Large Structures and Thermal Control subsystems; 2) System Level Management, Engineering, Product Assurance and Assembly, Integration and Test/Verification activities; 3) Mission Control; 4) Space Agency Program Level

Nuclear Thermal Rocket/Vehicle Design Options for Future NASA Missions to the Moon and Mars

NASA Technical Reports Server (NTRS)

Borowski, Stanley K.; Corban, Robert R.; Mcguire, Melissa L.; Beke, Erik G.

1995-01-01

The nuclear thermal rocket (NTR) provides a unique propulsion capability to planners/designers of future human exploration missions to the Moon and Mars. In addition to its high specific impulse (approximately 850-1000 s) and engine thrust-to-weight ratio (approximately 3-10), the NTR can also be configured as a 'dual mode' system capable of generating electrical power for spacecraft environmental systems, communications, and enhanced stage operations (e.g., refrigeration for long-term liquid hydrogen storage). At present the Nuclear Propulsion Office (NPO) is examining a variety of mission applications for the NTR ranging from an expendable, single-burn, trans-lunar injection (TLI) stage for NASA's First Lunar Outpost (FLO) mission to all propulsive, multiburn, NTR-powered spacecraft supporting a 'split cargo-piloted sprint' Mars mission architecture. Each application results in a particular set of requirements in areas such as the number of engines and their respective thrust levels, restart capability, fuel operating temperature and lifetime, cryofluid storage, and stage size. Two solid core NTR concepts are examined -- one based on NERVA (Nuclear Engine for Rocket Vehicle Application) derivative reactor (NDR) technology, and a second concept which utilizes a ternary carbide 'twisted ribbon' fuel form developed by the Commonwealth of Independent States (CIS). The NDR and CIS concepts have an established technology database involving significant nuclear testing at or near representative operating conditions. Integrated systems and mission studies indicate that clusters of two to four 15 to 25 klbf NDR or CIS engines are sufficient for most of the lunar and Mars mission scenarios currently under consideration. This paper provides descriptions and performance characteristics for the NDR and CIS concepts, summarizes NASA's First Lunar Outpost and Mars mission scenarios, and describes characteristics for representative cargo and piloted vehicles compatible with a

NASA Mars Science Laboratory Rover

NASA Technical Reports Server (NTRS)

Olson, Tim

2017-01-01

Since August 2012, the NASA Mars Science Laboratory (MSL) rover Curiosity has been operating on the Martian surface. The primary goal of the MSL mission is to assess whether Mars ever had an environment suitable for life. MSL Science Team member Dr. Tim Olson will provide an overview of the rover's capabilities and the major findings from the mission so far. He will also share some of his experiences of what it is like to operate Curiosity's science cameras and explore Mars as part of a large team of scientists and engineers.

World First MarsLink Mission Participants Learn and Enjoy Science

ERIC Educational Resources Information Center

Barry, Dana

2005-01-01

This article describes how students learn and experience the excitement of science by actively participating in the MarsLink Space Mission, an educational component of the National Aeronautics and Space Administration's (NASA) Mars Missions. This Mission has been made possible by Space Explorers, Inc., in collaboration with NASA. In the…

The Mars Express/NASA Project at JPL

NASA Technical Reports Server (NTRS)

Thompson, T. W.; Horttor, R. L.; Acton, C. H., Jr.; Zamani, P.; Johnson, W. T. K.; Plaut, J. J.; Holmes, D. P.; No, S.; Asmar, S.; Goltz, G.

2005-01-01

ESA s Mars Express Mission involves international collaboration between the European Space Agency (ESA) and the European space agencies with the National Aeronautics and Space Administration (NASA) as a junior partner. The primary objective of this mission is to search for hydrologic resources on the surface of Mars. Mars Express was launched from Baikonur, Kazakhstan on June 2, 2003 and arrived at Mars on December 25, 2003. Orbital science observations started in January 2004.

Large Parachute for NASA Mars Science Laboratory

NASA Image and Video Library

2009-04-22

The parachute for NASA Mars Science Laboratory mission opens to a diameter of nearly 16 meters 51 feet. This image shows a duplicate qualification-test parachute inside the world's largest wind tunnel, at NASA Ames Research Center, Moffett Field, Calif. The Mars Science Laboratory will be launched in 2011 for a landing on Mars in 2012. Its parachute is the largest ever built to fly on an extraterrestrial mission. The parachute uses a configuration called disk-gap-band, with 80 suspension lines. Most of the orange and white fabric is nylon, though a small disk of heavier polyester is used near the vent in the apex of the canopy due to higher stresses there. http://photojournal.jpl.nasa.gov/catalog/PIA11994

The Mars Express/NASA Project at JPL

NASA Technical Reports Server (NTRS)

Thompson, Thomas W.; Horttor, R. L.; Acton, C. H., Jr.; Zamani, P.; Johnson, W. T. K.; Plaut, J. J.; Holmes, D. P.; No, S.; Asmar, S. W.; Goltz, G.

2005-01-01

An overview of the Mars Express/NASA Project at JPL is presented. The topics include: 1) Mars Express Mission Experiments and Investigators; 2) Mars Advanced Radar for Subsurface and Ionospheric Soundig (MARSIS) Overview; 3) MARSIS Experiment Overview; 4) Interoperability Concept; 5) Mars Express Science Operations; 6) Mars Express Schedule (2003-2007);

Modular Growth NTR Space Transportation System for Future NASA Human Lunar, NEA and Mars Exploration Missions

NASA Technical Reports Server (NTRS)

Borowski, Stanley K.; McCurdy, David R.; Packard, Thomas W.

2012-01-01

The nuclear thermal rocket (NTR) is a proven, high thrust propulsion technology that has twice the specific impulse (I(sub sp) approx.900 s) of today's best chemical rockets. During the Rover and NERVA (Nuclear Engine for Rocket Vehicle Applications) programs, twenty rocket reactors were designed, built and ground tested. These tests demonstrated: (1) a wide range of thrust; (2) high temperature carbide-based nuclear fuel; (3) sustained engine operation; (4) accumulated lifetime; and (5) restart capability - everything required for affordable human missions beyond LEO. In NASA's recent Mars Design Reference Architecture (DRA) 5.0 study, the NTR was selected as the preferred propulsion option because of its proven technology, higher performance, lower IMLEO, versatile vehicle design, and growth potential. Furthermore, the NTR requires no large technology scale-ups since the smallest engine tested during the Rover program - the 25 klb(sub f) "Pewee" engine is sufficient for human Mars missions when used in a clustered engine configuration. The "Copernicus" crewed Mars transfer vehicle developed for DRA 5.0 was an expendable design sized for fast-conjunction, long surface stay Mars missions. It therefore has significant propellant capacity allowing a reusable "1-year" round trip human mission to a large, high energy near Earth asteroid (NEA) like Apophis in 2028. Using a "split mission" approach, Copernicus and its two key elements - a common propulsion stage and integrated "saddle truss" and LH2 drop tank assembly - configured as an Earth Return Vehicle / propellant tanker, can also support a short round trip (approx.18 month) / short orbital stay (60 days) Mars reconnaissance mission in the early 2030's before a landing is attempted. The same short stay orbital mission can be performed with an "all-up" vehicle by adding an "in-line" LH2 tank to Copernicus to supply the extra propellant needed for this higher energy, opposition-class mission. To transition to a

Middleware and Web Services for the Collaborative Information Portal of NASA's Mars Exploration Rovers Mission

NASA Technical Reports Server (NTRS)

Sinderson, Elias; Magapu, Vish; Mak, Ronald

2004-01-01

We describe the design and deployment of the middleware for the Collaborative Information Portal (CIP), a mission critical J2EE application developed for NASA's 2003 Mars Exploration Rover mission. CIP enabled mission personnel to access data and images sent back from Mars, staff and event schedules, broadcast messages and clocks displaying various Earth and Mars time zones. We developed the CIP middleware in less than two years time usins cutting-edge technologies, including EJBs, servlets, JDBC, JNDI and JMS. The middleware was designed as a collection of independent, hot-deployable web services, providing secure access to back end file systems and databases. Throughout the middleware we enabled crosscutting capabilities such as runtime service configuration, security, logging and remote monitoring. This paper presents our approach to mitigating the challenges we faced, concluding with a review of the lessons we learned from this project and noting what we'd do differently and why.

Mars Sample Return: Mars Ascent Vehicle Mission and Technology Requirements

NASA Technical Reports Server (NTRS)

Bowles, Jeffrey V.; Huynh, Loc C.; Hawke, Veronica M.; Jiang, Xun J.

2013-01-01

A Mars Sample Return mission is the highest priority science mission for the next decade recommended by the recent Decadal Survey of Planetary Science, the key community input process that guides NASAs science missions. A feasibility study was conducted of a potentially simple and low cost approach to Mars Sample Return mission enabled by the use of developing commercial capabilities. Previous studies of MSR have shown that landing an all up sample return mission with a high mass capacity lander is a cost effective approach. The approach proposed is the use of an emerging commercially available capsule to land the launch vehicle system that would return samples to Earth. This paper describes the mission and technology requirements impact on the launch vehicle system design, referred to as the Mars Ascent Vehicle (MAV).

Mars Sample Return: Mars Ascent Vehicle Mission and Technology Requirements

NASA Technical Reports Server (NTRS)

Bowles, Jeffrey V.; Huynh, Loc C.; Hawke, Veronica M.

2013-01-01

A Mars Sample Return mission is the highest priority science mission for the next decade recommended by the recent Decadal Survey of Planetary Science, the key community input process that guides NASA's science missions. A feasibility study was conducted of a potentially simple and low cost approach to Mars Sample Return mission enabled by the use of new commercial capabilities. Previous studies of MSR have shown that landing an all up sample return mission with a high mass capacity lander is a cost effective approach. The approach proposed is the use of a SpaceX Dragon capsule to land the launch vehicle system that would return samples to Earth. This paper describes the mission and technology requirements impact on the launch vehicle system design, referred to as the Mars Ascent Vehicle (MAV).

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

John Grunsfeld, NASA Associate Administrator for the Science Mission Directorate, speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Computer-Design Drawing for NASA 2020 Mars Rover

NASA Image and Video Library

2016-07-15

NASA's 2020 Mars rover mission will go to a region of Mars thought to have offered favorable conditions long ago for microbial life, and the rover will search for signs of past life there. It will also collect and cache samples for potential return to Earth, for many types of laboratory analysis. As a pioneering step toward how humans on Mars will use the Red Planet's natural resources, the rover will extract oxygen from the Martian atmosphere. This 2016 image comes from computer-assisted-design work on the 2020 rover. The design leverages many successful features of NASA's Curiosity rover, which landed on Mars in 2012, but it adds new science instruments and a sampling system to carry out the new goals for the mission. http://photojournal.jpl.nasa.gov/catalog/PIA20759

NASA's Mars 2020 Rover Artist's Concept #2

NASA Image and Video Library

2017-11-17

This artist's rendition depicts NASA's Mars 2020 rover studying a Mars rock outrcrop. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22105

NASA's Mars 2020 Rover Artist's Concept #4

NASA Image and Video Library

2017-11-17

This artist's concept depicts NASA's Mars 2020 rover exploring Mars. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22107

NASA's Space Launch System (SLS) Program: Mars Program Utilization

NASA Technical Reports Server (NTRS)

May, Todd A.; Creech, Stephen D.

2012-01-01

NASA's Space Launch System is being designed for safe, affordable, and sustainable human and scientific exploration missions beyond Earth's orbit (BEO), as directed by the NASA Authorization Act of 2010 and NASA's 2011 Strategic Plan. This paper describes how the SLS can dramatically change the Mars program's science and human exploration capabilities and objectives. Specifically, through its high-velocity change (delta V) and payload capabilities, SLS enables Mars science missions of unprecedented size and scope. By providing direct trajectories to Mars, SLS eliminates the need for complicated gravity-assist missions around other bodies in the solar system, reducing mission time, complexity, and cost. SLS's large payload capacity also allows for larger, more capable spacecraft or landers with more instruments, which can eliminate the need for complex packaging or "folding" mechanisms. By offering this capability, SLS can enable more science to be done more quickly than would be possible through other delivery mechanisms using longer mission times.

Mars Surface Mission Workshop

NASA Technical Reports Server (NTRS)

Duke, M. B. (Editor)

1997-01-01

A workshop was held at the Lunar and Planetary Institute on September 4-5, 1997, to address the surface elements of the Mars Reference Mission now being reviewed by NASA. The workshop considered the current reference mission and addressed the types of activities that would be expected for science and resource exploration and facilities operations. A set of activities was defined that can be used to construct "vignettes" of the surface mission. These vignettes can form the basis for describing the importance of the surface mission, for illustrating aspects of the surface mission, and for allowing others to extend and revise these initial ideas. The topic is rich with opportunities for additional conceptualization. It is recommended that NASA consider supporting university design teams to conduct further analysis of the possibilities.

NASA's Mars 2020 Rover Artist's Concept #7

NASA Image and Video Library

2017-11-17

NASA's Mars 2020 rover looks at the horizon in this artist's concept. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22110

NASA's Mars 2020 Rover Artist's Concept #6

NASA Image and Video Library

2017-11-17

This artist's rendition depicts NASA's Mars 2020 rover studying its surroundings. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22109

Planetary protection requirements for orbiter and netlander elements of the CNES/NASA Mars sample return mission

NASA Astrophysics Data System (ADS)

Debus, A.

In the framework of Mars exploration, particularly for missions dedicated to the search for life or for traces of ancient forms of life, NASA and CNES have decided to join their efforts in order to build a Mars sample return mission. Taking into account article IX of the OUTER SPACE TREATY (Treaty on principles governing the activities of states in the exploration and use of outer space, including the Moon and other celestial, referenced 610 UNTS 205 - resolution 2222(XXI) of December 1966, ratified in London / Washington January 27, 1967) and in order to comply with the COSPAR planetary protection recommendations, a common planetary protection program has to be established. Mars in-situ experimentations are limited by the size and the mass of the instruments necessary to perform exobiology investigations and, consequently, it appears that the best way to conduct such experiments is to bring back Mars samples to Earth. A sample return mission enables the use of a very large number of instruments and analysis protocols, giving exobiologists the best chance to find living entities or organic compounds related to life. Such a mission is complicated from a planetary protection point of view, it combines constraints for the protection of both the Mars environment as well as Earth, including the preservation of samples to ensure the validity of exobiological experiments.

Technology Needs for the Next Generation of NASA Science Missions

NASA Technical Reports Server (NTRS)

Anderson, David J.

2013-01-01

In-Space propulsion technologies relevant to Mars presentation is for the 14.03 Emerging Technologies for Mars Exploration panel. The talk will address propulsion technology needs for future Mars science missions, and will address electric propulsion, Earth entry vehicles, light weight propellant tanks, and the Mars ascent vehicle. The second panel presentation is Technology Needs for the Next Generation of NASA Science Missions. This talk is for 14.02 Technology Needs for the Next Generation of NASA Science Missions panel. The talk will summarize the technology needs identified in the NAC's Planetary Science Decadal Survey, and will set the stage for the talks for the 4 other panelist.

NASA's Mars 2020 Rover Artist's Concept #5

NASA Image and Video Library

2017-11-17

This artist's concept shows a close-up of NASA's Mars 2020 rover studying an outcrop. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22108

NASA's Mars 2020 Rover Artist's Concept #3

NASA Image and Video Library

2017-11-17

This artist's rendition depicts NASA's Mars 2020 rover studying rocks with its robotic arm. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22106

NASA's Mars 2020 Rover Artist's Concept #1 (Updated)

NASA Image and Video Library

2017-11-17

This artist's concept depicts NASA's Mars 2020 rover exploring Mars. The mission will not only seek out and study an area likely to have been habitable in the distant past, but it will take the next, bold step in robotic exploration of the Red Planet by seeking signs of past microbial life itself. Mars 2020 will use powerful instruments to investigate rocks on Mars down to the microscopic scale of variations in texture and composition. It will also acquire and store samples of the most promising rocks and soils that it encounters, and set them aside on the surface of Mars. A future mission could potentially return these samples to Earth. Mars 2020 is targeted for launch in July/August 2020 aboard an Atlas V-541 rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. https://photojournal.jpl.nasa.gov/catalog/PIA22111

The Panoramic Camera (Pancam) Investigation on the NASA 2003 Mars Exploration Rover Mission

NASA Technical Reports Server (NTRS)

Bell, J. F., III; Squyres, S. W.; Herkenhoff, K. E.; Maki, J.; Schwochert, M.; Dingizian, A.; Brown, D.; Morris, R. V.; Arneson, H. M.; Johnson, M. J.

2003-01-01

The Panoramic Camera System (Pancam) is part of the Athena science payload to be launched to Mars in 2003 on NASA's twin Mars Exploration Rover (MER) missions. The Pancam imaging system on each rover consists of two major components: a pair of digital CCD cameras, and the Pancam Mast Assembly (PMA), which provides the azimuth and elevation actuation for the cameras as well as a 1.5 meter high vantage point from which to image. Pancam is a multispectral, stereoscopic, panoramic imaging system, with a field of regard provided by the PMA that extends across 360 of azimuth and from zenith to nadir, providing a complete view of the scene around the rover.

Medical System Concept of Operations for Mars Exploration Missions

NASA Technical Reports Server (NTRS)

Urbina, Michelle; Rubin, D.; Hailey, M.; Reyes, D.; Antonsen, Eric

2017-01-01

Future exploration missions will be the first time humanity travels beyond Low Earth Orbit (LEO) since the Apollo program, taking us to cis-lunar space, interplanetary space, and Mars. These long-duration missions will cover vast distances, severely constraining opportunities for emergency evacuation to Earth and cargo resupply opportunities. Communication delays and blackouts between the crew and Mission Control will eliminate reliable, real-time telemedicine consultations. As a result, compared to current LEO operations onboard the International Space Station, exploration mission medical care requires an integrated medical system that provides additional in-situ capabilities and a significant increase in crew autonomy. The Medical System Concept of Operations for Mars Exploration Missions illustrates how a future NASA Mars program could ensure appropriate medical care for the crew of this highly autonomous mission. This Concept of Operations document, when complete, will document all mission phases through a series of mission use case scenarios that illustrate required medical capabilities, enabling the NASA Human Research Program (HRP) Exploration Medical Capability (ExMC) Element to plan, design, and prototype an integrated medical system to support human exploration to Mars.

MARS Mission research center

NASA Technical Reports Server (NTRS)

1991-01-01

The Mars Mission Research Center (M2RC) is one of nine University Space Engineering Research Centers established by NASA in June 1988. It is a cooperative effort between NCSU and A&T in Greensboro. The goal of the Center is to focus on research and educational technologies for planetary exploration with particular emphasis on Mars. The research combines Mission Analysis and Design, Hypersonic Aerodynamics and Propulsion, Structures and Controls, Composite Materials, and Fabrication Methods in a cross-disciplined program directed towards the development of space transportation systems for lunar and planetary travel. The activities of the students and faculty in the M2RC for the period 1 Jul. 1990 to 30 Jun. 1991 are described.

Dust Storm Impacts on Human Mars Mission Equipment and Operations

NASA Astrophysics Data System (ADS)

Rucker, M. A.

2017-06-01

NASA has accumulated a wealth of experience between the Apollo program and robotic Mars rover programs, but key differences between those missions and a human Mars mission that will require unique approaches to mitigate potential dust storm concerns.

A preliminary study of Mars rover/sample return missions

NASA Technical Reports Server (NTRS)

1987-01-01

The Solar System Exploration Committee (SSEC) of the NASA Advisory Council recommends that a Mars Sample Return mission be undertaken before the year 2000. Comprehensive studies of a Mars Sample Return mission have been ongoing since 1984. The initial focus of these studies was an integrated mission concept with the surface rover and sample return vehicle elements delivered to Mars on a single launch and landed together. This approach, to be carried out as a unilateral U.S. initiative, is still a high priority goal in an Augmented Program of exploration, as the SSEC recommendation clearly states. With this background of a well-understood mission concept, NASA decided to focus its 1986 study effort on a potential opportunity not previously examined; namely, a Mars Rover/Sample Return (MRSR) mission which would involve a significant aspect of international cooperation. As envisioned, responsibility for the various mission operations and hardware elements would be divided in a logical manner with clearly defined and acceptable interfaces. The U.S. and its international partner would carry out separately launched but coordinated missions with the overall goal of accomplishing in situ science and returning several kilograms of surface samples from Mars. Important considerations for implementation of such a plan are minimum technology transfer, maximum sharing of scientific results, and independent credibility of each mission role. Under the guidance and oversight of a Mars Exploration Strategy Advisory Group organized by NASA, a study team was formed in the fall of 1986 to develop a preliminary definition of a flight-separable, cooperative mission. The selected concept assumes that the U.S. would undertake the rover mission with its sample collection operations and our international partner would return the samples to Earth. Although the inverse of these roles is also possible, this study report focuses on the rover functions of MRSR because rover operations have not

NASA Ames Celebrates Curiosity Rover's Landing on Mars (Reporter Package)

NASA Image and Video Library

2012-08-08

Nearly 7,000 people came to NASA Ames Research Center, Moffett Field, Calif., to watch the Mars Science Laboratory rover Curiosity land on Mars. A full day's worth of activities and discussions with local Mars experts informed attendees about the contributions NASA Ames made to the mission. The highlight of the event was the live NASA TV broadcast of MSL's entry, descent and landing on the Martian surface.

Mars exploration advances: Missions to Mars - Mars base

NASA Technical Reports Server (NTRS)

Dejarnette, Fred R.; Mckay, Christopher P.

1992-01-01

An overview is presented of Mars missions and related planning with attention given to four mission architectures in the light of significant limitations. Planned unpiloted missions are discussed including the Mars Orbital Mapping Mission, the Mars Rover Sample Return, the Mars Aeronomy Orbiter, and the Mars Environmental Survey. General features relevant to the missions are mentioned including launch opportunities, manned-mission phases, and propulsion options. The four mission architectures are set forth and are made up of: (1) the Mars-exploration infrastructures; (2) science emphasis for the moon and Mars; (3) the moon to stay and Mars exploration; and (4) space resource utilization. The possibility of robotic missions to the moon and Mars is touched upon and are concluded to be possible by the end of the century. The ramifications of a Mars base are discussed with specific reference to habitability and base activities, and the human missions are shown to require a heavy-lift launcher and either chemical/aerobrake or nuclear-thermal propulsion system.

Operationalizing the 21st Century Learning Skills Framework for the NASA Mission to Mars Program

NASA Astrophysics Data System (ADS)

Smith, Burgess; Research, MSI; Evaluation Team; Interactive Videoconferences Teamlt/p>, MSI

2013-06-01

Internal evaluators working with the NASA Mission to Mars program, an out-of-school collaborative videoconferencing program at the Museum of Science and Industry Chicago (MSI), developed an observation protocol to collect evidence about the collaborative learning opportunities offered by the program’s unique technology. Details about the protocol’s development are discussed, along with results of the pilot observations of the program.

Robotic missions to Mars - Paving the way for humans

NASA Technical Reports Server (NTRS)

Pivirotto, D. S.; Bourke, R. D.; Cunningham, G. E.; Golombek, M. P.; Sturms, F. M.; Kahl, R. C.; Lance, N.; Martin, J. S.

1990-01-01

NASA is in the planning stages of a program leading to the human exploration of Mars. A critical element in that program is a set of robotic missions that will acquire information on the Martian environment and test critical functions (such as aerobraking) at the planet. This paper presents some history of Mars missions, as well as results of recent studies of the Mars robotic missions that are under consideration as part of the exploration program. These missions include: (1) global synoptic geochemical and climatological characterization from orbit (Mars Observer), (2) global network of small meteorological and seismic stations, (3) sample returns, (4) reconnaissance orbiters and (5) rovers.

Manned Mars Mission program concepts

NASA Technical Reports Server (NTRS)

Hamilton, E. C.; Johnson, P.; Pearson, J.; Tucker, W.

1988-01-01

This paper describes the SRS Manned Mars Mission and Program Analysis study designed to support a manned expedition to Mars contemplated by NASA for the purposes of initiating human exploration and eventual habitation of this planet. The capabilities of the interactive software package being presently developed by the SRS for the mission/program analysis are described, and it is shown that the interactive package can be used to investigate the impact of various mission concepts on the sensitivity of mass required in LEO, schedules, relative costs, and risk. The results, to date, indicate the need for an earth-to-orbit transportation system much larger than the present STS, reliable long-life support systems, and either advanced propulsion or aerobraking technology.

Reducing the Risk of Human Missions to Mars Through Testing

NASA Astrophysics Data System (ADS)

Drake, Bret G.

2007-07-01

The NASA Deputy Administrator charted an internal NASA planning group to develop the rationale for exploration beyond low-Earth orbit. This team, termed the Exploration Blueprint, performed architecture analyses to develop roadmaps for how to accomplish the first steps beyond Low-Earth Orbit through the human exploration of Mars. Following the results of the Exploration Blueprint study, the NASA Administrator asked for a recommendation on the next steps in human and robotic exploration. Much of the focus during this period was on integrating the results from the previous studies into more concrete implementation strategies in order to understand the relationship between NASA programs, timing, and resulting budgetary implications. This resulted in an integrated approach including lunar surface operations to retire risk of human Mars missions, maximum use of common and modular systems including what was termed the exploration transfer vehicle, Earth orbit and lunar surface demonstrations of long-life systems, collaboration of human and robotic missions to vastly increase mission return, and high-efficiency transportation systems (nuclear) for deep-space transportation and power. The data provided in this summary presentation was developed to begin to address one of the key elements of the emerging implementation strategy, namely how lunar missions help retire risk of human missions to Mars. During this process the scope of the activity broadened into the issue of how testing in general, in various venues including the moon, can help reduce the risk for Mars missions.

Arm and Mast of NASA Mars Rover Curiosity

NASA Image and Video Library

2011-04-06

The arm and the remote sensing mast of the Mars rover Curiosity each carry science instruments and other tools for NASA Mars Science Laboratory mission. This image shows the arm on the left and the mast just right of center.

Planetary protection and Mars: requirements and constraints on the 2016 and 2018 missions, and beyond

NASA Astrophysics Data System (ADS)

Rummel, J.; Kminek, G.; Conley, C.

2011-10-01

The suite of missions being planned currently by NASA and ESA as a partnership under the name "ExoMars" include an orbiter and an entry, descent, and landing demonstrator module (EDM) for the 2016 "ExoMars Trace Gas Orbiter" mission (ExoMars TGO), as well as a highly capable rover to be launched in 2018 to address the original ExoMars objectives (including the Pasteur payload). This 2018 ExoMars rover is expected to begin a series of missions leading to the first sample return mission from Mars, also conducted jointly between NASA, ESA, and their partners (JMSR). Each of these missions and mission components has a role in enabling future Mars exploration, including the search for life or life-related compounds on Mars, and each of them has the potential to carry confounding biological and organic materials into sensitive environments on Mars. Accordingly, this suite of missions will be subjected to joint planetary protection requirements applied by both ESA and NASA to their respective components, according to the COSPAR-delineated planetary protection policy to protect Mars from contamination, and eventually to provide for the protection of the Earth from potential life returned in a martian sample. This paper will discuss the challenges ahead for mission designers and the mission science teams, and will outline some of the potential pitfalls involved with different mission options.

Instrumentation and Methodology Development for Mars Mission

NASA Technical Reports Server (NTRS)

Chen, Yuan-Liang Albert

2002-01-01

The Mars environment comprises a dry, cold and low air pressure atmosphere with low gravity (0.38g) and high resistivity soil. The global dust storms that cover a large portion of Mars were observed often from Earth. This environment provides an idea condition for triboelectric charging. The extremely dry conditions on the Martian surface have raised concerns that electrostatic charge buildup will not be dissipated easily. If triboelectrically generated charge cannot be dissipated or avoided, then dust will accumulate on charged surfaces and electrostatic discharge may cause hazards for future exploration missions. The low surface temperature on Mars helps to prolong the charge decay on the dust particles and soil. To better understand the physics of Martian charged dust particles is essential to future Mars missions. We research and design two sensors, velocity/charge sensor and PZT momentum sensors, to detect the velocity distribution, charge distribution and mass distribution of Martian charged dust particles. These sensors are fabricated at NASA Kenney Space Center, Electromagnetic Physics Testbed. The sensors will be tested and calibrated for simulated Mars atmosphere condition with JSC MARS-1 Martian Regolith simulant in this NASA laboratory.

Can We Power Future Mars Missions?

NASA Technical Reports Server (NTRS)

Balint, Tibor S.; Sturm, Erick J., II; Woolley, Ryan C.; Jordan, James F.

2006-01-01

The Vision for Space Exploration identified the exploration of Mars as one of the key pathways. In response, NASAs Mars Program Office is developing a detailed mission lineup for the next decade that would lead to future explorations. Mission architectures for the next decade include both orbiters and landers. Existing power technologies, which could include solar panels, batteries, radioisotope power systems, and in the future fission power, could support these missions. Second and third decade explorations could target human precursor and human in-situ missions, building on increasingly complex architectures. Some of these could use potential feed forward from earlier Constellation missions to the Moon, discussed in the ESAS study. From a potential Mars Sample Return mission to human missions the complexity of the architectures increases, and with it the delivered mass and power requirements also amplify. The delivered mass at Mars mostly depends on the launch vehicle, while the landed mass might be further limited by EDL technologies, including the aeroshell, parachutes, landing platform, and pinpoint landing. The resulting in-situ mass could be further divided into payload elements and suitable supporting power systems. These power systems can range from tens of watts to multi-kilowatts, influenced by mission type, mission configuration, landing location, mission duration, and season. Regardless, the power system design should match the power needs of these surface assets within a given architecture. Consequently, in this paper we will identify potential needs and bounds of delivered mass and architecture dependent power requirements to surface assets that would enable future in-situ exploration of Mars.

The ExoMars 2016 Mission arriving at Mars

NASA Astrophysics Data System (ADS)

Svedhem, H.; Vago, J. L.

2016-12-01

The ExoMars 2016 mission was launched on a Proton rocket from Baikonur, Kazakhstan, on 14 March 2016 and is scheduled to arrive at Mars on 19 October 2016. ExoMars is a joint programme of the European Space Agency (ESA) and Roscosmos, Russia. It consists of the ExoMars 2016 mission with the Trace Gas Orbiter, TGO, and the Entry Descent and Landing Demonstrator, EDM, named Schiaparelli, and the ExoMars 2020 mission, which carries a lander and a rover. The TGO scientific payload consists of four instruments. These are: ACS and NOMAD, both infrared spectrometers for atmospheric measurements in solar occultation mode and in nadir mode, CASSIS, a multichannel camera with stereo imaging capability, and FREND, an epithermal neutron detector to search for subsurface hydrogen (as proxy for water ice and hydrated minerals). The mass of the TGO is 3700 kg, including fuel. The EDM, with a mass of 600 kg, is mounted on top of the TGO as seen in its launch configuration. The EDM is carried to Mars by the TGO and is separated three days before arrival at Mars. In addition to demonstrating the landing capability two scientific investigations are included with the EDM. The AMELIA investigation aims at characterising the Martian atmosphere during the entry and descent using technical and engineering sensors of the EDM, and the DREAMS suite of sensors that will characterise the environment of the landing site for a few days after the landing. ESA provides the TGO spacecraft and the Schiaparelli Lander demonstrator, ESA member states provide two of the TGO instruments and Roscosmos provides the launcher and the other two TGO instruments. After the arrival of the ExoMars 2020 mission at the surface of Mars, the TGO will handle all communications between the Earth and the Rover. The communication between TGO and the rover/lander is done through a UHF communications system, a contribution from NASA. This presentation will cover a description of the 2016 mission, including the spacecraft

A concept for NASA's Mars 2016 astrobiology field laboratory.

PubMed

Beegle, Luther W; Wilson, Michael G; Abilleira, Fernando; Jordan, James F; Wilson, Gregory R

2007-08-01

The Mars Program Plan includes an integrated and coordinated set of future candidate missions and investigations that meet fundamental science objectives of NASA and the Mars Exploration Program (MEP). At the time this paper was written, these possible future missions are planned in a manner consistent with a projected budget profile for the Mars Program in the next decade (2007-2016). As with all future missions, the funding profile depends on a number of factors that include the exact cost of each mission as well as potential changes to the overall NASA budget. In the current version of the Mars Program Plan, the Astrobiology Field Laboratory (AFL) exists as a candidate project to determine whether there were (or are) habitable zones and life, and how the development of these zones may be related to the overall evolution of the planet. The AFL concept is a surface exploration mission equipped with a major in situ laboratory capable of making significant advancements toward the Mars Program's life-related scientific goals and the overarching Vision for Space Exploration. We have developed several concepts for the AFL that fit within known budget and engineering constraints projected for the 2016 and 2018 Mars mission launch opportunities. The AFL mission architecture proposed here assumes maximum heritage from the 2009 Mars Science Laboratory (MSL). Candidate payload elements for this concept were identified from a set of recommendations put forth by the Astrobiology Field Laboratory Science Steering Group (AFL SSG) in 2004, for the express purpose of identifying overall rover mass and power requirements for such a mission. The conceptual payload includes a Precision Sample Handling and Processing System that would replace and augment the functionality and capabilities provided by the Sample Acquisition Sample Processing and Handling system that is currently part of the 2009 MSL platform.

Journey to Mars Update on This Week @NASA – September 30, 2016

NASA Image and Video Library

2016-09-30

NASA Administrator Charlie Bolden joined other leaders of the world’s space agencies to discuss the latest technological breakthroughs and developments in space exploration at the 67th International Astronautical Congress, Sept. 26-30th in Guadalajara, Mexico. At the event, NASA discussed new elements to its multi-phase Journey to Mars to extend the human footprint all the way to the Red Planet. NASA will continue operations aboard the International Space Station through 2024. Work currently underway aboard the station to encourage commercial development of low-Earth orbit, develop deep space systems, life support and human health is part of the Earth Reliant phase of the Journey to Mars. In the 2020s, during the Proving Ground phase when NASA steps out farther, the agency now plans to send an astronaut crew on a yearlong mission to a deep space destination near the moon. They will conduct activities to verify habitation and test our readiness for Mars. A round-trip robotic Mars sample return mission is being targeted for the 2020s, as part of the Earth Independent phase before finally sending humans on a mission to orbit Mars in the early 2030s. Also, Zurbuchen Named Head of NASA Science, Hubble Spots Possible Water Plumes on Europa, Rosetta’s Mission Ends, and Armstrong Celebrates 70 Years of Flight Research!

Landing Area Narrowed for 2016 InSight Mission to Mars

NASA Image and Video Library

2013-09-04

The process of selecting a site for NASA's next landing on Mars, planned for September 2016, has narrowed to four semifinalist sites located close together in the Elysium Planitia region of Mars. The mission known by the acronym InSight will study the Red Planet's interior, rather than surface features, to advance understanding of the processes that formed and shaped the rocky planets of the inner solar system, including Earth. The location of the cluster of semifinalist landing sites for InSight is indicated on this near-global topographic map of Mars, which also indicates landing sites of current and past NASA missions to the surface of Mars. The mission's full name is Interior Exploration Using Seismic Investigations, Geodesy and Heat Transport. The location of Elysium Planitia close to the Martian equator meets an engineering requirement for the stationary InSight lander to receive adequate solar irradiation year-round on its photovoltaic array. The location also meets an engineering constraint for low elevation, optimizing the amount of atmosphere the spacecraft can use for deceleration during its descent to the surface. The number of candidate landing sites for InSight was trimmed from 22 down to four in August 2013. This down-selection facilitates focusing the efforts to further evaluate the four sites. Cameras on NASA's Mars Reconnaissance Orbiter will be used to gather more information about them before the final selection. The topographic map uses data from the Mars Orbiter Laser Altimeter on NASA's Mars Global Surveyor spacecraft. The color coding on this map indicates elevation relative to a reference datum, since Mars has no "sea level." The lowest elevations are presented as dark blue; the highest as white. The difference between green and orange in the color coding is about 2.5 miles (4 kilometers) vertically. Note: After thorough examination, NASA managers have decided to suspend the planned March 2016 launch of the Interior Exploration using

Mars Sample Return: Do Australians trust NASA?

NASA Astrophysics Data System (ADS)

Joyce, S.; Tomkins, C. S.; Weinstein, P.

2008-09-01

Mars Sample Return (MSR) represents an important scientific goal in space exploration. Any sample return mission will be extremely challenging from a scientific, economic and technical standpoint. But equally testing, will be communicating with a public that may have a very different perception of the mission. A MSR mission will generate international publicity and it is vital that NASA acknowledge the nature and extent of public concern about the mission risks and, perhaps equally importantly, the public’s confidence in NASA’s ability to prepare for and manage these risks. This study investigated the level of trust in NASA in an Australian population sample, and whether this trust was dependent on demographic variables. Participants completed an online survey that explored their attitudes towards NASA and a MSR mission. The results suggested that people believe NASA will complete the mission successfully but have doubts as to whether NASA will be honest when communicating with the public. The most significant finding to emerge from this study was that confidence in NASA was significantly (p < 0.05) related to the respondent’s level of knowledge regarding the risks and benefits of MSR. These results have important implications for risk management and communication.

NASA/Haughton-Mars Project 2006 Lunar Medical Contingency Simulation

NASA Technical Reports Server (NTRS)

Scheuring, Richard A.; Jones, J. A.; Lee, P.; Comtois, J. M.; Chappell, S.; Rafiq, A.; Braham, S.

2007-01-01

A viewgraph presentation describing NASA's Haughton-Mars Project (HMP) medical requirements and lunar surface operations is shown. The topics onclude: 1) Mission Purpose/ Overview; 2) HMP as a Moon/Mars Analog; 3) Simulation objectives; 4) Discussion; and 5) Forward work.

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Sam Scimemi, Director of NASA's International Space Station Division, left, Phil McAlister, Director of NASA's Commercial Spaceflight Division, second from left, Dan Dumbacher, Deputy Associate Administrator of NASA's Exploration Systems Development, center, Michele Gates, Senior Technical Advisor of NASA's Human Exploration and Operations Mission Directorate, second from right, and Jason Crusan, Director of NASA's Advanced Exploration Systems Division, right, sit on a panel during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

A Phobos-Deimos Mission as an Element of the NASA Mars Design Reference Architecture 5.0

NASA Technical Reports Server (NTRS)

Hoffman, Stephen J.

