Science.gov

Sample records for lander mission measurement

  1. Mars 2001 Lander Mission: Measurement Synergy Through Coordinated Operations Planning And Implementation

    NASA Technical Reports Server (NTRS)

    Arvidson, R.; Bell, J. F., III; Kaplan, D.; Marshall, J.; Mishkin, A.; Saunders, S.; Smith, P.; Squyres, S.

    1999-01-01

    , together with quantitative information on material mineralogy, chemistry, and physical properties (rock textures; soil grain size and shape distributions; degree and nature of soil induration; soil magnetic properties). The calibration targets provide radiometric and mineralogical control surfaces. The magnets allow observations of magnetic phases. Patch plates are imaged to determine adhesive and abrasive properties of soils. Coordinated mission planning is crucial for optimizing the measurement synergy among the packages included on the lander. This planning has already begun through generation of multi-sol detailed operations activities. One focus has been to develop a scenario to use the arm to dig a soil trench to a depth of tens of centimeters. The activity will be monitored through use of Pancam and RAC to ensure nominal operations and to acquire data to determine subsurface physical properties (e.g., angle of repose of trench walls). Pancam and Mini-TES observations would also provide constraints on mineralogy and texture for the walls and bottom of the trench during excavation. If desired, soils excavated at depth could be deposited on the surface and Mossbauer and APXS measurements could be acquired for these materials. Soil samples from various depths would be delivered to MECA for characterization of aqueous geochemistry and physical properties of soil grains, particularly size, shape, and hardness. These physical properties would be determined by optical and atomic force microscopy. When completed, detailed information of soil properties as a function of depth would be obtained. These various data sets would constrain our understanding of whether or not there are systematic variations in soil characteristics as a function of depth. These variations might be related, for example, to evaporative moisture losses and formation of salt deposits, thereby indicating water transport processes occurred fairly recently. Many other value-added measurement scenarios are

  2. Small Body Landers for Near Earth Object Missions

    NASA Astrophysics Data System (ADS)

    Klaus, K.; Cook, T. S.; Kaplan, M.

    2009-12-01

    Our studies have concluded that PI-class science small body missions are possible with telecommunications infrastructure solar powered spacecraft. These spacecraft are flight proven with more than 60 yrs of cumulative in-space operation and are equipped with highly efficient solar arrays capable of accessing a wide variety of small bodies. Coupled with this capability, we are developing a “small body lander product line that leverages the significant investments that have been made in the highly successful DARPA Orbital Express program. Orbital Express demonstrated autonomous rendezvous, close proximity and capture with a passive space object, both capabilities that can also support autonomous precision “landings” on small bodies. An OE based NEO exploration lander can provide up to 100kg of science payload and 200 W of power available to the science payload. Our studies indicate that some of these missions can be accomplished within Discovery class budget, and most within a New Frontiers-class budget. OE autonomous robotic technology enables equipment relocation, surface sampling, sample retrieval and stowage, spacecraft and/or science instrument reconfiguration and alternate means of lander recovery. OE’s capture system technology enables repeatable lander and probe deployment and capture including lander refueling, setting in motion the design of missions to multiple small bodies and multiple sites on target bodies. Enhancements have been made to the navigation algorithms to enable precision natural body navigation. For science measurements that only require very small mass and power, we are developing nanosats that offer “full spacecraft-like” capabilities, e.g., 3 axis stability and control and on-board propulsion.

  3. Cooperative Lander-Surface/Aerial Microflyer Missions for Mars Exploration

    NASA Technical Reports Server (NTRS)

    Thakoor, Sarita; Lay, Norman; Hine, Butler; Zornetzer, Steven

    2004-01-01

    Concepts are being investigated for exploratory missions to Mars based on Bioinspired Engineering of Exploration Systems (BEES), which is a guiding principle of this effort to develop biomorphic explorers. The novelty lies in the use of a robust telecom architecture for mission data return, utilizing multiple local relays (including the lander itself as a local relay and the explorers in the dual role of a local relay) to enable ranges 10 to 1,000 km and downlink of color imagery. As illustrated in Figure 1, multiple microflyers that can be both surface or aerially launched are envisioned in shepherding, metamorphic, and imaging roles. These microflyers imbibe key bio-inspired principles in their flight control, navigation, and visual search operations. Honey-bee inspired algorithms utilizing visual cues to perform autonomous navigation operations such as terrain following will be utilized. The instrument suite will consist of a panoramic imager and polarization imager specifically optimized to detect ice and water. For microflyers, particularly at small sizes, bio-inspired solutions appear to offer better alternate solutions than conventional engineered approaches. This investigation addresses a wide range of interrelated issues, including desired scientific data, sizes, rates, and communication ranges that can be accomplished in alternative mission scenarios. The mission illustrated in Figure 1 offers the most robust telecom architecture and the longest range for exploration with two landers being available as main local relays in addition to an ephemeral aerial probe local relay. The shepherding or metamorphic plane are in their dual role as local relays and image data collection/storage nodes. Appropriate placement of the landing site for the scout lander with respect to the main mission lander can allow coverage of extremely large ranges and enable exhaustive survey of the area of interest. In particular, this mission could help with the path planning and risk

  4. Conductivity and Dielectric Characteristics of Planetary Surfaces Measured with Mutual Impedance Probes: From Huygens and Rosetta Lander to Netlanders and Future Missions

    NASA Astrophysics Data System (ADS)

    Hamelin, M.; Grard, R.; Laakso, H.; Ney, R.; Schmidt, W.; Simoes, F.; Trautner, R.