2011-01-01

NASA has conducted a series of mission studies over the past 25 years examining the eventual exploration of the surface of Mars by humans. The latest version of this evolutionary series of design reference missions/architectures - Design Reference Architecture 5 or DRA-5 - was completed in 2007. This paper examines the implications of including a human mission to explore the moons of Mars and teleoperate robots in various locations, but not to land the human crews on Mars, as an element of this reference architecture. Such a mission has been proposed several times during this same 25 year evolution leading up to the completion of DRA-5 primarily as a mission of testing the in-space vehicles and operations while surface vehicles and landers are under development. But such a precursor or test mission has never been explicitly included as an element of this Architecture. This paper will first summarize the key features of the DRA-5 to provide context for the remainder of the assessment. This will include a description of the in-space vehicles that would be the subject of a shakedown test during the Mars orbital mission. A decision tree will be used to illustrate the factors that will be analyzed, and the sequence in which they will be addressed, for this assessment. The factors that will be analyzed include the type of interplanetary transfer orbit (opposition class versus conjunction class), the type of parking orbit (circular versus elliptical), and the type of propulsion technology (high thrust chemical versus nuclear thermal rocket). The manner in which each of these factors impacts an individual mission will be described. In addition to the direct impact of these factors, additional considerations impacting crew health and overall programmatic outcomes will be discussed. Numerical results for each of the factors in the decision tree will be grouped with derived qualitative impacts from crew health and programmatic consideration. These quantitative and qualitative

Telecommunications Relay Support of the Mars Phoenix Lander Mission

NASA Technical Reports Server (NTRS)

Edwards, Charles D., Jr.; Erickson, James K.; Gladden, Roy E.; Guinn, Joseph R.; Ilott, Peter A.; Jai, Benhan; Johnston, Martin D.; Kornfeld, Richard P.; Martin-Mur, Tomas J.; McSmith, Gaylon W.;

Future Opportunities for Dynamic Power Systems for NASA Missions

NASA Technical Reports Server (NTRS)

Shaltens, Richard K.

2007-01-01

Dynamic power systems have the potential to be used in Radioisotope Power Systems (RPS) and Fission Surface Power Systems (FSPS) to provide high efficiency, reliable and long life power generation for future NASA applications and missions. Dynamic power systems have been developed by NASA over the decades, but none have ever operated in space. Advanced Stirling convertors are currently being developed at the NASA Glenn Research Center. These systems have demonstrated high efficiencies to enable high system specific power (>8 W(sub e)/kg) for 100 W(sub e) class Advanced Stirling Radioisotope Generators (ASRG). The ASRG could enable significant extended and expanded operation on the Mars surface and on long-life deep space missions. In addition, advanced high power Stirling convertors (>150 W(sub e)/kg), for use with surface fission power systems, could provide power ranging from 30 to 50 kWe, and would be enabling for both lunar and Mars exploration. This paper will discuss the status of various energy conversion options currently under development by NASA Glenn for the Radioisotope Power System Program for NASA s Science Mission Directorate (SMD) and the Prometheus Program for the Exploration Systems Mission Directorate (ESMD).

Trades Between Opposition and Conjunction Class Trajectories for Early Human Missions to Mars

NASA Technical Reports Server (NTRS)

Mattfeld, Bryan; Stromgren, Chel; Shyface, Hilary; Komar, David R.; Cirillo, William; Goodliff, Kandyce

2014-01-01

Candidate human missions to Mars, including NASA's Design Reference Architecture 5.0, have focused on conjunction-class missions with long crewed durations and minimum energy trajectories to reduce total propellant requirements and total launch mass. However, in order to progressively reduce risk and gain experience in interplanetary mission operations, it may be desirable that initial human missions to Mars, whether to the surface or to Mars orbit, have shorter total crewed durations and minimal stay times at the destination. Opposition-class missions require larger total energy requirements relative to conjunction-class missions but offer the potential for much shorter mission durations, potentially reducing risk and overall systems performance requirements. This paper will present a detailed comparison of conjunction-class and opposition-class human missions to Mars vicinity with a focus on how such missions could be integrated into the initial phases of a Mars exploration campaign. The paper will present the results of a trade study that integrates trajectory/propellant analysis, element design, logistics and sparing analysis, and risk assessment to produce a comprehensive comparison of opposition and conjunction exploration mission constructs. Included in the trade study is an assessment of the risk to the crew and the trade offs between the mission duration and element, logistics, and spares mass. The analysis of the mission trade space was conducted using four simulation and analysis tools developed by NASA. Trajectory analyses for Mars destination missions were conducted using VISITOR (Versatile ImpulSive Interplanetary Trajectory OptimizeR), an in-house tool developed by NASA Langley Research Center. Architecture elements were evaluated using EXploration Architecture Model for IN-space and Earth-to-orbit (EXAMINE), a parametric modeling tool that generates exploration architectures through an integrated systems model. Logistics analysis was conducted using

Evolution of a Mars Airplane Concept for the ARES Mars Scout Mission

NASA Technical Reports Server (NTRS)

Smith, Stephen C.; Guynn, Mark D.; Smith, Stephen C.; Parks, Robert W.; Gelhausen, Paul A.

2004-01-01

ARES (Aerial Regional-scale Environmental Survey of Mars) is a proposed Mars Scout mission using an airplane to provide high-value science measurements in the areas of atmospheric chemistry, surface geology and mineralogy, and crustal magnetism. The use of an airplane for robotic exploration of Mars has been studied for over 25 years. There are, however, significant challenges associated with getting an airplane to Mars and flying through the thin, carbon dioxide Martian atmosphere. The traditional wisdom for aircraft design does not always apply for this type of vehicle and geometric, aerodynamic, and mission constraints result in a limited feasible design space. The ARES airplane design is the result of a concept exploration and evolution involving a number of trade studies, downselects, and design refinements. Industry, university, and NASA partners initially proposed a number of different concepts, drawing heavily on past Mars airplane design experience. Concept downselects were conducted with qualitative evaluation and high level analyses, focused on the most important parameters for the ARES mission. Following a successful high altitude test flight of the basic configuration, additional design refinement led to the current design. The resulting Mars airplane concept enables the high-value science objectives of the ARES mission to be accomplished while also fulfilling the desire for a simple, low-risk design.

The NASA Mars Conference

NASA Astrophysics Data System (ADS)

Reiber, Duke B.

Papers about Mars and Mars exploration are presented, covering topics such as Martian history, geology, volcanism, channels, moons, atmosphere, meteorology, water on the planet, and the possibility of life. The unmanned exploration of Mars is discussed, including the Phobos Mission, the Mars Observer, the Mars Aeronomy Observer, the seismic network, Mars sample return missions, and the Mars Ball, an inflatable-sectored-tire rover concept. Issues dealing with manned exploration of Mars are examined, such as the reasons for exploring Mars, mission scenarios, a transportation system for routine visits, technologies for Mars expeditions, the human factors for Mars missions, life support systems, living and working on Mars, and the report of the National Commission on Space.

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Sam Scimemi, Director of NASA's International Space Station Division, second from left, Phil McAlister, Director of NASA's Commercial Spaceflight Division, third from left, Dan Dumbacher, Deputy Associate Administrator of NASA's Exploration Systems Development, center, Michele Gates, Senior Technical Advisor of NASA's Human Exploration and Operations Mission Directorate, second from right, and Jason Crusan, Director of NASA's Advanced Exploration Systems Division, right, sit on a panel during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

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).

Human Mars Mission Overview and Dust Storm Impacts on Site Selection

NASA Technical Reports Server (NTRS)

Hoffman, S. J.

2017-01-01

NASA has begun a process to identify and discuss candidate locations where humans could land, live and work on the martian surface. This process is being carried out as a cooperative effort by NASA's Human Exploration and Operations Mission Directorate (HEOMD), responsible for future human mission preparations, and the Science Mission Directorate (SMD), responsible for the on-going Mars Exploration Program of robotic vehicles in orbit and on the surface of Mars. Both of these Directorates have a significant interest in this process, as these candidate locations will be used by NASA as part of a multi-year effort to determine where and how humans could explore Mars. In the near term this process includes: (a) identifying locations that would maximize the potential science return from future human exploration missions, (b) identifying locations with the potential for resources required to support humans, (c) developing concepts and engineering systems needed by future human crews to conduct operations within a candidate location, and (d) identifying key characteristics of the proposed candidate locations that cannot be evaluated using existing data sets, thus helping to define precursor measurements needed in advance of human missions.

Mission Design Considerations for Mars Cargo of the Human Spaceflight Architecture Team's Evolvable Mars Campaign

NASA Technical Reports Server (NTRS)

Sjauw, Waldy K.; McGuire, Melissa L.; Freeh, Joshua E.

2016-01-01

Recent NASA interest in human missions to Mars has led to an Evolvable Mars Campaign by the agency's Human Architecture Team. Delivering the crew return propulsion stages and Mars surface landers, SEP based systems are employed because of their high specific impulse characteristics enabling missions requiring less propellant although with longer transfer times. The Earth departure trajectories start from an SLS launch vehicle delivery orbit and are spiral shaped because of the low SEP thrust. Previous studies have led to interest in assessing the divide in trip time between the Earth departure and interplanetary legs of the mission for a representative SEP cargo vehicle.

WATER ON MARS: EVIDENCE FROM MER MISSION RESULTS

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.

2006-01-01

The Mars Exploration Rover (MER) mission landed two rovers on Mars, equipped with a highly-capable suite of science instruments. The Spirit rover landed on the inside Gusev Crater on January 5, 2004, and the Opportunity rover three weeks later on Meridiani Planum. This paper summarizes some of the findings from the MER rovers related to the NASA science strategy of investigating past and present water on Mars.

Humans to Mars: Fifty Years of Mission Planning, 1950-2000

NASA Technical Reports Server (NTRS)

Portree, David S. F.

2001-01-01

Contents of this document include: On the Grand Scale; Earliest NASA Concepts; EMPIRE and After; A Hostile Environment; Apogee; Viking and the Resources of Mars; The Case for Mars; Challengers; Space Exploration Initiative; and Design Reference Mission.

The NASA Langley Mars Tumbleweed Rover Prototype

NASA Technical Reports Server (NTRS)

Antol, Jeffrey; Chattin, Richard L.; Copeland, Benjamin M.; Krizann, Shawn A.

2005-01-01

Mars Tumbleweed is a concept for an autonomous rover that would achieve mobility through use of the natural winds on Mars. The wind-blown nature of this vehicle make it an ideal platform for conducting random surveys of the surface, scouting for signs of past or present life as well as examining the potential habitability of sites for future human exploration. NASA Langley Research Center (LaRC) has been studying the dynamics, aerodynamics, and mission concepts of Tumbleweed rovers and has recently developed a prototype Mars Tumbleweed Rover for demonstrating mission concepts and science measurement techniques. This paper will provide an overview of the prototype design, instrumentation to be accommodated, preliminary test results, and plans for future development and testing of the vehicle.

Dust Storm Impacts on Human Mars Mission Equipment and Operations

NASA Technical Reports Server (NTRS)

Rucker, M. A.

2017-01-01

Although it is tempting to use dust impacts on Apollo lunar exploration mission equipment and operations as an analog for human Mars exploration, there are a number of important differences to consider. Apollo missions were about a week long; a human Mars mission will start at least two years before crew depart from Earth, when cargo is pre-deployed, and crewed mission duration may be over 800 days. Each Apollo mission landed at a different site; although no decisions have been made, NASA is investigating multiple human missions to a single Mars landing site, building up capability over time and lowering costs by re-using surface infrastructure. Apollo missions used two, single-use spacecraft; a human Mars mission may require as many as six craft for different phases of the mission, most of which would be re-used by subsequent crews. Apollo crews never ventured more than a few kilometers from their lander; Mars crews may take "camping trips" a hundred kilo-meters or more from their landing site, utilizing pressurized rovers to explore far from their base. Apollo mission designers weren't constrained by human for-ward contamination of the Moon; if we plan to search for evidence of life on Mars we'll have to be more careful. These differences all impact how we will mitigate and manage dust on our human Mars mission equipment and operations.

Solar electric propulsion cargo spacecraft for Mars missions

NASA Technical Reports Server (NTRS)

1991-01-01

One of the topics available to the 1990-91 Aerospace Engineering senior class was the development of a preliminary design of an unmanned cargo ferry that would support the Mars mission by bringing equipment and supplies from a low Earth orbit (LEO) to a low Mars orbit (LMO). Several previous studies initiated by NASA have indicated that low-thrust transportation systems seem to offer the best performance for Mars missions. Such systems are characterized by long spiral times during escape and capture maneuvers, high payload mass fractions, and, typically, low propellant mass fractions. Of two main low-thrust candidates, nuclear electric propulsion (NEP) and solar electric propulsion (SEP), only the first one received extensive consideration because it seemed to represent the most promising concept for a manned mission to Mars. However, any sustained Mars initiative will have to include an unmanned cargo transportation system, for which an SEP concept deserves very careful consideration. The key assumptions and requirements established in cooperation with the Space Exploration Initiative office at the NASA Langley Research Center were (1) vehicle is assembled at the Space Station Freedom (SSF); (2) Earth-to-orbit delivery of the vehicle components, propellant, and payload is via shuttle-C; (3) vehicle's cargo mass is 61,000 kg; (4) vehicle delivers cargo to LMO at an altitude of 500 km and inclination of 70 deg; (5) vehicle returns (without cargo) to SSF; (6) vehicle should be reusable for at least three missions; and (7) vehicle is powered by ion argon thrusters. Two configurations were developed by two student teams, working mostly independently.

Mars curiosity mission

NASA Image and Video Library

2012-08-04

NASA welcomed hundreds of children and accompanying adults to its INFINITY visitor center on Aug. 4, offering Mars-related activities that focused attention on the space agency's Curiosity mission to the Red Planet. Among other things, students from Gulfport High School, who field a team each year in the FIRST (For Inspiration and Recognition of Science and Technology) Robotics Competition, offered young visitors a firsthand look at how robots work Hundreds of persons visited the INFINITY facility during the day, including media representatives from surrounding communities.

Robust, affordable, semi-direct Mars mission

NASA Astrophysics Data System (ADS)

Salotti, Jean-Marc

2016-10-01

A new architecture is proposed for the first manned Mars mission, based on current NASA developments (SLS and Orion), chemical propulsion for interplanetary transit, aerocapture for all vehicles, a split strategy, and a long stay on the surface. Two important choices make this architecture affordable and appropriate for the first mission. The first is splitting the Earth return vehicle into two parts that are launched separately and dock in Mars orbit. This is necessary to make aerocapture feasible and efficient, which considerably reduces mass. The second is reducing the crew to 3 astronauts. This simplifies the mission and reduces the SLS payload mass under the 45-metric ton limit for a direct TMI (trans-Mars injection) burn without LEO assembly. Only 4 SLS launches are required. The first takes the Mars ascent vehicle and in situ resource utilization systems to the planet's surface. The second takes the first part of the Earth return vehicle, the habitat, into Mars orbit. Two years later, two further SLS launches take a dual-use habitat (outbound trip and surface), Orion, and an enhanced service module to LEO, and then into Mars orbit, followed by the landing of the habitat on the surface. Transit time is demonstrated to be easily reduced to less than 6 months, with relatively low impact on propellant mass and none at all on the architecture.

Solar-Electrochemical Power System for a Mars Mission

NASA Technical Reports Server (NTRS)

Withrow, Colleen A.; Morales, Nelson

1994-01-01

This report documents a sizing study of a variety of solar electrochemical power systems for the intercenter NASA study known as 'Mars Exploration Reference Mission'. Power systems are characterized for a variety of rovers, habitation modules, and space transport vehicles based on requirements derived from the reference mission. The mission features a six-person crew living on Mars for 500 days. Mission power requirements range from 4 kWe to 120 kWe. Primary hydrogen and oxygen fuel cells, regenerative hydrogen and oxygen fuel cells, sodium sulfur batteries advanced photovoltaic solar arrays of gallium arsenide on germanium with tracking and nontracking mechanisms, and tent solar arrays of gallium arsenide on germanium are evaluated and compared.

Austere Human Missions to Mars

NASA Technical Reports Server (NTRS)

Price, Hoppy; Hawkins, Alisa M.; Tadcliffe, Torrey O.

2009-01-01

The Design Reference Architecture 5 (DRA 5) is the most recent concept developed by NASA to send humans to Mars in the 2030 time frame using Constellation Program elements. DRA 5 is optimized to meet a specific set of requirements that would provide for a robust exploration program to deliver a new six-person crew at each biennial Mars opportunity and provide for power and infrastructure to maintain a highly capable continuing human presence on Mars. This paper examines an alternate architecture that is scaled back from DRA 5 and might offer lower development cost, lower flight cost, and lower development risk. It is recognized that a mission set using this approach would not meet all the current Constellation Mars mission requirements; however, this 'austere' architecture may represent a minimum mission set that would be acceptable from a science and exploration standpoint. The austere approach is driven by a philosophy of minimizing high risk or high cost technology development and maximizing development and production commonality in order to achieve a program that could be sustained in a flat-funded budget environment. Key features that would enable a lower technology implementation are as follows: using a blunt-body entry vehicle having no deployable decelerators, utilizing aerobraking rather than aerocapture for placing the crewed element into low Mars orbit, avoiding the use of liquid hydrogen with its low temperature and large volume issues, using standard bipropellant propulsion for the landers and ascent vehicle, and using radioisotope surface power systems rather than a nuclear reactor or large area deployable solar arrays. Flat funding within the expected NASA budget for a sustained program could be facilitated by alternating cargo and crew launches for the biennial Mars opportunities. This would result in two assembled vehicles leaving Earth orbit for Mars per Mars opportunity. The first opportunity would send two cargo landers to the Mars surface to

The Human Mars Mission: Transportation Assessment

NASA Technical Reports Server (NTRS)

Kos, Larry

1998-01-01

If funding is available, and for NASA planning purposes, the Human Mars Mission (HMM) is baselined to take place during the 2011 and 2013/2014 Mars opportunities. Two cargo flights will leave for Mars during the first opportunity, one to Mars orbit and the second to the surface, in preparation for the crew during the following opportunity. Each trans-Mars injection (TMI) stack will consist of a cargo / payload portion (currently coming in at between 65 and 78 mt) and a nuclear thermal propulsion (NTP) stage (currently coming in at between 69 and 77 mt loaded with propellant) for performing the departure (Delta)Vs to get on to the appropriate Mars trajectories. Three 66,700 N thrust NTP engines comprise the TMI stage for each stack and perform a (Delta)V ringing from 3580 to 3890 m/s is required by the trajectory (with gravity losses and various performance margins to this for the total TMI (Delta)V performed). This paper will discuss the current application of this NTP stage to a Human Mars mission, and project what implications a nuclear trans-Earth injection (TEI) stage as well as a bi-modal NTP stage could mean to a human visit to Mars.

A Mars Rover Mission Simulation on Kilauea Volcano

NASA Technical Reports Server (NTRS)

Stoker, Carol; Cuzzi, Jeffery N. (Technical Monitor)

1995-01-01

A field experiment to simulate a rover mission on Mars was performed using the Russian Marsokhod rover deployed on Kilauea Volcano HI in February, 1995. A Russian Marsokhod rover chassis was equipped with American avionics equipment, stereo cameras on a pan and tilt platform, a digital high resolution body-mounted camera, and a manipulator arm on which was mounted a camera with a close-up lens. The six wheeled rover is 2 meters long and has a mass of 120 kg. The imaging system was designed to simulate that used on the planned "Mars Together" mission. The rover was deployed on Kilauea Volcano HI and operated from NASA Ames by a team of planetary geologists and exobiologists. Two modes of mission operations were simulated for three days each: (1) long time delay, low data bandwidth (simulating a Mars mission), and (2) live video, wide-bandwidth data (allowing active control simulating a Lunar rover mission or a Mars rover mission controlled from on or near the Martian surface). Simulated descent images (aerial photographs) were used to plan traverses to address a detailed set of science questions. The actual route taken was determined by the science team and the traverse path was frequently changed in response to the data acquired and to unforeseen operational issues. Traverses were thereby optimized to efficiently answer scientific questions. During the Mars simulation, the rover traversed a distance of 800 m. Based on the time delay between Earth and Mars, we estimate that the same operation would have taken 30 days to perform on Mars. This paper will describe the mission simulation and make recommendations about incorporating rovers into the Mars surveyor program.

Design of human missions to Mars and robotic missions to Jupiter

NASA Astrophysics Data System (ADS)

Okutsu, Masataka

We consider human missions to Mars and robotic missions to Jupiter for launch dates in the near- and far-future. For the near-future, we design trajectories for currently proposed space missions that have well-defined spacecraft and mission requirements. For example, for early human missions to Mars we assume that the constraints used in NASA's design reference missions are indicative of current and near-future technologies, which of course limit our capabilities to explore Mars--and these limits make the problem challenging. Similarly, in the case of robotic exploration of Jupiter, we consider that the technology levels assumed for the proposed Europa Orbiter mission represent reasonable limits. For the far-future (two to three decades from now), we take the best estimates from current literature about the capabilities that may be available in nuclear-powered electric propulsion. We consider hardware capabilities (in terms of specific mass, specific impulse, thrust, power, etc.) for low-thrust trajectories, which range froth near-term to far-future technologies. In designing such missions, several techniques are found useful. For example, the Tisserand Graph, which tracks the changes in orbital shapes and energies, provides insight in designing Jovian tours for the Europa Orbiter mission. The graph is also useful in analyzing abort trajectories for human missions to Mars. Furthermore, a patched-conic propagator, which can generate thousands of potential trajectories, plays a vital role in three of four chapters of this thesis. For launches in the next three decades, we discovered a class of Earth- Mars-Venus-Earth free returns (which appear only four times in the 100-year period), Jovian tours involving ten to twenty flybys of the Galilean satellites, and low-thrust trajectories to Jupiter via gravity assists from Venus, Earth, and Mars. In addition, our continuation method, in which a solution for a conic trajectory is gradually converted into that for a low

Research from the NASA Twins Study and Omics in Support of Mars Missions

NASA Technical Reports Server (NTRS)

Kundrot, C.; Shelhamer, M.; Scott, G.

2015-01-01

The NASA Twins Study, NASA's first foray into integrated omic studies in humans, illustrates how an integrated omics approach can be brought to bear on the challenges to human health and performance on a Mars mission. The NASA Twins Study involves US Astronaut Scott Kelly and his identical twin brother, Mark Kelly, a retired US Astronaut. No other opportunity to study a twin pair for a prolonged period with one subject in space and one on the ground is available for the foreseeable future. A team of 10 principal investigators are conducting the Twins Study, examining a very broad range of biological functions including the genome, epigenome, transcriptome, proteome, metabolome, gut microbiome, immunological response to vaccinations, indicators of atherosclerosis, physiological fluid shifts, and cognition. A novel aspect of the study is the integrated study of molecular, physiological, cognitive, and microbiological properties. Major sample and data collection from both subjects for this study began approximately six months before Scott Kelly's one year mission on the ISS, continue while Scott Kelly is in flight and will conclude approximately six months after his return to Earth. Mark Kelly will remain on Earth during this study, in a lifestyle unconstrained by this study, thereby providing a measure of normal variation in the properties being studied. An overview of initial results and the future plans will be described as well as the technological and ethical issues raised for spaceflight studies involving omics.

Parachute Testing for NASA InSight Mission

NASA Image and Video Library

2015-05-27

This parachute testing for NASA's InSight mission to Mars was conducted inside the world's largest wind tunnel, at NASA Ames Research Center, Moffett Field, California, in February 2015. The wind tunnel is 80 feet (24 meters) tall and 120 feet (37 meters) wide. It is part of the National Full-Scale Aerodynamics Complex, operated by the Arnold Engineering Development Center of the U.S. Air Force. 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/PIA19405

Development of advanced entry, descent, and landing technologies for future Mars Missions

NASA Technical Reports Server (NTRS)

Chu, Cheng-Chih (Chester)

2006-01-01

Future Mars missions may need the capability to land much closer to a desired target and/or advanced methods of detecting, avoiding, or tolerating landing hazards. Therefore, technologies that enable 'pinpoint landing' (within tens of meters to 1 km of a target site) will be crucial to meet future mission requirements. As part of NASA Research Announcement, NRA 03-OSS-01, NASA solicited proposals for technology development needs of missions to be launched to Mars during or after the 2009 launch opportunity. Six technology areas were identified as of high priority including advanced entry, descent, and landing (EDL) technologies. In May 2004, 11 proposals with PIs from universities, industries, and NASA centers, were awarded in the area of advanced EDL by NASA for further study and development. This paper presents an overview of these developing technologies.

Mars Atmosphere Resource Verification INsitu (MARVIN) - In Situ Resource Demonstration for the Mars 2020 Mission

NASA Technical Reports Server (NTRS)

Sanders, Gerald B.; Araghi, Koorosh; Ess, Kim M.; Valencia, Lisa M.; Muscatello, Anthony C.; Calle, Carlos I.; Clark, Larry; Iacomini, Christie

2014-01-01

The making of oxygen from resources in the Martian atmosphere, known as In Situ Resource Utilization (ISRU), has the potential to provide substantial benefits for future robotic and human exploration. In particular, the ability to produce oxygen on Mars for use in propulsion, life support, and power systems can provide significant mission benefits such as a reducing launch mass, lander size, and mission and crew risk. To advance ISRU for possible incorporation into future human missions to Mars, NASA proposed including an ISRU instrument on the Mars 2020 rover mission, through an announcement of opportunity (AO). The purpose of the the Mars Atmosphere Resource Verification INsitu or (MARVIN) instrument is to provide the first demonstration on Mars of oxygen production from acquired and stored Martian atmospheric carbon dioxide, as well as take measurements of atmospheric pressure and temperature, and of suspended dust particle sizes and amounts entrained in collected atmosphere gases at different times of the Mars day and year. The hardware performance and environmental data obtained will be critical for future ISRU systems that will reduce the mass of propellants and other consumables launched from Earth for robotic and human exploration, for better understanding of Mars dust and mitigation techniques to improve crew safety, and to help further define Mars global circulation models and better understand the regional atmospheric dynamics on Mars. The technologies selected for MARVIN are also scalable for future robotic sample return and human missions to Mars using ISRU.

A Review of Aerothermal Modeling for Mars Entry Missions

NASA Technical Reports Server (NTRS)

Wright, Michael J; Tang, Chun Y.; Edquist, Karl T.; Hollis, Brian R.; Krasa, Paul

2009-01-01

The current status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a predominantly CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Localized heating due to penetrations or other singularities on the aeroshell must also be taken into account. The physical models employed to predict these phenomena are reviewed, and key uncertainties or deficiencies inherent in these models are explored. Capabilities of existing ground test facilities to support aeroheating validation are also summarized. Engineering flight data from the Viking and Pathfinder missions, which may be useful for aerothermal model validation, are discussed, and an argument is presented for obtaining additional flight data. Examples are taken from past, present, and future Mars entry missions, including the twin Mars Exploration Rovers and the Mars Science Laboratory, scheduled for launch by NASA in 2011.

Ablative Heat Shield Studies for NASA Mars/Earth Return Entry Vehicles

DTIC Science & Technology

1990-09-01

RETURN ENTRY VEHICLES by Michael K. Hamm September, 1990 NASA Thesis Advisor: William D. Henline Thesis Co-Advisor: Max F. Platzer Approved for public...STUDIES FOR NASA MARS/EARTH RETURN ENTRY VEHICLES (UNCLASSIFIED) 12. PERSONAL AUTHOR(S) Harm, Michael, K. 13a TYPE OF REPORT 13b TIME COVERED 14 DATE OF...theoretical values. The tests were performed to ascertain if RSI type materials could be used for entry vehicles proposed in NASA Mars missions. 20

The Long, Bumpy Road to a Mars Aeronomy Mission (Invited)

NASA Astrophysics Data System (ADS)

Grebowsky, J. M.; Luhmann, J. G.; Bougher, S. W.; Jakosky, B. M.

2013-12-01

With the advent of the space age, early focus was put into characterizing the Earth's upper atmosphere with aeronomy missions. These missions were designed to study the upper atmosphere region of a planet where the ionosphere is produced with particular attention given to the composition, properties and motion of atmosphere constituents. In particular a very successful US series of Atmosphere Explorer aeronomy spacecraft (1963-1977) was implemented. This upper atmosphere region is the envelope that all energy from the sun must penetrate and is recognized as an inseparable part of a planet's entire atmosphere. Venus was the next planet to have its upper atmosphere/ionosphere deeply probed via the Pioneer Venus Orbiter (1978-1986) that carried a complement of instruments similar to some flown on the Atmosphere Explorers. The planet which humans have long set their imagination on, Mars, has yet to be subjected to the same detailed upper atmosphere perusal until now, with MAVEN. Not that attempts have been wanting. More than 30 spacecraft launches to Mars were attempted, but half were not successful and those that attained orbit came far short of attaining the same level of knowledge of the Martian upper atmosphere. Other countries had planned Mars aeronomy missions that didn't bear fruit - e.g. Mars-96 and Nozomi and the US did studies for two missions, Mars Aeronomy Orbiter and MUADEE, that never were implemented. This is about to change. NASA's Scout Program singled out two aeronomy missions in its final competition and the selected mission, MAVEN, will fly with the needed sophistication of instruments to finally probe and understand the top of Mars' atmosphere. Was this late selection of a NASA aeronomy mission to Mars a philosophy change in US priorities or was it an accident of planning and budget constraints? Was it driven by the developing knowledge that Mars really had an early atmosphere environment conducive to life and that an aeronomy mission is indeed

The Challenges of Developing a Food System for a Mars Mission

NASA Technical Reports Server (NTRS)

Perchonok, Michele

2007-01-01

A viewgraph describing the food system that NASA is developing for Manned Mars Missions is shown. The topics include: 1) The President's Vision for U.S. Space Exploration -January 14, 2004; 2) Introducing Orion (and Ares); 3) Mercury (1961-1963); 4) Gemini (1965-1966); 5) Apollo (1968-1972); 6) Skylab (1973-1974); 7) Shuttle/Mir (1995-1998); 8) Shuttle (1981-present) International Space Station (2000-present); 9) NASA Stored Food System; 10) Advanced Food Technology; 11) Orion Missions; 12) Orion Challenges; 13) Food Packaging; 14) Mars Mission Assumptions; 15) Planetary Food System Selected Crops; 16) Food Processing Equipment Constraints; 17) Crew Involvement Constraints; 18) Advanced Food Technology Integration; 19) Research Highlights Internal; and 20) Research Highlights External.

Report on the Loss of the Mars Polar Lander and Deep Space 2 Missions

NASA Technical Reports Server (NTRS)

Albee, Arden; Battel, Steven; Brace, Richard; Burdick, Garry; Casani, John; Lavell, Jeffrey; Leising, Charles; MacPherson, Duncan; Burr, Peter; Dipprey, Duane

2000-01-01

NASA's Mars Surveyor Program (MSP) began in 1994 with plans to send spacecraft to Mars every 26 months. Mars Global Surveyor (MGS), a global mapping mission, was launched in 1996 and is currently orbiting Mars. Mars Surveyor '98 consisted of Mars Climate Orbiter (MCO) and Mars Polar Lander (MPL). Lockheed Martin Astronautics (LMA) was the prime contractor for Mars Surveyor '98. The Jet Propulsion Laboratory (JPL), California Institute of Technology, manages the Mars Surveyor Program for NASA's Office of Space Science. MPL was developed under very tight funding constraints. The combined development cost of MPL and MCO, including the cost of the two launch vehicles, was approximately the same as the development cost of the Mars Pathfinder mission, including the cost of its single launch vehicle. The MPL project accepted the challenge to develop effective implementation methodologies consistent with programmatic requirements.

Lowest cost, nearest term options for a manned Mars mission

NASA Technical Reports Server (NTRS)

Sauls, Bob; Mortensen, Michael; Myers, Renee; Guacci, Giovanni; Montes, Fred

1992-01-01

This study is part of a NASA/USRA Advanced Design Program project executed for the purpose of examining the requirements of a first manned Mars mission. The mission, classified as a split/sprint mission, has been designed for a crew of six with a total manned trip time of one year.

CNES-NASA Studies of the Mars Sample Return Orbiter Aerocapture Phase

NASA Technical Reports Server (NTRS)

Fraysse, H.; Powell, R.; Rousseau, S.; Striepe, S.

2000-01-01

A Mars Sample Return (MSR) mission has been proposed as a joint CNES (Centre National d'Etudes Spatiales) and NASA effort in the ongoing Mars Exploration Program. The MSR mission is designed to return the first samples of Martian soil to Earth. The primary elements of the mission are a lander, rover, ascent vehicle, orbiter, and an Earth entry vehicle. The Orbiter has been allocated only 2700 kg on the launch phase to perform its part of the mission. This mass restriction has led to the decision to use an aerocapture maneuver at Mars for the orbiter. Aerocapture replaces the initial propulsive capture maneuver with a single atmospheric pass. This atmospheric pass will result in the proper apoapsis, but a periapsis raise maneuver is required at the first apoapsis. The use of aerocapture reduces the total mass requirement by approx. 45% for the same payload. This mission will be the first to use the aerocapture technique. Because the spacecraft is flying through the atmosphere, guidance algorithms must be developed that will autonomously provide the proper commands to reach the desired orbit while not violating any of the design parameters (e.g. maximum deceleration, maximum heating rate, etc.). The guidance algorithm must be robust enough to account for uncertainties in delivery states, atmospheric conditions, mass properties, control system performance, and aerodynamics. To study this very critical phase of the mission, a joint CNES-NASA technical working group has been formed. This group is composed of atmospheric trajectory specialists from CNES, NASA Langley Research Center and NASA Johnson Space Center. This working group is tasked with developing and testing guidance algorithms, as well as cross-validating CNES and NASA flight simulators for the Mars atmospheric entry phase of this mission. The final result will be a recommendation to CNES on the algorithm to use, and an evaluation of the flight risks associated with the algorithm. This paper will describe the

Mars integrated transportation system multistage Mars mission

NASA Technical Reports Server (NTRS)

1991-01-01

In accordance with the objective of the Mars Integrated Transport System (MITS) program, the Multistage Mars Mission (MSMM) design team developed a profile for a manned mission to Mars. The purpose of the multistage mission is to send a crew of five astronauts to the martian surface by the year 2019. The mission continues man's eternal quest for exploration of new frontiers. This mission has a scheduled duration of 426 days that includes experimentation en route as well as surface exploration and experimentation. The MSMM is also designed as a foundation for a continuing program leading to the colonization of the planet Mars.

Optimizing Mars Sphere of Influence Maneuvers for NASA's Evolvable Mars Campaign

NASA Technical Reports Server (NTRS)

Merrill, Raymond G.; Komar, D. R.; Chai, Patrick; Qu, Min

2016-01-01

NASA's Human Spaceflight Architecture Team is refining human exploration architectures that will extend human presence to the Martian surface. For both Mars orbital and surface missions, NASA's Evolvable Mars Campaign assumes that cargo and crew can be delivered repeatedly to the same destination. Up to this point, interplanetary trajectories have been optimized to minimize the total propulsive requirements of the in-space transportation systems, while the pre-deployed assets and surface systems are optimized to minimize their respective propulsive requirements separate from the in-space transportation system. There is a need to investigate the coupled problem of optimizing the interplanetary trajectory and optimizing the maneuvers within Mars's sphere of influence. This paper provides a description of the ongoing method development, analysis and initial results of the effort to resolve the discontinuity between the interplanetary trajectory and the Mars sphere of influence trajectories. Assessment of Phobos and Deimos orbital missions shows the in-space transportation and crew taxi allocations are adequate for missions in the 2030s. Because the surface site has yet to be selected, the transportation elements must be sized to provide enough capability to provide surface access to all landing sites under consideration. Analysis shows access to sites from elliptical parking orbits with a lander that is designed for sub-periapsis landing location is either infeasible or requires expensive orbital maneuvers for many latitude ranges. In this case the locus of potential arrival perigee vectors identifies the potential maximum north or south latitudes accessible. Higher arrival velocities can decrease reorientation costs and increase landing site availability. Utilizing hyperbolic arrival and departure vectors in the optimization scheme will increase transportation site accessibility and provide more optimal solutions.

Artist Rendering of NASA Dawn Spacecraft Approaching Mars

NASA Image and Video Library

2009-05-23

Artist rendering of NASA's Dawn spacecraft approaching Mars. Dawn, part of NASA's Discovery Program of competitively selected missions, was launched in 2007 to orbit the large asteroid Vesta and the dwarf planet Ceres. The two bodies have very different properties from each other. By observing them both with the same set of instruments, Dawn will probe the early solar system and specify the properties of each body. http://photojournal.jpl.nasa.gov/catalog/PIA18152

Current NASA Plans for Mars In Situ Resource Utilization

NASA Technical Reports Server (NTRS)

Sanders, Gerald

2018-01-01

The presentation is to provide relevant information to the NASA funded Center for the Utilization of Biological Engineering in Space (CUBES) Institute. The presentation cover the following: 1) What is In Situ Resource Utilization (ISRU), 2) What are the resources of interest at the Moon and Mars, 3) ISRU-related mission requirements and ISRU economics, 4) Challenges and Risk for ISRU, 5) Concept of Operation for Mars ISRU Systems, 6) Current State of the Art (SOA) in ISRU, and 7) Current ISRU development and mission status.

Relay Support for the Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Edwards, Charles D. Jr,; Bell, David J.; Gladden, Roy E.; Ilott, Peter A.; Jedrey, Thomas C.; Johnston, M. Daniel; Maxwell, Jennifer L.; Mendoza, Ricardo; McSmith, Gaylon W.; Potts, Christopher L.;

MAVEN - Mars Atmosphere and Volatile EvolutioN Mission

NASA Technical Reports Server (NTRS)

Grebowsky, Joseph M.; Jakosky, Bruce M.

2011-01-01

NASA's MAVEN mission (to be launched in late 2013) is the first mission to Mars devoted to sampling all of the upper atmosphere neutral and plasma environments, including the well-mixed atmosphere, the exosphere, ionosphere, outer magnetosphere and near-Mars solar wind. It will fill in some measurement gaps remaining from the successful Mars Global Surveyor and the on-going Mars Express missions. The primary science objectives of MAVEN are: 1. Provide a comprehensive picture of the present state of the upper atmosphere and ionosphere of Mars; 2. Understand the processes controlling the present state; and 3. Determine how loss of volatiles to outer space in the present epoch varies with changing solar condition - EUY, solar wind and interplanetary magnetic field measurements will provide the varying solar energy inputs into the system. Knowing how these processes respond to the Sun's energy inputs in the current epoch will provide a framework for projecting atmospheric processes back in time to profile MARS' atmospheric evolution and to explore "where the water went", A description will be given of the science objectives, the instruments, and the current status of the project, emphasizing the value of having collaborations between the MAVEN project and the Mars upper atmosphere science community.

Mars Relay Satellite: Key to Enabling Low-Cost Exploration Missions

NASA Technical Reports Server (NTRS)

Hastrup, R.; Cesarone, R.; Miller, A.

1993-01-01

Recently, there has been increasing evidence of a renewed focus on Mars exploration both by NASA and the international community. The thrust of this renewed interest appears to be manifesting itself in numerous low-cost missions employing small, light weight elements, which utilize advanced technologies including integrated microelectronics. A formidable problem facing these low-cost missions is communications with Earth. Providing adequate direct-link performance has very significant impacts on spacecraft power, pointing, mass and overall complexity. Additionally, for elements at or near the surface of Mars, there are serious connectivity constraints, especially at higher latitudes, which lose view of Earth for up to many months at a time. This paper will discuss the role a Mars relay satellite can play in enabling and enhancing low-cost missions to Mars...

Nuclear Thermal Propulsion Mars Mission Systems Analysis and Requirements Definition

NASA Technical Reports Server (NTRS)

Mulqueen, Jack; Chiroux, Robert C.; Thomas, Dan; Crane, Tracie

2007-01-01

This paper describes the Mars transportation vehicle design concepts developed by the Marshall Space Flight Center (MSFC) Advanced Concepts Office. These vehicle design concepts provide an indication of the most demanding and least demanding potential requirements for nuclear thermal propulsion systems for human Mars exploration missions from years 2025 to 2035. Vehicle concept options vary from large "all-up" vehicle configurations that would transport all of the elements for a Mars mission on one vehicle. to "split" mission vehicle configurations that would consist of separate smaller vehicles that would transport cargo elements and human crew elements to Mars separately. Parametric trades and sensitivity studies show NTP stage and engine design options that provide the best balanced set of metrics based on safety, reliability, performance, cost and mission objectives. Trade studies include the sensitivity of vehicle performance to nuclear engine characteristics such as thrust, specific impulse and nuclear reactor type. Tbe associated system requirements are aligned with the NASA Exploration Systems Mission Directorate (ESMD) Reference Mars mission as described in the Explorations Systems Architecture Study (ESAS) report. The focused trade studies include a detailed analysis of nuclear engine radiation shield requirements for human missions and analysis of nuclear thermal engine design options for the ESAS reference mission.

2011 Mars Science Laboratory Mission Design Overview

NASA Technical Reports Server (NTRS)

Abilleira, Fernando

2010-01-01

Scheduled to launch in the fall of 2011 with arrival at Mars occurring in the summer of 2012, NASA's Mars Science Laboratory will explore and assess whether Mars ever had conditions capable of supporting microbial life. In order to achieve its science objectives, the Mars Science Laboratory will be equipped with the most advanced suite of instruments ever sent to the surface of the Red Planet. Delivering the next mobile science laboratory safely to the surface of Mars has various key challenges derived from a strict set of requirements which include launch vehicle performance, spacecraft mass, communications coverage during Entry, Descent, and Landing, atmosphere-relative entry speeds, latitude accessibility, and dust storm season avoidance among others. The Mars Science Laboratory launch/arrival strategy selected after careful review satisfies all these mission requirements.

NASA Mars Rover Curiosity at JPL, Side View

NASA Image and Video Library

2011-04-06

The rover for NASA Mars Science Laboratory mission, named Curiosity, is about 3 meters 10 feet long, not counting the additional length that the rover arm can be extended forward. The front of the rover is on the left in this side view.

The Mars 2020 Mission: The Next Step Forward in Mars Exploration

NASA Astrophysics Data System (ADS)

Meyer, M. A.; Schulte, M. D.

2014-12-01

The next rover mission to Mars represents the culmination of almost two decades of strategic missions in the exploration of Mars. Our understanding of the Red Planet has evolved from a global frozen desert to a dynamic world that once was warmer, wetter, and could have supported microbial life, and the series of missions reflect this evolution, moving from global reconnaissance to seeking the signs of life. The 2020 rover will be outfitted with seven sophisticated payload elements to conduct remote sensing and contact science, demonstrate exploration technology, and cache samples for potential return to Earth. The mission's capabilities exceed the threshold mission detailed in the Mars 2020 Science Definition Team 2013 report1 and meets the NRC's 2011 Decadal Survey's requirements for the highest priority mission of NASA's Planetary Science2. The instruments selected July 31, 2014, are able to determine elemental composition and mineralogy and detect organic compounds across spatial scales of meters to 100's of micrometers. The instrument suite includes a combination of a zooming, binocular, multi-spectral camera; a telescopic imager; two Raman spectrometers with different wavelength lasers (UV and Green); a visible/near-infrared spectrometer; a Laser-Induced Breakdown Spectrometer; an X-ray fluorescence spectrometer, a microscopic imager, and ground-penetrating radar. Their purpose is to enable the science team to establish the geological context of the landing site area, to assess whether past or present environments could support microbial life, to search for potential biosignatures, and to use this information to identify samples for caching. To prepare for future human exploration, the payload includes the ability for in situ resource utilization, converting CO2 to O2, the ability to assess physical characteristics of the dust, and environmental monitoring of the temperature, pressure, humidity, wind, and radiation. The Mars 2020 mission will pave a

Mars geoscience/climatology orbiter low cost mission operations

NASA Technical Reports Server (NTRS)

Erickson, K. D.

1984-01-01

It will not be possible to support the multiple planetary missions of the magnitude and order of previous missions on the basis of foreseeable NASA funding. It is, therefore, necessary to seek innovative means for accomplishing the goals of planetary exploration with modestly allocated resources. In this connection, a Core Program set of planetary exploration missions has been recommended. Attention is given to a Mission Operations design overview which is based on the Mars Geoscience/Climatology Orbiter Phase-A study performed during spring of 1983.

Probing below the Surface of Mars. ITEA/NASA-JPL Learning Activity.

ERIC Educational Resources Information Center

Urquhart, Mary; Urquhart, Sally

2000-01-01

This activity, developed by NASA's Jet Propulsion Laboratory, involves students in recording and graphing temperature data to learn about NASA's Mars Microprobe Mission, Deep Space 2, and how the properties of a material affect the transfer of heat. (Author/JOW)

ExoMars Mission 2016, Orbiter Module Power System Architecture (Based On An Unregulated Bus & MPPT Controlled Step-Down Voltage Regulators)

NASA Astrophysics Data System (ADS)

Digoin, JJ.; Boutelet, E.

2011-10-01

The main objective of the ExoMars program is to demonstrate key flight in situ enabling technologies in support of the European ambitions for future exploration missions and to pursue fundamental scientific investigations. Two missions are foreseen within the ExoMars program for the 2016 and 2018 launch opportunities to Mars. The 2016 mission is an ESA led mission that will supply a Mars Orbiter Module (OM) carrying an Entry Descent module (EDM) and NASA/ESA scientific instruments. The 2018 mission is a NASA led mission bringing one ESA rover and one NASA rover onto the Mars surface. This paper presents the OM Electrical Power Sub- system (EPS) design achieved at the end of pre- development phase. The main aspects addressed are: - EPS major constraints due to mission and environment, a succinct description of the power units, - Trade-off analyses results leading to the selected EPS architecture, - Preliminary results of electrical and energy simulations, - EPS units development plan.

Parametric Analysis for Aurora Mars Manned Mission Concept Definition

NASA Astrophysics Data System (ADS)

Augros, P.; Bonnefond, F.; Ranson, S.

In the frame of the Aurora program (ESA program), Europe plans to get its own vision about future Mars manned mission. Within this context, we have performed an end-to-end analysis of what could be these missions, focusing on transportation aspects and mobile in-situ infrastructure. This paper will define what is needed to land on Mars, what is needed to return from Mars surface, will explore the round trip options and their consequences on the mission design and feasibility and will analyze the launcher issue and the in-orbit assembly scenarios. The main results enable to rediscover a candidate mission based on a scenario close to the NASA reference mission (Ref [1]). The main interest, from transportation point of view, is that the spacecraft are similar: same insertion stage, same descent vehicle. Such design can be possible with deployable aeroshield for Mars entry vehicle, in-situ water and propellant production, improved habitat technology, conjunction like round trip (minimum V avoiding science fiction design), a launcher payload capability of 100 tons in LEO with a payload size of 30 m long and 7.5 m diameter. An alternative, limiting also the overall mass in LEO, could be a no Mars infrastructure deployment and a single spacecraft going to Mars and returning back to Earth. But it implies for the crew to stay in Mars orbit several months, waiting for the next opportunity ensuring a minimum V.

Science objectives of ESA's ExoMars mission

NASA Astrophysics Data System (ADS)

Vago, J. L.; Gardini, B.; Baglioni, P.; Kminek, G.; Gianfiglio, G.; Exomars Project Team

ExoMars will deliver two science elements to the Martian surface: a Rover, carrying the Pasteur scientific payload; and a small, fixed surface station -the Geophysics & Environment Package (GEP). The ExoMars mission's scientific objectives are: 1) To search for signs of past and present life on Mars; 2) To characterise the water/geochemical environment as a function of depth in the shallow subsurface; 3) To study the surface environment and identify hazards to future human missions; and 4) To investigate the planet's deep interior to better understand Mars's evolution and habitability. Over its planned 6-month lifetime, the Rover will travel a few kilometres searching for traces of past and present signs of life. It will do this by collecting and analysing samples from within surface rocks, and from underground -down to 2-m depth. The very powerful combination of mobility with the capability to access locations where organic molecules may be well preserved is unique to this mission. The ExoMars mission contains two other elements: a Carrier and a Descent Module. The Carrier will bring the Descent Module to Mars and release it from the hyperbolic arrival trajectory. The Descent Module's objective is to safely deploy the Pasteur Rover and the GEP -developing a robust European Entry, Descent and Landing System (EDLS) is another fundamental goal of this mission. The mission's data relay capability will be provided by a NASA orbiter. The Pasteur Rover's mass is presently estimated at 190 kg, including the Pasteur scientific payload. The Pasteur payload contains: Panoramic Instruments: stereoscopic cameras, a ground-penetrating radar, and an IR spectrometer; Contact Instrument for studying surface rocks: a close-up imager and a Mössbauer spectrometer; a subsurface drill capable of reaching a depth of 2 m, and also of collecting specimens from exposed bedrock; a sample preparation and distribution unit; a microscope; an oxidation sensor; and a variety of analytical

A Water Rich Mars Surface Mission Scenario

NASA Technical Reports Server (NTRS)

Hoffman, Stephen J.; Andrews, Alida; Joosten, B. Kent; Watts, Kevin

2017-01-01

In an on-going effort to make human Mars missions more affordable and sustainable, NASA continues to investigate the innovative leveraging of technological advances in conjunction with the use of accessible Martian resources directly applicable to these missions. One of the resources with the broadest utility for human missions is water. Many past studies of human Mars missions assumed a complete lack of water derivable from local sources. However, recent advances in our understanding of the Martian environment provides growing evidence that Mars may be more "water rich" than previously suspected. This is based on data indicating that substantial quantities of water are mixed with surface regolith, bound in minerals located at or near the surface, and buried in large glacier-like forms. This paper describes an assessment of what could be done in a "water rich" human Mars mission scenario. A description of what is meant by "water rich" in this context is provided, including a quantification of the water that would be used by crews in this scenario. The different types of potential feedstock that could be used to generate these quantities of water are described, drawing on the most recently available assessments of data being returned from Mars. This paper specifically focuses on sources that appear to be buried quantities of water ice. (An assessment of other potential feedstock materials is documented in another paper.) Technologies and processes currently used in terrestrial Polar Regions are reviewed. One process with a long history of use on Earth and with potential application on Mars - the Rodriguez Well - is described and results of an analysis simulating the performance of such a well on Mars are presented. These results indicate that a Rodriguez Well capable of producing the quantities of water identified for a "water rich" human mission are within the capabilities assumed to be available on the Martian surface, as envisioned in other comparable Evolvable

A Water Rich Mars Surface Mission Scenario

NASA Technical Reports Server (NTRS)

Hoffman, Stephen J.; Andrews, Alida; Joosten, B. Kent; Watts, Kevin

2017-01-01

In an on-going effort to make human Mars missions more affordable and sustainable, NASA continues to investigate the innovative leveraging of technological advances in conjunction with the use of accessible Martian resources directly applicable to these missions. One of the resources with the broadest utility for human missions is water. Many past studies of human Mars missions assumed a complete lack of water derivable from local sources. However, recent advances in our understanding of the Martian environment provides growing evidence that Mars may be more "water rich" than previously suspected. This is based on data indicating that substantial quantities of water are mixed with surface regolith, bound in minerals located at or near the surface, and buried in large glacier-like forms. This paper describes an assessment of what could be done in a "water rich" human Mars mission scenario. A description of what is meant by "water rich" in this context is provided, including a quantification of the water that would be used by crews in this scenario. The different types of potential feedstock that could be used to generate these quantities of water are described, drawing on the most recently available assessments of data being returned from Mars. This paper specifically focuses on sources that appear to be buried quantities of water ice. (An assessment of other potential feedstock materials is documented in another paper.) Technologies and processes currently used in terrestrial polar regions is reviewed. One process with a long history of use on Earth and with potential application on Mars - the Rodriguez Well - is described and results of an analysis simulating the performance of such a well on Mars are presented. These results indicate that a Rodriguez Well capable of producing the quantities of water identified for a "water rich" human mission are within the capabilities assumed to be available on the Martian surface, as envisioned in other comparable Evolvable

MRSR: Rationale for a Mars Rover/Sample Return mission

NASA Technical Reports Server (NTRS)

Carr, Michael H.

1992-01-01

The Solar System Exploration Committee of the NASA Advisory Council has recommended that a Mars Rover/Sample Return mission be launched before the year 2000. The recommendation is consistent with the science objectives as outlined by the National Academy of Sciences committees on Planetary and Lunar Exploration, and Planetary Biology and Chemical Evolution. Interest has also focused on Mars Rover/Sample Return (MRSR) missions, because of their crucial role as precursors for human exploration. As a result of this consensus among the advisory groups, a study of an MRSR mission began early in 1987. The study has the following goals: (1) to assess the technical feasibility of the mission; (2) to converge on two or three options for the general architecture of the mission; (3) to determine what new technologies need to be developed in order to implement the mission; (4) to define the different options sufficiently well that preliminary cost estimates can be made; and (5) to better define the science requirements. This chapter briefly describes Mars Rover/Sample Return missions that were examined in the late 1980s. These missions generally include a large (1000 kg) rover and return of over 5 kg of sample.

Reducing the Risk of Human Missions to Mars Through Testing

NASA Astrophysics Data System (ADS)

Drake, Bret G.

2007-07-01

During the summer of 2002 the NASA Deputy Administrator charted an internal NASA planning group to develop the rationale for exploration beyond low-Earth orbit. This team, termed the Exploration Blueprint, performed architecture analyses to develop roadmaps for how to accomplish the first steps beyond Low-Earth Orbit through the human exploration of Mars. The previous NASA Exploration Team (NEXT) activities laid the foundation and framework for development of NASA s Integrated Space Plan. The reference missions resulting from the analysis performed by the Exploration Blueprint team formed the basis for requirement definition, systems development, technology roadmapping, and risk assessments for future human exploration beyond low-Earth orbit. Emphasis was placed on developing recommendations on what could be done now to effect future exploration activities. The Exploration Blueprint team embraced the Stepping Stone approach to exploration where human and robotic activities are conducted through progressive expansion outward beyond low- Earth orbit. Results from this study produced a long-term strategy for exploration with near-term implementation plans, program recommendations, and technology investments. Specific results included the development of a common exploration crew vehicle concept, a unified space nuclear strategy, focused bioastronautics research objectives, and an integrated human and robotic exploration strategy. Recommendations from the Exploration Blueprint included the endorsement of the Nuclear Systems Initiative, augmentation of the bioastronautics research, a focused space transportation program including heavy-lift launch and a common exploration vehicle design for ISS and exploration missions, as well as an integrated human and robotic exploration strategy for Mars. Following the results of the Exploration Blueprint study, the NASA Administrator has asked for a recommendation by June, 2003 on the next steps in human and robotic exploration in

Reducing the Risk of Human Missions to Mars Through Testing

NASA Technical Reports Server (NTRS)

Drake, Bret G.

2007-01-01

During the summer of 2002 the NASA Deputy Administrator charted an internal NASA planning group to develop the rationale for exploration beyond low-Earth orbit. This team, termed the Exploration Blueprint, performed architecture analyses to develop roadmaps for how to accomplish the first steps beyond Low-Earth Orbit through the human exploration of Mars. The previous NASA Exploration Team (NEXT) activities laid the foundation and framework for development of NASA s Integrated Space Plan. The reference missions resulting from the analysis performed by the Exploration Blueprint team formed the basis for requirement definition, systems development, technology roadmapping, and risk assessments for future human exploration beyond low-Earth orbit. Emphasis was placed on developing recommendations on what could be done now to effect future exploration activities. The Exploration Blueprint team embraced the Stepping Stone approach to exploration where human and robotic activities are conducted through progressive expansion outward beyond low- Earth orbit. Results from this study produced a long-term strategy for exploration with near-term implementation plans, program recommendations, and technology investments. Specific results included the development of a common exploration crew vehicle concept, a unified space nuclear strategy, focused bioastronautics research objectives, and an integrated human and robotic exploration strategy. Recommendations from the Exploration Blueprint included the endorsement of the Nuclear Systems Initiative, augmentation of the bioastronautics research, a focused space transportation program including heavy-lift launch and a common exploration vehicle design for ISS and exploration missions, as well as an integrated human and robotic exploration strategy for Mars. Following the results of the Exploration Blueprint study, the NASA Administrator has asked for a recommendation by June, 2003 on the next steps in human and robotic exploration in

Mars Surface Systems Common Capabilities and Challenges for Human Missions

NASA Technical Reports Server (NTRS)

Toups, Larry; Hoffman, Stephen J.; Watts, Kevin

2016-01-01

This paper describes the current status of common systems and operations as they are applied to actual locations on Mars that are representative of Exploration Zones (EZ) - NASA's term for candidate locations where humans could land, live and work on the martian surface. Given NASA's current concepts for human missions to Mars, an EZ is a collection of Regions of Interest (ROIs) located within approximately 100 kilometers of a centralized landing site. ROIs are areas that are relevant for scientific investigation and/or development/maturation of capabilities and resources necessary for a sustainable human presence. An EZ also contains a habitation site that will be used by multiple human crews during missions to explore and utilize the ROIs within the EZ. The Evolvable Mars Campaign (EMC), a description of NASA's current approach to these human Mars missions, assumes that a single EZ will be identified within which NASA will establish a substantial and durable surface infrastructure that will be used by multiple human crews. The process of identifying and eventually selecting this single EZ will likely take many years to finalized. Because of this extended EZ selection process it becomes important to evaluate the current suite of surface systems and operations being evaluated for the EMC as they are likely to perform at a variety of proposed EZ locations and for the types of operations - both scientific and development - that are proposed for these candidate EZs. It is also important to evaluate proposed EZs for their suitability to be explored or developed given the range of capabilities and constraints for the types of surface systems and operations being considered within the EMC.

NASA Software Lets You Explore Mars, the Asteroid Vesta and the Moon

NASA Image and Video Library

2016-10-06

NASA wants you to use your web browser to explore Mars, the Moon and the asteroid Vesta! The three portals are some of NASA's planetary mapping and modeling web portals. It makes it easy for mission planners, scientists, students and the public to visualize details on the surface of Mars, the Moon and Vesta, as seen with a variety of instruments aboard a number of spacecraft.

Radiation Protection Challenges for a Human Mission to Mars

NASA Astrophysics Data System (ADS)

Zeitlin, C. J.; Hassler, D.; Wimmer-Schweingruber, R. F.; Schwadron, N.; Spence, H. E.

2015-12-01

A human mission to Mars presents many challenges, not least of which is the radiation exposure that crew members will certainly receive in all phases of the journey, but most critically during the transits to and from Mars. Measurements from the Radiation Assessment Detector (RAD) aboard the Mars Science Laboratory Curiosity rover, made both in flight and on the surface of Mars, confirm previous estimates that crew members under reasonable shielding would receive a dose equivalent of about 1 Sievert on a 1000-day mission. In standard radiation biology, an acute exposure to 1 Sievert would be expected to increase lifetime fatal cancer risk by about 5%. This is well beyond the currently allowed 3% risk increase limit used by NASA and JAXA. Perhaps more significantly, the nature of exposure in space differs greatly from the terrestrial exposures that lead to the 5% estimate -- in space, the exposure is received at a very low dose rate, and includes a significant component from heavy ions in the Galactic Cosmic Rays (GCRs). Acute exposures to Solar Energetic Particles are also possible, but the generally lower energies of SEPs (kinetic energies typically below 100 MeV/nuc) mean that modest amounts of shielding are effective against them. Thus the greater concern for long-duration deep-space missions is the GCR exposure. In this presentation, I will briefly review the MSL-RAD data and discuss current approaches to radiation risk estimation, including the NASA limit of 3% at the 95% confidence level. Recent results from the NASA radiation biology program indicate that cancer may not be the only risk that needs to be considered, with emerging concerns about cardiovascular and central nervous system health. These health effects are not accounted for in the current methodology and could potentially be threatening to mission success if they manifest in the course of the mission, rather than appearing many years after the exposure as radiation-induced cancer typically does.

Mars Hybrid Propulsion System Trajectory Analysis. Part II; Cargo Missions

NASA Technical Reports Server (NTRS)

Chai, Patrick R.; Merrill, Raymond G.; Qu, Min

2015-01-01

NASA's Human Spaceflight Architecture Team is developing a reusable hybrid transportation architecture in which both chemical and electric propulsion systems are used to send crew and cargo to Mars destinations such as Phobos, Deimos, the surface of Mars, and other orbits around Mars. By combining chemical and electrical propulsion into a single spaceship and applying each where it is more effective, the hybrid architecture enables a series of Mars trajectories that are more fuel-efficient than an all chemical architecture without significant increases in flight times. This paper shows the feasibility of the hybrid transportation architecture to pre-deploy cargo to Mars and Phobos in support of the Evolvable Mars Campaign crew missions. The analysis shows that the hybrid propulsion stage is able to deliver all of the current manifested payload to Phobos and Mars through the first three crew missions. The conjunction class trajectory also allows the hybrid propulsion stage to return to Earth in a timely fashion so it can be reused for additional cargo deployment. The 1,100 days total trip time allows the hybrid propulsion stage to deliver cargo to Mars every other Earth-Mars transit opportunity. For the first two Mars surface mission in the Evolvable Mars Campaign, the short trip time allows the hybrid propulsion stage to be reused for three round-trip journeys to Mars, which matches the hybrid propulsion stage's designed lifetime for three round-trip crew missions to the Martian sphere of influence.

MEDA, The New Instrument for Mars Environment Analysis for the Mars 2020 Mission

NASA Astrophysics Data System (ADS)

Moreno-Alvarez, Jose F.; Pena-Godino, Antonio; Rodriguez-Manfredi, Jose Antonio; Cordoba, Elizabeth; MEDA Team

2016-08-01

The Mars 2020 rover mission is part of NASA's Mars Exploration Program, a long-term effort of robotic exploration of the red planet. Designed to advance high-priority science goals for Mars exploration, the mission will address key questions about the potential for life on Mars. The mission will also provide opportunities to gather knowledge and demonstrate technologies that address the challenges of future human expeditions to Mars.The Mars Environmental Dynamics Analyzer (MEDA) is an integrated full suite of sensors designed to address the Mars 2020 mission objectives of characterization of dust size and morphology and surface weather measurements.MEDA system consists of one control unit and 10 separated sensor enclosures distributed in different positions along the Mars 2020 rover. MEDA is composed of an ARM-based control computer with its flight software application, two wind sensors including mixed ASICs inside, five air temperature sensors, one sky pointing camera complemented with 16 photo- detectors looking up and around, one thermal infrared sensor using five measurement bands, one relative humidity sensor, one pressure sensor and the harness that interconnects all of them. It is a complex system intended to operate in one of the harshest environments possible, the Mars surface, for many years to come.This will become a short term reality thanks to the combination of a strong international science team driving the science and system requirements working together with a powerful industrial organization to design and build the instrument. The instrument is being built right now, with its Critical Design Review at the end of 2016, and the flight model to be provided in 2018.This paper summarizes the main scientific objective of the MEDA instrument, the links between the Mission and the MEDA science objectives, and the challenging environmental Mars requirements. It will then focus on the engineered definition of the instrument, showing the overall

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.

Telecommunications and navigation systems design for manned Mars exploration missions

NASA Astrophysics Data System (ADS)

Hall, Justin R.; Hastrup, Rolf C.

1989-06-01

This paper discusses typical manned Mars exploration needs for telecommunications, including preliminary navigation support functions. It is a brief progress report on an ongoing study program within the current NASA JPL Deep Space Network (DSN) activities. A typical Mars exploration case is defined, and support approaches comparing microwave and optical frequency performance for both local in situ and Mars-earth links are described. Optical telecommunication and navigation technology development opportunities in a Mars exploration program are also identified. A local Mars system telecommunication relay and navigation capability for service support of all Mars missions has been proposed as part of an overall solar system communications network. The effects of light-time delay and occultations on real-time mission decision-making are discussed; the availability of increased local mass data storage may be more important than increasing peak data rates to earth. The long-term frequency use plan will most likely include a mix of microwave, millimeter-wave and optical link capabilities to meet a variety of deep space mission needs.

Telecommunications and navigation systems design for manned Mars exploration missions

NASA Technical Reports Server (NTRS)

Hall, Justin R.; Hastrup, Rolf C.

1989-01-01

This paper discusses typical manned Mars exploration needs for telecommunications, including preliminary navigation support functions. It is a brief progress report on an ongoing study program within the current NASA JPL Deep Space Network (DSN) activities. A typical Mars exploration case is defined, and support approaches comparing microwave and optical frequency performance for both local in situ and Mars-earth links are described. Optical telecommunication and navigation technology development opportunities in a Mars exploration program are also identified. A local Mars system telecommunication relay and navigation capability for service support of all Mars missions has been proposed as part of an overall solar system communications network. The effects of light-time delay and occultations on real-time mission decision-making are discussed; the availability of increased local mass data storage may be more important than increasing peak data rates to earth. The long-term frequency use plan will most likely include a mix of microwave, millimeter-wave and optical link capabilities to meet a variety of deep space mission needs.

A Lean, Fast Mars Round-trip Mission Architecture: Using Current Technologies for a Human Mission in the 2030s

NASA Technical Reports Server (NTRS)

Bailey, Lora; Folta, David; Barbee, Brent W.; Vaughn, Frank; Kirchman, Frank; Englander, Jacob; Campbell, Bruce; Thronson, Harley; Lin, Tzu Yu

2013-01-01

We present a lean fast-transfer architecture concept for a first human mission to Mars that utilizes current technologies and two pivotal parameters: an end-to-end Mars mission duration of approximately one year, and a deep space habitat of approximately 50 metric tons. These parameters were formulated by a 2012 deep space habitat study conducted at the NASA Johnson Space Center (JSC) that focused on a subset of recognized high- engineering-risk factors that may otherwise limit space travel to destinations such as Mars or near-Earth asteroid (NEA)s. With these constraints, we model and promote Mars mission opportunities in the 2030s enabled by a combination of on-orbit staging, mission element pre-positioning, and unique round-trip trajectories identified by state-of-the-art astrodynamics algorithms.

Exobiology and Future Mars Missions

NASA Technical Reports Server (NTRS)

Mckay, Christopher P. (Editor); Davis, Wanda, L. (Editor)

1989-01-01

Scientific questions associated with exobiology on Mars were considered and how these questions should be addressed on future Mars missions was determined. The mission that provided a focus for discussions was the Mars Rover/Sample Return Mission.

Objectives for Mars Orbital Missions in the 2020s: Report from a MEPAG Science Analysis Group

NASA Astrophysics Data System (ADS)

Zurek, R. W.; Campbell, B. A.; Diniega, S.; Lock, R. E.

2015-12-01

NASA Headquarters is looking at possible missions to Mars to follow the proposed 2020 Mars rover mission currently in development. One option being considered is a multi-functional orbiter, launched in the early 2020's, whose capabilities could address objectives in the following areas: • Replenishment of the telecommunications and reconnaissance infrastructure presently provided by the aging Mars Odyssey and Mars Reconnaissance Orbiters; • Scientific and technical progress on the NRC Planetary Science Decadal Survey priorities, updated MEPAG Goals, and/or follow-up of new discoveries; • Location and quantification of in situ resources for utilization by future robotic and human surface-based missions; and • Data needed to address Strategic Knowledge Gaps (SKGs), again for possible human missions. The Mars Exploration Program Analysis Group (MEPAG) was asked to prepare an analysis of possible science objectives and remote sensing capabilities that could be implemented by such a multi-purpose Mars orbiter launched in the 2022/24 timeframe. MEPAG conducted this analysis through formation of a Next Orbiter Science Analysis Group (NEX-SAG), which was chartered jointly by the NASA Science and Human Exploration Directorates. The SAG was asked to conduct this study within a range of mission capabilities, including the possible first use of Solar Electric Propulsion (SEP) in the Mars system. SEP could provide additional power enabling new payload components and possible changes in orbit (e.g., orbital inclination change) that permit different mission observational campaigns (e.g., polar and non-polar). Special attention was paid towards identifying synergies between science investigations, reconnaissance, and resource/SKG needs. We will present the findings and conclusions of this NEX-SAG regarding possible objectives for the next NASA Orbiter to Mars.

Integrated Human-Robotic Missions to the Moon and Mars: Mission Operations Design Implications

NASA Technical Reports Server (NTRS)

Mishkin, Andrew; Lee, Young; Korth, David; LeBlanc, Troy

2007-01-01

For most of the history of space exploration, human and robotic programs have been independent, and have responded to distinct requirements. The NASA Vision for Space Exploration calls for the return of humans to the Moon, and the eventual human exploration of Mars; the complexity of this range of missions will require an unprecedented use of automation and robotics in support of human crews. The challenges of human Mars missions, including roundtrip communications time delays of 6 to 40 minutes, interplanetary transit times of many months, and the need to manage lifecycle costs, will require the evolution of a new mission operations paradigm far less dependent on real-time monitoring and response by an Earthbound operations team. Robotic systems and automation will augment human capability, increase human safety by providing means to perform many tasks without requiring immediate human presence, and enable the transfer of traditional mission control tasks from the ground to crews. Developing and validating the new paradigm and its associated infrastructure may place requirements on operations design for nearer-term lunar missions. The authors, representing both the human and robotic mission operations communities, assess human lunar and Mars mission challenges, and consider how human-robot operations may be integrated to enable efficient joint operations, with the eventual emergence of a unified exploration operations culture.

Integrated Human-Robotic Missions to the Moon and Mars: Mission Operations Design Implications

NASA Technical Reports Server (NTRS)

Korth, David; LeBlanc, Troy; Mishkin, Andrew; Lee, Young

2006-01-01

For most of the history of space exploration, human and robotic programs have been independent, and have responded to distinct requirements. The NASA Vision for Space Exploration calls for the return of humans to the Moon, and the eventual human exploration of Mars; the complexity of this range of missions will require an unprecedented use of automation and robotics in support of human crews. The challenges of human Mars missions, including roundtrip communications time delays of 6 to 40 minutes, interplanetary transit times of many months, and the need to manage lifecycle costs, will require the evolution of a new mission operations paradigm far less dependent on real-time monitoring and response by an Earthbound operations team. Robotic systems and automation will augment human capability, increase human safety by providing means to perform many tasks without requiring immediate human presence, and enable the transfer of traditional mission control tasks from the ground to crews. Developing and validating the new paradigm and its associated infrastructure may place requirements on operations design for nearer-term lunar missions. The authors, representing both the human and robotic mission operations communities, assess human lunar and Mars mission challenges, and consider how human-robot operations may be integrated to enable efficient joint operations, with the eventual emergence of a unified exploration operations culture.

Dosimetry of a Deep-Space (Mars) Mission using Measurements from RAD on the Mars Science Laboratory

NASA Astrophysics Data System (ADS)

Hassler, D.; Zeitlin, C.; Ehresmann, B.; Wimmer-Schweingruber, R. F.; Guo, J.; Matthiae, D.; Reitz, G.

2017-12-01

The space radiation environment is one of the outstanding challenges of a manned deep-space mission to Mars. To improve our understanding and take us one step closer to enabling a human Mars to mission, the Radiation Assessment Detector (RAD) on the Mars Science Laboratory (MSL) has been characterizing the radiation environment, both during cruise and on the surface of Mars for the past 5 years. Perhaps the most significant difference between space radiation and radiation exposures from terrestrial exposures is that space radiation includes a significant component of heavy ions from Galactic Cosmic Rays (GCRs). Acute exposures from Solar Energetic Particles (SEPs) are possible during and around solar maximum, but the energies from SEPs are generally lower and more easily shielded. Thus the greater concern for long duration deep-space missions is the GCR exposure. In this presentation, I will review the the past 5 years of MSL RAD observations and discuss current approaches to radiation risk estimation used by NASA and other space agencies.

Mars Mission Surface Operation Simulation Testing of Lithium-Ion Batteries

NASA Technical Reports Server (NTRS)

Smart, M. C.; Bugga, R.; Whitcanack, L. D.; Chin, K. B.; Davies, E. D.; Surampudi, S.

2003-01-01

The objectives of this program are to 1) Assess viability of using lithium-ion technology for future NASA applications, with emphasis upon Mars landers and rovers which will operate on the planetary surface; 2) Support the JPL 2003 Mars Exploration Rover program to assist in the delivery and testing of a 8 AHr Lithium-Ion battery (Lithion/Yardney) which will power the rover; 3) Demonstrate applicability of using lithium-ion technologyfor future Mars applications: Mars 09 Science Laboratory (Smart Lander) and Future Mars Surface Operations (General). Mission simulation testing was carried out for cells and batteries on the Mars Surveyor 2001 Lander and the 2003 Mars Exploration Rover.

NASA Systems Analysis and Concepts Directorate Mission and Trade Study Analysis

NASA Technical Reports Server (NTRS)

Ricks, Wendell; Guynn, Mark; Hahn, Andrew; Lepsch, Roger; Mazanek, Dan; Dollyhigh, Sam

2006-01-01

Mission analysis, as practiced by the NASA Langley Research Center's Systems Analysis and Concepts Directorate (SACD), consists of activities used to define, assess, and evaluate a wide spectrum of aerospace systems for given requirements. The missions for these systems encompass a broad range from aviation to space exploration. The customer, who is usually another NASA organization or another government agency, often predefines the mission. Once a mission is defined, the goals and objectives that the system will need to meet are delineated and quantified. A number of alternative systems are then typically developed and assessed relative to these goals and objectives. This is done in order to determine the most favorable design approaches for further refinement. Trade studies are performed in order to understand the impact of a requirement on each system and to select among competing design options. Items varied in trade studies typically include: design variables or design constraints; technology and subsystem options; and operational approaches. The results of trade studies are often used to refine the mission and system requirements. SACD studies have been integral to the decision processes of many organizations for decades. Many recent examples of SACD mission and trade study analyses illustrate their excellence and influence. The SACD-led, Agency-wide effort to analyze a broad range of future human lunar exploration scenarios for NASA s Exploration Systems Mission Directorate (ESMD) and the Mars airplane design study in support of the Aerial Regional-scale Environment Survey of Mars (ARES) mission are two such examples. This paper describes SACD's mission and trade study analysis activities in general and presents the lunar exploration and Mars airplane studies as examples of type of work performed by the SACD.

Surface Nuclear Power for Human Mars Missions

NASA Technical Reports Server (NTRS)

Mason, Lee S.

1999-01-01

The Design Reference Mission for NASA's human mission to Mars indicates the desire for in-situ propellant production and bio-regenerative life systems to ease Earth launch requirements. These operations, combined with crew habitation and science, result in surface power requirements approaching 160 kilowatts. The power system, delivered on an early cargo mission, must be deployed and operational prior to crew departure from Earth. The most mass efficient means of satisfying these requirements is through the use of nuclear power. Studies have been performed to identify a potential system concept using a mobile cart to transport the power system away from the Mars lander and provide adequate separation between the reactor and crew. The studies included an assessment of reactor and power conversion technology options, selection of system and component redundancy, determination of optimum separation distance, and system performance sensitivity to some key operating parameters. The resulting system satisfies the key mission requirements including autonomous deployment, high reliability, and cost effectiveness at a overall system mass of 12 tonnes and a stowed volume of about 63 cu m.

Extreme Underwater Mission on This Week @NASA – July 29, 2016

NASA Image and Video Library

2016-07-29

The 21st NASA Extreme Environment Mission Operations got underway July 21 in the Florida Keys. NASA astronauts Reid Wiseman and Megan McArthur are part of the international crew of NEEMO-21 aquanauts performing research during the 16-day mission, which takes place about 60 feet below the surface of the Atlantic Ocean, in the Aquarius habitat – the world's only undersea science station. Simulated spacewalks are designed to evaluate tools and mission operation techniques that could be used on future space missions. NEEMO-21’s objectives include testing a mini DNA sequencer similar to the one NASA astronaut Kate Rubins also will test aboard the International Space Station, and a telemedicine device that will be used for future space applications. The mission also will simulate communications delays like those that would be encountered on a mission to Mars. Also, Space Launch System Work Platforms, All-Electric X-Plane Arrives, Asteroid Mission Technology, and NASA @Comic-Con International.

Mission Design Overview for Mars 2003/2005 Sample Return Mission

NASA Technical Reports Server (NTRS)

Lee, Wayne J.; DAmario, Louis A.; Roncoli, Ralph B.; Smith, John C.