    2004-04-01

    Both conductivity and dielectric constant measurements can contribute to the identification of sub-surface materials. They are of great interest in the case of water and ice possibly embedded in other materials due to the high variability with frequency of the dielectric constant of water ice, the high contrast between rocks and liquid water and also the high conductivity generally observed in wet terrains. A first instrument, Permittivity, Waves and Altimetry (PWA-HASI), on the HUYGENS probe should measure the complex permittivity of Titan after landing in January 2005. It consists of a particular mode of the Mutual Impedance (MI) probe designed mainly for atmospheric conductivity measurements. The success of the measurement depends strongly on the configuration of the probe after an uncontrolled landing and in any case the data analysis will be complex as the electrodes are very close to the probe body. A second instrument, the Permittivity Probe (PP-SESAME), on the Rosetta Lander is ready to be launched towards the GuerassimoChuryumov comet in February 2004. In this case safe landing is a major requirement of the mission. The electrode array, using the lander feet and two other hosting deployable parts, is less influenced by the lander body than in the HUYGENS case. However the perturbing influence of neighbouring sensors has to be suppressed by active methods and such a system is better but again complex. In the Netlander project to the surface of Mars, actually in pause after its phase B study, the opportunity to use long GPR electric antennas deployed on the ground as permittivity sensors has been studied and will be implemented in the design with minor modifications. Our goal is to design the future generation of permittivity probes not considered as `add on's but fully optimised for their task, making simpler the analysis and providing also the possibility to calibrate the former space pioneer instruments on selected earth targets. In addition, these future

  5. Europa Lander Mission: A Challenge to Find Traces of Alien Life

    NASA Astrophysics Data System (ADS)

    Zelenyi, Lev; Korablev, Oleg; Vorobyova, Elena; Martynov, Maxim; Akim, Efraim L.; Zakahrov, Alexander

    2010-01-01

    An international effort dedicated to science exploration of Jupiter system planned by ESA and NASA in the beginning of next decade includes in-depth science investigation of Europa. In parallel to EJSM (Europa-Jupiter System Mission) Russian Space Agency and the academy of Science plan Laplace-Europa Lander mission, which will include the small telecommunication and science orbiter and the surface element: Europa Lander. In-situ methods on the lander provide the only direct possibility to assess environmental conditions, and to perform the search for signatures of life. A critical advantage of such in situ analysis is the possibility to enhance concentration and detection limits and to provide ground truth for orbital measurements. The science mission of the lander is biological, geophysical, chemical, and environmental characterizations of the Europa surface. Remote investigations from the orbit around Europa would not be sufficient to address fully the astrobiology, geodesy, and geology goals. The science objectives of the planned mission, the synergy between the Europa Lander and EJSM mission elements, and a brief description of the Laplace-Europa Lander mission are presented.

  6. Orbiter, Flyby and Lander Mission Concepts for Investigating Europa's Habitability

    NASA Astrophysics Data System (ADS)

    Prockter, L. M.

    2012-04-01

    . Each of the three mission options would address this goal in different and complementary ways, and each has high science value of its own, independent of the others. Each mission concept traces geophysical, compositional, and/or geological investigations that are best addressed by that specific platform. Investigations best addressed through near-continuous global data sets that are obtained under relatively uniform conditions could be undertaken by the orbiter; investigations that are more focused on characterization of local regions could be accomplished by a spacecraft making multiple flybys from Jupiter orbit; and measurements that are most effective from the surface could be addressed by a lander. Although there is overlap in the science objectives of these three mission concepts, each stands alone as a viable Europa mission concept.

  7. Jovian tour design for orbiter and lander missions to Europa

    NASA Astrophysics Data System (ADS)

    Campagnola, Stefano; Buffington, Brent B.; Petropoulos, Anastassios E.

    2014-07-01

    Europa is one of the most interesting targets for solar system exploration, as its ocean of liquid water could harbor life. Following the recommendation of the Planetary Decadal Survey, NASA commissioned a study for a multiple flyby only mission, an orbiter mission, and a lander mission. This paper presents the moon tours for the lander and orbiter concepts. The total Δv and radiation dose would be reduced when compared to previous designs by exploiting multi-body dynamics and avoiding multi-revolution transfers in the Ganymede-to-Europa transfer. Tours 11-O3, 12-L1 and 12-L4 and their performances compared to other tours from previous Europa mission studies are presented in detail.

  8. Future Plans for MetNet Lander Mars Missions

    NASA Astrophysics Data System (ADS)

    Harri, A.-M.; Schmidt, W.; Guerrero, H.; Vázquez, L.

    2012-04-01

    simplifies the integration into the transfer vehicle where besides the deployment mechanism only a power cable is needed to fully charge the batteries before separation. A bi-directional data link would be of advantage allowing besides a full system checkout also the last-minute adjustments of operational parameters once the most likely landing area is defined. The initial landing sites are selected in a latitude range of +/- 30 degrees and at low altitudes, thereby allowing the use of only solar panels as energy source and avoiding the political problems of including radioactive generators into the Lander. For high-latitude missions radioactive heaters will be necessary to make the systems survive the Martian winter. The MNL will be separated from the transfer vehicle either during the Mars-approaching trajectory or from the Martian orbit. The point of separation relative to the Martian orientation and the initial deployment angle define the final landing site, which additionally is influenced by atmospheric parameters during the descent phase. The behavior of the MNL's during its flight across the different layers of the Martian atmosphere is monitored by 3-axis accelerometers and 3-axis gyroscopes. This information is transmitted to the transfer vehicle via dedicated beacon antennas already during the descent phase. For the precursor missions this results in an initial velocity of 6080 m/s, a relative entry angle of -15° and a landing velocity of about 50 m/s. Later units will go also to higher latitudes and altitudes, using optimized payloads and power systems. The core payload contains the meteorological sensors for temperature, pressure and humidity measurements, a 4-lense panoramic camera and a 3-axis accelerometer for descent control. For the precursor missions this is extended to include also a 3-axis gyroscope device. Additionally a Solar Incident Sensor with a wide range of dedicated wavelength filters, an optical dust sensor, a 3-axis magnetometer and a

  9. Future Plans for MetNet Lander Mars Missions

    NASA Astrophysics Data System (ADS)

    Harri, A.-M.; Schmidt, W.; Guerrero, H.; Vázquez, L.

    2012-04-01

    simplifies the integration into the transfer vehicle where besides the deployment mechanism only a power cable is needed to fully charge the batteries before separation. A bi-directional data link would be of advantage allowing besides a full system checkout also the last-minute adjustments of operational parameters once the most likely landing area is defined. The initial landing sites are selected in a latitude range of +/- 30 degrees and at low altitudes, thereby allowing the use of only solar panels as energy source and avoiding the political problems of including radioactive generators into the Lander. For high-latitude missions radioactive heaters will be necessary to make the systems survive the Martian winter. The MNL will be separated from the transfer vehicle either during the Mars-approaching trajectory or from the Martian orbit. The point of separation relative to the Martian orientation and the initial deployment angle define the final landing site, which additionally is influenced by atmospheric parameters during the descent phase. The behavior of the MNL's during its flight across the different layers of the Martian atmosphere is monitored by 3-axis accelerometers and 3-axis gyroscopes. This information is transmitted to the transfer vehicle via dedicated beacon antennas already during the descent phase. For the precursor missions this results in an initial velocity of 6080 m/s, a relative entry angle of -15° and a landing velocity of about 50 m/s. Later units will go also to higher latitudes and altitudes, using optimized payloads and power systems. The core payload contains the meteorological sensors for temperature, pressure and humidity measurements, a 4-lense panoramic camera and a 3-axis accelerometer for descent control. For the precursor missions this is extended to include also a 3-axis gyroscope device. Additionally a Solar Incident Sensor with a wide range of dedicated wavelength filters, an optical dust sensor, a 3-axis magnetometer and a

  10. 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

  11. 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

  12. Small Lunar Lander - A Near Term Precursor Mission

    NASA Astrophysics Data System (ADS)

    Soppa, Uwe; Kyr, Peter; Bolz, Joerg; Bischof, Bernd

    In preparation of the Ministerial Conference in November 2008, the European Space Agency is currently developing a roadmap leading to the capability to sustain long term planetary exploration missions and manned missions to Moon and Mars. Embedded in the cornerstone missions of today's European planetary exploration program, which are marked by the two robotic Exo-Mars and Mars Sample Return missions, ESA has defined a Small Lunar Landing Mission serving as a precursor mission allowing to validate key enabling technologies for planetary exploration, while providing a scientific platform to Lunar exploration at the same time. In reply for the call for missions fitting into the mission time frame ranging from 2014 through 2016, EADS Astrium has proposed a Lunar Lander which can be launched by a Soyuz Fregat, combined with a programmatic planning with the goal being ready to fly within the given time. In the meantime, a European lunar exploration program has gained momentum such that the goals of the proposed mission have been expanded towards the preparation of technologies required for the logistics of lunar exploration including transportation to the Moon and back, building and supporting large scale outposts up to permanently manned bases. These key functions are the capability of autonomous, soft and precision landing, the Rendez-Vous in lunar orbit, plus the provision of surface mobility for science and logistic operations. The paper will first present the concept of the proposed Lunar Landing mission, describe the technical design and programmatic planning, and put it into context of the Mars Sample Return mission. The spacecraft shall be launched into the GTO by a Soyuz Fregat from the Kourou Space Center, and travel to the Moon from there on direct, 5 days transfer trajectory. The spacecraft is a single stage lander with the capability to autonomously perform all operations from launcher separation down to the lunar surface. A lunar rover shall provide

  13. 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.; Thomas, Reid C.; Varghese, Phil; Signori, Gina; Schmitz, Peter

    2010-01-01

    The Phoenix Lander, first of NASA's Mars Scout missions, arrived at the Red Planet on May 25, 2008. From the moment the lander separated from its interplanetary cruise stage shortly before entry, the spacecraft could no longer communicate directly with Earth, and was instead entirely dependent on UHF relay communications via an international network of orbiting Mars spacecraft, including NASA's 2001 Mars Odyssey (ODY) and Mars Reconnaissance Orbiter (MRO) spacecraft, as well as ESA's Mars Express (MEX) spacecraft. All three orbiters captured critical event telemetry and/or tracking data during Phoenix Entry, Descent and Landing. During the Phoenix surface mission, ODY and MRO provided command and telemetry services, far surpassing the original data return requirements. The availability of MEX as a backup relay asset enhanced the robustness of the surface relay plan. In addition to telecommunications services, Doppler tracking observables acquired on the UHF link yielded an accurate position for the Phoenix landing site.

  14. Mars 101: Linking Educational Content to Mission Purpose on the Phoenix Mars Lander Mission Web Site

    NASA Astrophysics Data System (ADS)

    Schmidt, L. J.; Smith, P. H.; Lombardi, D.