2000-01-01

In May 2003, a new and exciting chapter in Mars exploration will begin with the launch of the first of three spacecraft that will collectively contribute toward the goal of delivering samples from the Red Planet to Earth. This mission is called Mars Sample Return (MSR) and will utilize both the 2003 and 2005 launch opportunities with an expected sample return in October 2008. NASA and CNES are major partners in this mission. The baseline mission mode selected for MSR is Mars orbit rendezvous (MOR), analogous in concept to the lunar orbit rendezvous (LOR) mode used for Apollo in the 1960s. Specifically, MSR will employ two NASA-provided landers of nearly identical design and one CNES-provided orbiter carrying a NASA payload of rendezvous sensors, orbital capture mechanisms, and an Earth entry vehicle (EEV). The high-level concept is that the landers will launch surface samples into Mars orbit, and the orbiter will retrieve the samples in orbit and then carry them back to Earth. The first element to depart for Mars will be one of the two landers. Currently, it is proposed that an intermediate class launch vehicle, such as the Boeing Delta 3 or Lockheed Martin Atlas 3A, will launch this 1800-kg lander from Cape Canaveral during the May 2003 opportunity. The lander will utilize a Type-1 transfer trajectory with an arrival at Mars in mid-December 2003. Landing will be aided by precision approach navigation and a guided hypersonic entry to achieve a touchdown accuracy of 10 km or better. Although the exact landing site has not yet been determined, it is estimated that lander resource constraints will limit the site to between 15 degrees north and south latitudes. Following touchdown, the lander will deploy a six-wheeled, 60-kg rover carrying an extensive suite of instruments designed to aid in the analysis of the local terrain and collection of core samples from selected rocks. The surface mission is currently designed around a concept called the surface traverse. Each

Nuclear risk assessment for the Mars 2020 mission environmental impact statement.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Clayton, Daniel James; Bignell, John L.; Jones, Christopher Andrew

In the summer of 2020, the National Aeronautics and Space Administration (NASA) plans to launch a spacecraft as part of the Mars 2020 mission. One option for the rover on the proposed spacecraft uses a Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) to provide continuous electrical and thermal power for the mission. An alternative option being considered is a set of solar panels for electrical power with up to 80 Light-Weight Radioisotope Heater Units (LWRHUs) for local component heating. Both the MMRTG and the LWRHUs use radioactive plutonium dioxide. NASA is preparing an Environmental Impact Statement (EIS) in accordance with the Nationalmore » Environmental Policy Act. The EIS will include information on the risks of mission accidents to the general public and on-site workers at the launch complex. This Nuclear Risk Assessment (NRA) addresses the responses of the MMRTG or LWRHU options to potential accident and abort conditions during the launch opportunity for the Mars 2020 mission and the associated consequences. This information provides the technical basis for the radiological risks of both options for the EIS.« less

Calculation of Operations Efficiency Factors for Mars Surface Missions

NASA Technical Reports Server (NTRS)

Laubach, Sharon

2014-01-01

The duration of a mission--and subsequently, the minimum spacecraft lifetime--is a key component in designing the capabilities of a spacecraft during mission formulation. However, determining the duration is not simply a function of how long it will take the spacecraft to execute the activities needed to achieve mission objectives. Instead, the effects of the interaction between the spacecraft and ground operators must also be taken into account. This paper describes a method, using "operations efficiency factors", to account for these effects for Mars surface missions. Typically, this level of analysis has not been performed until much later in the mission development cycle, and has not been able to influence mission or spacecraft design. Further, the notion of moving to sustainable operations during Prime Mission--and the effect that change would have on operations productivity and mission objective choices--has not been encountered until the most recent rover missions (MSL, the (now-cancelled) joint NASA-ESA 2018 Mars rover, and the proposed rover for Mars 2020). Since MSL had a single control center and sun-synchronous relay assets (like MER), estimates of productivity derived from MER prime and extended missions were used. However, Mars 2018's anticipated complexity (there would have been control centers in California and Italy, and a non-sun-synchronous relay asset) required the development of an explicit model of operations efficiency that could handle these complexities. In the case of the proposed Mars 2018 mission, the model was employed to assess the mission return of competing operations concepts, and as an input to component lifetime requirements. In this paper we provide examples of how to calculate the operations efficiency factor for a given operational configuration, and how to apply the factors to surface mission scenarios. This model can be applied to future missions to enable early effective trades between operations design, science mission

Mission and Design Sensitivities for Human Mars Landers Using Hypersonic Inflatable Aerodynamic Decelerators

NASA Technical Reports Server (NTRS)

Polsgrove, Tara P.; Thomas, Herbert D.; Dwyer Ciancio, Alicia; Collins, Tim; Samareh, Jamshid

2017-01-01

Landing humans on Mars is one of NASA's long term goals. NASA's Evolvable Mars Campaign (EMC) is focused on evaluating architectural trade options to define the capabilities and elements needed to sustain human presence on the surface of Mars. The EMC study teams have considered a variety of in-space propulsion options and surface mission options. Understanding how these choices affect the performance of the lander will allow a balanced optimization of this complex system of systems problem. This paper presents the effects of mission and vehicle design options on lander mass and performance. Beginning with Earth launch, options include fairing size assumptions, co-manifesting elements with the lander, and Earth-Moon vicinity operations. Capturing into Mars orbit using either aerocapture or propulsive capture is assessed. For entry, descent, and landing both storable as well as oxygen and methane propellant combinations are considered, engine thrust level is assessed, and sensitivity to landed payload mass is presented. This paper focuses on lander designs using the Hypersonic Inflatable Aerodynamic Decelerators, one of several entry system technologies currently considered for human missions.

NASA's strategy for Mars exploration in the 1990s and beyond

NASA Astrophysics Data System (ADS)

Huntress, W. T.; Feeley, T. J.; Boyce, J. M.

NASA's Office of Space Science is changing its approach to all its missions, both current and future. Budget realities are necessitating that we change the way we do business and the way we look at NASA's role in the U.S. Government. These challenges are being met by a new and innovative approach that focuses on achieving a balanced world-class space science program that requires less U.S. resources while providing an enhanced role for technology and education as integral components of our Research and Development (R&D) programs. Our Mars exploration plans, especially the Mars Surveyor program, are a key feature of this new NASA approach to space science. The Mars Surveyor program will be affordable, engaging to the public with global and close-up images of Mars, have high scientific value, employ a distributed risk strategy (two launches per opportunity), and will use significant advanced technologies.

MAPGEN : mixed initiative planning and scheduling for the Mars '03 MER mission

NASA Technical Reports Server (NTRS)

Ai-Chang, Mitchell; Bresina, John; Charest, Len; Jonsson, Ari; Hsu, Jennifer; Kanefsky, Bob; Maldague, Pierre; Morris, Paul; Rajan, Kanna; Yglesias, Jeffrey

2003-01-01

The Mars Exploration Rovers Mars '03 mission is one of NASA's most ambitious science missions to date. The rovers will be launched in the summer of 2003 with each rover carrying instruments to conduct remote and in-situ observation to elucidate the planet's past climate, water activity, and habitability. Science is the primary driver of MER and, as a consequence, making best use of the scientific instruments, within the available resources, is a crucial aspect of the mission. To address this critically, the MER project has selected MAPGEN (Mixed-Initiative Activity Plan GENerator) as an activity planning tool. MAPGEN combines two exiting systems, each with a strong heritage: APGEN the Activity Planning tool from the Jet Propulsion Laboratory and the Europs Planning/Scheduling system from NASA Ames Research Center. This paper discusses the issues arising from combining these tools in the context of this mission.

InSight, a Mars MIssion Artist Concept

NASA Image and Video Library

2012-02-28

This artist rendition is of the Interior exploration using Seismic Investigations, Geodesy and Heat Transport InSight Lander. InSight proposes to place a single geophysical lander on Mars to study its deep interior. 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/PIA13958

PERCIVAL mission to Mars

NASA Astrophysics Data System (ADS)

Reed, David W.; Lilley, Stewart; Sirman, Melinda; Bolton, Paul; Elliott, Susan; Hamilton, Doug; Nickelson, James; Shelton, Artemus

1992-12-01

With the downturn of the world economy, the priority of unmanned exploration of the solar system has been lowered. Instead of foregoing all missions to our neighbors in the solar system, a new philosophy of exploration mission design has evolved to insure the continued exploration of the solar system. The 'Discovery-class' design philosophy uses a low cost, limited mission, available technology spacecraft instead of the previous 'Voyager-class' design philosophy that uses a 'do-everything at any cost' spacecraft. The Percival Mission to Mars was proposed by Ares Industries as one of the new 'Discovery-class' of exploration missions. The spacecraft will be christened Percival in honor of American astronomer Percival Lowell who proposed the existence of life on Mars in the early twentieth century. The main purpose of the Percival mission to Mars is to collect and relay scientific data to Earth suitable for designing future manned and unmanned missions to Mars. The measurements and observations made by Percival will help future mission designers to choose among landing sites based on the feasibility and scientific interest of the sites. The primary measurements conducted by the Percival mission include gravity field determination, surface and atmospheric composition, sub-surface soil composition, sub-surface seismic activity, surface weather patterns, and surface imaging. These measurements will be taken from the orbiting Percival spacecraft and from surface penetrators deployed from Mars orbit. The design work for the Percival Mission to Mars was divided among four technical areas: Orbits and Propulsion System, Surface Penetrators, Gravity and Science Instruments, and Spacecraft Structure and Systems. The results for each of the technical areas is summarized and followed by a design cost analysis and recommendations for future analyses.

PERCIVAL mission to Mars

NASA Technical Reports Server (NTRS)

Reed, David W.; Lilley, Stewart; Sirman, Melinda; Bolton, Paul; Elliott, Susan; Hamilton, Doug; Nickelson, James; Shelton, Artemus

1992-01-01

With the downturn of the world economy, the priority of unmanned exploration of the solar system has been lowered. Instead of foregoing all missions to our neighbors in the solar system, a new philosophy of exploration mission design has evolved to insure the continued exploration of the solar system. The 'Discovery-class' design philosophy uses a low cost, limited mission, available technology spacecraft instead of the previous 'Voyager-class' design philosophy that uses a 'do-everything at any cost' spacecraft. The Percival Mission to Mars was proposed by Ares Industries as one of the new 'Discovery-class' of exploration missions. The spacecraft will be christened Percival in honor of American astronomer Percival Lowell who proposed the existence of life on Mars in the early twentieth century. The main purpose of the Percival mission to Mars is to collect and relay scientific data to Earth suitable for designing future manned and unmanned missions to Mars. The measurements and observations made by Percival will help future mission designers to choose among landing sites based on the feasibility and scientific interest of the sites. The primary measurements conducted by the Percival mission include gravity field determination, surface and atmospheric composition, sub-surface soil composition, sub-surface seismic activity, surface weather patterns, and surface imaging. These measurements will be taken from the orbiting Percival spacecraft and from surface penetrators deployed from Mars orbit. The design work for the Percival Mission to Mars was divided among four technical areas: Orbits and Propulsion System, Surface Penetrators, Gravity and Science Instruments, and Spacecraft Structure and Systems. The results for each of the technical areas is summarized and followed by a design cost analysis and recommendations for future analyses.

Mars Stratigraphy Mission

NASA Technical Reports Server (NTRS)

Budney, C. J.; Miller, S. L.; Cutts, J. A.

2000-01-01

The Mars Stratigraphy Mission lands a rover on the surface of Mars which descends down a cliff in Valles Marineris to study the stratigraphy. The rover carries a unique complement of instruments to analyze and age-date materials encountered during descent past 2 km of strata. The science objective for the Mars Stratigraphy Mission is to identify the geologic history of the layered deposits in the Valles Marineris region of Mars. This includes constraining the time interval for formation of these deposits by measuring the ages of various layers and determining the origin of the deposits (volcanic or sedimentary) by measuring their composition and imaging their morphology.

Mars Rover Sample Return mission study

NASA Technical Reports Server (NTRS)

Bourke, Roger D.

1989-01-01

The Mars Rover/Sample Return mission is examined as a precursor to a manned mission to Mars. The value of precursor missions is noted, using the Apollo lunar program as an example. The scientific objectives of the Mars Rover/Sample Return mission are listed and the basic mission plans are described. Consideration is given to the options for mission design, launch configurations, rover construction, and entry and lander design. Also, the potential for international cooperation on the Mars Rover/Sample Return mission is discussed.

Deep Space Gateway - Enabling Missions to Mars

NASA Technical Reports Server (NTRS)

Rucker, Michelle; Connolly, John

2017-01-01

There are many opportunities for commonality between Lunar vicinity and Mars mission hardware and operations. Best approach: Identify Mars mission risks that can be bought down with testing in the Lunar vicinity, then explore hardware and operational concepts that work for both missions with minimal compromise. Deep Space Transport will validate the systems and capabilities required to send humans to Mars orbit and return to Earth. Deep Space Gateway provides a convenient assembly, checkout, and refurbishment location to enable Mars missions Current deep space transport concept is to fly missions of increasing complexity: Shakedown cruise, Mars orbital mission, Mars surface mission; Mars surface mission would require additional elements.

An Overview of Mars Vicinity Transportation Concepts for a Human Mars Mission

NASA Technical Reports Server (NTRS)

Dexter, Carol E.; Kos, Larry

1998-01-01

To send a piloted mission to Mars, transportation systems must be developed for the Earth to Orbit, trans Mars injection (TMI), capture into Mars orbit, Mars descent, surface stay, Mars ascent, trans Earth injection (TEI), and Earth return phases. This paper presents a brief overview of the transportation systems for the Human Mars Mission (HMM) only in the vicinity of Mars. This includes: capture into Mars orbit, Mars descent, surface stay, and Mars ascent. Development of feasible mission scenarios now is important for identification of critical technology areas that must be developed to support future human missions. Although there is no funded human Mars mission today, architecture studies are focusing on missions traveling to Mars between 2011 and the early 2020's.

A Subjective Assessment of Alternative Mission Architecture Operations Concepts for the Human Exploration of Mars at NASA Using a Three-Dimensional Multi-Criteria Decision Making Model

NASA Technical Reports Server (NTRS)

Tavana, Madjid

2003-01-01

The primary driver for developing missions to send humans to other planets is to generate significant scientific return. NASA plans human planetary explorations with an acceptable level of risk consistent with other manned operations. Space exploration risks can not be completely eliminated. Therefore, an acceptable level of cost, technical, safety, schedule, and political risks and benefits must be established for exploratory missions. This study uses a three-dimensional multi-criteria decision making model to identify the risks and benefits associated with three alternative mission architecture operations concepts for the human exploration of Mars identified by the Mission Operations Directorate at Johnson Space Center. The three alternatives considered in this study include split, combo lander, and dual scenarios. The model considers the seven phases of the mission including: 1) Earth Vicinity/Departure; 2) Mars Transfer; 3) Mars Arrival; 4) Planetary Surface; 5) Mars Vicinity/Departure; 6) Earth Transfer; and 7) Earth Arrival. Analytic Hierarchy Process (AHP) and subjective probability estimation are used to captures the experts belief concerning the risks and benefits of the three alternative scenarios through a series of sequential, rational, and analytical processes.

Entry, Descent, and Landing for Human Mars Missions

NASA Technical Reports Server (NTRS)

Munk, Michelle M.; DwyerCianciolo, Alicia M.

2012-01-01

One of the most challenging aspects of a human mission to Mars is landing safely on the Martian surface. Mars has such low atmospheric density that decelerating large masses (tens of metric tons) requires methods that have not yet been demonstrated, and are not yet planned in future Mars missions. To identify the most promising options for Mars entry, descent, and landing, and to plan development of the needed technologies, NASA's Human Architecture Team (HAT) has refined candidate methods for emplacing needed elements of the human Mars exploration architecture (such as ascent vehicles and habitats) on the Mars surface. This paper explains the detailed, optimized simulations that have been developed to define the mass needed at Mars arrival to accomplish the entry, descent, and landing functions. Based on previous work, technology options for hypersonic deceleration include rigid, mid-L/D (lift-to-drag ratio) aeroshells, and inflatable aerodynamic decelerators (IADs). The hypersonic IADs, or HIADs, are about 20% less massive than the rigid vehicles, but both have their technology development challenges. For the supersonic regime, supersonic retropropulsion (SRP) is an attractive option, since a propulsive stage must be carried for terminal descent and can be ignited at higher speeds. The use of SRP eliminates the need for an additional deceleration system, but SRP is at a low Technology Readiness Level (TRL) in that the interacting plumes are not well-characterized, and their effect on vehicle stability has not been studied, to date. These architecture-level assessments have been used to define the key performance parameters and a technology development strategy for achieving the challenging mission of landing large payloads on Mars.

Launch and Assembly Reliability Analysis for Mars Human Space Exploration Missions

NASA Technical Reports Server (NTRS)

Cates, Grant R.; Stromgren, Chel; Cirillo, William M.; Goodliff, Kandyce E.

2013-01-01

NASA s long-range goal is focused upon human exploration of Mars. Missions to Mars will require campaigns of multiple launches to assemble Mars Transfer Vehicles in Earth orbit. Launch campaigns are subject to delays, launch vehicles can fail to place their payloads into the required orbit, and spacecraft may fail during the assembly process or while loitering prior to the Trans-Mars Injection (TMI) burn. Additionally, missions to Mars have constrained departure windows lasting approximately sixty days that repeat approximately every two years. Ensuring high reliability of launching and assembling all required elements in time to support the TMI window will be a key enabler to mission success. This paper describes an integrated methodology for analyzing and improving the reliability of the launch and assembly campaign phase. A discrete event simulation involves several pertinent risk factors including, but not limited to: manufacturing completion; transportation; ground processing; launch countdown; ascent; rendezvous and docking, assembly, and orbital operations leading up to TMI. The model accommodates varying numbers of launches, including the potential for spare launches. Having a spare launch capability provides significant improvement to mission success.

Deep Space Mission Applications for NEXT: NASA's Evolutionary Xenon Thruster

NASA Technical Reports Server (NTRS)

Oh, David; Benson, Scott; Witzberger, Kevin; Cupples, Michael

2004-01-01

NASA's Evolutionary Xenon Thruster (NEXT) is designed to address a need for advanced ion propulsion systems on certain future NASA deep space missions. This paper surveys seven potential missions that have been identified as being able to take advantage of the unique capabilities of NEXT. Two conceptual missions to Titan and Neptune are analyzed, and it is shown that ion thrusters could decrease launch mass and shorten trip time, to Titan compared to chemical propulsion. A potential Mars Sample return mission is described, and compassion made between a chemical mission and a NEXT based mission. Four possible near term applications to New Frontiers and Discovery class missions are described, and comparisons are made to chemical systems or existing NSTAR ion propulsion system performance. The results show that NEXT has potential performance and cost benefits for missions in the Discovery, New Frontiers, and larger mission classes.

Mars mission safety

DOE Office of Scientific and Technical Information (OSTI.GOV)

Buden, D.

1989-06-01

Precautions that need to be taken to assure safety on a manned Mars mission with nuclear thermal propulsion are briefly considered. What has been learned from the 1955 SNAP-10A operation of a nuclear reactor in space and from the Rover/NERVA project is reviewed. The ways that radiation hazards can be dealt with at various stages of a Mars mission are examined.

Report of the NASA Science Definition Team for the Mars Science Orbiter (MSO)

NASA Technical Reports Server (NTRS)

Smith, Michael

2007-01-01

NASA is considering that its Mars Exploration Program (MEP) will launch an orbiter to Mars in the 2013 launch opportunity. To further explore this opportunity, NASA has formed a Science Definition Team (SDT) for this orbiter mission, provisionally called the Mars Science Orbiter (MSO). Membership and leadership of the SDT are given in Appendix 1. Dr. Michael D. Smith chaired the SDT. The purpose of the SDT was to define the: 1) Scientific objectives of an MSO mission to be launched to Mars no earlier than the 2013 launch opportunity, building on the findings for Plan A [Atmospheric Signatures and Near-Surface Change] of the Mars Exploration Program Analysis Group (MEPAG) Second Science Analysis Group (SAG-2); 2) Science requirements of instruments that are most likely to make high priority measurements from the MSO platform, giving due consideration to the likely mission, spacecraft and programmatic constraints. The possibilities and opportunities for international partners to provide the needed instrumentation should be considered; 3) Desired orbits and mission profile for optimal scientific return in support of the scientific objectives, and the likely practical capabilities and the potential constraints defined by the science requirements; and 4) Potential science synergies with, or support for, future missions, such as a Mars Sample Return. This shall include imaging for evaluation and certification of future landing sites. As a starting point, the SDT was charged to assume spacecraft capabilities similar to those of the Mars Reconnaissance Orbiter (MRO). The SDT was further charged to assume that MSO would be scoped to support telecommunications relay of data from, and commands to, landed assets, over a 10 Earth year period following orbit insertion. Missions supported by MSO may include planned international missions such as EXOMARS. The MSO SDT study was conducted during October - December 2007. The SDT was directed to complete its work by December 15, 2007

InSight/SEIS@Mars Educational program : Sharing the InSight NASA mission and the Seismic Discovery of Mars with a International Network of classes

NASA Astrophysics Data System (ADS)

Lognonne, P. H.; Berenguer, J. L.; Sauron, A.; Denton, P.; Carrer, D.; Taber, J.; Bravo, T. K.; Gaboriaud, A.; Houston Jones, J.; Banerdt, W. B.; Martinuzzi, J. M.

2015-12-01

The InSIght mission will deploy in September 2016 a Geophysical Station on Mars, equipped with a suite of geophysical instruments, including 3 axis Very Broad Band Seismometer, 3 axis Short Period Seismometer, 3 axis Flux gate Magnetometer, Heat flow probe, geodetic beacon, infrasound/microbarometer, wind sensors and cameras. As for all NASA missions, Children and teenagers will be associated to the mission in the framework of the K12 InSight program, part of it being associated to the SEIS instrument.The two faces of the InSight/SEIS Education program are directed toward the promotion of Space Technologies and of Space Science.For Space technologies, this has already started with the InSight Elysium Educational project. The goal of the project, supported by CNES and performed by Technical High School near Toulouse, was the fabrication of a full scale mockup of the lander (see more at https://jeunes.cnes.fr/fr/elysium-le-jumeau-terrestre-dinsight ). The mockup was exhibited during the June, 2015 Paris air show. More than 300 students participated to the Elysium project.For Space Science, this will be made with the SEIS@Mars Educational project. Its plan is to transmit the SEIS data to a network of several hundred of middle and high schools worldwide, associated to existing "seismo(graph) at school" programs in the United States (https://www.iris.edu/hq/sis), France (www.edusismo.org) Switzerland (www.seismoatschool.ethz.ch) and United Kingdom (http://www.bgs.ac.uk/schoolseismology/). If the transmission of these data to the SEIS@school network will be automatic after their release by the NASA Planetary Data System, an earlier transmission will be made, especially after mid 2017, but also before through the integration of selected Schools to the project activities: the selected classrooms will perform the same activities as the project scientists. They will have to process rapidly the proprietary data in order to identify MarsQuake(s) and will be allowed to perform

Manned Mars mission cost estimate

NASA Technical Reports Server (NTRS)

Hamaker, Joseph; Smith, Keith

1986-01-01

The potential costs of several options of a manned Mars mission are examined. A cost estimating methodology based primarily on existing Marshall Space Flight Center (MSFC) parametric cost models is summarized. These models include the MSFC Space Station Cost Model and the MSFC Launch Vehicle Cost Model as well as other modes and techniques. The ground rules and assumptions of the cost estimating methodology are discussed and cost estimates presented for six potential mission options which were studied. The estimated manned Mars mission costs are compared to the cost of the somewhat analogous Apollo Program cost after normalizing the Apollo cost to the environment and ground rules of the manned Mars missions. It is concluded that a manned Mars mission, as currently defined, could be accomplished for under $30 billion in 1985 dollars excluding launch vehicle development and mission operations.

Moon-Mars Analogue Mission (EuroMoonMars 1 at the Mars Desert Research Station)

NASA Astrophysics Data System (ADS)

Lia Schlacht, Irene; Voute, Sara; Irwin, Stacy; Foing, Bernard H.; Stoker, Carol R.; Westenberg, Artemis

The Mars Desert Research Station (MDRS) is situated in an analogue habitat-based Martian environment, designed for missions to determine the knowledge and equipment necessary for successful future planetary exploration. For this purpose, a crew of six people worked and lived together in a closed-system environment. They performed habitability experiments within the dwelling and conducted Extra-Vehicular Activities (EVAs) for two weeks (20 Feb to 6 Mar 2010) and were guided externally by mission support, called "Earth" within the simulation. Crew 91, an international, mixed-gender, and multidisciplinary group, has completed several studies during the first mission of the EuroMoonMars campaign. The crew is composed of an Italian designer and human factors specialist, a Dutch geologist, an American physicist, and three French aerospace engineering students from Ecole de l'Air, all with ages between 21 and 31. Each crewmember worked on personal research and fulfilled a unique role within the group: commander, executive officer, engineer, health and safety officer, scientist, and journalist. The expedition focused on human factors, performance, communication, health and safety pro-tocols, and EVA procedures. The engineers' projects aimed to improve rover manoeuvrability, far-field communication, and data exchanges between the base and the rover or astronaut. The crew physicist evaluated dust control methods inside and outside the habitat. The geologist tested planetary geological sampling procedures. The crew designer investigated performance and overall habitability in the context of the Mars Habitability Experiment from the Extreme-Design group. During the mission the crew also participated in the Food Study and in the Ethospace study, managed by external groups. The poster will present crew dynamics, scientific results and daily schedule from a Human Factors perspective. Main co-sponsors and collaborators: ILEWG, ESA ESTEC, NASA Ames, Ecole de l'Air, SKOR, Extreme

Mars 2020 Science Rover: Science Goals and Mission Concept

NASA Astrophysics Data System (ADS)

Mustard, John F.; Beaty, D.; Bass, D.

2013-10-01

The Mars 2020 Science Definition Team (SDT), chartered in January 2013 by NASA, formulated a spacecraft mission concept for a science-focused, highly mobile rover to explore and investigate in detail a site on Mars that likely was once habitable. The mission, based on the Mars Science Laboratory landing and rover systems, would address, within a cost- and time-constrained framework, four objectives: (A) Explore an astrobiologically relevant ancient environment on Mars to decipher its geological processes and history, including the assessment of past habitability; (B) Assess the biosignature preservation potential within the selected geological environment and search for potential biosignatures; (C) Demonstrate significant technical progress towards the future return of scientifically selected, well-documented samples to Earth; and (D) provide an opportunity for contributed instruments from Human Exploration or Space Technology Programs. The SDT addressed the four mission objectives and six additional charter-specified tasks independently while specifically looking for synergy among them. Objectives A and B are each ends unto themselves, while Objective A is also the means by which samples are selected for objective B, and together they motivate and inform Objective C. The SDT also found that Objective D goals are well aligned with A through C. Critically, Objectives A, B, and C as an ensemble brought the SDT to the conclusion that exploration oriented toward both astrobiology and the preparation of a returnable cache of scientifically selected, well documented surface samples is the only acceptable mission concept. Importantly the SDT concluded that the measurements needed to attain these objectives were essentially identical, consisting of six types of field measurements: 1) context imaging 2) context mineralogy, 3) fine-scale imaging, 4) fine-scale mineralogy, 5) fine-scale elemental chemistry, and 6) organic matter detection. The mission concept fully addresses

Evolvable Mars Campaign Long Duration Habitation Strategies: Architectural Approaches to Enable Human Exploration Missions

NASA Technical Reports Server (NTRS)

Simon, Matthew A.; Toups, Larry; Howe, A. Scott; Wald, Samuel I.

2015-01-01

The Evolvable Mars Campaign (EMC) is the current NASA Mars mission planning effort which seeks to establish sustainable, realistic strategies to enable crewed Mars missions in the mid-2030s timeframe. The primary outcome of the Evolvable Mars Campaign is not to produce "The Plan" for sending humans to Mars, but instead its intent is to inform the Human Exploration and Operations Mission Directorate near-term key decisions and investment priorities to prepare for those types of missions. The FY'15 EMC effort focused upon analysis of integrated mission architectures to identify technically appealing transportation strategies, logistics build-up strategies, and vehicle designs for reaching and exploring Mars moons and Mars surface. As part of the development of this campaign, long duration habitats are required which are capable of supporting crew with limited resupply and crew abort during the Mars transit, Mars moons, and Mars surface segments of EMC missions. In particular, the EMC design team sought to design a single, affordable habitation system whose manufactured units could be outfitted uniquely for each of these missions and reused for multiple crewed missions. This habitat system must provide all of the functionality to safely support 4 crew for long durations while meeting mass and volume constraints for each of the mission segments set by the chosen transportation architecture and propulsion technologies. This paper describes several proposed long-duration habitation strategies to enable the Evolvable Mars Campaign through improvements in mass, cost, and reusability, and presents results of analysis to compare the options and identify promising solutions. The concepts investigated include several monolithic concepts: monolithic clean sheet designs, and concepts which leverage the co-manifested payload capability of NASA's Space Launch System (SLS) to deliver habitable elements within the Universal Payload Adaptor between the SLS upper stage and the Orion

Solar Electric Propulsion for Future NASA Missions

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.; Oleson, Steven R.; Mercer, Carolyn R.

2015-01-01

Use of high-power solar arrays, at power levels ranging from approximately 500 KW to several megawatts, has been proposed for a solar-electric propulsion (SEP) demonstration mission, using a photovoltaic array to provide energy to a high-power xenon-fueled engine. One of the proposed applications of the high-power SEP technology is a mission to rendezvous with an asteroid and move it into lunar orbit for human exploration, the Asteroid Retrieval mission. The Solar Electric Propulsion project is dedicated to developing critical technologies to enable trips to further away destinations such as Mars or asteroids. NASA needs to reduce the cost of these ambitious exploration missions. High power and high efficiency SEP systems will require much less propellant to meet those requirements.

Architectural design proposal for a Martian base to continue NASA Mars Design Reference Mission

NASA Astrophysics Data System (ADS)

Kozicki, Janek

The issue of extraterrestrial bases has recently been a very vivid one. There are orbital stations currently existing and humans will travel to Mars around 2030. They will need stations established there, which will provide them the proper living conditions. Firstly, it might be a small module brought from Earth (e.g. NASA Mars Design Reference Mission module (DRM)), in later stages equivalents of Earth houses may be built from local resources. The goal of this paper is to propose an architectural design for an intermediate stage — for a larger habitable unit transported from Earth. It is inspired by terrestrial portable architecture ideas. A pneumatic structure requires small volume during transportation. However, it provides large habitable space after deployment. It is designed for transport by DRM transportation module and its deployment is considerable easy and brief. An architectural solution analogous to a terrestrial house with a studio and a workshop was assumed. Its form was a result of technical and environmental limitations, and the need for an ergonomic interior. The spatial placement of following zones was carefully considered: residential, agricultural and science, as well as a garage with a workshop, transportation routes, and a control and communication center. The issues of Life Support System, energy, food, water and waste recycling were also discussed. This Martian base was designed to be crewed by a team of eight people to stay on Mars for at least 1.5 year. An Open Plan architectural solution was assumed in pneumatic modules, with a high level of modularity. Walls of standardized sizes with zip-fasteners allow free rearrangement of the interior to adapt to a new situation (e.g. damage of one of the pneumatic modules or a psychological ,,need of a change"). The architectural design focuses on ergonomic and psychological aspects of longer stay in hostile Martian environment. This solution provides Martian crew with a comfortable habitable

Advance Inspection of NASA Next Mars Landing Site

NASA Image and Video Library

2017-03-29

This map shows footprints of images taken from Mars orbit by the High Resolution Imaging Science Experiment (HiRISE) camera as part of advance analysis of the area where NASA's InSight mission will land in 2018. The final planned image of the set is targeted to fill in the yellow-outlined rectangle on March 30, 2017. HiRISE is one of six science instruments on NASA's Mars Reconnaissance Orbiter, which reached Mars in 2006 and surpassed 50,000 orbits on March 27, 2017. The map covers an area about 100 miles (160 kilometers) across. HiRISE has been used since 2006 to inspect dozens of candidate landing sites on Mars, including the sites where the Phoenix and Curiosity missions landed in 2008 and 2012. The site selected for InSight's Nov. 26, 2018, landing is on a flat plain in the Elysium Planitia region of Mars, between 4 and 5 degrees north of the equator. HiRISE images are detailed enough to reveal individual boulders big enough to be a landing hazard. The March 30 observation that completes the planned advance imaging of this landing area brings the number of HiRISE images of the area to 73. Some are pairs covering the same ground. Overlapping observations provide stereoscopic, 3-D information for evaluating characteristics such as slopes. On this map, coverage by stereo pairs is coded in pale blue, compared to the gray-green of single HiRISE image footprints. The ellipses on the map are about 81 miles (130 kilometers) west-to-east by about 17 miles (27 kilometers) north-to-south. InSight has about 99 percent odds of landing within the ellipse for which it is targeted. The three ellipses indicate landing expectations for three of the possible InSight launch dates: white outline for launch at the start of the launch period, on May 5, 2018; blue for launch on May 26, 2018; orange for launch on June 8, 2018. InSight -- an acronym for "Interior Exploration using Seismic Investigations, Geodesy and Heat Transport" -- will study the deep interior of Mars to improve

Diverse Orbits Around Mars Graphic

NASA Image and Video Library

2015-05-04

This graphic depicts the relative shapes and distances from Mars for five active orbiter missions plus the planet's two natural satellites. It illustrates the potential for intersections of the spacecraft orbits. The number of active orbiter missions at Mars increased from three to five in 2014. With the increased traffic, NASA has augmented a process for anticipating orbit intersections and avoiding collisions. NASA's Mars Odyssey and MRO (Mars Reconnaissance Orbiter) travel near-circular orbits. The European Space Agency's Mars Express, NASA's MAVEN (Mars Atmosphere and Volatile Evolution) and India's MOM (Mars Orbiter Mission), travel more elliptical orbits. Phobos and Deimos are the two natural moons of Mars. http://photojournal.jpl.nasa.gov/catalog/PIA19396

Mission and Navigation Design for the 2009 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

D'Amario, Louis A.

2008-01-01

NASA s Mars Science Laboratory mission will launch the next mobile science laboratory to Mars in the fall of 2009 with arrival at Mars occurring in the summer of 2010. A heat shield, parachute, and rocket-powered descent stage, including a sky crane, will be used to land the rover safely on the surface of Mars. The direction of the atmospheric entry vehicle lift vector will be controlled by a hypersonic entry guidance algorithm to compensate for entry trajectory errors and counteract atmospheric and aerodynamic dispersions. The key challenges for mission design are (1) develop a launch/arrival strategy that provides communications coverage during the Entry, Descent, and Landing phase either from an X-band direct-to-Earth link or from a Ultra High Frequency link to the Mars Reconnaissance Orbiter for landing latitudes between 30 deg North and 30 deg South, while satisfying mission constraints on Earth departure energy and Mars atmospheric entry speed, and (2) generate Earth-departure targets for the Atlas V-541 launch vehicle for the specified launch/arrival strategy. The launch/arrival strategy employs a 30-day baseline launch period and a 27-day extended launch period with varying arrival dates at Mars. The key challenges for navigation design are (1) deliver the spacecraft to the atmospheric entry interface point (Mars radius of 3522.2 km) with an inertial entry flight path angle error of +/- 0.20 deg (3 sigma), (2) provide knowledge of the entry state vector accurate to +/- 2.8 km (3 sigma) in position and +/- 2.0 m/s (3 sigma) in velocity for initializing the entry guidance algorithm, and (3) ensure a 99% probability of successful delivery at Mars with respect to available cruise stage propellant. Orbit determination is accomplished via ground processing of multiple complimentary radiometric data types: Doppler, range, and Delta-Differential One-way Ranging (a Very Long Baseline Interferometry measurement). The navigation strategy makes use of up to five

Mars Hybrid Propulsion System Trajectory Analysis. Part I; Crew Missions

NASA Technical Reports Server (NTRS)

Chai, Patrick R.; Merrill, Raymond G.; Qu, Min

2015-01-01

NASAs Human spaceflight Architecture team is developing a reusable hybrid transportation architecture in which both chemical and electric propulsion systems are used to send crew and cargo to Mars destinations such as Phobos, Deimos, the surface of Mars, and other orbits around Mars. By combining chemical and electrical propulsion into a single space- ship and applying each where it is more effective, the hybrid architecture enables a series of Mars trajectories that are more fuel-efficient than an all chemical architecture without significant increases in flight times. This paper provides the analysis of the interplanetary segments of the three Evolvable Mars Campaign crew missions to Mars using the hybrid transportation architecture. The trajectory analysis provides departure and arrival dates and propellant needs for the three crew missions that are used by the campaign analysis team for campaign build-up and logistics aggregation analysis. Sensitivity analyses were performed to investigate the impact of mass growth, departure window, and propulsion system performance on the hybrid transportation architecture. The results and system analysis from this paper contribute to analyses of the other human spaceflight architecture team tasks and feed into the definition of the Evolvable Mars Campaign.

2001 Mars Odyssey Mission

NASA Technical Reports Server (NTRS)

Varghese, Philip

2008-01-01

This viewgraph presentation reviews the 2001 Mars Odyssey Mission. The contents include: 1) Mission Overview; 2) Current Scope of Work: 3) Facilities; 4) Critical Role of DSN; 5) Relay as Mission Supplement; 6) Current Mars Telecom Infrastructure; 7) PHX EDL Comm Overview; 8) EDL Geometry (Entry through Landing); 9) Phoenix Support; 10) Preparations for Phoenix; 11) EDL Support Timeline; 12) One Year Rolling Schedule; 13) E3 Rationale; and 14) Spacecraft Status.

HEDS-UP Mars Exploration Forum

NASA Technical Reports Server (NTRS)

Budden, Nancy Ann (Editor); Duke, Micheal B. (Editor)

1998-01-01

In the early 1990s, Duke and Budden convened a series of workshops addressing mission rationale, exploration objectives, and key constraints and issues facing human crews on Mars. The focal point was "why" the U.S. should fly humans to Mars. In the mid-1990s, strategies for a Mars mission matured and evolved, driven formally by NASA Johnson Space Center's Office of Exploration. In 1997, NASA published a report capturing the current thinking: the NASA Mars Reference Mission. In the 1997-1998 school year, HEDS-UP sponsored six universities to conduct design studies on Mars exploration, using the Reference Mission as a basis for their work. The 1998 Mars Exploration Forum presents the results of these university studies, suggesting "how" we might explore Mars, in terms of specific technical components that would enable human missions to Mars. A primary objective of the HEDS-UP Mars Exploration Forum was to provide a forum for active interaction among NASA, industry, and the university community on the subject of human missions to Mars. NASA scientists and engineers were asked to present the state of exploration for Mars mission options currently under study. This status "snapshot" of current Mars strategies set the stage for the six HEDS-UP universities to present their final design study results. Finally, a panel of industry experts discussed readiness for human missions to Mars as it pertains to the aerospace industries and technologies. A robust poster session provided the backdrop for government-industry-university discussions and allowed for feedback to NASA on the Mars Reference Mission. The common thread woven through the two days was discussion of technologies, proven and emerging, that will be required to launch, land, and sustain human crews on the Red Planet. As this decade (and indeed this millenium) draws to a close, Mars will continue to loom in our sights as the next target for human space exploration. It is our hope that the efforts of the Mars

Power Requirements for The NASA Mars Design Reference Architecture (DRA) 5.0

NASA Technical Reports Server (NTRS)

Cataldo, Robert L.

2009-01-01

This paper summarizes the power systems analysis results from NASA s recent Mars DRA 5.0 study which examined three architecture options and resulting mission requirements for a human Mars landing mission in the post-2030 timeframe. DRA 5.0 features a long approximately 500 day surface stay split mission using separate cargo and crewed Mars transfer vehicles. Two cargo flights, utilizing minimum energy trajectories, pre-deploy a cargo lander to the surface and a habitat lander into a 24-hour elliptical Mars parking orbit where it remains until the arrival of the crew during the next mission opportunity approximately 26 months later. The pre-deployment of cargo poses unique challenges for set-up and emplacement of surface assets that results in the need for self or robotically deployed designs. Three surface architecture options were evaluated for breadth of science content, extent of exploration range/capability and variations in system concepts and technology. This paper describes the power requirements for the surface operations of the three mission options, power system analyses including discussion of the nuclear fission, solar photovoltaic and radioisotope concepts for main base power and long range mobility.

Mars ISRU for Production of Mission Critical Consumables - Options, Recent Studies, and Current State of the Art

NASA Technical Reports Server (NTRS)

Sanders, G. B.; Paz, A.; Oryshchyn, L.; Araghi, K.; Muscatello, A.; Linne, D.; Kleinhenz, J.; Peters, T.