    2006-12-01

    The Phoenix Mars Lander, scheduled to launch in August 2007, is the first mission in NASA's Scout Program. Phoenix has been specifically designed to measure volatiles (especially water) in the northern arctic plains of Mars, where the Mars Odyssey detected evidence of ice-rich soil near the surface. A fundamental part of the mission's goal-driven education and public outreach program is the Phoenix Mars Lander 2007 web site. Content for the site was designed not only to further the casual user's understanding of the Phoenix mission and its objectives, but also to meet the needs of the more science-attentive user who desires in-depth information. To this end, the web site's "Mars 101" module includes five distinct themes, all of which are directly connected to the mission's purpose: Mars Intro includes basic facts about Mars and how the planet differs from Earth; Polar Regions discusses the history of polar exploration on Earth and the similarities between these regions on Mars and Earth; Climate covers the effects that Earth's polar regions have on climate and how these same effects may occur on Mars; Water on Mars introduces the reader to the idea of liquid water and water ice on Mars; and Biology includes a discussion of the requirements of life and life in the universe to facilitate reader understanding of what Phoenix might find. Each of the five themes is described in simple language accompanied by relevant images and graphics, with hypertext links connecting the science-attentive user to more in-depth content. By presenting the "Mars 101" content in a manner that relates each subheading to a specific component of the mission's purpose, the Phoenix web site nurtures understanding of the mission and its relevance to NASA's Mars Exploration goals by the general lay public as well as the science-attentive user.

  15. 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.

  16. Navigation Strategy for the Mars 2001 Lander Mission

    NASA Technical Reports Server (NTRS)

    Mase, Robert A.; Spencer, David A.; Smith, John C.; Braun, Robert D.

    2000-01-01

    The Mars Surveyor Program (MSP) is an ongoing series of missions designed to robotically study, map and search for signs of life on the planet Mars. The MSP 2001 project will advance the effort by sending an orbiter, a lander and a rover to the red planet in the 2001 opportunity. Each vehicle will carry a science payload that will Investigate the Martian environment on both a global and on a local scale. Although this mission will not directly search for signs of life, or cache samples to be returned to Earth, it will demonstrate certain enabling technologies that will be utilized by the future Mars Sample Return missions. One technology that is needed for the Sample Return mission is the capability to place a vehicle on the surface within several kilometers of the targeted landing site. The MSP'01 Lander will take the first major step towards this type of precision landing at Mars. Significant reduction of the landed footprint will be achieved through two technology advances. The first, and most dramatic, is hypersonic aeromaneuvering; the second is improved approach navigation. As a result, the guided entry will produce in a footprint that is only tens of kilometers, which is an order of magnitude improvement over the Pathfinder and Mars Polar Lander ballistic entries. This reduction will significantly enhance scientific return by enabling the potential selection of otherwise unreachable landing sites with unique geologic interest and public appeal. A landed footprint reduction from hundreds to tens of kilometers is also a milestone on the path towards human exploration of Mars, where the desire is to place multiple vehicles within several hundred meters of the planned landing site. Hypersonic aeromaneuvering is an extension of the atmospheric flight goals of the previous landed missions, Pathfinder and Mars Polar Lander (MPL), that utilizes aerodynamic lift and an autonomous guidance algorithm while in the upper atmosphere. The onboard guidance algorithm will

  17. Navigation Strategy for the Mars 2001 Lander Mission

    NASA Technical Reports Server (NTRS)

    Mase, Robert A.; Spencer, David A.; Smith, John C.; Braun, Robert D.

    2000-01-01

    The Mars Surveyor Program (MSP) is an ongoing series of missions designed to robotically study, map and search for signs of life on the planet Mars. The MSP 2001 project will advance the effort by sending an orbiter, a lander and a rover to the red planet in the 2001 opportunity. Each vehicle will carry a science payload that will Investigate the Martian environment on both a global and on a local scale. Although this mission will not directly search for signs of life, or cache samples to be returned to Earth, it will demonstrate certain enabling technologies that will be utilized by the future Mars Sample Return missions. One technology that is needed for the Sample Return mission is the capability to place a vehicle on the surface within several kilometers of the targeted landing site. The MSP'01 Lander will take the first major step towards this type of precision landing at Mars. Significant reduction of the landed footprint will be achieved through two technology advances. The first, and most dramatic, is hypersonic aeromaneuvering; the second is improved approach navigation. As a result, the guided entry will produce in a footprint that is only tens of kilometers, which is an order of magnitude improvement over the Pathfinder and Mars Polar Lander ballistic entries. This reduction will significantly enhance scientific return by enabling the potential selection of otherwise unreachable landing sites with unique geologic interest and public appeal. A landed footprint reduction from hundreds to tens of kilometers is also a milestone on the path towards human exploration of Mars, where the desire is to place multiple vehicles within several hundred meters of the planned landing site. Hypersonic aeromaneuvering is an extension of the atmospheric flight goals of the previous landed missions, Pathfinder and Mars Polar Lander (MPL), that utilizes aerodynamic lift and an autonomous guidance algorithm while in the upper atmosphere. The onboard guidance algorithm will

  18. Lunette: A Dual Lander Mission to the Moon to Explore Early Planetary Differentiation

    NASA Astrophysics Data System (ADS)

    Neal, C. R.; Banerdt, B.; Jones, M.; Elliott, J.; Alkalai, L.; Turyshev, S.; Lognonné, P.; Kobayashi, N.; Grimm, R. E.; Spohn, T.; Weber, R. C.; Lunette Science; Instrument Support Team

    2010-12-01

    The Moon is critical for understanding fundamental aspects of how terrestrial planets formed and evolved. The Moon’s size means that a record of early planetary differentiation has been preserved. However, data from previous, current and planned missions are (will) not (be) of sufficient fidelity to provide definitive conclusions about its internal state, structure, and composition. Lunette rectifies this situation. Lunette is a solar-powered, 2 identical lander geophysical network mission that operates for at least 4 years on the surface of the Moon. Each Lunette lander carries an identical, powerful geophysical payload consisting of four instruments: 1) An extremely sensitive instrument combining a 3-axis triad of Short Period sensors and a 3-axis set of Long Period sensors, to be placed with its environmental shield on the surface; 2) A pair of self-penetrating “Moles,” each carrying thermal and physical sensors at least 3 m below the surface to measure the heat flow from the lunar interior; 3) Lunar Laser Ranging Retro-Reflector: A high-precision, high-performance corner cube reflector for laser ranging between the Earth and the Moon; and 4) ElectroMagnetic Sounder: A set of directional magnetometers and electrometers that together probe the electrical resistivity and thermal conductivity of the interior. The 2 landers are deployed to distinct lunar terranes: the Feldspathic Highlands Terrane (FHT) and the Procellarum KREEP Terrane (PKT) on the lunar nearside. They are launched together on a single vehicle, then separate shortly after trans-lunar injection, making their way individually to an LL2 staging point. Each lander descends to the lunar surface at the beginning of consecutive lunar days; the operations team can concentrate on completing lander checkout and instrument deployments well before lunar night descends. Lunette has one primary goal: Understand the early stages of terrestrial planet differentiation. Lunette uses Apollo knowledge of deep

  19. Viking lander imaging investigation during extended and continuation automatic missions. Volume 1: Lander 1 picture catalog of experiment data record

    NASA Technical Reports Server (NTRS)

    Jones, K. L.; Henshaw, M.; Mcmenomy, C.; Robles, A.; Scribner, P. C.; Wall, S. D.; Wilson, J. W.

    1981-01-01

    All images returned by Viking Lander 1 during the extended and continuation automatic phases of the Viking Mission are presented. Listings of supplemental information which describe the conditions under which the images were acquired are included together with skyline drawings which show where the images are positioned in the field of view of the cameras. Subsets of the images are listed in a variety of sequences to aid in locating images of interest. The format and organization of the digital magnetic tape storage of the images are described as well as the mission and the camera system.

  20. Viking lander imaging investigation during extended and continuation automatic missions. Volume 2: Lander 2 picture catalog of experiment data record

    NASA Technical Reports Server (NTRS)

    Jones, K. L.; Henshaw, M.; Mcmenomy, C.; Robles, A.; Scribner, P. C.; Wall, S. D.; Wilson, J. W.

    1981-01-01

    Images returned by the two Viking landers during the extended and continuation automatic phases of the Viking Mission are presented. Information describing the conditions under which the images were acquired is included with skyline drawings showing the images positioned in the field of view of the cameras. Subsets of the images are listed in a variety of sequences to aid in locating images of interest. The format and organization of the digital magnetic tape storage of the images are described. A brief description of the mission and the camera system is also included.

  1. UHF Relay Antenna Measurements on Phoenix Mars Lander Mockup

    NASA Technical Reports Server (NTRS)

    Ilott, Peter; Harrel, Jefferson; Arnold, Bradford; Bliznyuk, Natalia; Nielsen, Rick; Dawson, David; McGee, Jodi

    2006-01-01

    The Phoenix Lander, a NASA Discovery mission which lands on Mars in the spring of 2008, will rely entirely on UHF relay links between it and Mars orbiting assets, (Odyssey and Mars Reconnaissance Orbiter (MRO)), to communicate with the Earth. As with the Mars Exploration Rover (MER) relay system, non directional antennas will be used to provide roughly emispherical coverage of the Martian sky. Phoenix lander deck object pattern interference and obscuration are significant, and needed to be quantified to answer system level design and operations questions. This paper describes the measurement campaign carried out at the SPAWAR (Space and Naval Warfare Research) Systems Center San Diego (SSC-SD) hemispherical antenna range, using a Phoenix deck mockup and engineering model antennas. One goal of the measurements was to evaluate two analysis tools, the time domain CST, and the moment method WIPL-D software packages. These would subsequently be used to provide pattern analysis for configurations that would be difficult and expensive to model and test on Earth.

  2. The DREAMS experiment on-board the Schiaparelli lander of ExoMars mission

    NASA Astrophysics Data System (ADS)

    Esposito, F.

    2015-10-01

    The DREAMS package is a suite of sensors for the characterization of the Martian basic state meteorology and of the atmospheric electric properties at the landing site of the Entry, descent and landing Demonstration Module (EDM) of the ExoMars mission. The EDM will land on Meridiani Planum in October 2016, during the statistical dust storm season. This will allow DREAMS to investigate the status of the atmosphere of Mars during this particular season and also to understand the role of dust as a potential source of electrical phenomena on Mars. DREAMS will be the first instrument to perform a measurement of electric field on Mars. DREAMS FM has been completely developed and tested and it has been delivered to ESA for integration on the Schiaparelli lander of the ExoMars 2016 mission. Launch is foreseen for January 2016.

  3. GLXP BMT: Lunar Lander Mission Definition & Opportunistic Science during Nominal Operations

    NASA Astrophysics Data System (ADS)

    Colmenarejo, P.; Mammarella, M.; Zaballa, M.; Claramunt, X.; García, C.; Martínez, A.

    2012-09-01

    The GLXP BMT "MoonRaise" mission is the Barcelona Moon Team Lunar Lander and Lunar exploration mission within the GLXP initiative. GMV is the mission technical leader and is in charge of the primary mission analysis that will later derive into the different mission subsystems and elements requirements and specifications for design and manufacturing. The classical scientific missions pivot around the scientific requirement and most of the mission elements design have the final purpose of fulfilling with the scientific requirements. This has the advantage of producing a dedicated mission to cope with all the scientific objectives (design-toperformance). The main drawback being the usually high mission complexity and cost. The GLXP BMT "MoonRaise" mission is a low cost mission and, thus, design-to-cost approach is used instead. Even if the "MoonRaise" mission will have some dedicated scientific objectives and dedicated resources, the maximization of the scientific content of the mission is a challenge in itself, and emphasis has to be placed in the imagination and achievement of opportunistic science while in nominal (nonscientific) operational phases. This paper presents the GLXP BMT "MoonRaise" mission architecture and mission approach and will identify potential opportunistic science targets with minimum impact on the Lunar Lander module and Rover module systems and at quasi-zero cost. The first section/s will be devoted to analyse the mission aspects, while the later section/s will be devoted to identification of interesting opportunistic science.