2015-01-01

In 1978, a ground breaking paper titled, "Feasibility of Rocket Propellant Production on Mars" by Ash, Dowler, and Varsi discussed how ascent propellants could be manufactured on the Mars surface from carbon dioxide collected from the atmosphere to reduce launch mass. Since then, the concept of making mission critical consumables such as propellants, fuel cell reactants, and life support consumables from local resources, commonly known as In-Situ Resource Utilization (ISRU), for robotic and human missions to Mars has been studied many times. In the late 1990's, NASA initiated a series of Mars Human Design Reference Missions (DRMs), the first of which was released in 1997. These studies primarily focused on evaluating the impact of making propellants on Mars for crew ascent to Mars orbit, but creating large caches of life support consumables (water & oxygen) as a backup for regenerative life support systems for long-duration surface stays (>500 days) was also considered in Mars DRM 3.0. Until science data from the Mars Odyssey orbiter and subsequent robotic missions revealed that water may be widely accessable across the surface of Mars, prior Mars ISRU studies were limited to processing Mars atmospheric resources (carbon dioxide, nitrogen, argon, oxygen, and water vapor). In December 2007, NASA completed the Mars Human Design Reference Architecture (DRA) 5.0 study which considered water on Mars as a potential resource for the first time in a human mission architecture. While knowledge of both water resources on Mars and the hardware required to excavate and extract the water were very preliminary, the study concluded that a significant reduction in mass and significant enhancements to the mission architecture were possible if Mars water resources were utilized. Two subsequent Mars ISRU studies aimed at reexamining ISRU technologies, processing options, and advancements in the state-of-the-art since 2007 and to better understand the volume and packaging associated

Radiation hazard during a manned mission to Mars.

PubMed

Jäkel, Oliver

2004-01-01

The radiation hazard of interplanetary flights is currently one of the major obstacles to manned missions to Mars. Highly energetic, heavy-charged particles from galactic cosmic radiation can not be sufficiently shielded in space vehicles. The long-term radiation effects to humans of these particles are largely unknown. In addition, unpredictable storms of solar particles may expose the crew to doses that lead to acute radiation effects. A manned flight to Mars currently seems to be a high-risk adventure. This article provides an overview on the radiation sources and risks for a crew on a manned flight to Mars, as currently estimated by scientists of the US National Administration for Space and Aeronautics (NASA) and the Space Studies Board (SSB) of the US National Research Council.

Analysis of a spacecraft life support system for a Mars mission.

PubMed

Czupalla, M; Aponte, V; Chappell, S; Klaus, D

2004-01-01

This report summarizes a trade study conducted as part of the Fall 2002 semester Spacecraft Life Support System Design course (ASEN 5116) in the Aerospace Engineering Sciences Department at the University of Colorado. It presents an analysis of current life support system technologies and a preliminary design of an integrated system for supporting humans during transit to and on the surface of the planet Mars. This effort was based on the NASA Design Reference Mission (DRM) for the human exploration of Mars [NASA Design Reference Mission (DRM) for Mars, Addendum 3.0, from the world wide web: http://exploration.jsc.nasa.gov/marsref/contents.html.]. The integrated design was broken into four subsystems: Water Management, Atmosphere Management, Waste Processing, and Food Supply. The process started with the derivation of top-level requirements from the DRM. Additional system and subsystem level assumptions were added where clarification was needed. Candidate technologies were identified and characterized based on performance factors. Trade studies were then conducted for each subsystem. The resulting technologies were integrated into an overall design solution using mass flow relationships. The system level trade study yielded two different configurations--one for the transit to Mars and another for the surface habitat, which included in situ resource utilization. Equivalent System Mass analyses were used to compare each design against an open-loop (non-regenerable) baseline system. c2003 International Astronautical Federation. Published by Elsevier Ltd. All rights reserved.

NASA Participates in Mars Day Activities at National Air and Space Museum

NASA Image and Video Library

2017-07-21

NASA participated in the July 21 Mars Day event at the Smithsonian National Air and Space Museum (NASM) in Washington, D.C. The museum hosts this annual event, which includes exhibits, speakers and educational activities, to celebrate the Red Planet.    Jim Green, director of NASA’s Planetary Science Division, along with other NASA scientists and engineers, was on hand to talk with visitors about the agency’s Mars exploration missions. There was also a Mars concept rover on display, developed by vehicle designers the Parker Brothers with advice from NASA. The vehicle is currently on an East Coast tour from its home base at the Kennedy Space Center Visitor’s Complex in Florida. The concept rover is designed to engage and educate the public by demonstrating the types of features and equipment a future human exploration vehicle may need.

Performance Testing of Yardney Li-Ion Cells and Batteries in Support of Future NASA Missions

NASA Technical Reports Server (NTRS)

Smart, M. C.; Ratnakumar, B. V.; Whitcanack, L. D.; Puglia, F. J.; Santee, S.; Gitzendanner, R.

2009-01-01

NASA requires lightweight rechargeable batteries for future missions to Mars and the outer planets that are capable of operating over a wide range of temperatures, with high specific energy and energy densities. Due to the attractive performance characteristics, Li-ion batteries have been identified as the battery chemistry of choice for a number of future applications. For example, JPL is planning to launch another unmanned rover mission to the planet Mars. This mission, referred to as the Mars Science Laboratory (MSL), will involve the use of a rover that is much larger than the previously developed Spirit and Opportunity Rovers for the 2003 Mars Exploration Rover (MER) mission, that are currently still in operation on the surface of the planet after more than five years. Part of the reason that the MER rovers have operated so successfully, far exceeding the required mission duration of 90 sols, is that they possess robust Li-ion batteries, manufactured by Yardney Technical Products, which have demonstrated excellent life characteristics. Given the excellent performance characteristics displayed, similar Li-ion batteries have been projected to successfully meet the mission requirements of the up-coming MSL mission. In addition to future missions to Mars, Li-ion technology is attractive for a number of other future NASA applications which require high specific energy, rechargeable batteries. To ascertain the viability of using Li-ion batteries for these applications, a number of performance validation tests have been performed on both Yardney cells and batteries of various sizes. These tests include mission simulation tests, charge and discharge rate characterization testing, cycle life testing under various conditions, and storage testing.

The Role of Synthetic Biology in NASA's Missions

NASA Technical Reports Server (NTRS)

Rothschild, Lynn J.

2016-01-01

The time has come to for NASA to exploit synthetic biology in pursuit of its missions, including aeronautics, earth science, astrobiology and most notably, human exploration. Conversely, NASA advances the fundamental technology of synthetic biology as no one else can because of its unique expertise in the origin of life and life in extreme environments, including the potential for alternate life forms. This enables unique, creative "game changing" advances. NASA's requirement for minimizing upmass in flight will also drive the field toward miniaturization and automation. These drivers will greatly increase the utility of synthetic biology solutions for military, health in remote areas and commercial purposes. To this end, we have begun a program at NASA to explore the use of synthetic biology in NASA's missions, particular space exploration. As part of this program, we began hosting an iGEM team of undergraduates drawn from Brown and Stanford Universities to conduct synthetic biology research at NASA Ames Research Center. The 2011 team (http://2011.igem.org/Team:Brown-Stanford) produced an award-winning project on using synthetic biology as a basis for a human Mars settlement.

The Mars Express - NASA Project at JPL

NASA Technical Reports Server (NTRS)

Thompson, Thomas W.; Horttor, Richard L.; Acton, C. H., Jr.; Zamani, P.; Johnson, W. T. K.; Plaut, J. J.; Holmes, D. P.; No, S.; Asmar, S. W.; Goltz, G.

2006-01-01

This viewgraph presentation gives a general overview of the Mars Express NASA Project at JPL. The contents include: 1) Mars Express/NASA Project Overview; 2) Experiment-Investigator Matrix; 3) Mars Express Support of NASA's Mars Exploration Objectives; 4) U.S./NASA Support of Mars Express; 5) Mars Express Schedule (2003-2007); 6) Mars Express Data Rates; 7) MARSIS Overview Results; 8) MARSIS with Antennas Deployed; 9) MARSIS Science Objectives; 10) Mars Advanced Radar for Subsurface and Ionospheric Sounding (MARSIS) Experiment Overview; 11) Mars Express Orbit Evolution; 12) MARSIS Science - Subsurface Sounding; 13) MARSIS-North Polar Ice Cap; 14) MARSIS Data-Buried Basin; 15) MARSIS over a Crater Basin; 16) MARSIS-Buried Basin; 17) Ionogram - Orbit 2032 (example from Science paper); 18) Ionogram-Orbit 2018 (example from Science paper); and 19) Recent MARSIS Results ESA Press Releases.

Planning Mars Memory: Learning from the Mer Mission

NASA Technical Reports Server (NTRS)

Linde, Charlotte

2004-01-01

Knowledge management for space exploration is part of a multi-generational effort at recognizing, preserving and transmitting learning. Each mission should be built on the learning, of both successes and failures, derived from previous missions. Knowledge management begins with learning, and the recognition that this learning has produced knowledge. The Mars Exploration Rover mission provides us with an opportunity to track how learning occurs, how it is recorded, and whether the representations of this learning will be optimally useful for subsequent missions. This paper focuses on the MER science and engineering teams during Rover operations. A NASA team conducted an observational study of the ongoing work and learning of the these teams. Learning occurred in a wide variety of areas: how to run two teams on Mars time for three months; how to use the instruments within the constraints of the martian environment, the deep space network and the mission requirements; how to plan science strategy; how best to use the available software tools. This learning is preserved in many ways. Primarily it resides in peoples memories, to be carried on to the next mission. It is also encoded in stones, in programming sequences, in published reports, and in lessons learned activities, Studying learning and knowledge development as it happens allows us to suggest proactive ways of capturing and using it across multiple missions and generations.

JPL-20180505-INSIGHf-0001-NASA InSight on Its Way to Mars

NASA Image and Video Library

2018-05-05

Making history as the first interplanetary launch from the West Coast, NASA's InSight spacecraft is now soaring towards Mars. The spacecraft, which lifted off from Vandenberg Air Force Base in Central California, will be the first mission to study the deep interior of Mars. Its instruments include a seismometer to detect marsquakes for the first time and a heat flow p[robe that will embed itself as deep as about 16 feet (5 meters) below the surface of Mars.

Comparison of mission design options for manned Mars missions

NASA Technical Reports Server (NTRS)

Babb, Gus R.; Stump, William R.

1986-01-01

A number of manned Mars mission types, propulsion systems, and operational techniques are compared. Conjunction and opposition class missions for cryogenic, hybrid (cryo/storable), and NERVA propulsion concepts are addressed. In addition, both Earth and Mars orbit aerobraking, direct entry of landers, hyperbolic rendezvous, and electric propulsion cases are examined. A common payload to Mars was used for all cases. The basic figure of merit used was weight in low Earth orbit (LEO) at mission initiation. This is roughly proportional to launch costs.

SOLAR SYSTEM EXPLORATION: A More Cautious NASA Sets Plans for Mars.

PubMed

Lawler, A

2000-11-03

Twice burned by mission failures last year, NASA managers last week unveiled a new 15-year blueprint for Mars exploration. The revamped strategy allows for doing more science, but at a slower pace, while delaying a sample return until well into the next decade.

NASA's Analog Missions: Driving Exploration Through Innovative Testing

NASA Technical Reports Server (NTRS)

Reagan, Marcum L.; Janoiko, Barbara A.; Parker, Michele L.; Johnson, James E.; Chappell, Steven P.; Abercromby, Andrew F.

2012-01-01

Human exploration beyond low-Earth orbit (LEO) will require a unique collection of advanced, innovative technologies and the precise execution of complex and challenging operational concepts. One tool we in the Analog Missions Project at the National Aeronautics and Space Administration (NASA) utilize to validate exploration system architecture concepts and conduct technology demonstrations, while gaining a deeper understanding of system-wide technical and operational challenges, is our analog missions. Analog missions are multi-disciplinary activities that test multiple features of future spaceflight missions in an integrated fashion to gain a deeper understanding of system-level interactions and integrated operations. These missions frequently occur in remote and extreme environments that are representative in one or more ways to that of future spaceflight destinations. They allow us to test robotics, vehicle prototypes, habitats, communications systems, in-situ resource utilization, and human performance as it relates to these technologies. And they allow us to validate architectural concepts, conduct technology demonstrations, and gain a deeper understanding of system-wide technical and operational challenges needed to support crewed missions beyond LEO. As NASA develops a capability driven architecture for transporting crew to a variety of space environments, including the moon, near-Earth asteroids (NEA), Mars, and other destinations, it will use its analog missions to gather requirements and develop the technologies that are necessary to ensure successful human exploration beyond LEO. Currently, there are four analog mission platforms: Research and Technology Studies (RATS), NASA s Extreme Environment Mission Operations (NEEMO), In-Situ Resource Utilization (ISRU), and International Space Station (ISS) Test bed for Analog Research (ISTAR).

A consensus approach to planetary protection requirements: recommendations for Mars lander missions

NASA Technical Reports Server (NTRS)

Rummel, J. D.; Meyer, M. A.

1996-01-01

Over the last several years, the nature of the surface conditions on the planet Mars, our knowledge of the growth capabilities of Earth organisms under extreme conditions, and future opportunities for Mars exploration have been under extensive review in the United States and elsewhere. As part of these examinations, in 1992 the US Space Studies Board made a series of recommendations to NASA on the requirements that should be implemented on future missions that will explore Mars. In particular, significant changes were recommended in the requirements for Mars landers, changes that significantly alleviated the burden of planetary protection implementation for these missions. In this paper we propose a resolution implementing this new set of recommendations, for adoption by COSPAR at its 30th meeting in Hamburg. We also discuss future directions and study areas for planetary protection, in light of changing plans for Mars exploration.

Photovoltaic Power for Future NASA Missions

NASA Technical Reports Server (NTRS)

Landis, Geoffrey; Bailey, Sheila G.; Lyons, Valerie J. (Technical Monitor)

2002-01-01

Recent advances in crystalline solar cell technology are reviewed. Dual-junction and triple-junction solar cells are presently available from several U. S. vendors. Commercially available triple-junction cells consisting of GaInP, GaAs, and Ge layers can produce up to 27% conversion efficiency in production lots. Technology status and performance figures of merit for currently available photovoltaic arrays are discussed. Three specific NASA mission applications are discussed in detail: Mars surface applications, high temperature solar cell applications, and integrated microelectronic power supplies for nanosatellites.

Palmer Quest: A Feasible Nuclear Fission "Vision Mission" to the Mars Polar Caps

NASA Technical Reports Server (NTRS)

Carsey, F. D.; Beegle, L. W.; Nakagawa, R.; Elliott, J. O.; Matthews, J. B.; Coleman, M. L.; Hecht, M. H.; Ivaniov, A. B.; Head, J. W.; Milkovich, S.

2005-01-01

We are engaged in a NASA Vision Mission study, called Palmer Quest after the American Antarctic explorer Nathaniel Palmer, to assess the presence of life and evaluate the habitability of the basal domain of the Mars polar caps. We address this goal through four objectives: 1. Determine the presence of amino acids, nutrients, and geochemical heterogeneity in the ice sheet. 2. Quantify and characterize the provenance of the amino acids in Mars ice. 3. Assess the stratification of outcropped units for indications of habitable zones. 4. Determine the accumulation of ice, mineralogic material, and amino acids in Mars ice caps over the present epoch. Because of the defined scientific goal for the vision mission, the Palmer Quest focus is astrobiological; however, the results of the study make us optimistic that aggressive multi-platform in-situ missions that address a wide range of objectives, such as climate change, can be supported by variations of the approach used on this mission. Mission Overview: The Palmer Quest baseline

Model of Mars-Bound MarCO CubeSat

NASA Image and Video Library

2015-06-12

Engineers for NASA's MarCO technology demonstration display a full-scale mechanical mock-up of the small craft in development as part of NASA's next mission to Mars. Mechanical engineer Joel Steinkraus and systems engineer Farah Alibay are on the team at NASA's Jet Propulsion Laboratory, Pasadena, California, preparing twin MarCO (Mars Cube One) CubeSats for a March 2016 launch. MarCO is the first interplanetary mission using CubeSat technologies for small spacecraft. The briefcase-size MarCO twins will ride along on an Atlas V launch vehicle lifting off from Vandenberg Air Force Base, California, with NASA's next Mars lander, InSight. The mock-up in the photo is in a configuration to show the deployed position of components that correspond to MarCO's two solar panels and two antennas. During launch, those components will be stowed for a total vehicle size of about 14.4 inches (36.6 centimeters) by 9.5 inches (24.3 centimeters) by 4.6 inches (11.8 centimeters). After launch, the two MarCO CubeSats and InSight will be navigated separately to Mars. The MarCO twins will fly past the planet in September 2016 just as InSight is descending through the atmosphere and landing on the surface. MarCO is a technology demonstration mission to relay communications from InSight to Earth during InSight's descent and landing. InSight communications during that critical period will also be recorded by NASA's Mars Reconnaissance Orbiter for delayed transmission to Earth. InSight -- an acronym for Interior Exploration using Seismic Investigations, Geodesy and Heat Transport -- will study the interior of Mars to improve understanding of the processes that formed and shaped rocky planets, including Earth. After launch, the MarCO twins and InSight will be navigated separately to Mars. 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

Science Instruments on NASA Mars 2020 Rover

NASA Image and Video Library

2015-06-10

This 2015 diagram shows components of the investigations payload for NASA's Mars 2020 rover mission. Mars 2020 will re-use the basic engineering of NASA's Mars Science Laboratory to send a different rover to Mars, with new objectives and instruments, launching in 2020. The rover will carry seven instruments to conduct its science and exploration technology investigations. They are: Mastcam-Z, an advanced camera system with panoramic and stereoscopic imaging capability and the ability to zoom. The instrument also will determine mineralogy of the Martian surface and assist with rover operations. The principal investigator is James Bell, Arizona State University in Tempe. SuperCam, an instrument that can provide imaging, chemical composition analysis, and mineralogy. The instrument will also be able to detect the presence of organic compounds in rocks and regolith from a distance. The principal investigator is Roger Wiens, Los Alamos National Laboratory, Los Alamos, New Mexico. This instrument also has a significant contribution from the Centre National d'Etudes Spatiales, Institut de Recherche en Astrophysique et Planétologie (CNES/IRAP) France. Planetary Instrument for X-ray Lithochemistry (PIXL), an X-ray fluorescence spectrometer that will also contain an imager with high resolution to determine the fine-scale elemental composition of Martian surface materials. PIXL will provide capabilities that permit more detailed detection and analysis of chemical elements than ever before. The principal investigator is Abigail Allwood, NASA's Jet Propulsion Laboratory, Pasadena, California. Scanning Habitable Environments with Raman & Luminescence for Organics and Chemicals (SHERLOC), a spectrometer that will provide fine-scale imaging and uses an ultraviolet (UV) laser to determine fine-scale mineralogy and detect organic compounds. SHERLOC will be the first UV Raman spectrometer to fly to the surface of Mars and will provide complementary measurements with other

A Comparative Study of Aerocapture Missions with a Mars Destination

NASA Technical Reports Server (NTRS)

Vaughan, Diane; Miller, Heather C.; Griffin, Brand; James, Bonnie F.; Munk, Michelle M.

2005-01-01

Conventional interplanetary spacecraft use propulsive systems to decelerate into orbit. Aerocapture is an alternative approach for orbit capture, in which the spacecraft makes a single pass through a target destination's atmosphere. Although this technique has never been performed, studies show there are substantial benefits of using aerocapture for reduction of propellant mass, spacecraft size, and mission cost. The In-Space Propulsion (ISP) Program, part of NASA's Science Mission Directorate, has invested in aerocapture technology development since 2002. Aerocapture investments within ISP are largely driven by mission systems analysis studies, The purpose of this NASA-funded report is to identify and document the fundamental parameters of aerocapture within previous human and robotic Mars mission studies which will assist the community in identifying technology research gaps in human and robotic missions, and provide insight for future technology investments. Upon examination of the final data set, some key attributes within the aerocapture disciplines are identified.

Utilizing Mars Global Reference Atmospheric Model (Mars-GRAM 2005) to Evaluate Entry Probe Mission Sites

NASA Technical Reports Server (NTRS)

Justh, Hilary L.; Justus, C. G.

2008-01-01

Engineering-level atmospheric model widely used for diverse mission applications. Mars-GRAM s perturbation modeling capability is commonly used, in a Monte-Carlo mode, to perform high fidelity engineering end-to-end simulations for entry, descent, and landing (EDL)1. Traditional Mars-GRAM options for representing the mean atmosphere along entry corridors include: a) TES Mapping Years 1 and 2, with Mars-GRAM data coming from MGCM model results driven by observed TES dust optical depth; and b) TES Mapping Year 0, with user-controlled dust optical depth and Mars-GRAM data interpolated from MGCM model results driven by selected values of globally-uniform dust optical depth. From the surface to 80 km altitude, Mars-GRAM is based on NASA Ames Mars General Circulation Model (MGCM). Mars-GRAM and MGCM use surface topography from Mars Global Surveyor Mars Orbiter Laser Altimeter (MOLA), with altitudes referenced to the MOLA areoid, or constant potential surface. Mars-GRAM 2005 has been validated2 against Radio Science data, and both nadir and limb data from the Thermal Emission Spectrometer (TES)

Planning for the V&V of infused software technologies for the Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Feather, Martin S.; Fesq, Lorraine M.; Ingham, Michel D.; Klein, Suzanne L.; Nelson, Stacy D.

2004-01-01

NASA's Mars Science Laboratory (MSL) rover mission is planning to make use of advanced software technologies in order to support fulfillment of its ambitious science objectives. The mission plans to adopt the Mission Data System (MDS) as the mission software architecture, and plans to make significant use of on-board autonomous capabilities for the rover software.

Communicating the Science of Nasa's Maven Mission through Public Engagement

NASA Astrophysics Data System (ADS)

Mason, T.; Peticolas, L. M.; Wood, E. L.

2014-12-01

As education, public outreach, and communications professionals, we see the direct benefits of online outreach and other public engagement strategies in communicating complex scientific concepts. While public understanding of science and scientific literacy rates has stagnated at best, online engagement has never been more active. About 40% of Americans receive information about science and technology primarily from online sources; however, the ability to pursue enhanced learning opportunities is directly correlated with higher education and income. The MAVEN E/PO team has recognized an opportunity to bring the science of the mission to a growing, online community of engaged learners and potential supporters of future scientific research and data. We have taken a wide variety of approaches to educate the public—particularly non-traditional audiences—about a mission that is not as "sexy" as many other NASA missions, but is critical to understanding the evolution of Mars over time as part of an ongoing, long-term effort by NASA's Mars Exploration Program. We will highlight some of the tools—including online platforms—that we have used to share the science of MAVEN and will present preliminary evaluation results from our education and public outreach projects.

Mars Surface Systems Common Capabilities and Challenges for Human Missions

NASA Technical Reports Server (NTRS)

Toups, Larry; Hoffman, Stephen J.

2016-01-01

This paper describes the current status of common systems and operations as they are applied to actual locations on Mars that are representative of Exploration Zones (EZ) - NASA's term for candidate locations where humans could land, live and work on the Martian surface. Given NASA's current concepts for human missions to Mars, an EZ is a collection of Regions of Interest (ROIs) located within approximately 100 kilometers of a centralized landing site. ROIs are areas that are relevant for scientific investigation and/or development/maturation of capabilities and resources necessary for a sustainable human presence. An EZ also contains a habitation site that will be used by multiple human crews during missions to explore and utilize the ROIs within the EZ. The Evolvable Mars Campaign (EMC), a description of NASA's current approach to these human Mars missions, assumes that a single EZ will be identified within which NASA will establish a substantial and durable surface infrastructure that will be used by multiple human crews. The process of identifying and eventually selecting this single EZ will likely take many years to finalized. Because of this extended EZ selection process it becomes important to evaluate the current suite of surface systems and operations being evaluated for the EMC as they are likely to perform at a variety of proposed EZ locations and for the types of operations - both scientific and development - that are proposed for these candidate EZs. It is also important to evaluate proposed EZs for their suitability to be explored or developed given the range of capabilities and constraints for the types of surface systems and operations being considered within the EMC. Four locations identified in the Mars Exploration Program Analysis Group (MEPAG)'s Human Exploration of Mars Science Analysis Group (HEM-SAG) report are used in this paper as representative of candidate EZs that will emerge from the selection process that NASA has initiated. A field

Telecommunications IT and navigation for future Mars exploration missions 2006 IEEE Aerospace Conference

NASA Technical Reports Server (NTRS)

Wyatt, E. Jay; Ely, Todd A.; Klimesh, Matthew A.; Krupiarz, Christopher J.

2006-01-01

There are three primary drivers behind current investments in telecommunications information technology and navigation. One is finding ways to maximize the volume of science data returned from missions since i nstrument data generation often exceeds communication bandwidth. Another is to provide the necessary technology to enable networked spacecraft around Mars. The third driver is to enable more precise landing so in-situ vehicles can be placed in the more scientifically interesting regions. This paper describes the current NASA investments in these areas funded through the NASA Mars Technology Base Program NRA.

Human Mars Mission Performance Crew Taxi Profile

NASA Technical Reports Server (NTRS)

Duaro, Vince A.

1999-01-01

Using the results from Integrated Mission Program (IMP), a simulation language and code used to model present and future Earth Moon, or Mars missions, this report presents six different case studies of a manned Mars mission. The mission profiles, timelines, propellant requirements, feasibility and perturbation analysis is presented for two aborted, two delayed rendezvous, and two normal rendezvous cases for a future Mars mission.

Mission and Design Sensitivities for Human Mars Landers Using Hypersonic Inflatable Aerodynamic Decelerators

NASA Technical Reports Server (NTRS)

Polsgrove, Tara P.; Thomas, Herbert D.; Collins, Tim; Dwyer Cianciolo, Alicia; Samareh, Jamshid

2017-01-01

Landing humans on Mars is one of NASA's long term goals. The Evolvable Mars Campaign (EMC) is focused on evaluating architectural trade options to define the capabilities and elements needed for a sustainable human presence on the surface of Mars. The EMC study teams have considered a variety of in-space propulsion options and surface mission options. As we seek to better understand how these choices affect the performance of the lander, this work informs and influences requirements for transportation systems to deliver the landers to Mars and enable these missions. This paper presents the effects of mission and vehicle design options on lander mass and performance. Beginning with Earth launch, options include fairing size assumptions, co-manifesting other elements with the lander, and Earth-Moon vicinity operations. Capturing into Mars orbit using either aerocapture or propulsive capture is assessed. For entry, descent, and landing both storable as well as oxygen and methane propellant combinations are considered, engine thrust level is assessed, and sensitivity to landed payload mass is presented. This paper focuses on lander designs using the Hypersonic Inflatable Aerodynamic Decelerators (HIAD), one of several entry system technologies currently considered for human missions.

Mars Exploration Rovers: 4 Years on Mars

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.

2008-01-01

This January, the Mars Exploration Rovers "Spirit" and "Opportunity" are starting their fifth year of exploring the surface of Mars, well over ten times their nominal 90-day design lifetime. This lecture discusses the Mars Exploration Rovers, presents the current mission status for the extended mission, some of the most results from the mission and how it is affecting our current view of Mars, and briefly presents the plans for the coming NASA missions to the surface of Mars and concepts for exploration with robots and humans into the next decade, and beyond.

EuroGeoMars Field Campaign: habitability studies in preparation for future Mars missions

NASA Astrophysics Data System (ADS)

Ehrenfreund, Pascale; Foing, B. H.; Stoker, C.; Zhavaleta, J.; Orzechowska, G.; Kotler, M.; Martins, Z.; Sephton, M.; Becker, L.; Quinn, R.; van Sluis, C.; Boche-Sauvan, L.; Gross, C.; Thiel, C.; Wendt, L.; Sarrazin, P.; Mahapatra, P.; Direito, S.; Roling, W.

The goal of the EuroGeoMars field campaign sponsored by ESA, NASA and the international lunar exploration working group (ILEWG) was to demonstrate instrument capabilities in sup-port of current and future planetary missions, to validate a procedure for Martian surface in-situ and return science, and to study human performance aspects. The Mars Desert Re-search Station (MDRS) represents an ideal basis to simulate aspects of robotic and human exploration in support of future missions to planetary bodies. During the campaign, MDRS Crew 77 tested X-ray diffraction and Raman instruments, and assessed habitat and operations. Special emphasis was given to sample collection in the geologically rich vicinity of MDRS and subsequent analysis of organic molecules in the soil to simulate the search for bio-signatures with field instrumentation. We describe the results of in-situ and posterior analysis of the physical and chemical properties including elemental composition, salt concentrations as well as carbon and amino acid abundances. The analyses of organics and minerals show that the subsurface mineral matrix represents a key to our understanding of the survival of organics on Mars.

NASA Participates in Mars Day Activities at the National Air and Space Museum

NASA Image and Video Library

2017-07-21

NASA participated in the July 21 Mars Day event at the Smithsonian National Air and Space Museum (NASM) in Washington, D.C. The museum hosts this annual event, which includes exhibits, speakers and educational activities, to celebrate the Red Planet. Jim Green, director of NASA’s Planetary Science Division, along with other NASA scientists and engineers, was on hand to talk with visitors about the agency’s Mars exploration missions. There was also a Mars concept rover on display, developed by vehicle designers the Parker Brothers with advice from NASA. The vehicle is currently on an East Coast tour from its home base at the Kennedy Space Center Visitor’s Complex in Florida. The concept rover is designed to engage and educate the public by demonstrating the types of features and equipment a future human exploration vehicle may need.

A High Power Solar Electric Propulsion - Chemical Mission for Human Exploration of Mars

NASA Technical Reports Server (NTRS)

Burke, Laura M.; Martini, Michael C.; Oleson, Steven R.

2014-01-01

Recently Solar Electric Propulsion (SEP) as a main propulsion system has been investigated as an option to support manned space missions to near-Earth destinations for the NASA Gateway spacecraft. High efficiency SEP systems are able to reduce the amount of propellant long duration chemical missions require, ultimately reducing the required mass delivered to Low Earth Orbit (LEO) by a launch vehicle. However, for long duration interplanetary Mars missions, using SEP as the sole propulsion source alone may not be feasible due to the long trip times to reach and insert into the destination orbit. By combining an SEP propulsion system with a chemical propulsion system the mission is able to utilize the high-efficiency SEP for sustained vehicle acceleration and deceleration in heliocentric space and the chemical system for orbit insertion maneuvers and trans-earth injection, eliminating the need for long duration spirals. By capturing chemically instead of with low-thrust SEP, Mars stay time increases by nearly 200 days. Additionally, the size the of chemical propulsion system can be significantly reduced from that of a standard Mars mission because the SEP system greatly decreases the Mars arrival and departure hyperbolic excess velocities (V(sub infinity)).

Mars Observer: Mission toward a basic understanding of Mars

NASA Technical Reports Server (NTRS)

Albee, Arden L.

1992-01-01

The Mars Observer Mission will provide a spacecraft platform about Mars from which the entire Martian surface and atmosphere will be observed and mapped by remote sensing instruments for at least 1 Martian year. The scientific objectives for the Mission emphasize qualitative and quantitative determination of the elemental and mineralogical composition of the surface; measurement of the global surface topography, gravity field, and magnetic field; and the development of a synoptic data base of climatological conditions. The Mission will provide basic global understanding of Mars as it exists today and will provide a framework for understanding its past.

Game Changing: NASA's Space Launch System and Science Mission Design

NASA Technical Reports Server (NTRS)

Creech, Stephen D.

2013-01-01

NASA s Marshall Space Flight Center (MSFC) is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will carry the Orion Multi-Purpose Crew Vehicle (MPCV) and other important payloads far beyond Earth orbit (BEO). Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids and Mars. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required - with several gravity-assist planetary fly-bys - to achieve the necessary outbound velocity. The SLS rocket, using significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, reducing trip time and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as "monolithic" telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

Game changing: NASA's space launch system and science mission design

NASA Astrophysics Data System (ADS)

Creech, S. D.

NASA's Marshall Space Flight Center (MSFC) is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will carry the Orion Multi-Purpose Crew Vehicle (MPCV) and other important payloads far beyond Earth orbit (BEO). Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids and Mars. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required - with several gravity-assist planetary fly-bys - to achieve the necessary outbound velocity. The SLS rocket, using significantly higher characteristic energy (C3) energies, can more quickly and effectively take the mission directly to its destination, reducing trip time and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as “ monolithic” telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

Interplanetary Mission Design Handbook: Earth-to-Mars Mission Opportunities and Mars-to-Earth Return Opportunities 2009-2024

NASA Technical Reports Server (NTRS)

George, L. E.; Kos, L. D.

1998-01-01

This paper provides information for trajectory designers and mission planners to determine Earth-Mars and Mars-Earth mission opportunities for the years 2009-2024. These studies were performed in support of a human Mars mission scenario that will consist of two cargo launches followed by a piloted mission during the next opportunity approximately 2 years later. "Porkchop" plots defining all of these mission opportunities are provided which include departure energy, departure excess speed, departure declination arrival excess speed, and arrival declinations for the mission space surrounding each opportunity. These plots are intended to be directly applicable for the human Mars mission scenario described briefly herein. In addition, specific trajectories and several alternate trajectories are recommended for each cargo and piloted opportunity. Finally, additional studies were performed to evaluate the effect of various thrust-to-weight ratios on gravity losses and total time-of-flight tradeoff, and the resultant propellant savings and are briefly summarized.

Tracking and data system support for the Mariner Mars 1971 mission. Volume 3: Orbit insertion through end of primary mission

NASA Technical Reports Server (NTRS)

Barnum, P. W.; Renzetti, N. A.; Textor, G. P.; Kelly, L. B.

1973-01-01

The Tracking and Data System (TDS) Support for the Mariner Mars 1971 Mission final report contains the deep space tracking and data acquisition activities in support of orbital operations. During this period a major NASA objective was accomplished: completion of the 180th revolution and 90th day of data gathering with the spacecraft about the planet Mars. Included are presentations of the TDS flight support pass chronology data for each of the Deep Space Stations used, and performance evaluation for the Deep Space Network Telemetry, Tracking, Command, and Monitor Systems. With the loss of Mariner 8 at launch, Mariner 9 assumed the mission plan of Mariner 8, which included the TV mapping cycles and a 12-hr orbital period. The mission plan was modified as a result of a severe dust storm on the surface of Mars, which delayed the start of the TV mapping cycles. Thus, the end of primary mission date was extended to complete the TV mapping cycles.

Accessing Information on the Mars Exploration Rovers Mission

NASA Astrophysics Data System (ADS)

Walton, J. D.; Schreiner, J. A.

2005-12-01

In January 2004, the Mars Exploration Rovers (MER) mission successfully deployed two robotic geologists - Spirit and Opportunity - to opposite sides of the red planet. Onboard each rover is an array of cameras and scientific instruments that send data back to Earth, where ground-based systems process and store the information. During the height of the mission, a team of about 250 scientists and engineers worked around the clock to analyze the collected data, determine a strategy and activities for the next day and then carefully compose the command sequences that would instruct the rovers in how to perform their tasks. The scientists and engineers had to work closely together to balance the science objectives with the engineering constraints so that the mission achieved its goals safely and quickly. To accomplish this coordinated effort, they adhered to a tightly orchestrated schedule of meetings and processes. To keep on time, it was critical that all team members were aware of what was happening, knew how much time they had to complete their tasks, and could easily access the information they need to do their jobs. Computer scientists and software engineers at NASA Ames Research Center worked closely with the mission managers at the Jet Propulsion Laboratory (JPL) to create applications that support the mission. One such application, the Collaborative Information Portal (CIP), helps mission personnel perform their daily tasks, whether they work inside mission control or the science areas at JPL, or in their homes, schools, or offices. With a three-tiered, service-oriented architecture (SOA) - client, middleware, and data repository - built using Java and commercial software, CIP provides secure access to mission schedules and to data and images transmitted from the Mars rovers. This services-based approach proved highly effective for building distributed, flexible applications, and is forming the basis for the design of future mission software systems. Almost two

A Comparison of Transportation Systems for Human Missions to Mars

NASA Technical Reports Server (NTRS)

Thomas, Brent; Vaughan, Diane; Drake, Bret; Griffin, Brand; Woodcock, Gordon

2004-01-01

There are many ways to send humans to Mars. Credible technical reports can be traced to the 1950's. More recently, NASA has funded major studies that depict a broad variety of trajectories, technologies, stay times, and costs. Much of this data is still valid with direct application to today's exploration planning. This paper presents results comparing these studies with particular emphasis on the in-space transportation aspects of the mission. Specifically, comparisons are made on propulsion systems used for getting the crew and mission equipment from Earth orbit to Mars orbit, descending and ascending from the surface, and returning to Earth orbit. Areas of comparison for each of these phases include crew size, mission mass, propellant mass, delta v, specific impulse, transit time, surface stay time, aero-braking, and others. Data is analyzed to demonstrate either strong trends toward particular technologies or diverging solutions.

Planetary protection implementation on Mars Reconnaissance Orbiter mission

NASA Astrophysics Data System (ADS)

Barengoltz, J.; Witte, J.

2008-09-01

In August 2005 NASA launched a large orbiting science observatory, the Mars Reconnaissance Orbiter (MRO), for what is scheduled to be a 5.4-year mission. High resolution imaging of the surface is a principal goal of the mission. One consequence of this goal however is the need for a low science orbit. Unfortunately this orbit fails the required 20-year orbit life set in NASA Planetary Protection (PP) requirements [NASA. Planetary protection provisions for robotic extraterrestrial missions, NASA procedural requirements NPR 8020.12C, NASA HQ, Washington, DC, April 2005.]. So rather than sacrifice the science goals of the mission by raising the science orbit, the MRO Project chose to be the first orbiter to pursue the bio-burden reduction approach. Cleaning alone for a large orbiter like MRO is insufficient to achieve the bio-burden threshold requirement in NASA PP requirements. The burden requirement for an orbiter includes spores encapsulated in non-metallic materials and trapped in joints, as well as located on all internal and external surfaces (the total spore burden). Total burden estimates are dominated by the mated and encapsulated burden. The encapsulated burden cannot be cleaned. The total burden of a smaller orbiter (e.g., Mars Odyssey) likely could not have met the requirement by cleaning; for the large MRO it is clearly impossible. Of course, a system-level partial sterilization, with its attendant costs and system design issues, could have been employed. In the approach taken by the MRO Project, hardware which will burn up (completely vaporize or ablate) before reaching the surface or will at least attain high temperature (500 °C for 0.5 s or more) due to entry heating was exempt from burden accounting. Thus the bio-burden estimate was reduced. Lockheed Martin engineers developed a process to perform what is called breakup and burn-up (B&B) analysis.Lockheed Martin Corporation.2 The use of the B&B analysis to comply with the spore burden requirement is

Status and Mission Applicability of NASA's In-Space Propulsion Technology Project

NASA Technical Reports Server (NTRS)

Anderson, David J.; Munk, Michelle M.; Dankanich, John; Pencil, Eric; Liou, Larry

2009-01-01

The In-Space Propulsion Technology (ISPT) project develops propulsion technologies that will enable or enhance NASA robotic science missions. Since 2001, the ISPT project developed and delivered products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. These in-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. This paper provides status of the technology development, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of advanced chemical thrusters, electric propulsion, aerocapture, and systems analysis tools. The current chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. Investments in electric propulsion technologies focused on completing NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system, and the High Voltage Hall Accelerator (HiVHAC) thruster, which is a mid-term product specifically designed for a low-cost electric propulsion option. Aerocapture investments developed a family of thermal protections system materials and structures; guidance, navigation, and control models of blunt-body rigid aeroshells; atmospheric models for Earth, Titan, Mars and Venus; and models for aerothermal effects. In 2009 ISPT started the development of propulsion technologies that would enable future sample return missions. The paper describes the ISPT project's future focus on propulsion for sample return missions. The future technology development areas for ISPT is: Planetary Ascent Vehicles (PAV), with a Mars Ascent Vehicle (MAV) being the initial development focus; multi-mission technologies for Earth Entry Vehicles (MMEEV) needed

76 FR 4133 - National Environmental Policy Act; Mars Science Laboratory (MSL) Mission

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-24

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION [Notice (11-008)] National Environmental Policy Act; Mars Science Laboratory (MSL) Mission AGENCY: National Aeronautics and Space Administration (NASA...). SUMMARY: Pursuant to the National Environmental Policy Act, as amended, (NEPA) (42 U.S.C. 4321 et seq...