  4. Surface Lander Missions to Mars: Support via Analysis of the NASA Ames Mars General Circulation Model

    NASA Technical Reports Server (NTRS)

    Murphy, James R.; Bridger, Alison F.C.; Haberle, Robert M.

    1997-01-01

    We have characterized the near-surface martian wind environment as calculated with a set of numerical simulations carried out with the NASA Ames Mars General Circulation Model (Mars GCM). These wind environments are intended to offer future spacecraft missions to the martian surface a data base from which to choose those locations which meet the mission's criteria for minimal near surface winds to enable a successful landing. We also became involved in the development and testing of the wind sensor which is currently onboard the Mars-bound Pathfinder lander. We began this effort with a comparison of Mars GCM produced winds with those measured by the Viking landers during their descent through the martian atmosphere and their surface wind measurements during the 3+ martian year lifetime of the mission. Unexpected technical difficulties in implementing the sophisticated Planetary Boundary Layer (PBL) scheme of Haberle et al. (1993) within the Mars GCM precluded our carrying out this investigation with the desired improvement to the model's treatment of the PBL. Thus, our results from this effort are not as conclusive as we had anticipated. As it turns out, similar difficulties have been experienced by other Mars modelling groups in attempting to implement very similar PBL routines into their GCMs (Mars General Circulation Model Intercomparison Workshop, held at Oxford University, United Kingdom, July 22-24, 1996; organized by J. Murphy, J. Hollingsworth, M. Joshi). These problems, which arise due to the nature of the time stepping in each of the models, are near to being resolved at the present. The model discussions which follow herein are based upon results using the existing, less sophisticated PBL routine. We fully anticipate implementing the tools we have developed in the present effort to investigate GCM results with the new PBL scheme implemented, and thereafter producing the technical document detailing results from the analysis tools developed during this

  5. Source and event selection for radio-planetary frame-tie measurements using the Phobos Landers

    NASA Technical Reports Server (NTRS)

    Linfield, R.; Ulvestad, J.

    1988-01-01

    The Soviet Phobos Lander mission will place two spacecraft on the Martian moon Phobos in 1989. Measurements of the range from Earth-based stations to the landers will allow an accurate determination of the ephemerides of Phobos and Mars. Delta Very Long Base Interferometry (VLBI) between the landers and compact radio sources nearby on the sky will be used to obtain precise estimates of the angular offset between the radio and planetary reference frames. The accuracy of this frame-tie estimate is expected to be in the vicinity of 10 mrad, depending on how well several error sources can be controlled (calibrated or reduced). Many candidate radio sources for VLBI measurements were identified, but additional work is necessary to select those sources which have characteristics appropriate to the present application. Strategies for performing the source selection are described.

  6. Learning to Live on a Mars Day: Fatigue Countermeasures during the Phoenix Mars Lander Mission

    PubMed Central

    Barger, Laura K.; Sullivan, Jason P.; Vincent, Andrea S.; Fiedler, Edna R.; McKenna, Laurence M.; Flynn-Evans, Erin E.; Gilliland, Kirby; Sipes, Walter E.; Smith, Peter H.; Brainard, George C.; Lockley, Steven W.

    2012-01-01

    Study Objectives: To interact with the robotic Phoenix Mars Lander (PML) spacecraft, mission personnel were required to work on a Mars day (24.65 h) for 78 days. This alien schedule presents a challenge to Earth-bound circadian physiology and a potential risk to workplace performance and safety. We evaluated the acceptability, feasibility, and effectiveness of a fatigue management program to facilitate synchronization with the Mars day and alleviate circadian misalignment, sleep loss, and fatigue. Design: Operational field study. Setting: PML Science Operations Center. Participants: Scientific and technical personnel supporting PML mission. Interventions: Sleep and fatigue education was offered to all support personnel. A subset (n = 19) were offered a short-wavelength (blue) light panel to aid alertness and mitigate/reduce circadian desynchrony. They were assessed using a daily sleep/work diary, continuous wrist actigraphy, and regular performance tests. Subjects also completed 48-h urine collections biweekly for assessment of the circadian 6-sulphatoxymelatonin rhythm. Measurements and Results: Most participants (87%) exhibited a circadian period consistent with adaptation to a Mars day. When synchronized, main sleep duration was 5.98 ± 0.94 h, but fell to 4.91 ± 1.22 h when misaligned (P < 0.001). Self-reported levels of fatigue and sleepiness also significantly increased when work was scheduled at an inappropriate circadian phase (P < 0.001). Prolonged wakefulness (≥ 21 h) was associated with a decline in performance and alertness (P < 0.03 and P < 0.0001, respectively). Conclusions: The ability of the participants to adapt successfully to the Mars day suggests that future missions should utilize a similar circadian rhythm and fatigue management program to reduce the risk of sleepiness-related errors that jeopardize personnel safety and health during critical missions. Citation: Barger LK; Sullivan JP; Vincent AS; Fiedler ER; McKenna LM; Flynn-Evans EE

  7. System-level Analysis of Food Moisture Content Requirements for the Mars Dual Lander Transit Mission

    NASA Technical Reports Server (NTRS)

    Levri, Julie A.; Perchonok, Michele H.