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.

The CanMars Analogue Mission: Lessons Learned for Mars Sample Return

NASA Astrophysics Data System (ADS)

Osinski, G. R.; Beaty, D.; Battler, M.; Caudill, C.; Francis, R.; Haltigin, T.; Hipkin, V.; Pilles, E.

2018-04-01

We present an overview and lessons learned for Mars Sample Return from CanMars — an analogue mission that simulated a Mars 2020-like cache mission. Data from 39 sols of operations conducted in the Utah desert in 2015 and 2016 are presented.

NASA Social and Media Briefing on Next Mars Mission

NASA Image and Video Library

2018-05-03

News media and social media participants gathered at Vandenberg Air Force Base in Central California Thursday, May 3 to hear from NASA and its partners about the agency’s mission to study the interior of the Red Planet. NASA’s Interior Exploration using Seismic Investigations, Geodesy and Heat Transport (InSight) is scheduled to launch May 5 on a United Launch Alliance Atlas V rocket, from Space Launch Complex 3 at Vandenberg.

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.

Moon and Mars Analog Mission Activities for Mauna Kea 2012

NASA Technical Reports Server (NTRS)

Graham, Lee D.; Morris, Richard V.; Graff, Trevor G.; Yingst, R. Aileen; tenKate, I. L.; Glavin, Daniel P.; Hedlund, Magnus; Malespin, Charles A.; Mumm, Erik

2012-01-01

Rover-based 2012 Moon and Mars Analog Mission Activities (MMAMA) scientific investigations were recently completed at Mauna Kea, Hawaii. Scientific investigations, scientific input, and science operations constraints were tested in the context of an existing project and protocols for the field activities designed to help NASA achieve the Vision for Space Exploration. Initial science operations were planned based on a model similar to the operations control of the Mars Exploration Rovers (MER). However, evolution of the operations process occurred as the analog mission progressed. We report here on the preliminary sensor data results, an applicable methodology for developing an optimum science input based on productive engineering and science trades discussions and the science operations approach for an investigation into the valley on the upper slopes of Mauna Kea identified as "Apollo Valley".

Mission Applications of a HIAD for the Mars Southern Highlands

NASA Technical Reports Server (NTRS)

Winski, Richard; Bose, Dave; Komar, David R.; Samareh, Jamshid

2013-01-01

Recent discoveries of evidence of a flowing liquid in craters throughout the Mars Southern Highlands, like Terra Sirenum, have spurred interest in sending science missions to those locations; however, these locations are at elevations that are much higher (0 to +4 km MOLA) than any previous landing site (-1 to -4 km MOLA). New technologies may be needed to achieve a landing at these sites with significant payload mass to the surface. A promising technology is the hypersonic inflatable aerodynamic decelerator (HIAD); a number of designs have been advanced but the stacked torus has been recently successfully flight tested in the IRVE-2 and IRVE-3 projects through the NASA Langley Research Center. This paper will focus on a variety of mission applications of the stacked torus type attached HIAD to the Mars southern highlands.

Emirates Mars Mission Planetary Protection Plan

NASA Astrophysics Data System (ADS)

Awadhi, Mohsen Al

2016-07-01

The United Arab Emirates is planning to launch a spacecraft to Mars in 2020 as part of the Emirates Mars Mission (EMM). The EMM spacecraft, Amal, will arrive in early 2021 and enter orbit about Mars. Through a sequence of subsequent maneuvers, the spacecraft will enter a large science orbit and remain there throughout the primary mission. This paper describes the planetary protection plan for the EMM mission. The EMM science orbit, where Amal will conduct the majority of its operations, is very large compared to other Mars orbiters. The nominal orbit has a periapse altitude of 20,000 km, an apoapse altitude of 43,000 km, and an inclination of 25 degrees. From this vantage point, Amal will conduct a series of atmospheric investigations. Since Amal's orbit is very large, the planetary protection plan is to demonstrate a very low probability that the spacecraft will ever encounter Mars' surface or lower atmosphere during the mission. The EMM team has prepared methods to demonstrate that (1) the launch vehicle targets support a 0.01% probability of impacting Mars, or less, within 50 years; (2) the spacecraft has a 1% probability or less of impacting Mars during 20 years; and (3) the spacecraft has a 5% probability or less of impacting Mars during 50 years. The EMM mission design resembles the mission design of many previous missions, differing only in the specific parameters and final destination. The following sequence describes the mission: 1.The mission will launch in July, 2020. The launch includes a brief parking orbit and a direct injection to the interplanetary cruise. The launch targets are specified by the hyperbolic departure's energy C3, and the hyperbolic departure's direction in space, captured by the right ascension and declination of the launch asymptote, RLA and DLA, respectively. The targets of the launch vehicle are biased away from Mars such that there is a 0.01% probability or less that the launch vehicle arrives onto a trajectory that impacts Mars

Planning For Multiple NASA Missions With Use Of Enabling Radioisotope Power

DOE Office of Scientific and Technical Information (OSTI.GOV)

S.G. Johnson; K.L. Lively; C.C. Dwight

Since the early 1960’s the Department of Energy (DOE) and its predecessor agencies have provided radioisotope power systems (RPS) to NASA as an enabling technology for deep space and various planetary missions. They provide reliable power in situations where solar and/or battery power sources are either untenable or would place an undue mass burden on the mission. In the modern era of the past twenty years there has been no time that multiple missions have been considered for launching from Kennedy Space Center (KSC) during the same year. The closest proximity of missions that involved radioisotope power systems would bemore » that of Galileo (October 1989) and Ulysses (October 1990). The closest that involved radioisotope heater units would be the small rovers Spirit and Opportunity (May and July 2003) used in the Mars Exploration Rovers (MER) mission. It can be argued that the rovers sent to Mars in 2003 were essentially a special case since they staged in the same facility and used a pair of small launch vehicles (Delta II). This paper examines constraints on the frequency of use of radioisotope power systems with regard to launching them from Kennedy Space Center using currently available launch vehicles. This knowledge may be useful as NASA plans for its future deep space or planetary missions where radioisotope power systems are used as an enabling technology. Previous descriptions have focused on single mission chronologies and not analyzed the timelines with an emphasis on multiple missions.« less

Planetary Protection Provisions for the Mars 2020 Mission: Enabling Discovery by Constraining Contamination

NASA Astrophysics Data System (ADS)

Rummel, J. D.; Conley, C. A.

2013-12-01

The 2013-2022 NRC Decadal Survey named its #1 Flagship priority as a large, capable Mars rover that would be the first of a three-mission, multi-decadal effort to return samples from Mars. More recently, NASA's Mars Program has stated that a Mars rover mission known as 'Mars 2020' would be flown to Mars (in 2020) to accomplish a subset of the goals specified by the NRC, and the recent report of the Mars 2020 Science Definition Team (SDT) has recommended that the mission accomplish broad and rigorous in situ science, including seeking biosignatures, acquiring a diverse set of samples intended to address a range of Mars science questions and storing them in a cache for potential return to Earth at a later time, and other engineering goals to constrain costs and support future human exploration. In some ways Mars 2020 will share planetary protection requirements with the Mars Science Laboratory mission that landed in 2012, which included landing site constraints based on the presence of a perennial heat source (the MMRTG) aboard the lander/rover. In a very significant way, however, the presence of a sample-cache and the potential that Mars 2020 will be the first mission in the chain that will return a sample from Mars to Earth. Thus Mars 2020 will face more stringent requirements aimed at keeping the mission from returning Earth contamination with the samples from Mars. Mars 2020 will be looking for biosignatures of ancient life, on Mars, but will also need to be concerned with the potential to detect extant biosignatures or life itself within the sample that is eventually returned. If returned samples are able to unlock wide-ranging questions about the geology, surface processes, and habitability of Mars that cannot be answered by study of meteorites or current mission data, then either the returned samples must be free enough of Earth organisms to be releasable from a quarantine facility or the planned work of sample scientists, including high- and low

Mars MetNet Mission Status

NASA Astrophysics Data System (ADS)

Harri, A.-M.; Aleksashkin, S.; Arruego, I.; Schmidt, W.; Genzer, M.; Vazquez, L.; Haukka, H.; Palin, M.; Nikkanen, T.

2015-10-01

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 semihard landing vehicle called MetNet Lander (MNL). The scientific payload of the Mars MetNet Precursor [1] 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.

Preparing for Humans at Mars, MPPG Updates to Strategic Knowledge Gaps and Collaboration with Science Missions

NASA Technical Reports Server (NTRS)

Baker, John; Wargo, Michael J.; Beaty, David

2013-01-01

The Mars Program Planning Group (MPPG) was an agency wide effort, chartered in March 2012 by the NASA Associate Administrator for Science, in collaboration with NASA's Associate Administrator for Human Exploration and Operations, the Chief Scientist, and the Chief Technologist. NASA tasked the MPPG to develop foundations for a program-level architecture for robotic exploration of Mars that is consistent with the President's challenge of sending humans to the Mars system in the decade of the 2030s and responsive to the primary scientific goals of the 2011 NRC Decadal Survey for Planetary Science. The Mars Exploration Program Analysis Group (MEPAG) also sponsored a Precursor measurement Strategy Analysis Group (P-SAG) to revisit prior assessments of required precursor measurements for the human exploration of Mars. This paper will discuss the key results of the MPPG and P-SAG efforts to update and refine our understanding of the Strategic Knowledge Gaps (SKGs) required to successfully conduct human Mars missions.

Flag and Footprints Mission Mars: Preliminary Design Review Two

NASA Astrophysics Data System (ADS)

1998-01-01

SMI has developed a preliminary guideline for a flag and footprints manned mission to Mars. The manned mission is a split mission where the return and ground supplies will be sent on a cargo spacecraft. The crew spacecraft will leave on a high-energy trajectory once the cargo spacecraft has arrived in the prescribed orbit about Mars. The trajectory will be approximately 150-day from Low Earth Orbit (LEO) to the prescribed rendezvous orbit. The crew spacecraft will then dock with the orbiting cargo spacecraft for refuel and resupply. In addition, once safely docked, the crew members will transfer to the Mars Excursion Vehicle (MEV) for transport to the Martian surface. Each vehicle will be equipped with all necessary subsystems. To facilitate the transport of a large payload from Earth to Mars, the cargo spacecraft will utilize Ion propulsion. The Ion propulsion is ideal due to the high Isp characteristics. The crew spacecraft will be propelled with high-thrust RL-10 engines. Due to the smaller mass of the crew spacecraft, the spacecraft will utilize a 150-day high-energy trajectory. The MEV propulsion will be hypergolic. This choice of fuel is due to the reliability and simplicity of use. The crew members will stay on the surface of Mars for 30-days. During the 30-days, the crew will perform a series of scientific and exploratory experiments. To broaden the astronauts range of exploration, the astronauts will have access to three Unmanned Aerial Vehicles (UAV) and one rover while on the surface. The scientific experiments will consist of several soil and rock analyses as well as atmospheric study. Upon completion of the 30-day ground phase, the astronauts will return to the orbiting crew ship for return to Earth. SMI's flag and footprints mission outlines the fundamental systems and general requirements for these systems. SMI feels that with the fulfillment of these fundamental systems, this mission will be a highly desirable and potential candidate for development

NASAs Evolvable Mars Campaign: Mars Moons Robotic Precursor

NASA Technical Reports Server (NTRS)

Gernhardt, Michael L.; Abercromby, Andrew F. J.; Abell, Paul A.; Love, Stanley G.; Lee, David E.; Chappell, Steven P.; Howe, A. Scott; Friedensen, Victoria

2015-01-01

Human exploration missions to the moons of Mars are being considered within NASA's Evolvable Mars Campaign (EMC) as an intermediate step for eventual human exploration and pioneering of the surface of Mars. A range of mission architectures is being evaluated in which human crews would explore one or both moons for as little as 14 days or for as long as 500 days with a variety of orbital and surface habitation and mobility options being considered. Relatively little is known about the orbital, surface, or subsurface characteristics of either moon. This makes them interesting but challenging destinations for human exploration missions during which crewmembers must be able to effectively conduct scientific exploration without being exposed to undue risks due to radiation, dust, micrometeoroids, or other hazards. A robotic precursor mission to one or both moons will be required to provide data necessary for the design and operation of subsequent human systems and for the identification and prioritization of scientific exploration objectives. This paper identifies and discusses considerations for the design of such a precursor mission based on current human mission architectures. Objectives of a Mars' moon precursor in support of human missions are expected to include: 1) identifying hazards on the surface and the orbital environment at up to 50-km distant retrograde orbits; 2) collecting data on physical characteristics for planning of detailed human proximity and surface operations; 3) performing remote sensing and in situ science investigations to refine and focus future human scientific activities; and 4) prospecting for in situ resource utilization. These precursor objectives can be met through a combination or remote sensing (orbital) and in-situ (surface) measurements. Analysis of spacecraft downlink signals using radio science techniques would measure the moon's mass, mass distribution, and gravity field, which will be necessary to enable trajectory planning

Human-in-the-Loop Operations over Time Delay: NASA Analog Missions Lessons Learned

NASA Technical Reports Server (NTRS)

Rader, Steven N.; Reagan, Marcum L.; Janoiko, Barbara; Johnson, James E.

2013-01-01

Teams at NASA have conducted studies of time-delayed communications as it effects human exploration. In October 2012, the Advanced Exploration Systems (AES) Analog Missions project conducted a Technical Interchange Meeting (TIM) with the primary stakeholders to share information and experiences of studying time delay, to build a coherent picture of how studies are covering the problem domain, and to determine possible forward plans (including how to best communicate study results and lessons learned, how to inform future studies and mission plans, and how to drive potential development efforts). This initial meeting s participants included personnel from multiple NASA centers (HQ, JSC, KSC, ARC, and JPL), academia, and ESA. It included all of the known studies, analog missions, and tests of time delayed communications dating back to the Apollo missions including NASA Extreme Environment Mission Operations (NEEMO), Desert Research and Technology Studies (DRATS/RATS), International Space Station Test-bed for Analog Research (ISTAR), Pavilion Lake Research Project (PLRP), Mars 520, JPL Mars Orbiters/Rovers, Advanced Mission Operations (AMO), Devon Island analog missions, and Apollo experiences. Additionally, the meeting attempted to capture all of the various functional perspectives via presentations by disciplines including mission operations (flight director and mission planning), communications, crew, Capcom, Extra-Vehicular Activity (EVA), Behavioral Health and Performance (BHP), Medical/Surgeon, Science, Education and Public Outreach (EPO), and data management. The paper summarizes the descriptions and results from each of the activities discussed at the TIM and includes several recommendations captured in the meeting for dealing with time delay in human exploration along with recommendations for future development and studies to address this issue.

An Overview of the Mars Reconnaissance Orbiter (MRO) Science Mission

NASA Technical Reports Server (NTRS)

Zurek, Richard W.; Smrekar, Suzanne E.

2007-01-01

The Mars Reconnaissance Orbiter (MRO) is the latest addition to the suite of missions on or orbiting Mars as part of the NASA Mars Exploration Program. Launched on 12 August 2005, the orbiter successfully entered Mars orbit on 10 March 2006 and finished aerobraking on 30 August 2006. Now in its near-polar, near-circular, low-altitude (approximately 300 km), 3 p.m. orbit, the spacecraft is operating its payload of six scientific instruments throughout a one-Mars-year Primary Science Phase (PSP) of global mapping, regional survey, and targeted observations. Eight scientific investigations were chosen for MRO, two of which use either the spacecraft accelerometers or tracking of the spacecraft telecom signal to acquire data needed for analysis. Six instruments, including three imaging systems, a visible-near infrared spectrometer, a shallow-probing subsurface radar, and a thermal-infrared profiler, were selected to complement and extend the capabilities of current working spacecraft at Mars. Whether observing the atmosphere, surface, or subsurface, the MRO instruments are designed to achieve significantly higher resolution while maintaining coverage comparable to the current best observations. The requirements to return higher-resolution data, to target routinely from a low-altitude orbit, and to operate a complex suite of instruments were major challenges successfully met in the design and build of the spacecraft, as well as by the mission design. Calibration activities during the seven-month cruise to Mars and limited payload operations during a three-day checkout prior to the start of aerobraking demonstrated, where possible, that the spacecraft and payload still had the functions critical to the science mission. Two critical events, the deployment of the SHARAD radar antenna and the opening of the CRISM telescope cover, were successfully accomplished in September 2006. Normal data collection began 7 November 2006 after solar conjunction. As part of its science

50 Years of Mars Exploration

NASA Image and Video Library

2015-08-20

2015 marks 50 years of successful NASA missions to Mars starting with Mariner 4 in 1965. Since then, a total of 15 robotic missions led by various NASA centers have laid the groundwork for future human missions to the Red Planet. The journey to Mars continues with additional robotic missions planned for 2016 and 2020, and human missions in the 2030s.

Reliability and Failure in NASA Missions: Blunders, Normal Accidents, High Reliability, Bad Luck

NASA Technical Reports Server (NTRS)

Jones, Harry W.

2015-01-01

NASA emphasizes crew safety and system reliability but several unfortunate failures have occurred. The Apollo 1 fire was mistakenly unanticipated. After that tragedy, the Apollo program gave much more attention to safety. The Challenger accident revealed that NASA had neglected safety and that management underestimated the high risk of shuttle. Probabilistic Risk Assessment was adopted to provide more accurate failure probabilities for shuttle and other missions. NASA's "faster, better, cheaper" initiative and government procurement reform led to deliberately dismantling traditional reliability engineering. The Columbia tragedy and Mars mission failures followed. Failures can be attributed to blunders, normal accidents, or bad luck. Achieving high reliability is difficult but possible.

Mission Options Scoping Tool for Mars Orbiters: Mass Cost Calculator (MC2)

NASA Technical Reports Server (NTRS)

Sturm, Eric J., II; Deutsch, Marie-Jose; Harmon, Corey; Nakagawa, Roy; Kinsey, Robert; Lopez, Nino; Kudrle, Paul; Evans, Alex

2007-01-01

Prior to developing the details of an advanced mission study, the mission architecture trade space is typically explored to assess the scope of feasible options. This paper describes the main features of an Excel-based tool, called the Mass-Cost-Calculator (MC2 ), which is used to perform rapid, high-level mass and cost options analyses of Mars orbiter missions. MC2 consists of a combination of databases, analytical solutions, and parametric relationships to enable quick evaluation of new mission concepts and comparison of multiple architecture options. The tool's outputs provide program management and planning teams with answers to "what if" queries, as well as an understanding of the driving mission elements, during the pre-project planning phase. These outputs have been validated against the outputs generated by the Advanced Projects Design Team (Team X) at NASA's Jet Propulsion Laboratory (JPL). The architecture of the tool allows for future expansion to other orbiters beyond Mars, and to non-orbiter missions, such as those involving fly-by spacecraft, probes, landers, rovers, or other mission elements.

In-Space Propulsion Technology Products for NASA's Future Science and Exploration Missions

NASA Technical Reports Server (NTRS)

Anderson, David J.; Pencil, Eric; Peterson, Todd; Dankanich, John; Munk, Michelle M.

2011-01-01

Since 2001, the In-Space Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling, for future NASA flagship and sample return missions currently being considered, as well as having broad applicability to future competed mission solicitations. The high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost was completed in 2009. Two other ISPT technologies are nearing completion of their technology development phase: 1) NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 2) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; aerothermal effect models: and atmospheric models for Earth, Titan, Mars and Venus. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that have recently completed their technology development and will be ready for infusion into NASA s Discovery, New Frontiers, Science Mission Directorate (SMD) Flagship, and Exploration technology demonstration missions

Reassessment of Planetary Protection Requirements for Mars Sample Return Missions

NASA Astrophysics Data System (ADS)

Smith, David; Race, Margaret; Farmer, Jack

In 2008, NASA asked the US National Research Council (NRC) to review the findings of the report, Mars Sample Return: Issues and Recommendations (National Academy Press, 1997), and to update its recommendations in the light of both current understanding of Mars's biolog-ical potential and ongoing improvements in biological, chemical, and physical sample-analysis capabilities and technologies. The committee established to address this request was tasked to pay particular attention to five topics. First, the likelihood that living entities may be included in samples returned from Mars. Second, scientific investigations that should be conducted to reduce uncertainty in the assessment of Mars' biological potential. Third, the possibility of large-scale effects on Earth's environment if any returned entity is released into the environment. Fourth, the status of technological measures that could be taken on a mission to prevent the inadvertent release of a returned sample into Earth's biosphere. Fifth, criteria for intentional sample release, taking note of current and anticipated regulatory frameworks. The paper outlines the recommendations contained in the committee's final report, Planetary Protection Requirements for Mars Sample Return Missions (The National Academies Press, 2009), with particular emphasis placed on the scientific, technical and policy changes since 1997 and indications as to how these changes modify the recommendations contained in the 1997 report.

JPL-20180504-INSIGHf-0001-NASA's First Mission to Study the Interior of Mars Awaits Launch

NASA Image and Video Library

2018-05-04

Pre-launch video file. InSight's launch to Mars is scheduled for as early as May 5, 2018. Animations: Launch visibility. EDL. Instrument deployments. HP3. Detecting a marsquake. MarCO cubesats. Video: InSight being built at Lockheed Martin Space, Denver. Atlas V rocket and encapsulated InSight spacecraft. How the Atlas V performs this mission.

In Situ Resource Utilization Technologies for Enhancing and Expanding Mars Scientific and Exploration Missions

NASA Technical Reports Server (NTRS)

Sridhar, K. R.; Finn, J. E.

2000-01-01

The primary objectives of the Mars exploration program are to collect data for planetary science in a quest to answer questions related to Origins, to search for evidence of extinct and extant life, and to expand the human presence in the solar system. The public and political engagement that is critical for support of a Mars exploration program is based on all of these objectives. In order to retain and to build public and political support, it is important for NASA to have an integrated Mars exploration plan, not separate robotic and human plans that exist in parallel or in sequence. The resolutions stemming from the current architectural review and prioritization of payloads may be pivotal in determining whether NASA will have such a unified plan and retain public support. There are several potential scientific and technological links between the robotic-only missions that have been flown and planned to date, and the combined robotic and human missions that will come in the future. Taking advantage of and leveraging those links are central to the idea of a unified Mars exploration plan. One such link is in situ resource utilization (ISRU) as an enabling technology to provide consumables such as fuels, oxygen, sweep and utility gases from the Mars atmosphere.

NASA Mission: The Universe

NASA Technical Reports Server (NTRS)

1990-01-01

This booklet is mainly a recruitment tool for the various NASA Centers. This well illustrated booklet briefly describes NASA's mission and career opportunities on the NASA team. NASA field installations and their missions are briefly noted. NASA's four chief program offices are briefly described. They are: (1) Aeronautics, Exploration, and Space Technology; (2) Space Flight; (3) Space Operations; and (4) Space Science and Applications.

NASA Science Mission Directorate's Year of the Solar System: An Opportunity for Scientist Involvement

NASA Astrophysics Data System (ADS)

Dalton, Heather; Shipp, S.; Boonstra, D.; Shupla, C.; CoBabe-Ammann, E.; LaConte, K.; Ristvey, J.; Wessen, A.; Zimmerman-Bachman, R.; Science E/PO Community, Planetary

2010-10-01

Between October 2010 and August 2012 - across a Martian year - a large number of Science Mission Directorate's (SMD) planetary missions will pass milestones (e.g., EPOXI, Stardust-NExT, MESSENGER, Dawn, Juno, GRAIL, and Mars Science Laboratory), with many other missions continuing to explore (e.g., Lunar Reconnaissance Orbiter, Mars Odyssey, Mars Exploration Rovers, Mars Reconnaissance Orbiter, Mars Express, Cassini, New Horizons, and Voyager). This Year of the Solar System (YSS) offers the Planetary Science Education and Public Outreach (E/PO) community an opportunity to collaborate with each other and the science community. Based on audience needs from formal and informal educators, YSS is structured to have monthly thematic topics that are driven by mission milestones, as well as observing opportunities. YSS will connect to ongoing and planned events nationwide. A website for YSS is in development and will be hosted off of the existing JPL Solar System website (http://solarsystem.nasa.gov/index.cfm). Once live, scientists, educators, and E/PO professionals will have a place to interact and collaborate. YSS will tie to NASA's Big Questions in Planetary Science - how did the Sun's family of planets and minor bodies originate and how have they evolved? - how did life begin and evolve on Earth, is it elsewhere, and what characteristics of the solar system lead to the origins of life? The thematic topics are broad in order to encompass many missions and planetary bodies each month, as well as address the Big Questions. YSS will kick off in October with the theme "Solar System Components and Scale” and a national event involving building solar system scale models across the country. Scientists are encouraged to contact schools, museums, planetaria, etc. in their communities to give presentations, provide science content, and collaborate on educational materials and events related to YSS.

Manned Mars mission crew factors

NASA Technical Reports Server (NTRS)

Santy, Patricia A.

1986-01-01

Crew factors include a wide range of concerns relating to the human system and its role in a Mars mission. There are two important areas which will play a large part in determining the crew for a Mars mission. The first relates to the goals and priorities determined for such a vast endeavor. The second is the design of the vehicle for the journey. The human system cannot be separated from the other systems in that vehicle. In fact it will be the human system which drives the development of many of the technical breakthroughs necessary to make a Mars mission successful. As much as possible, the engineering systems must adapt to the needs of the human system and its individual components.

The MARS2013 Mars analog mission.

PubMed

Groemer, Gernot; Soucek, Alexander; Frischauf, Norbert; Stumptner, Willibald; Ragonig, Christoph; Sams, Sebastian; Bartenstein, Thomas; Häuplik-Meusburger, Sandra; Petrova, Polina; Evetts, Simon; Sivenesan, Chan; Bothe, Claudia; Boyd, Andrea; Dinkelaker, Aline; Dissertori, Markus; Fasching, David; Fischer, Monika; Föger, Daniel; Foresta, Luca; Fritsch, Lukas; Fuchs, Harald; Gautsch, Christoph; Gerard, Stephan; Goetzloff, Linda; Gołebiowska, Izabella; Gorur, Paavan; Groemer, Gerhard; Groll, Petra; Haider, Christian; Haider, Olivia; Hauth, Eva; Hauth, Stefan; Hettrich, Sebastian; Jais, Wolfgang; Jones, Natalie; Taj-Eddine, Kamal; Karl, Alexander; Kauerhoff, Tilo; Khan, Muhammad Shadab; Kjeldsen, Andreas; Klauck, Jan; Losiak, Anna; Luger, Markus; Luger, Thomas; Luger, Ulrich; McArthur, Jane; Moser, Linda; Neuner, Julia; Orgel, Csilla; Ori, Gian Gabriele; Paternesi, Roberta; Peschier, Jarno; Pfeil, Isabella; Prock, Silvia; Radinger, Josef; Ramirez, Barbara; Ramo, Wissam; Rampey, Mike; Sams, Arnold; Sams, Elisabeth; Sandu, Oana; Sans, Alejandra; Sansone, Petra; Scheer, Daniela; Schildhammer, Daniel; Scornet, Quentin; Sejkora, Nina; Stadler, Andrea; Stummer, Florian; Taraba, Michael; Tlustos, Reinhard; Toferer, Ernst; Turetschek, Thomas; Winter, Egon; Zanella-Kux, Katja

2014-05-01

We report on the MARS2013 mission, a 4-week Mars analog field test in the northern Sahara. Nineteen experiments were conducted by a field crew in Morocco under simulated martian surface exploration conditions, supervised by a Mission Support Center in Innsbruck, Austria. A Remote Science Support team analyzed field data in near real time, providing planning input for the management of a complex system of field assets; two advanced space suit simulators, four robotic vehicles, an emergency shelter, and a stationary sensor platform in a realistic work flow were coordinated by a Flight Control Team. A dedicated flight planning group, external control centers for rover tele-operations, and a biomedical monitoring team supported the field operations. A 10 min satellite communication delay and other limitations pertinent to human planetary surface activities were introduced. The fields of research for the experiments were geology, human factors, astrobiology, robotics, tele-science, exploration, and operations research. This paper provides an overview of the geological context and environmental conditions of the test site and the mission architecture, in particular the communication infrastructure emulating the signal travel time between Earth and Mars. We report on the operational work flows and the experiments conducted, including a deployable shelter prototype for multiple-day extravehicular activities and contingency situations.

Mars Analog Research and Technology Experiment (MARTE): A Simulated Mars Drilling Mission to Search for Subsurface Life at the Rio Tinto, Spain

NASA Technical Reports Server (NTRS)

Stoker, Carol; Lemke, Larry; Mandell, Humboldt; McKay, David; George, Jeffrey; Gomez-Alvera, Javier; Amils, Ricardo; Stevens, Todd; Miller, David

2003-01-01

The MARTE (Mars Astrobiology Research and Technology Experiment) project was selected by the new NASA ASTEP program, which supports field experiments having an equal emphasis on Astrobiology science and technology development relevant to future Astrobiology missions. MARTE will search for a hypothesized subsurface anaerobic chemoautotrophic biosphere in the region of the Tinto River in southwestern Spain while also demonstrating technology needed to search for a subsurface biosphere on Mars. The experiment is informed by the strategy for searching for life on Mars.

Human Mars Mission Design - The Ultimate Systems Challenge

NASA Technical Reports Server (NTRS)

Connolly, John F.; Joosten, B. Kent; Drake, Bret; Hoffman, Steve; Polsgrove, Tara; Rucker, Michelle; Andrews, Alida; Williams, Nehemiah

2017-01-01

A human mission to Mars will occur at some time in the coming decades. When it does, it will be the end result of a complex network of interconnected design choices, systems analyses, technical optimizations, and non-technical compromises. This mission will extend the technologies, engineering design, and systems analyses to new limits, and may very well be the most complex undertaking in human history. It can be illustrated as a large menu, or as a large decision tree. Whatever the visualization tool, there are numerous design decisions required to assemble a human Mars mission, and many of these interconnect with one another. This paper examines these many decisions and further details a number of choices that are highly interwoven throughout the mission design. The large quantity of variables and their interconnectedness results in a highly complex systems challenge, and the paper illustrates how a change in one variable results in ripples (sometimes unintended) throughout many other facets of the design. The paper concludes with a discussion of some mission design variables that can be addressed first, and those that have already been addressed as a result of ongoing National Aeronautics and Space Administration (NASA) developments, or as a result of decisions outside the technical arena. It advocates the need for a 'reference design' that can be used as a point of comparison, and to illustrate the system-wide impacts as design variables change.

NASA Intelligent Systems Project: Results, Accomplishments and Impact on Science Missions.

NASA Astrophysics Data System (ADS)

Coughlan, J. C.

2005-12-01

The Intelligent Systems Project was responsible for much of NASA's programmatic investment in artificial intelligence and advanced information technologies. IS has completed three major project milestones which demonstrated increased capabilities in autonomy, human centered computing, and intelligent data understanding. Autonomy involves the ability of a robot to place an instrument on a remote surface with a single command cycle, human centered computing supported a collaborative, mission centric data and planning system for the Mars Exploration Rovers and data understanding has produced key components of a terrestrial satellite observation system with automated modeling and data analysis capabilities. This paper summarizes the technology demonstrations and metrics which quantify and summarize these new technologies which are now available for future NASA missions.

NASA Intelligent Systems Project: Results, Accomplishments and Impact on Science Missions

NASA Technical Reports Server (NTRS)

Coughlan, Joseph C.

2005-01-01

The Intelligent Systems Project was responsible for much of NASA's programmatic investment in artificial intelligence and advanced information technologies. IS has completed three major project milestones which demonstrated increased capabilities in autonomy, human centered computing, and intelligent data understanding. Autonomy involves the ability of a robot to place an instrument on a remote surface with a single command cycle. Human centered computing supported a collaborative, mission centric data and planning system for the Mars Exploration Rovers and data understanding has produced key components of a terrestrial satellite observation system with automated modeling and data analysis capabilities. This paper summarizes the technology demonstrations and metrics which quantify and summarize these new technologies which are now available for future Nasa missions.

Lunar and Mars missions - Challenges for advanced life support

NASA Technical Reports Server (NTRS)

Duke, Michael B.

1988-01-01

The development of a suite of scenarios is a prerequisite to the studies that will enable an informed decision by the United States on a program to meet the recently announced space policy goal to expand human presence beyond earth orbit. NASA's Office of Exploration is currently studying a range of initiative options that would extend the sphere of human activity in space to Mars and include permanent bases or outposts on the moon and on Mars. This paper describes the evolutionary lunar base and the Mars expedition scenarios in some detail so that an evaluation can be made from the point of view of human support and opportunities. Alternative approaches in the development of lunar outposts are outlined along with Mars expeditionary scenarios. Human environmental issues are discussed, including: closed loop life support systems; EVA systems; mobility systems; and medical support, physiological deconditioning, and psychological effects associated with long-duration missions.

Simulation Based Studies of Low Latency Teleoperations for NASA Exploration Missions

NASA Technical Reports Server (NTRS)

Gernhardt, Michael L.; Crues, Edwin Z.; Bielski, Paul; Dexter, Dan; Litaker, Harry L.; Chappell, Steven P.; Beaton, Kara H.; Bekdash, Omar S.

2017-01-01

Human exploration of Mars will involve both crewed and robotic systems. Many mission concepts involve the deployment and assembly of mission support assets prior to crew arrival on the surface. Some of these deployment and assembly activities will be performed autonomously while others will be performed using teleoperations. However, significant communications latencies between the Earth and Mars make teleoperations challenging. Alternatively, low latency teleoperations are possible from locations in Mars orbit like Mars' moons Phobos and Deimos. To explore these latency opportunities, NASA is conducting a series of studies to investigate the effects of latency on telerobotic deployment and assembly activities. These studies are being conducted in laboratory environments at NASA's Johnson Space Center (JSC), the Human Exploration Research Analog (HERA) at JSC and the NASA Extreme Environment Mission Operations (NEEMO) underwater habitat off the coast of Florida. The studies involve two human-in-the-loop interactive simulations developed by the NASA Exploration Systems Simulations (NExSyS) team at JSC. The first simulation investigates manipulation related activities while the second simulation investigates mobility related activities. The first simulation provides a simple real-time operator interface with displays and controls for a simulated 6 degree of freedom end effector. The initial version of the simulation uses a simple control mode to decouple the robotic kinematic constraints and a communications delay to model latency effects. This provides the basis for early testing with more detailed manipulation simulations planned for the future. Subjects are tested using five operating latencies that represent teleoperation conditions from local surface operations to orbital operations at Phobos, Deimos and ultimately high Martian orbit. Subject performance is measured and correlated with three distance-to-target zones of interest. Each zone represents a target

Lightweight, High Performance, Low Cost Propulsion Systems for Mars Exploration Missions to Maximize Science Payload

NASA Astrophysics Data System (ADS)

Trinh, H. P.

2012-06-01

Utilization of new cold hypergolic propellants and leverage Missile Defense Agency technology for propulsion systems on Mars explorations will provide an increase of science payload and have significant payoffs and benefits for NASA missions.

The NASA In-Space Propulsion Technology Project, Products, and Mission Applicability

NASA Technical Reports Server (NTRS)

Anderson, David J.; Pencil, Eric; Liou, Larry; Dankanich, John; Munk, Michelle M.; Kremic, Tibor

2009-01-01

The In-Space Propulsion Technology (ISPT) Project, funded by NASA s Science Mission Directorate (SMD), is continuing to invest in propulsion technologies that will enable or enhance NASA robotic science missions. This overview provides development status, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of aerocapture, electric propulsion, advanced chemical thrusters, and systems analysis tools. Aerocapture investments improved: guidance, navigation, and control models of blunt-body rigid aeroshells; atmospheric models for Earth, Titan, Mars, and Venus; and models for aerothermal effects. Investments in electric propulsion technologies focused on completing NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6 to 7 kW throttle-able gridded ion system. The project is also concluding its High Voltage Hall Accelerator (HiVHAC) mid-term product specifically designed for a low-cost electric propulsion option. The primary chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. The project is also delivering products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. In-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations.

Mars Telecom Orbiter mission operations concepts

NASA Technical Reports Server (NTRS)

Deutsch, Marie-Jose; Komarek, Tom; Lopez, Saturnino; Townes, Steve; Synnott, Steve; Austin, Richard; Guinn, Joe; Varghese, Phil; Edwards, Bernard; Bondurant, Roy;

Planetary Protection for Polar Mars Missions

NASA Technical Reports Server (NTRS)

Rummel, J. D.

2003-01-01

The picture of Mars that is emerging from the Mars Global Surveyor and Odyssey results contrasts markedly from that portrayed shortly after the Viking missions ended. Particularly intriguing is the abundance of water ice seen both in the polar caps themselves, and in lower latitudes outside of the polar regions. Along with the new data comes a heightened consideration of the potential for biological contamination that may be carried by future missions, and its possible effects. Particularly challenging are scenarios where missions carrying perennial heat sources of high capacity and longevity (e.g., Radioisotope Thermoelectric Generators) could, by non-nominal landings or other mission operations be introduced to close contact with water ice on Mars - potentially forming Earthlike environments that could accommodate the growth of contaminant organisms.

Description of the REMS Ground Temperature Sensor aboard MSL NASA mission to Mars

NASA Astrophysics Data System (ADS)

Armiens, C.; Sebastian, E.; Gomez-Elvira, J.

2009-04-01

The Rover Environmental Monitoring Station, REMS, is part of the payload of the Mars Science Laboratory, MSL, a NASA mission to the red planet recently scheduled to launch on the fall of 2011. REMS comprises several instruments aimed at measuring ground and air temperature, wind speed and direction, ultraviolet radiation, pressure and humidity. The Ground Temperature Sensor, GTS, is a contactless multi band pyrometer. It is composed of three thermopiles measuring in different bands: 8 - 14 um, 16 - 20 um and 14.5 - 15.5 um. The first two bands are optimized for the higher and lower temperatures expected to be present on Mars during the lifetime of the mission. They also avoid the radiation generated by the rover itself, the Radioisotope Thermoelectric Generator, RTG, and the Sun that is reflected on the ground and reaches the thermopiles, as well as the atmospheric emission originated by the CO2. The use of two different bands to measure ground temperature allows the estimation of the emissivity of the surface by means of colour pyrometry algorithms. Thus we may determine not only the brightness temperature but also the real temperature of the ground, i.e., the kinetic temperature. The estimation of the emissivity may serve also to detect changes in the composition of the ground, as, for example, the formation of frost. The third thermopile is centred in the CO2 absorption band, the main component of the Martian atmosphere. This allows the determination of the residual influence that the atmosphere may have in the other two thermopile's bands. The brightness temperature of the air may also be estimated from this third thermopile. During Martian operations, the system may be degraded due to the deposition of dust over the thermopiles' filter. In order to correct for this degradation, the system includes a calibration plate, which partially fills the field of view of the thermopiles. This plate may be heated several degrees. Analyzing the signals before and during

Software Aids Visualization Of Mars Pathfinder Mission

NASA Technical Reports Server (NTRS)

Weidner, Richard J.

1996-01-01

Report describes Simulator for Imager for Mars Pathfinder (SIMP) computer program. SIMP generates "virtual reality" display of view through video camera on Mars lander spacecraft of Mars Pathfinder mission, along with display of pertinent textual and graphical data, for use by scientific investigators in planning sequences of activities for mission.

Mars Science Laboratory (MSL) : the US 2009 Mars rover mission

NASA Technical Reports Server (NTRS)

Palluconi, Frank; Tampari, Leslie; Steltzner, Adam; Umland, Jeff

2003-01-01

The Mars Science Laboratory mission is the 2009 United States Mars Exploration Program rover mission. The MSL Project expects to complete its pre-Phase A definition activity this fiscal year (FY2003), investigations in mid-March 2004, launch in 2009, arrive at Mars in 2010 during Northern hemisphere summer and then complete a full 687 day Mars year of surface exploration. MSL will assess the potential for habitability (past and present) of a carefully selected landing region on Mars by exploring for the chemical building blocks of life, and seeking to understand quantitatively the chemical and physical environment with which these components have interacted over the geologic history of the planet. Thus, MSL will advance substantially our understanding of the history of Mars and potentially, its capacity to sustain life.

Engaging Students Through Classroom Connection Webinars to Improve Their Understanding of the Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Graff, Paige V.; Achilles, Cherie

2013-01-01

Planetary exploration missions to other worlds, like Mars, can generate a lot of excitement and wonder for the public. The Mars Science Laboratory Mission is one of the latest planetary missions that has intrigued the public perhaps more than most. How can scientists and educational specialists capitalize on the allure of this mission and involve students and teachers in a way that not only shares the story of the mission, but actively engages classrooms with scientists and improves their understanding of the science? The Expedition Earth and Beyond (EEAB) Program [1], facilitated by the Astromaterials Research and Exploration Science (ARES) Directorate Education Program at the NASA Johnson Space Center achieves this by facilitating MSL mission focused classroom connection webinars. Five MSL-focused webinars facilitated through EEAB during the 2012 fall semester engaged almost 3000 students and teachers. Involved STEM experts/role models helped translate the science behind the Mars Science Laboratory mission in a comprehensive, exciting, and engaging manner. These virtual events captured participants attention while increasing their science awareness and understanding of the MSL mission.

Mars Global Surveyor Mission: Environmental Assessment

NASA Technical Reports Server (NTRS)

1995-01-01

This environmental assessment addresses the proposed action to complete the integration and launch the Mars Global Surveyor (MGS) spacecraft from Cape Canaveral Air Station (CCAS), Florida, during the launch window in November 1996. Mars Global Surveyor is part of the Solar System Exploration Program to the inner planets designed to maintain a sufficient level of scientific investigation and accomplishment so that the United States retains a leading position in solar system exploration through the end of the century. The Program consists of a specific sequence of missions, based on technological readiness, launch opportunities, rapidity of data return, and a balance of scientific disciplines. The purpose of the MGS mission would be to deliver a spacecraft platform to a low-altitude polar orbit around Mars where it would collect global observations of basic geological, geophysical, and climatological processes of the planet. To satisfy this purpose, the MGS mission would support a scientific set of objectives. Detailed global maps of surface topography, the distribution of minerals, the planet's mass, size, and shape, the characterization of Mars gravitational and magnetic fields, and the monitoring of global weather, collected over the period of one Martian year (about two Earth years), would help answer some of the questions about the evolution of Mars. Such an investigation would help scientists better understand the current state of water on Mars, the evolution of the planet's atmosphere, and the factors that led to major changes in the Martian climate. It would also provide much needed information on the magnetic field of Mars. Data collected from this mission would provide insight into the evolution of both Earth and the solar system, as well as demonstrate technological approaches that could be applicable to future Mars missions.

Portable Diagnostics Technology Assessment for Space Missions. Part 1; General Technology Capabilities for NASA Exploration Missions

NASA Technical Reports Server (NTRS)

Nelson, Emily S.; Chait, Arnon

2010-01-01

The changes in the scope of NASA s mission in the coming decade are profound and demand nimble, yet insightful, responses. On-board clinical and environmental diagnostics must be available for both mid-term lunar and long-term Mars exploration missions in an environment marked by scarce resources. Miniaturization has become an obvious focus. Despite solid achievements in lab-based devices, broad-based, robust tools for application in the field are not yet on the market. The confluence of rapid, wide-ranging technology evolution and internal planning needs are the impetus behind this work. This report presents an analytical tool for the ongoing evaluation of promising technology platforms based on mission- and application-specific attributes. It is not meant to assess specific devices, but rather to provide objective guidelines for a rational down-select of general categories of technology platforms. In this study, we have employed our expertise in the microgravity operation of fluidic devices, laboratory diagnostics for space applications, and terrestrial research in biochip development. A rating of the current state of technology development is presented using the present tool. Two mission scenarios are also investigated: a 30-day lunar mission using proven, tested technology in 5 years; and a 2- to 3-year mission to Mars in 10 to 15 years.

(abstract) Telecommunications for Mars Rovers and Robotic Missions

NASA Technical Reports Server (NTRS)

Cesarone, Robert J.; Hastrup, Rolf C.; Horne, William; McOmber, Robert

1997-01-01

Telecommunications plays a key role in all rover and robotic missions to Mars both as a conduit for command information to the mission and for scientific data from the mission. Telecommunications to the Earth may be accomplished using direct-to-Earth links via the Deep Space Network (DSN) or by relay links supported by other missions at Mars. This paper reviews current plans for missions to Mars through the 2005 launch opportunity and their capabilities in support of rover and robotic telecommunications.

MetNet Precursor - Network Mission to Mars

NASA Astrophysics Data System (ADS)

Harri, Arri-Matti

2010-05-01

We are developing a new kind of planetary exploration mission for Mars - MetNet in situ observation network based on a new semi-hard landing vehicle called the Met-Net Lander (MNL). The first MetNet vehicle, MetNet Precursor, slated for launch in 2011. The MetNet development work started already in 2001. The actual practical Precursor Mission development work started in January 2009 with participation from various space research institutes and agencies. The scientific rationale and goals as well as key mission solutions will be discussed. The eventual scope of the MetNet Mission is to deploy some 20 MNLs on the Martian surface using inflatable descent system structures, which will be supported by observations from the orbit around Mars. Currently we are working on the MetNet Mars Precursor Mission (MMPM) to deploy one MetNet Lander to Mars in the 2011 launch window as a technology and science demonstration mission. The MNL will have a versatile science payload focused on the atmospheric science of Mars. Time-resolved in situ Martian meteorological measurements acquired by the Viking, Mars Pathfinder and Phoenix landers and remote sensing observations by the Mariner 9, Viking, Mars Global Surveyor, Mars Odyssey and the Mars Express orbiters have provided the basis for our current understanding of the behavior of weather and climate on Mars. However, the available amount of data is still scarce and a wealth of additional in situ observations are needed on varying types of Martian orography, terrain and altitude spanning all latitudes and longitudes to address microscale and mesoscale atmospheric phenomena. Detailed characterization of the Martian atmospheric circulation patterns and climatological cycles requires simultaneous in situ atmospheric observations. The scientific payload of the MetNet Mission encompasses separate instrument packages for the atmospheric entry and descent phase and for the surface operation phase. The MetNet mission concept and key probe

Mars Surface Habitability Options

NASA Technical Reports Server (NTRS)

Howe, A. Scott; Simon, Matthew; Smitherman, David; Howard, Robert; Toups, Larry; Hoffman, Stephen J.

2015-01-01

This paper reports on current habitability concepts for an Evolvable Mars Campaign (EMC) prepared by the NASA Human Spaceflight Architecture Team (HAT). For many years NASA has investigated alternative human Mars missions, examining different mission objectives, trajectories, vehicles, and technologies; the combinations of which have been referred to as reference missions or architectures. At the highest levels, decisions regarding the timing and objectives for a human mission to Mars continue to evolve while at the lowest levels, applicable technologies continue to advance. This results in an on-going need for assessments of alternative system designs such as the habitat, a significant element in any human Mars mission scenario, to provide meaningful design sensitivity characterizations to assist decision-makers regarding timing, objectives, and technologies. As a subset of the Evolvable Mars Campaign activities, the habitability team builds upon results from past studies and recommends options for Mars surface habitability compatible with updated technologies.

Planetary protection implementation on future Mars lander missions

NASA Astrophysics Data System (ADS)

Howell, Robert; Devincenzi, Donald L.

1993-06-01

A workshop was convened to discuss the subject of planetary protection implementation for Mars lander missions. It was sponsored and organized by the Exobiology Implementation Team of the U.S./Russian Joint Working Group on Space Biomedical and Life Support Systems. The objective of the workshop was to discuss planetary protection issues for the Russian Mars '94 mission, which is currently under development, as well as for additional future Mars lander missions including the planned Mars '96 and U.S. MESUR Pathfinder and Network missions. A series of invited presentations was made to ensure that workshop participants had access to information relevant to the planned discussions. The topics summarized in this report include exobiology science objectives for Mars exploration, current international policy on planetary protection, planetary protection requirements developed for earlier missions, mission plans and designs for future U.S. and Russian Mars landers, biological contamination of spacecraft components, and techniques for spacecraft bioload reduction. In addition, the recent recommendations of the U.S. Space Studies Board (SSB) on this subject were also summarized. Much of the discussion focused on the recommendations of the SSB. The SSB proposed relaxing the planetary protection requirements for those Mars lander missions that do not contain life detection experiments, but maintaining Viking-like requirements for those missions that do contain life detection experiments. The SSB recommendations were found to be acceptable as a guide for future missions, although many questions and concerns about interpretation were raised and are summarized. Significant among the concerns was the need for more quantitative guidelines to prevent misinterpretation by project offices and better access to and use of the Viking data base of bio-assays to specify microbial burden targets. Among the questions raised were how will the SSB recommendations be integrated with existing

Planetary protection implementation on future Mars lander missions

NASA Technical Reports Server (NTRS)

Howell, Robert; Devincenzi, Donald L.

1993-01-01

A workshop was convened to discuss the subject of planetary protection implementation for Mars lander missions. It was sponsored and organized by the Exobiology Implementation Team of the U.S./Russian Joint Working Group on Space Biomedical and Life Support Systems. The objective of the workshop was to discuss planetary protection issues for the Russian Mars '94 mission, which is currently under development, as well as for additional future Mars lander missions including the planned Mars '96 and U.S. MESUR Pathfinder and Network missions. A series of invited presentations was made to ensure that workshop participants had access to information relevant to the planned discussions. The topics summarized in this report include exobiology science objectives for Mars exploration, current international policy on planetary protection, planetary protection requirements developed for earlier missions, mission plans and designs for future U.S. and Russian Mars landers, biological contamination of spacecraft components, and techniques for spacecraft bioload reduction. In addition, the recent recommendations of the U.S. Space Studies Board (SSB) on this subject were also summarized. Much of the discussion focused on the recommendations of the SSB. The SSB proposed relaxing the planetary protection requirements for those Mars lander missions that do not contain life detection experiments, but maintaining Viking-like requirements for those missions that do contain life detection experiments. The SSB recommendations were found to be acceptable as a guide for future missions, although many questions and concerns about interpretation were raised and are summarized. Significant among the concerns was the need for more quantitative guidelines to prevent misinterpretation by project offices and better access to and use of the Viking data base of bioassays to specify microbial burden targets. Among the questions raised were how will the SSB recommendations be integrated with existing

Asteroid Redirect Mission Briefing on This Week @NASA – September 19, 2016

NASA Image and Video Library

2016-09-19

On Sept. 14, officials from the White House and NASA discussed the space agency’s Asteroid Redirect Mission (ARM) during a televised event at NASA’s Goddard Space Flight Center. On the mission, which is targeted for launch in Dec. 2021, NASA plans to send a robotic spacecraft to an asteroid tens of millions of miles from Earth, capture a multi-ton boulder, and bring it to an orbit near the moon for future exploration by astronauts on a following mission aboard NASA’s Orion spacecraft. During the live discussion, John Holdren, assistant to President Obama for Science and Technology, NASA Administrator Charles Bolden and ARM Program Director Michele Gates highlighted the mission’s scientific and technological benefits, how the mission will support NASA’s goal of sending humans to Mars in the 2030s, and how it will demonstrate technology relevant to defending Earth from potentially hazardous asteroids. Also, Astronaut Tim Kopra Visits DC Area, The Warmest August in 136 Years, and 2016 Arctic Sea Ice Minimum Ties 2nd Lowest on Record!

Forward Contamination of the Moon and Mars: Implications for Future Life Detection Missions

NASA Technical Reports Server (NTRS)

Glavin, Daniel P.; Dworkin, Jason P.; Lupisella, Mark; Kminek, Gerhard; Rummel, John D.

2004-01-01

NASA and ESA have outlined new visions for solar system exploration that will include a series of lunar robotic missions to prepare for, and support a human return to the Moon, and future human exploration of Mars and other destinations. One of the guiding principles for exploration is to pursue compelling scientific questions about the origin and evolution of life. The search for life on objects such as Mars will require that all spacecraft and instrumentation be sufficiently cleaned and sterilized prior to launch to ensure that the scientific integrity of extraterrestrial samples is not jeopardized by terrestrial organic contamination. Under COSPAR's current planetary protection policy for the Moon, no sterilization procedures are required for outbound lunar spacecraft. Nonetheless, future in situ investigations of a variety of locations on the Moon by highly sensitive instruments designed to search for biologically derived organic compounds would help assess the contamination of the Moon by lunar spacecraft. These studies could also provide valuable "ground truth" data for Mars sample return missions and help define planetary protection requirements for future Mars bound spacecraft carrying life detection experiments. In addition, studies of the impact of terrestrial contamination of the lunar surface by the Apollo astronauts could provide valuable data to help refine future Mars surface exploration plans for a human mission to Mars.

Using NASA's Space Launch System to Enable Game Changing Science Mission Designs

NASA Technical Reports Server (NTRS)

Creech, Stephen D.

2013-01-01

NASA's Marshall Space Flight Center is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will help restore U.S. leadership in space by carrying the Orion Multi-Purpose Crew Vehicle and other important payloads far beyond Earth orbit. Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids, Mars, and the outer solar system. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required with several gravity-assist planetary fly-bys to achieve the necessary outbound velocity. The SLS rocket, using significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, reducing trip times and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as monolithic telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

NASA to Launch Mars Rover in 2020 Artist Concept

NASA Image and Video Library

2016-07-14

NASA's Mars 2020 Project will re-use the basic engineering of NASA's Mars Science Laboratory/Curiosity to send a different rover to Mars, with new objectives and instruments. This artist's concept depicts the top of the 2020 rover's mast. http://photojournal.jpl.nasa.gov/catalog/PIA20760

Frost on Mars

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.

How safe is safe enough? Radiation risk for a human mission to Mars.

PubMed

Cucinotta, Francis A; Kim, Myung-Hee Y; Chappell, Lori J; Huff, Janice L

2013-01-01

Astronauts on a mission to Mars would be exposed for up to 3 years to galactic cosmic rays (GCR)--made up of high-energy protons and high charge (Z) and energy (E) (HZE) nuclei. GCR exposure rate increases about three times as spacecraft venture out of Earth orbit into deep space where protection of the Earth's magnetosphere and solid body are lost. NASA's radiation standard limits astronaut exposures to a 3% risk of exposure induced death (REID) at the upper 95% confidence interval (CI) of the risk estimate. Fatal cancer risk has been considered the dominant risk for GCR, however recent epidemiological analysis of radiation risks for circulatory diseases allow for predictions of REID for circulatory diseases to be included with cancer risk predictions for space missions. Using NASA's models of risks and uncertainties, we predicted that central estimates for radiation induced mortality and morbidity could exceed 5% and 10% with upper 95% CI near 10% and 20%, respectively for a Mars mission. Additional risks to the central nervous system (CNS) and qualitative differences in the biological effects of GCR compared to terrestrial radiation may significantly increase these estimates, and will require new knowledge to evaluate.

How Safe Is Safe Enough? Radiation Risk for a Human Mission to Mars

PubMed Central

Cucinotta, Francis A.; Kim, Myung-Hee Y.; Chappell, Lori J.; Huff, Janice L.

2013-01-01

Astronauts on a mission to Mars would be exposed for up to 3 years to galactic cosmic rays (GCR) — made up of high-energy protons and high charge (Z) and energy (E) (HZE) nuclei. GCR exposure rate increases about three times as spacecraft venture out of Earth orbit into deep space where protection of the Earth's magnetosphere and solid body are lost. NASA's radiation standard limits astronaut exposures to a 3% risk of exposure induced death (REID) at the upper 95% confidence interval (CI) of the risk estimate. Fatal cancer risk has been considered the dominant risk for GCR, however recent epidemiological analysis of radiation risks for circulatory diseases allow for predictions of REID for circulatory diseases to be included with cancer risk predictions for space missions. Using NASA's models of risks and uncertainties, we predicted that central estimates for radiation induced mortality and morbidity could exceed 5% and 10% with upper 95% CI near 10% and 20%, respectively for a Mars mission. Additional risks to the central nervous system (CNS) and qualitative differences in the biological effects of GCR compared to terrestrial radiation may significantly increase these estimates, and will require new knowledge to evaluate. PMID:24146746

Pioneer Mars surface penetrator mission. Mission analysis and orbiter design

NASA Technical Reports Server (NTRS)

1974-01-01

The Mars Surface Penetrator mission was designed to provide a capability for multiple and diverse subsurface science measurements at a low cost. Equipment required to adapt the Pioneer Venus spacecraft for the Mars mission is described showing minor modifications to hardware. Analysis and design topics which are similar and/or identical to the Pioneer Venus program are briefly discussed.

A Trade Study and Metric for Penetration and Sampling Devices for Possible Use on the NASA 2003 and 2005 Mars Sample Return Missions

NASA Technical Reports Server (NTRS)

McConnell, Joshua B.

2000-01-01

The scientific exploration of Mars will require the collection and return of subterranean samples to Earth for examination. This necessitates the use of some type of device or devices that possesses the ability to effectively penetrate the Martian surface, collect suitable samples and return them to the surface in a manner consistent with imposed scientific constraints. The first opportunity for such a device will occur on the 2003 and 2005 Mars Sample Return missions, being performed by NASA. This paper reviews the work completed on the compilation of a database containing viable penetrating and sampling devices, the performance of a system level trade study comparing selected devices to a set of prescribed parameters and the employment of a metric for the evaluation and ranking of the traded penetration and sampling devices, with respect to possible usage on the 03 and 05 sample return missions. The trade study performed is based on a select set of scientific, engineering, programmatic and socio-political criterion. The use of a metric for the various penetration and sampling devices will act to expedite current and future device selection.

Emirates Mars Mission (EMM) Overview

NASA Astrophysics Data System (ADS)

Sharaf, Omran; Amiri, Sarah; AlMheiri, Suhail; Alrais, Adnan; Wali, Mohammad; AlShamsi, Zakareyya; AlQasim, Ibrahim; AlHarmoodi, Khuloud; AlTeneiji, Nour; Almatroushi, Hessa; AlShamsi, Maryam; AlAwadhi, Mohsen; McGrath, Michael; Withnell, Pete; Ferrington, Nicolas; Reed, Heather; Landin, Brett; Ryan, Sean; Pramann, Brian

2017-04-01

United Arab Emirates (UAE) has entered the space exploration race with the announcement of Emirates Mars Mission (EMM), the first Arab Islamic mission to another planet, in 2014. Through this mission, UAE is to send an unmanned probe, called Hope probe, to be launched in summer 2020 and reach Mars by 2021 to coincide with UAE's 50th anniversary. Through a sequence of subsequent maneuvers, the spacecraft will enter a large science orbit that has a periapsis altitude of 20,000 km, an apoapsis altitude of 43,000 km, and an inclination of 25 degrees. The mission is designed to (1) characterize the state of the Martian lower atmosphere on global scales and its geographic, diurnal and seasonal variability, (2) correlate rates of thermal and photochemical atmospheric escape with conditions in the collisional Martian atmosphere, and (3) characterize the spatial structure and variability of key constituents in the Martian exosphere. These objectives will be met by four investigations with diurnal variability on sub-seasonal timescales which are (1) determining the three-dimensional thermal state of the lower atmosphere, (2) determining the geographic and diurnal distribution of key constituents in the lower atmosphere, (3) determining the abundance and spatial variability of key neutral species in the thermosphere, and (4) determining the three-dimensional structure and variability of key species in the exosphere. EMM will collect these information about the Mars atmospheric circulation and connections through a combination of three distinct instruments that image Mars in the visible, thermal infrared and ultraviolet wavelengths and they are the Emirates eXploration Imager (EXI), the Emirates Mars InfraRed Spectrometer (EMIRS), and the EMM Mars Ultraviolet Spectrometer (EMUS). EMM has passed its Mission Concept Review (MCR), System Requirements Review (SRR), System Design Review (SDR), and Preliminary Design Review (PDR) phases. The mission is led by Emiratis from Mohammed

Human Mars Surface Mission Nuclear Power Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2018-01-01

A key decision facing Mars mission designers is how to power a crewed surface field station. Unlike the solar-powered Mars Exploration Rovers (MER) that could retreat to a very low power state during a Martian dust storm, human Mars surface missions are estimated to need at least 15 kilowatts of electrical (kWe) power simply to maintain critical life support and spacecraft functions. 'Hotel' loads alone for a pressurized crew rover approach two kWe; driving requires another five kWe-well beyond what the Curiosity rover’s Radioisotope Power System (RPS) was designed to deliver. Full operation of a four-crew Mars field station is estimated at about 40 kWe. Clearly, a crewed Mars field station will require a substantial and reliable power source, beyond the scale of robotic mission experience. This paper explores the applications for both fission and RPS nuclear options for Mars.

NASA's Phoenix Lander on Mars, Nearly a Decade Later

NASA Image and Video Library

2018-02-20

This is one of two images taken nearly a decade apart of NASA's Mars Phoenix Lander and related hardware around the mission's May 25, 2008, landing site on far-northern Mars. By late 2017, dust had obscured much of what was visible two months after the landing. Both images were taken by the High Resolution Imaging Science Experiment (HiRISE) camera on NASA's Mars Reconnaissance Orbiter. The one with three patches of darker ground -- where landing events removed dust -- was taken on July 20, 2008. It is Fig. 1, an excerpt of HiRISE observation PSP_009290_2485. The one with a more even coating of pale dust throughout the area was taken on Dec. 21, 2017. It is Fig. 2, an excerpt of HiRISE observation ESP_053451_2485. Both cover an area roughly 300 meters wide at 68 degrees north latitude, 234 degrees east longitude, and the two are closely matched in viewing and illumination geometry, from about five Martian years apart in northern hemisphere summers. An animation comparing the two images shows a number of changes between mid-2008 and late 2017. The lander (top) appears darker, and is now covered by dust. The dark spot created by the heat shield impact (right) is brighter, again due to dust deposition. The back shell and parachute (bottom) shows a darker parachute and brighter area of impact disturbance, thanks again to deposits of dust. We also see that the parachute has shifted in the wind, moving to the east. In August 2008, Phoenix completed its three-month mission studying Martian ice, soil and atmosphere. The lander worked for two additional months before reduced sunlight caused energy to become insufficient to keep the lander functioning. The solar-powered robot was not designed to survive through the dark and cold conditions of a Martian arctic winter. An animation and both images are available at https://photojournal.jpl.nasa.gov/catalog/PIA22223

A Mars orbiter mission design

NASA Astrophysics Data System (ADS)

Castronuovo, Marco M.

1992-08-01

A preliminary study of a new orbiter mission to Mars using an earth gravity assist is presented. The trajectory resulting from this study has been evaluated utilizing Everhart's (1985) integrator RADAU. The mission sequences are described and compared to other proposed mission designs and some mission opportunities for the years 1997 to 2014 are discussed.

PADME (Phobos And Deimos and Mars Environment): A Proposed NASA Discovery Mission to Investigate the Two Moons of Mars

NASA Technical Reports Server (NTRS)

Lee, Pascal; Benna, Mehdi; Britt, Daniel; Colaprete, Anthony; Davis, Warren; Delory, Greg; Elphic, Richard; Fulsang, Ejner; Genova, Anthony; Glavin, Daniel;

Nuclear power technology requirements for NASA exploration missions

NASA Technical Reports Server (NTRS)

Bloomfield, Harvey S.

1990-01-01

It is pointed out that future exploration of the moon and Mars will mandate developments in many areas of technology. In particular, major advances will be required in planet surface power systems. Critical nuclear technology challenges that can enable strategic self-sufficiency, acceptable operational costs, and cost-effective space transportation goals for NASA exploration missions have been identified. Critical technologies for surface power systems include stationary and mobile nuclear reactor and radioisotope heat sources coupled to static and dynamic power conversion devices. These technologies can provide dramatic reductions in mass, leading to operational and transportation cost savings. Critical technologies for space transportation systems include nuclear thermal rocket and nuclear electric propulsion options, which present compelling concepts for significantly reducing mass, cost, or travel time required for Earth-Mars transport.

Mars Sample Return in the Context of the Mars Exploration Program

NASA Astrophysics Data System (ADS)

Garvin, J. B.

2002-05-01

The scientific priorities developed for the scientific exploration of Mars by the Mars Exploration Program Assessment Group [MEPAG, 2001] and as part of the Committee on Planetary and Lunar Exploration (COMPLEX) recent assessment of the NASA Mars Exploration Program [COMPLEX, 2001] all involve a campaign of Mars Sample Return (MSR) missions. Such MSR missions are required to address in a definitive manner most of the highest priority investigations within overarching science themes which include: (1) biological potential (past or present); (2) climate (past or present); (3) solid planet (surface and interior, past and present); (4) knowledge necessary to prepare for eventual human exploration of Mars. NASA's current Mars Exploration Program (MEP) contains specific flight mission developments and plans only for the present decade (2002-2010), including a cascade of missions designed to set the stage for an inevitable campaign of MSR missions sometime in the second decade (2011-2020). Studies are presently underway to examine implementation options for a first MSR mission in which at least 500g of martian materials (including lithic fragments) would be returned to Earth from a landing vicinity carefully selected on the basis of the comprehensive orbital and surface-based remote sensing campaign that is ongoing (MGS, ODYSSEY) and planned (MER, MRO, 2009 MSL). Key to the first of several MSR's is attention to risk, cost, and enabling technologies that facilitate access to most scientifically-compelling martian materials at very local scales. The context for MSR's in the upcoming decade remains a vital part of NASA's scientific strategy for Mars exploration.

Planned Environmental Microbiology Aspects of Future Lunar and Mars Missions

NASA Technical Reports Server (NTRS)

Ott, C. Mark; Castro, Victoria A.; Pierson, Duane L.

2006-01-01

With the establishment of the Constellation Program, NASA has initiated efforts designed similar to the Apollo Program to return to the moon and subsequently travel to Mars. Early lunar sorties will take 4 crewmembers to the moon for 4 to 7 days. Later missions will increase in duration up to 6 months as a lunar habitat is constructed. These missions and vehicle designs are the forerunners of further missions destined for human exploration of Mars. Throughout the planning and design process, lessons learned from the International Space Station (ISS) and past programs will be implemented toward future exploration goals. The standards and requirements for these missions will vary depending on life support systems, mission duration, crew activities, and payloads. From a microbiological perspective, preventative measures will remain the primary techniques to mitigate microbial risk. Thus, most of the effort will focus on stringent preflight monitoring requirements and engineering controls designed into the vehicle, such as HEPA air filters. Due to volume constraints in the CEV, in-flight monitoring will be limited for short-duration missions to the measurement of biocide concentration for water potability. Once long-duration habitation begins on the lunar surface, a more extensive environmental monitoring plan will be initiated. However, limited in-flight volume constraints and the inability to return samples to Earth will increase the need for crew capabilities in determining the nature of contamination problems and method of remediation. In addition, limited shelf life of current monitoring hardware consumables and limited capabilities to dispose of biohazardous trash will drive flight hardware toward non-culture based methodologies, such as hardware that rapidly distinguishes biotic versus abiotic surface contamination. As missions progress to Mars, environmental systems will depend heavily on regeneration of air and water and biological waste remediation and

Life Sciences Issues for a Mission to Mars

NASA Technical Reports Server (NTRS)

1997-01-01

Session MP5 includes short reports on: (1) Cardiovascular Concerns for a Mars Mission: Autonomic and Biomechanical Effects; (2) Reducing the Risk of Space Radiation Induced Bioeffects: Vehicle Design and Protectant Molecules; (3) Musculoskeletal Issues for Long Duration Mission: Muscle Mass Preservation, Renal Stone Risk Factors, Countermeasures, and Contingency Treatment Planning; (4) Psychological Issues and Crew Selection for a Mars Mission: Maximizing the Mix for the Long Haul; and (5) Issues in Crew Health, Medical Selection and Medical Officer (CMO) Training for a Mission to Mars.

Extending the NASA Ames Mars General Circulation Model to Explore Mars’ Middle Atmosphere

NASA Astrophysics Data System (ADS)

Brecht, Amanda; Hollingsworth, J.; Kahre, M.; Schaeffer, J.

2013-10-01

The NASA Ames Mars General Circulation Model (MGCM) upper boundary has been extended to ~120 km altitude (p ~10-5 mbar). The extension of the MGCM upper boundary initiates the ability to understand the connection between the lower and upper atmosphere of Mars through the middle atmosphere 70 - 120 km). Moreover, it provides the opportunity to support future missions (i.e. the 2013 MAVEN mission). A major factor in this extension is the incorporation of the Non-Local Thermodynamic Equilibrium (NLTE) heating (visible) and cooling (infrared). This modification to the radiative transfer forcing (i.e., RT code) has been significantly tested in a 1D vertical column and now has been ported to the full 3D Mars GCM. Initial results clearly show the effects of NLTE in the upper middle atmosphere. Diagnostic of seasonal mean fields and large-scale wave activity will be shown with insight into circulation patterns in the middle atmosphere. Furthermore, sensitivity tests with the resolution of the pressure and temperature grids, in which the k-coefficients are calculated upon, have been performed in the 1D RT code. Our progress on this research will be presented. Brecht is supported by NASA’s Postdoctoral Program at the Ames Research Center, administered by Oak Ridge Associated Universities through a contract with NASA.

Southern Meridiani Planum - A candidate landing site for the first crewed mission to Mars

NASA Astrophysics Data System (ADS)

Clarke, J. D. A.; Willson, D.; Smith, H.; Hobbs, S. W.; Jones, E.

2017-04-01

Astronauts working on the surface of Mars have the capability to explore efficiently, rapidly, and flexibly, allowing them to perform a wide range of field investigations. NASA has begun an open international process to identify and evaluate candidate locations where crews could land, live and work on the martian surface, beginning with the First Landing Site/Exploration Zone Workshop for Human Missions to the Surface of Mars in October 2015. Forty seven sites were proposed, including several at or near the Meridiani area, the subject of this paper. We consider the Meridiani area an excellent candidate for the first missions to Mars. It is accessible, safe, contains potential water resources in the form of poly-hydrated magnesium sulphates, has diverse science features with high likelihood of meeting all science goals, has other potential resources and potential for further longer-ranged exploration. The presence of hardware from previous missions will be of benefit to studies of materials to martian conditions, assessing the effectiveness of historic planetary protection strategies, and engaging public interest. Lastly, parts of the Meridiani region have been well studied from the surface by the Opportunity mission, providing ground truth for orbital data. As one of the best documented regions of Mars this will allow a "Go where you know" approach for the first crewed missions, especially with regard to safety, trafficability, and water resource potential.

The Mawrth Vallis region of Mars: A potential landing site for the Mars Science Laboratory (MSL) mission.

PubMed

Michalski, Joseph R; Jean-PierreBibring; Poulet, François; Loizeau, Damien; Mangold, Nicolas; Dobrea, Eldar Noe; Bishop, Janice L; Wray, James J; McKeown, Nancy K; Parente, Mario; Hauber, Ernst; Altieri, Francesca; Carrozzo, F Giacomo; Niles, Paul B

2010-09-01

The primary objective of NASA's Mars Science Laboratory (MSL) mission, which will launch in 2011, is to characterize the habitability of a site on Mars through detailed analyses of the composition and geological context of surface materials. Within the framework of established mission goals, we have evaluated the value of a possible landing site in the Mawrth Vallis region of Mars that is targeted directly on some of the most geologically and astrobiologically enticing materials in the Solar System. The area around Mawrth Vallis contains a vast (>1 × 10⁶ km²) deposit of phyllosilicate-rich, ancient, layered rocks. A thick (>150 m) stratigraphic section that exhibits spectral evidence for nontronite, montmorillonite, amorphous silica, kaolinite, saponite, other smectite clay minerals, ferrous mica, and sulfate minerals indicates a rich geological history that may have included multiple aqueous environments. Because phyllosilicates are strong indicators of ancient aqueous activity, and the preservation potential of biosignatures within sedimentary clay deposits is high, martian phyllosilicate deposits are desirable astrobiological targets. The proposed MSL landing site at Mawrth Vallis is located directly on the largest and most phyllosilicate-rich deposit on Mars and is therefore an excellent place to explore for evidence of life or habitability.

MarCOs, Mars and Earth

NASA Image and Video Library

2018-03-29

An artist's rendering of the twin Mars Cube One (MarCO) spacecraft flying over Mars with Earth in the distance. The MarCOs will be the first CubeSats -- a kind of modular, mini-satellite -- flown in deep space. They're designed to fly along behind NASA's InSight lander on its cruise to Mars. If they make the journey, they will test a relay of data about InSight's entry, descent and landing back to Earth. Though InSight's mission will not depend on the success of the MarCOs, they will be a test of how CubeSats can be used in deep space. https://photojournal.jpl.nasa.gov/catalog/PIA22316

Antenna Technologies for Future NASA Exploration Missions

NASA Technical Reports Server (NTRS)

Miranda, Felix A.

2006-01-01

NASA s plans for the manned exploration of the moon and Mars will rely heavily on the development of a reliable communications infrastructure on the surface and back to Earth. Future missions will thus focus not only on gathering scientific data, but also on the formation of the communications network. In either case, unique requirements become imposed on the antenna technologies necessary to accomplish these tasks. For example, surface activity applications such as robotic rovers, human extravehicular activities (EVA), and probes will require small size, lightweight, low power, multi-functionality, and robustness for the antenna elements being considered. Trunk-line communications to a centralized habitat on the surface and back to Earth (e.g., surface relays, satellites, landers) will necessitate wide-area coverage, high gain, low mass, deployable antennas. Likewise, the plethora of low to high data rate services desired to guarantee the safety and quality of mission data for robotic and human exploration will place additional demands on the technology. Over the past year, NASA Glenn Research Center has been heavily involved in the development of candidate antenna technologies with the potential for meeting these strict requirements. This technology ranges from electrically small antennas to phased array and large inflatable structures. A summary of this overall effort is provided, with particular attention being paid to small antenna designs and applications. A discussion of the Agency-wide activities of the Exploration Systems Mission Directorate (ESMD) in forthcoming NASA missions, as they pertain to the communications architecture for the lunar and Martian networks is performed, with an emphasis on the desirable qualities of potential antenna element designs for envisioned communications assets. Identified frequency allocations for the lunar and Martian surfaces, as well as asset-specific data services will be described to develop a foundation for viable

Mars MetNet Precursor Mission Status

NASA Astrophysics Data System (ADS)

Harri, A.-M.; Aleksashkin, S.; Guerrero, H.; Schmidt, W.; Genzer, M.; Vazquez, L.; Haukka, H.

2013-09-01

We are developing a new kind of planetary exploration mission for Mars 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 [1] 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.

Mars Observer Mission: Mapping the Martian World

NASA Technical Reports Server (NTRS)

1992-01-01

The 1992 Mars Observer Mission is highlighted in this video overview of the mission objectives and planning. Using previous photography and computer graphics and simulation, the main objectives of the 687 day (one Martian year) consecutive orbit by the Mars Observer Satellite around Mars are explained. Dr. Arden Albee, the project scientist, speaks about the pole-to-pole mapping of the Martian surface topography, the planned relief maps, the chemical and mineral composition analysis, the gravity fields analysis, and the proposed search for any Mars magnetic fields.

In-Space Propulsion Technology Products Ready for Infusion on NASA's Future Science Missions

NASA Technical Reports Server (NTRS)

Anderson, David J.; Pencil, Eric; Peterson, Todd; Dankanich, John; Munk, Michele M.

2012-01-01

Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing and delivering in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling, for future NASA flagship and sample return missions currently being considered. They have a broad applicability to future competed mission solicitations. The high-temperature Advanced Material Bipropellant Rocket (AMBR) engine, providing higher performance for lower cost, was completed in 2009. Two other ISPT technologies are nearing completion of their technology development phase: 1) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 2) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; aerothermal effect models; and atmospheric models for Earth, Titan, Mars and Venus. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that have recently completed their technology development and will be ready for infusion into NASA s Discovery, New Frontiers, SMD Flagship, or technology demonstration missions.

Medical Systems Engineering to Support Mars Mission Crew Autonomy

NASA Technical Reports Server (NTRS)

Antonsen, Erik; Mindock, Jennifer

2017-01-01

Human spaceflight missions to Mars face exceptionally challenging resource limitations that far exceed those faced before. Increasing transit times, decreasing opportunity for resupply, communications challenges, and extended time to evacuate a crew to definitive medical care dictate a level of crew autonomy in medical care that is beyond the current medical model. To approach this challenge, a medical systems engineering approach is proposed that relies on a clearly articulated Concept of Operations and risk analysis tools that are in development at NASA. This paper proposes an operational clinical model with key terminology and concepts translated to a controls theory paradigm to frame a common language between clinical and engineering teams. This common language will be used for design and validation of an exploration medical system that is fully integrated into a Mars transit vehicle. This approach merges medical simulation, human factors evaluation techniques, and human-in-the-loop testing in ground based analogs to tie medical hardware and software subsystem performance and overall medical system functionality to metrics of operational medical autonomy. Merging increases in operational clinical autonomy with a more restricted vehicle system resource scenario in interplanetary spaceflight will require an unprecedented level of medical and engineering integration. Full integration of medical capabilities into a Mars vehicle system may require a new approach to integrating medical system design and operations into the vehicle Program structure. Prior to the standing-up of a Mars Mission Program, proof of concept is proposed through the Human Research Program.

ourney to Mars: An international effort on This Week @NASA – October 16, 2015

NASA Image and Video Library

2015-10-16

During meetings and public events at the International Astronautical Congress (IAC), Oct. 12-16 in Jerusalem, NASA Administrator Charlie Bolden and several other NASA officials highlighted the agency’s recently released plan to send astronauts to Mars in the 2030’s. They also emphasized the need for international partnerships and cooperation to make a mission of this magnitude a reality, the importance of harnessing enthusiasm for space exploration and the need to encourage young people to develop the skills we’ll need for the Journey to Mars. Also, New American record in space, Flyby of Saturnian moon, Next launch for Cygnus, Access to space for small satellites and more! JPL Open House is a big draw.