    2004-01-01

    In order to ensure that adequate water resources are available during a mission, any net water loss from the habitat must be balanced with an equivalent amount of required makeup water. Makeup water may come from a variety of sources, including water in shipped tanks, water stored in prepackaged food, product water from fuel cells, and in-situ water resources. This paper specifically addresses the issue of storing required makeup water in prepackaged food versus storing the water in shipped tanks for the Mars Dual Lander Transit Mission, one of the Advanced Life Support Reference Missions. In this paper, water mass balances have been performed for the Dual Lander Transit Mission, to determine the necessary requirement of makeup water under nominal operation (i.e. no consideration of contingency needs), on a daily basis. Contingency issues are briefly discussed with respect to impacts on makeup water storage (shipped tanks versus storage in prepackaged food). The Dual Lander Transit Mission was selected for study because it has been considered by the Johnson Space Center Exploration Office in enough detail to define a reasonable set of scenario options for nominal system operation and contingencies. This study also illustrates the concept that there are multiple, reasonable life support system scenarios for any one particular mission. Thus, the need for a particular commodity can depend upon many variables in the system. In this study, we examine the need for makeup water as it depends upon the configuration of the rest of the life support system.

  8. Manned Mars lander launch-to-rendezvous analysis for a 1981 Venus-swingby mission

    NASA Technical Reports Server (NTRS)

    Faust, N. L.; Murtagh, T. B.

    1971-01-01

    A description is given of the return of a manned Mars lander by a launch from the surface of Mars to some intermediate orbit, with subsequent maneuvers to rendezvous with a primary spacecraft (called the orbiter) in a Mars parking orbit. The type of Mars mission used to demonstrate the analytical technique includes a Venus swingby on the Mars-to-Earth portion of the trajectory in order to reduce the total mission velocity requirement. The total velocity requirement for the mission considered (if inplane launches are assumed) is approximately 17,500 ft/sec.

  9. A lander mission to probe subglacial water on Saturn's moon Enceladus for life

    NASA Astrophysics Data System (ADS)

    Konstantinidis, Konstantinos; Flores Martinez, Claudio L.; Dachwald, Bernd; Ohndorf, Andreas; Dykta, Paul; Bowitz, Pascal; Rudolph, Martin; Digel, Ilya; Kowalski, Julia; Voigt, Konstantin; Förstner, Roger

    2015-01-01

    The plumes discovered by the Cassini mission emanating from the south pole of Saturn's moon Enceladus and the unique chemistry found in them have fueled speculations that Enceladus may harbor life. The presumed aquiferous fractures from which the plumes emanate would make a prime target in the search for extraterrestrial life and would be more easily accessible than the moon's subglacial ocean. A lander mission that is equipped with a subsurface maneuverable ice melting probe will be most suitable to assess the existence of life on Enceladus. A lander would have to land at a safe distance away from a plume source and melt its way to the inner wall of the fracture to analyze the plume subsurface liquids before potential biosignatures are degraded or destroyed by exposure to the vacuum of space. A possible approach for the in situ detection of biosignatures in such samples can be based on the hypothesis of universal evolutionary convergence, meaning that the independent and repeated emergence of life and certain adaptive traits is wide-spread throughout the cosmos. We thus present a hypothetical evolutionary trajectory leading towards the emergence of methanogenic chemoautotrophic microorganisms as the baseline for putative biological complexity on Enceladus. To detect their presence, several instruments are proposed that may be taken aboard a future subglacial melting probe. The "Enceladus Explorer" (EnEx) project funded by the German Space Administration (DLR), aims to develop a terrestrial navigation system for a subglacial research probe and eventually test it under realistic conditions in Antarctica using the EnEx-IceMole, a novel maneuverable subsurface ice melting probe for clean sampling and in situ analysis of ice and subglacial liquids. As part of the EnEx project, an initial concept study is foreseen for a lander mission to Enceladus to deploy the IceMole near one of the active water plumes on the moon's South-Polar Terrain, where it will search for

  10. Instrument study of the Lunar Dust eXplorer (LDX) for a lunar lander mission

    NASA Astrophysics Data System (ADS)

    Li, Yanwei; Srama, Ralf; Henkel, Hartmut; Sternovsky, Zoltan; Kempf, Sascha; Wu, Yiyong; Grün, Eberhard

    2014-11-01

    One of the highest-priority issues for a future human or robotic lunar exploration is the lunar dust. This problem should be studied in depth in order to develop an environment model for a future lunar exploration. A future ESA lunar lander mission requires the measurement of dust transport phenomena above the lunar surface. Here, we describe an instrument design concept to measure slow and fast moving charged lunar dust which is based on the principle of charge induction. LDX has a low mass and measures the speed and trajectory of individual dust particles with sizes below one micrometer. Furthermore, LDX has an impact ionization target to monitor the interplanetary dust background. The sensor consists of three planes of segmented grid electrodes and each electrode is connected to an individual charge sensitive amplifier. Numerical signals were computed using the Coulomb software package. The LDX sensitive area is approximately 400 cm2. Our simulations reveal trajectory uncertainties of better than 2° with an absolute position accuracy of better than 2 mm.

  11. Viking Lander imaging investigation: Picture catalog of primary mission experiment data record

    NASA Technical Reports Server (NTRS)

    Tucker, R. B.

    1978-01-01

    All the images returned by the two Viking Landers during the primary phase of the Viking Mission are presented. Listings of supplemental information which described the conditions under which the images were acquired are included together with skyline drawings which show where the images are positioned in the field of view of the cameras. Subsets of the images are listed in a variety of sequences to aid in locating images of interest. The format and organization of the digital magnetic tape storage of the images are described. The mission and the camera system are briefly described.