Effect of Earth and Mars departure delays on human missions to Mars

NASA Technical Reports Server (NTRS)

Desai, Prasun N.; Tartabini, Paul V.

1993-01-01

This study determines the impact on the initial mass in low-Earth orbit (IMLEO) for delaying departure from Mars and Earth by 5, 15, and 30 days, once a nominal mission to Mars has been selected. Additionally, the use of a deep space maneuver (DSM) is attempted to alleviate the IMLEO penalties. Three different classes of missions are analyzed using chemical and nuclear thermal propulsion systems in the 2000-2025 time-frame: opposition, conjunction, and fast-transfer conjunction. The results indicate that Mars and Earth delays can lead to large IMLEO penalties. Opposition and fast-transfer conjunction class missions have the highest IMLEO penalties, upwards of 432.4 mt and 1977.3 mt, respectively. Conjunction class missions, on the other hand, tend to be insensitive to Mars and Earth delays having IMLEO penalties under 103.5 mt. As expected, nuclear thermal propulsion had significantly lower IMLEO penalties as compared to chemical propulsion. The use of a DSM is found not to have a significant impact on reducing the IMLEO penalties. Through this investigation, the effect of off-nominal departure conditions on the overall mission (i.e., IMLEO) can be gained, enabling mission designers to incorporate the influence of off-nominal departure conditions of the interplanetary trajectory in the overall conceptual design process of a Mars transfer vehicle.

Emirates Mars Mission (EMM) 2020 Overview

NASA Astrophysics Data System (ADS)

Amiri, S.; Sharaf, O.; AlMheiri, S.; AlRais, A.; Wali, M.; Al Shamsi, Z.; Al Qasim, I.; Al Harmoodi, K.; Al Teneiji, N.; Almatroushi, H. R.; Al Shamsi, M. R.; Altunaiji, E. S.; Lootah, F. H.; Badri, K. M.; McGrath, M.; Withnell, P.; Ferrington, N.; Reed, H.; Landin, B.; Ryan, S.; Pramann, B.; Brain, D.; Deighan, J.; Chaffin, M.; Holsclaw, G.; Drake, G.; Wolff, M. J.; Edwards, C. S.; Lillis, R. J.; Smith, M. D.; Forget, F.; Fillingim, M. O.; England, S.; Christensen, P. R.; Osterloo, M. M.; Jones, A. R.

2017-12-01

United Arab Emirates (UAE) has entered the space exploration race with the announcement of Emirates Mars Mission (EMM), the first Emirati mission to another planet, in 2014. Through this mission, UAE is to send an unmanned probe, called Hope probe, to be launched in summer 2020 and reach Mars by 2021 to coincide with UAE's 50th anniversary. The mission should be unique, and should aim for novel and significant discoveries that contributed to the ongoing work of the global space science community. EMM has passed its Mission Concept Review (MCR), System Requirements Review (SRR), System Design Review (SDR), Preliminary Design Review (PDR), and Critical Design Review (CDR) phases. The mission is led by the Mohammed Bin Rashid Space Centre (MBRSC), in partnership with the University of Colorado Laboratory for Atmospheric and Space Physics (LASP), University of California Berkeley Space Sciences Laboratory (SSL), and Arizona State University (ASU) School of Earth and Space Exploration. The mission is designed to answer the following three science questions: (1) How does the Martian lower atmosphere respond globally, diurnally, and seasonally to solar forcing? (2) How do conditions throughout the Martian atmosphere affect rates of atmospheric escape? (3) How does the Martian exosphere behave temporally and spatially?. Each question is aligned with three mission objectives and four investigations that study the Martian atmospheric circulation and connections through measurements done using three instruments that image Mars in the visible, thermal infrared and ultraviolet wavelengths. Data will be collected around Mars for a period of an entire Martian year to provide scientists with valuable understanding of the changes to the Martian atmosphere today. The presentation will focus on the overviews of the mission and science objectives, instruments and spacecraft, as well as the ground and launch segments.

A Mission Concept: Re-Entry Hopper-Aero-Space-Craft System on-Mars (REARM-Mars)

NASA Technical Reports Server (NTRS)

Davoodi, Faranak

2013-01-01

Future missions to Mars that would need a sophisticated lander, hopper, or rover could benefit from the REARM Architecture. The mission concept REARM Architecture is designed to provide unprecedented capabilities for future Mars exploration missions, including human exploration and possible sample-return missions, as a reusable lander, ascend/descend vehicle, refuelable hopper, multiple-location sample-return collector, laboratory, and a cargo system for assets and humans. These could all be possible by adding just a single customized Re-Entry-Hopper-Aero-Space-Craft System, called REARM-spacecraft, and a docking station at the Martian orbit, called REARM-dock. REARM could dramatically decrease the time and the expense required to launch new exploratory missions on Mars by making them less dependent on Earth and by reusing the assets already designed, built, and sent to Mars. REARM would introduce a new class of Mars exploration missions, which could explore much larger expanses of Mars in a much faster fashion and with much more sophisticated lab instruments. The proposed REARM architecture consists of the following subsystems: REARM-dock, REARM-spacecraft, sky-crane, secure-attached-compartment, sample-return container, agile rover, scalable orbital lab, and on-the-road robotic handymen.

NASA’s MAVEN Mission Observes Ups and Downs of Water Escape from Mars

NASA Image and Video Library

2017-12-08

After investigating the upper atmosphere of the Red Planet for a full Martian year, NASA’s MAVEN mission has determined that the escaping water does not always go gently into space. Sophisticated measurements made by a suite of instruments on the Mars Atmosphere and Volatile Evolution, or MAVEN, spacecraft revealed the ups and downs of hydrogen escape – and therefore water loss. The escape rate peaked when Mars was at its closest point to the sun and dropped off when the planet was farthest from the sun. The rate of loss varied dramatically overall, with 10 times more hydrogen escaping at the maximum. “MAVEN is giving us unprecedented detail about hydrogen escape from the upper atmosphere of Mars, and this is crucial for helping us figure out the total amount of water lost over billions of years,” said Ali Rahmati, a MAVEN team member at the University of California at Berkeley who analyzed data from two of the spacecraft’s instruments. Hydrogen in Mars’ upper atmosphere comes from water vapor in the lower atmosphere. An atmospheric water molecule can be broken apart by sunlight, releasing the two hydrogen atoms from the oxygen atom that they had been bound to. Several processes at work in Mars’ upper atmosphere may then act on the hydrogen, leading to its escape. Read more: go.nasa.gov/2dAgAV4 NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Mars Polar Lander Mission Distributed Operations

NASA Technical Reports Server (NTRS)

Norris, J.; Backes, P.; Slostad, J.; Bonitz, R.; Tharp, G.; Tso, K.

2000-01-01

The Mars Polar Lander (MPL) mission is the first planetary mission to use Internet-based distributed ground operations where scientists and engineers collaborate in daily mission operations from multiple geographically distributed locations via the Internet.

A Mars 1984 mission

NASA Technical Reports Server (NTRS)

1977-01-01

Mission objectives are developed for the next logical step in the investigation of the local physical and chemical environments and the search for organic compounds on Mars. The necessity of three vehicular elements: orbiter, penetrator, and rover for in situ investigations of atmospheric-lithospheric interactions is emphasized. A summary report and committee recommendations are included with the full report of the Mars Science Working Group.

In-Space Transportation for NASA's Evolvable Mars Campaign

NASA Technical Reports Server (NTRS)

Percy, Thomas K.; McGuire, Melissa; Polsgrove, Tara

2015-01-01

As the nation embarks on a new and bold journey to Mars, significant work is being done to determine what that mission and those architectural elements will look like. The Evolvable Mars Campaign, or EMC, is being evaluated as a potential approach to getting humans to Mars. Built on the premise of leveraging current technology investments and maximizing element commonality to reduce cost and development schedule, the EMC transportation architecture is focused on developing the elements required to move crew and equipment to Mars as efficiently and effectively as possible both from a performance and a programmatic standpoint. Over the last 18 months the team has been evaluating potential options for those transportation elements. One of the key aspects of the EMC is leveraging investments being made today in missions like the Asteroid Redirect Mission (ARM) mission using derived versions of the Solar Electric Propulsion (SEP) propulsion systems and coupling them with other chemical propulsion elements that maximize commonality across the architecture between both transportation and Mars operations elements. This paper outlines the broad trade space being evaluated including the different technologies being assessed for transportation elements and how those elements are assembled into an architecture. Impacts to potential operational scenarios at Mars are also investigated. Trades are being made on the size and power level of the SEP vehicle for delivering cargo as well as the size of the chemical propulsion systems and various mission aspects including Inspace assembly and sequencing. Maximizing payload delivery to Mars with the SEP vehicle will better support the operational scenarios at Mars by enabling the delivery of landers and habitation elements that are appropriately sized for the mission. The purpose of this investigation is not to find the solution but rather a suite of solutions with potential application to the challenge of sending cargo and crew to Mars

Thermal Protection Materials Technology for NASA's Exploration Systems Mission Directorate

NASA Technical Reports Server (NTRS)

Valentine, Peter G.; Lawerence, Timtohy W.; Gubert, Michael K.; Flynn, Kevin C.; Milos, Frank S.; Kiser, James D.; Ohlhorst, Craig W.; Koenig, John R.

2005-01-01

To fulfill the President s Vision for Space Exploration - successful human and robotic missions between the Earth and other solar system bodies in order to explore their atmospheres and surfaces - NASA must reduce trip time, cost, and vehicle weight so that payload and scientific experiment capabilities are maximized. As a collaboration among NASA Centers, this project will generate products that will enable greater fidelity in mission/vehicle design trade studies, support risk reduction for material selections, assist in optimization of vehicle weights, and provide the material and process templates for development of human-rated qualification and certification Thermal Protection System (TPS) plans. Missions performing aerocapture, aerobraking, or direct aeroentry rely on technologies that reduce vehicle weight by minimizing the need for propellant. These missions use the destination planet s atmosphere to slow the spacecraft. Such mission profiles induce heating environments on the spacecraft that demand thermal protection heatshields. This program offers NASA essential advanced thermal management technologies needed to develop new lightweight nonmetallic TPS materials for critical thermal protection heatshields for future spacecraft. Discussion of this new program (a December 2004 new start) will include both initial progress made and a presentation of the work to be preformed over the four-year life of the program. Additionally, the relevant missions and environments expected for Exploration Systems vehicles will be presented, along with discussion of the candidate materials to be considered and of the types of testing to be performed (material property tests, space environmental effects tests, and Earth and Mars gases arc jet tests).

Mars mission science operations facilities design

NASA Technical Reports Server (NTRS)

Norris, Jeffrey S.; Wales, Roxana; Powell, Mark W.; Backes, Paul G.; Steinke, Robert C.

2002-01-01

A variety of designs for Mars rover and lander science operations centers are discussed in this paper, beginning with a brief description of the Pathfinder science operations facility and its strengths and limitations. Particular attention is then paid to lessons learned in the design and use of operations facilities for a series of mission-like field tests of the FIDO prototype Mars rover. These lessons are then applied to a proposed science operations facilities design for the 2003 Mars Exploration Rover (MER) mission. Issues discussed include equipment selection, facilities layout, collaborative interfaces, scalability, and dual-purpose environments. The paper concludes with a discussion of advanced concepts for future mission operations centers, including collaborative immersive interfaces and distributed operations. This paper's intended audience includes operations facility and situation room designers and the users of these environments.

The Mars Pathfinder Mission

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.

Trade Study of Five In-Situ Propellant Production Systems for a Mars Sample Return Mission

NASA Technical Reports Server (NTRS)

Green, S. T.; Deffenbaugh, D. M.; Miller, M. A.

1999-01-01

One of the goals of NASA's HEDS enterprise is to establish a long-term human presence on Mars at a fraction of the cost of employing today's technology. The most direct method of reducing mission cost is to reduce the launch mass of the spacecraft. If the propellants for the return phase of the mission are produced on Mars, the total spacecraft mass could be reduced significantly. An interim goal is a Mars Sample Return (MSR) mission, which is proposed to demonstrate the feasibility of in-situ propellant production (ISPP). Five candidate ISPP systems for producing two fuels and oxygen from the Martian atmosphere are considered in this design trade-off study: 1) Zirconia cell with methanol synthesis, 2) Reverse water gas shift with water electrolysis and methanol synthesis, 3) Sabatier process for methane product ion with water electrolysis, 4) Sabatier process with water electrolysis and partial methane pyrolysis, and 5) Sabatier/RWGS combination with water electrolysis.

Development of Charge to Mass Ratio Microdetector for Future Mars Mission

NASA Technical Reports Server (NTRS)

Chen, Yuan-Lian Albert

2003-01-01

The Mars environment comprises a dry, cold and low air pressure atmosphere with low gravity (0.38g) and high resistivity soil. The global dust storms that cover a large portion of Mars are observed often from Earth. This environment provides an ideal condition for turboelectric charging. The extremely dry conditions on the Martian surface have raised concerns that electrostatic charge buildup will not be dissipated easily. If turboelectrically generated charge cannot be dissipated or avoided, then dust will accumulate on charged surfaces and electrostatic discharge may cause hazards for future exploration missions. The low surface on Mars helps to prolong the charge decay on the dust particles and soil. To better understanding the physics of Martian charged dust particles is essential to future Mars missions. We research and design two sensors, velocity/charge sensor and PZT momentum sensors, to measure the velocity distribution, charge distribution and mass distribution of Martian wed dust particles. These sensors are fabricated at NASA Kenney Space Center, Electrostatic and Surface Physics Laboratory. The sensors are calibrated. The momentum sensor is capable to measure 45 pan size particles. The designed detector is very simple, robust, without moving parts, and does not require a high voltage power supply. Two sensors are combined to form the Dust Microdetector - CHAL.

Mars Mission Concepts: SAR and Solar Electric Propulsion

NASA Astrophysics Data System (ADS)

Elsperman, M.; Klaus, K.; Smith, D. B.; Clifford, S. M.; Lawrence, S. J.

2012-12-01

Introduction: The time has come to leverage technology advances (including advances in autonomous operation and propulsion technology) to reduce the cost and increase the flight rate of planetary missions, while actively developing a scientific and engineering workforce to achieve national space objectives. Mission Science at Mars: A SAR imaging radar offers an ability to conduct high resolution investigations of the shallow (<10 m depth) subsurface of Mars, enabling identification of fine-scale layering within the Martian polar layered deposits (PLD), as well as the identification of pingos, investigations of polygonal terrain, and measurements of the thickness of mantling layers at non-polar latitudes. It would allow systematic near-surface prospecting, which is tremendously useful for human exploration purposes (in particular, the identification of accessible ice deposits and quantification of Martian regolith properties). Limited color capabilities in a notional high-resolution stereo imaging system would enable the generation of false color images, resulting in useful science results, and the stereo data could be reduced into high-resolution Digital Elevation Models uniquely useful for exploration planning and science purposes. Since the SAR and the notional high-resolution stereo imaging system would be huge data volume producers - to maximize the science return we are currently considering the usage of laser communications systems; this notional spacecraft represents one pathway to evaluate the utility of laser communications in planetary exploration while providing useful science return.. Mission Concept: Using a common space craft for multiple missions reduces costs. Solar electric propulsion (SEP) provides the flexibility required for multiple mission objectives. SEP provides the greatest payload advantage albeit at the sacrifice of mission time. Our concept involves using a SEP enabled space craft (Boeing 702SP) with a highly capable SAR imager that also

Research Needs in Electrostatics for Lunar and Mars Space Missions

NASA Technical Reports Server (NTRS)

Calle, Carlos I.

2005-01-01

The new space exploratory vision announced by President Bush on January 14, 2004, initiated new activities at the National Science and Space Administration (NASA) for human space missions to further explore our solar system. NASA is undertaking Lunar exploration to support sustained human and robotic exploration of Mars and beyond. A series of robotic missions to the Moon by 2008 to prepare for human exploration as early as 2015 but no later than 2020 are anticipated. In a similar way, missions to the Moon and Mars are being planned in Europe, Japan and Russia. These space missions will require international participation to solve problems in a number of important technological areas where research is needed, including biomedical risk mitigation as well as life support and habitability on the surface of Mars. Mitigation of dust hazards is one of the most important problems to be resolved for both Lunar and Mars missions. Both Lunar and Martian regolith are unique materials and completely different from the terrestrial soils that we are exposed to on earth. The total absence of water and an atmosphere on the moon and the formation of soil and fine dust by micrometeorite impacts over billions of years resulted in a layer of soil with unique properties. The soil is primarily basaltic in composition with a high glass concentration. The depth of the soil layer varies from a few meters in the mare areas (dark areas on the Lunar near side) to tens of meters in the highland areas (the lighter mountainous areas) and the particle size distribution of this dust layer varies widely with a major mass fraction less than 10 micrometer in diameter. The hard soil from the moon which has been extensively studied by several researchers showed clearly unique properties of Lunar soil. Apollo astronauts became aware of the potentially serious threat to crew health and mission hardware that can be caused by the lunar dust. As reported by McKay and Carrier the mass fraction of the lunar

JPL Tech Works Mars 2020 Descent Stage

NASA Image and Video Library

2018-03-13

A technician works on the descent stage for NASA's Mars 2020 mission inside JPL's Spacecraft Assembly Facility. Mars 2020 is slated to carry NASA's next Mars rover to the Red Planet in July of 2020. https://photojournal.jpl.nasa.gov/catalog/PIA22342

Training Space Surgeons for Missions to the Moon and Mars

NASA Technical Reports Server (NTRS)

Pool, S. L.; McSwain, N.

2004-01-01

Over a period of 4 years, several working groups reviewed the provisions for medical care in low earth orbit and for future flights such as to the Moon and Mars. More than 60 medical experts representing a wide variety of clinical backgrounds participated in the working groups. They concluded that NASA medical training for long-duration missions, while critical to success, is currently aimed at short-term skill retention. They noted that several studies have shown that skills and knowledge deteriorate rapidly in the absence of adequate sustainment training. American Heart Association studies have shown that typically less than twenty-five percent of learned skills remain after 6 to 8 months. In addition to identifying the current training deficiencies, the working groups identified additional skill and knowledge sets required for missions to the Moon and Mars and curricula were developed to address inadequacies. Space medicine care providers may be categorized into 4 types based on health care responsibilities and level of education required. The first 2 types are currently recognized positions within the flight crew: crew medical officers and astronaut-physician. The crew medical officer (CMO), a non-medically trained astronaut crewmember, is given limited emergency medical technician-like training to provide medical care on orbit. Many of hidher duties are carried out under the direction of a ground-based flight surgeon in mission control. Second is the astronaut- physician whose primary focus is on mission specialist duties and training, and who has very limited ability to maintain medical proficiency. Two new categories are recommended to complete the 4 types of care providers primarily to address the needs of those who will travel to the Moon and Mars. Physician astronaut - a physician, who in addition to being a mission specialist, will be required to maintain and enhance hidher medical proficiency while serving as an astronaut. Space surgeon - a physician

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

NASA Administrator Charles Bolden speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Mars Science Laboratory's Descent Stage

NASA Technical Reports Server (NTRS)

2008-01-01

This portion of NASA's Mars Science Laboratory, called the descent stage, does its main work during the final few minutes before touchdown on Mars.

The descent stage will provide rocket-powered deceleration for a phase of the arrival at Mars after the phases using the heat shield and parachute. When it nears the surface, the descent stage will lower the rover on a bridle the rest of the way to the ground.

The Mars Science Laboratory spacecraft is being assembled and tested for launch in 2011.

This image was taken at NASA's Jet Propulsion Laboratory, Pasadena, Calif., which manages the Mars Science Laboratory Mission for NASA's Science Mission Directorate, Washington. JPL is a division of the California Institute of Technology.

Halfway point of the one year mission on This Week @NASA – September 18, 2015

NASA Image and Video Library

2015-09-18

Sept. 15 marked the halfway point in the yearlong mission on the International Space Station with NASA astronaut Scott Kelly and Russian cosmonaut Mikhail Kornienko. An event the day before at the National Press Club in Washington included a discussion about the biomedical research conducted on the station, to help formulate future human missions to Mars. Kelly participated from the space station. His identical twin, retired NASA astronaut Mark Kelly, and NASA astronaut Terry Virts, who served as commander of Expedition 43, participated from the press club. Also, I spy the space station: Live!, Expedition 43 post-flight visit, Key milestone for Orion spacecraft, Global ocean on Enceladus, Connecting space to village and more!

EDL Pathfinder Missions

NASA Technical Reports Server (NTRS)

Drake, Bret G.

2016-01-01

NASA is developing a long-term strategy for achieving extended human missions to Mars in support of the policies outlined in the 2010 NASA Authorization Act and National Space Policy. The Authorization Act states that "A long term objective for human exploration of space should be the eventual international exploration of Mars." Echoing this is the National Space Policy, which directs that NASA should, "By 2025, begin crewed missions beyond the moon, including sending humans to an asteroid. By the mid-2030s, send humans to orbit Mars and return them safely to Earth." Further defining this goal, NASA's 2014 Strategic Plan identifies that "Our long-term goal is to send humans to Mars. Over the next two decades, we will develop and demonstrate the technologies and capabilities needed to send humans to explore the red planet and safely return them to Earth." Over the past several decades numerous assessments regarding human exploration of Mars have indicated that landing humans on the surface of Mars remains one of the key critical challenges. In 2015 NASA initiated an Agency-wide assessment of the challenges associated with Entry, Descent, and Landing (EDL) of large payloads necessary for supporting human exploration of Mars. Due to the criticality and long-lead nature of advancing EDL techniques, it is necessary to determine an appropriate strategy to improve the capability to land large payloads. This paper provides an overview of NASA's 2015 EDL assessment on understanding the key EDL risks with a focus on determining what "must" be tested at Mars. This process identified the various risks and potential risk mitigation strategies, that is, benefits of flight demonstration at Mars relative to terrestrial test, modeling, and analysis. The goal of the activity was to determine if a subscale demonstrator is necessary, or if NASA should take a direct path to a human-scale lander. This assessment also provided insight into how EDL advancements align with other Agency

Integrated Network Architecture for NASA's Orion Missions

NASA Technical Reports Server (NTRS)

Bhasin, Kul B.; Hayden, Jeffrey L.; Sartwell, Thomas; Miller, Ronald A.; Hudiburg, John J.

2008-01-01

NASA is planning a series of short and long duration human and robotic missions to explore the Moon and then Mars. The series of missions will begin with a new crew exploration vehicle (called Orion) that will initially provide crew exchange and cargo supply support to the International Space Station (ISS) and then become a human conveyance for travel to the Moon. The Orion vehicle will be mounted atop the Ares I launch vehicle for a series of pre-launch tests and then launched and inserted into low Earth orbit (LEO) for crew exchange missions to the ISS. The Orion and Ares I comprise the initial vehicles in the Constellation system of systems that later includes Ares V, Earth departure stage, lunar lander, and other lunar surface systems for the lunar exploration missions. These key systems will enable the lunar surface exploration missions to be initiated in 2018. The complexity of the Constellation system of systems and missions will require a communication and navigation infrastructure to provide low and high rate forward and return communication services, tracking services, and ground network services. The infrastructure must provide robust, reliable, safe, sustainable, and autonomous operations at minimum cost while maximizing the exploration capabilities and science return. The infrastructure will be based on a network of networks architecture that will integrate NASA legacy communication, modified elements, and navigation systems. New networks will be added to extend communication, navigation, and timing services for the Moon missions. Internet protocol (IP) and network management systems within the networks will enable interoperability throughout the Constellation system of systems. An integrated network architecture has developed based on the emerging Constellation requirements for Orion missions. The architecture, as presented in this paper, addresses the early Orion missions to the ISS with communication, navigation, and network services over five

Exploring Mars

NASA Astrophysics Data System (ADS)

Breuil, Stéphanie

2016-04-01

Mars is our neighbour planet and has always fascinated humans as it has been seen as a potential abode for life. Knowledge about Mars is huge and was constructed step by step through numerous missions. It could be difficult to describe these missions, the associated technology, the results, the questions they raise, that's why an activity is proposed, that directly interests students. Their production is presented in the poster. Step 1: The main Mars feature and the first Mars explorations using telescope are presented to students. It should be really interesting to present "Mars Canals" from Percival Lowell as it should also warn students against flawed interpretation. Moreover, this study has raised the big question about extra-terrestrial life on Mars for the first time. Using Google Mars is then a good way to show the huge knowledge we have on the planet and to introduce modern missions. Step 2: Students have to choose and describe one of the Mars mission from ESA and NASA. They should work in pairs. Web sites from ESA and NASA are available and the teacher makes sure the main missions will be studied. Step 3: Students have to collect different pieces of information about the mission - When? Which technology? What were the main results? What type of questions does it raise? They prepare an oral presentation in the form they want (role play, academic presentation, using a poster, PowerPoint). They also have to produce playing cards about the mission that could be put on a timeline. Step 4: As a conclusion, the different cards concerning different missions are mixed. Groups of students receive cards and they have to put them on a timeline as fast as possible. It is also possible to play the game "timeline".

Exobiology on Mars

NASA Technical Reports Server (NTRS)

Devincenzi, D. L. (Editor); Marshall, J. R. (Editor); Andersen, D. (Editor)

1990-01-01

Descriptions of several instrument concepts that were generated during a workshop entitled, Exobiology Instrument Concepts for a Soviet Mars 94/94 Mission, held at NASA Ames Research Center in 1989 are presented. The objective was to define and describe instrument concepts for exobiology and related science that would be compatible with the mission types under discussion for the 1994 and 1996 Soviet Mars missions. Experiments that use existing technology were emphasized. The concepts discussed could also be used on U.S. missions that follow Mars Observer.

Radiation health for a Mars mission

NASA Technical Reports Server (NTRS)

Robbins, Donald E.

1992-01-01

Uncertainties in risk assessments for exposure of a Mars mission crew to space radiation place limitations on mission design and operation. Large shielding penalties are imposed in order to obtain acceptable safety margins. Galactic cosmic rays (GCR) and solar particle events (SPE) are the major concern. A warning system and 'safe-haven' are needed to protect the crew from large SPE which produce lethal doses. A model developed at NASA Johnson Space Center (JSC) to describe solar modulation of GCR intensities reduces that uncertainty to less than 10 percent. Radiation transport models used to design spacecraft shielding have large uncertainties in nuclear fragmentation cross sections for GCR which interact with spacecraft materials. Planned space measurements of linear energy transfer (LET) spectra behind various shielding thicknesses will reduce uncertainties in dose-versus-shielding thickness relationships to 5-10 percent. The largest remaining uncertainty is in biological effects of space radiation. Data on effects of energetic ions in human are nonexistent. Experimental research on effects in animals and cell is needed to allow extrapolation to the risk of carcinogenesis in humans.

Mars Pathfinder and Mars Global Surveyor Outreach Compilation

NASA Astrophysics Data System (ADS)

1999-09-01

This videotape is a compilation of the best NASA JPL (Jet Propulsion Laboratory) videos of the Mars Pathfinder and Mars Global Surveyor missions. The mission is described using animation and narration as well as some actual footage of the entire sequence of mission events. Included within these animations are the spacecraft orbit insertion; descent to the Mars surface; deployment of the airbags and instruments; and exploration by Sojourner, the Mars rover. JPL activities at spacecraft control during significant mission events are also included at the end. The spacecraft cameras pan the surrounding Mars terrain and film Sojourner traversing the surface and inspecting rocks. A single, brief, processed image of the Cydonia region (Mars face) at an oblique angle from the Mars Global Surveyor is presented. A description of the Mars Pathfinder mission, instruments, landing and deployment process, Mars approach, spacecraft orbit insertion, rover operation are all described using computer animation. Actual color footage of Sojourner as well as a 360 deg pan of the Mars terrain surrounding the spacecraft is provided. Lower quality black and white photography depicting Sojourner traversing the Mars surface and inspecting Martian rocks also is included.

Mars Pathfinder and Mars Global Surveyor Outreach Compilation

NASA Technical Reports Server (NTRS)

1999-01-01

This videotape is a compilation of the best NASA JPL (Jet Propulsion Laboratory) videos of the Mars Pathfinder and Mars Global Surveyor missions. The mission is described using animation and narration as well as some actual footage of the entire sequence of mission events. Included within these animations are the spacecraft orbit insertion; descent to the Mars surface; deployment of the airbags and instruments; and exploration by Sojourner, the Mars rover. JPL activities at spacecraft control during significant mission events are also included at the end. The spacecraft cameras pan the surrounding Mars terrain and film Sojourner traversing the surface and inspecting rocks. A single, brief, processed image of the Cydonia region (Mars face) at an oblique angle from the Mars Global Surveyor is presented. A description of the Mars Pathfinder mission, instruments, landing and deployment process, Mars approach, spacecraft orbit insertion, rover operation are all described using computer animation. Actual color footage of Sojourner as well as a 360 deg pan of the Mars terrain surrounding the spacecraft is provided. Lower quality black and white photography depicting Sojourner traversing the Mars surface and inspecting Martian rocks also is included.

Computer Interactives for the Mars Atmospheric and Volatile Evolution (MAVEN) Mission through NASA's "Project Spectra!"

NASA Astrophysics Data System (ADS)

Wood, E. L.

2014-12-01

"Project Spectra!" is a standards-based E-M spectrum and engineering program that includes paper and pencil activities as well as Flash-based computer games that help students solidify understanding of high-level planetary and solar physics. Using computer interactive games, students experience and manipulate information making abstract concepts accessible, solidifying understanding and enhancing retention of knowledge. Since students can choose what to watch and explore, the interactives accommodate a broad range of learning styles. Students can go back and forth through the interactives if they've missed a concept or wish to view something again. In the end, students are asked critical thinking questions and conduct web-based research. As part of the Mars Atmospheric and Volatile EvolutioN (MAVEN) mission education programming, we've developed two new interactives. The MAVEN mission will study volatiles in the upper atmosphere to help piece together Mars' climate history. In the first interactive, students explore black body radiation, albedo, and a simplified greenhouse effect to establish what factors contribute to overall planetary temperature. Students design a planet that is able to maintain liquid water on the surface. In the second interactive, students are asked to consider conditions needed for Mars to support water on the surface, keeping some variables fixed. Ideally, students will walk away with the very basic and critical elements required for climate studies, which has far-reaching implications beyond the study of Mars. These interactives were pilot tested at Arvada High School in Colorado.

NASA's In-Space Propulsion Technology Project Overview, Near-term Products and Mission Applicability

NASA Technical Reports Server (NTRS)

Dankanich, John; Anderson, David J.

2008-01-01

The In-Space Propulsion Technology (ISPT) Project, funded by NASA's Science Mission Directorate (SMD), is continuing to invest in propulsion technologies that will enable or enhance NASA robotic science missions. This overview provides development status, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of aerocapture, electric propulsion, advanced chemical thrusters, and systems analysis tools. Aerocapture investments improved (1) guidance, navigation, and control models of blunt-body rigid aeroshells, 2) atmospheric models for Earth, Titan, Mars and Venus, and 3) models for aerothermal effects. Investments in electric propulsion technologies focused on completing NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system. The project is also concluding its High Voltage Hall Accelerator (HiVHAC) mid-term product specifically designed for a low-cost electric propulsion option. The primary chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. The project is also delivering products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. In-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations.

21st century early mission concepts for Mars delivery and earth return

NASA Technical Reports Server (NTRS)

Cruz, Manuel I.; Ilgen, Marc R.

1990-01-01

In the 21st century, the early missions to Mars will entail unmanned Rover and Sample Return reconnaissance missions to be followed by manned exploration missions. High performance leverage technologies will be required to reach Mars and return to earth. This paper describes the mission concepts currently identified for these early Mars missions. These concepts include requirements and capabilities for Mars and earth aerocapture, Mars surface operations and ascent, and Mars and earth rendezvous. Although the focus is on the unmanned missions, synergism with the manned missions is also discussed.

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Robert Lightfoot, NASA Associate Adminstrator, delivers closing remarks at an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Optimization of vehicle weight for Mars excursion missions

NASA Technical Reports Server (NTRS)

Ferebee, Melvin J., Jr.

1991-01-01

The excursion class mission to Mars is defined as a mission with one year durations coupled with a stay time of up to 30 days. The fuel budget for such a mission is investigated. The overall figure of merit in such an assessment is the vehicle weight ratio, the ratio between the wet vehicle weight to the dry vehicle weight. It is necessary to minimize the overall fuel budget for the mission in order to maximize the benefits that could be obtained by sending humans to Mars. Assumptions used in the analysis are: each mission will depart and terminate in low-earth-orbit (LEO) (500 km circular) and the maximum stay time at Mars is 30 days. The maximum mission duration is one year (355-375 days). The mass returned to LEO is 135,000 kg, the dropoff mass left at Mars is 168,000 kg. Three propulsive techniques for atmospheric interface are investigated: aerobraking, all-chemical propulsion, and nuclear thermal propulsion. By defining the fuel requirements, the space transfer vehicle's configuration is defined.

Developing the NASA food system for long-duration missions.

PubMed

Cooper, Maya; Douglas, Grace; Perchonok, Michele

2011-03-01

Even though significant development has transformed the space food system over the last 5 decades to attain more appealing dietary fare for low-orbit space crews, the advances do not meet the need for crews that might travel to Mars and beyond. It is estimated that a food system for a long-duration mission must maintain organoleptic acceptability, nutritional efficacy, and safety for a 3- to 5-y period to be viable. In addition, the current mass and subsequent waste of the food system must decrease significantly to accord with the allowable volume and payload limits of the proposed future space vehicles. Failure to provide the appropriate food or to optimize resource utilization introduces the risk that an inadequate food system will hamper mission success and/or threaten crew performance. Investigators for the National Aeronautics and Space Administration (NASA) Advanced Food Technology (AFT) consider identified concerns and work to mitigate the risks to ensure that any new food system is adequate for the mission. Yet, even with carefully planned research, some technological gaps remain. NASA needs research advances to develop food that is nutrient-dense and long-lasting at ambient conditions, partial gravity cooking processes, methods to deliver prescribed nutrients over time, and food packaging that meets the mass, barrier, and processing requirements of NASA. This article provides a brief review of research in each area, details the past AFT research efforts, and describes the remaining gaps that present barriers to achieving a food system for long exploration missions.

An Overview of Space Power Systems for NASA Missions

NASA Technical Reports Server (NTRS)

Lyons, Valerie J.; Scott, John H.

2007-01-01

Power is a critical commodity for all engineering efforts and is especially challenging in the aerospace field. This paper will provide a broad brush overview of some of the immediate and important challenges to NASA missions in the field of aerospace power, for generation, energy conversion, distribution, and storage. NASA s newest vehicles which are currently in the design phase will have power systems that will be developed from current technology, but will have the challenges of being light-weight, energy-efficient, and space-qualified. Future lunar and Mars "outposts" will need high power generation units for life support and energy-intensive exploration efforts. An overview of the progress in concepts for power systems and the status of the required technologies are discussed.

Electromechanical Power for NASA Missions

NASA Technical Reports Server (NTRS)

Manzo, Michelle A.

2005-01-01

NASA has a wide range of missions that require electrochemical power sources. These needs are met with a variety of options that include primary and secondary cells and batteries, fuel cells, and regenerative fuel cells. This presentation wil cover an overview of NASA missions and requirements for electrochemical power sources and investigate the synergy and diversity that exist between NASA's requirements and those for military tactical power sources. Current development programs at GRC and other NASA centers, aimed at meeting NASA's future requirements will also be discussed.

Small Habitat Commonality Reduces Cost for Human Mars Missions

NASA Technical Reports Server (NTRS)

Griffin, Brand N.; Lepsch, Roger; Martin, John; Howard, Robert; Rucker, Michelle; Zapata, Edgar; McCleskey, Carey; Howe, Scott; Mary, Natalie; Nerren, Philip (Inventor)

2015-01-01

Most view the Apollo Program as expensive. It was. But, a human mission to Mars will be orders of magnitude more difficult and costly. Recently, NASA's Evolvable Mars Campaign (EMC) mapped out a step-wise approach for exploring Mars and the Mars-moon system. It is early in the planning process but because approximately 80% of the total life cycle cost is committed during preliminary design, there is an effort to emphasize cost reduction methods up front. Amongst the options, commonality across small habitat elements shows promise for consolidating the high bow-wave costs of Design, Development, Test and Evaluation (DDT&E) while still accommodating each end-item's functionality. In addition to DDT&E, there are other cost and operations benefits to commonality such as reduced logistics, simplified infrastructure integration and with inter-operability, improved safety and simplified training. These benefits are not without a cost. Some habitats are sub-optimized giving up unique attributes for the benefit of the overall architecture and because the first item sets the course for those to follow, rapidly developing technology may be excluded. The small habitats within the EMC include the pressurized crew cabins for the ascent vehicle,

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Sam Scimemi, Director of NASA's International Space Station Division, speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

David Miller, NASA Chief Technologist, participate in a panel discussion during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

Jason Crusan, Director of NASA's Advanced Exploration Systems Division, speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

NASA Exploration Forum: Human Path to Mars

NASA Image and Video Library

2014-04-29

William Gerstenmaier, NASA Associate Administrator for Human Exploration and Operations, speaks during an Exploration Forum showcasing NASA's human exploration path to Mars in the James E. Webb Auditorium at NASA Headquarters on Tuesday, April 29, 2014. Photo Credit: (NASA/Joel Kowsky)

Review of NASA approach to space radiation risk assessments for Mars exploration.

PubMed

Cucinotta, Francis A

2015-02-01

Long duration space missions present unique radiation protection challenges due to the complexity of the space radiation environment, which includes high charge and energy particles and other highly ionizing radiation such as neutrons. Based on a recommendation by the National Council on Radiation Protection and Measurements, a 3% lifetime risk of exposure-induced death for cancer has been used as a basis for risk limitation by the National Aeronautics and Space Administration (NASA) for low-Earth orbit missions. NASA has developed a risk-based approach to radiation exposure limits that accounts for individual factors (age, gender, and smoking history) and assesses the uncertainties in risk estimates. New radiation quality factors with associated probability distribution functions to represent the quality factor's uncertainty have been developed based on track structure models and recent radiobiology data for high charge and energy particles. The current radiation dose limits are reviewed for spaceflight and the various qualitative and quantitative uncertainties that impact the risk of exposure-induced death estimates using the NASA Space Cancer Risk (NSCR) model. NSCR estimates of the number of "safe days" in deep space to be within exposure limits and risk estimates for a Mars exploration mission are described.