  12. Feasibility of a Dragon-Derived Mars Lander for Scientific and Human-Precursor Missions

    NASA Technical Reports Server (NTRS)

    Karcz, John S.; Davis, Sanford S.; Allen, Gary A.; Glass, Brian J.; Gonzales, Andrew; Heldmann, Jennifer Lynne; Lemke, Lawrence G.; McKay, Chris; Stoker, Carol R.; Wooster, Paul Douglass; Zarchi, Kerry A.

    2013-01-01

    A minimally-modified SpaceX Dragon capsule launched on a Falcon Heavy rocket presents the possibility of a new low-cost, high-capacity Mars lander for robotic missions. We have been evaluating such a "Red Dragon" platform as an option for the Icebreaker Discovery Program mission concept. Dragon is currently in service ferrying cargo to and from the International Space Station, and a crew transport version is in development. The upcoming version, unlike other Earth-return vehicles, exhibits most of the capabilities necessary to land on Mars. In particular, it has a set of high-thrust, throttleable, storable bi-propellant "SuperDraco" engines integrated directly into the capsule that are intended for launch abort and powered landings on Earth. These thrusters provide the possibility of a parachute-free, fully-propulsive deceleration at Mars from supersonic speeds to the surface, a descent approach which would also scale well to larger future human landers. We will discuss the motivations for exploring a Red Dragon lander, the current results of our analysis of its feasibility and capabilities, and the implications of the platform for the Icebreaker mission concept. In particular, we will examine entry, descent, and landing (EDL) in detail. We will also describe the modifications to Dragon necessary for interplanetary cruise, EDL, and operations on the Martian surface. Our analysis to date indicates that a Red Dragon lander is feasible and that it would be capable of delivering more than 1000 kg of payload to sites at elevations three kilometers below the Mars Orbiter Laser Altimeter (MOLA) reference, which includes sites throughout most of the northern plains and Hellas.

  13. Solar Electric and Chemical Propulsion Technology Applications to a Titan Orbiter/Lander Mission

    NASA Technical Reports Server (NTRS)

    Cupples, Michael

    2007-01-01

    Several advanced propulsion technology options were assessed for a conceptual Titan Orbiter/Lander mission. For convenience of presentation, the mission was broken into two phases: interplanetary and Titan capture. The interplanetary phase of the mission was evaluated for an advanced Solar Electric Propulsion System (SEPS), while the Titan capture phase was evaluated for state-of-art chemical propulsion (NTO/Hydrazine), three advanced chemical propulsion options (LOX/Hydrazine, Fluorine/Hydrazine, high Isp mono-propellant), and advanced tank technologies. Hence, this study was referred to as a SEPS/Chemical based option. The SEPS/Chemical study results were briefly compared to a 2002 NASA study that included two general propulsion options for the same conceptual mission: an all propulsive based mission and a SEPS/Aerocapture based mission. The SEP/Chemical study assumed identical science payload as the 2002 NASA study science payload. The SEPS/Chemical study results indicated that the Titan mission was feasible for a medium launch vehicle, an interplanetary transfer time of approximately 8 years, an advanced SEPS (30 kW), and current chemical engine technology (yet with advanced tanks) for the Titan capture. The 2002 NASA study showed the feasibility of the mission based on a somewhat smaller medium launch vehicle, an interplanetary transfer time of approximately 5.9 years, an advanced SEPS (24 kW), and advanced Aerocapture based propulsion technology for the Titan capture. Further comparisons and study results were presented for the advanced chemical and advanced tank technologies.

  14. Lunar Radio_phase Ranging in Chinese Lunar Lander Mission for Astrometry

    NASA Astrophysics Data System (ADS)

    Ping, Jinsong; Meng, Qiao; Li, Wenxiao; Wang, Mingyuan; Wang, Zhen; Zhang, Tianyi; Han, Songtao

    2015-08-01

    The radio tracking data in lunar and planetary missions can be directly applied for scientific investigation. The variations of phase and of amplitude of the radio carrier wave signal linked between the spacecraft and the ground tracking antenna are used to deduce the planetary atmospheric and ionospheric structure, planetary gravity field, mass, ring, ephemeris, and even to test the general relativity. In the Chinese lunar missions, we developed the lunar and planetary radio science receiver to measure the distance variation between the tracking station-lander by means of open loop radio phase tracking. Using this method in Chang’E-3 landing mission, a lunar radio_phase ranging (LRR) technique was realized at Chinese deep space tracking stations and astronomical VLBI stations with H-maser clocks installed. Radio transponder and transmitter had been installed on the Chang’E-3/4. Transponder will receive the uplink S/X band radio wave transmitted from the two newly constructed Chinese deep space stations, where the high quality hydrogen maser atomic clocks have been used as local time and frequency standard. The clocks between VLBI stations and deep space stations can be synchronized to UTC standard within 20 nanoseconds using satellite common view methods. In the near future there will be a plan to improve this accuracy to 5 nanoseconds or better, as the level of other deep space network around world. In the preliminary LRR experiments of Chang'E-3, the obtained 1sps phase ranging observables have a resolution of 0.2 millimeter or better, with a fitting RMS about 2~3 millimeter, after the atmospheric and ionospheric errors removed. This method can be a new astrometric technique to measure the Earth tide and rotation, lunar orbit, tides and liberation, by means of solo observation or of working together with Lunar Laser Ranging. After differencing the ranging, we even obtained 1sps doppler series of 2-way observables with resolution of 0.07mm/second, which can

  15. A simulation of the Four-way lunar Lander-Orbiter tracking mode for the Chang'E-5 mission

    NASA Astrophysics Data System (ADS)

    Li, Fei; Ye, Mao; Yan, Jianguo; Hao, Weifeng; Barriot, Jean-Pierre

    2016-06-01

    The Chang'E-5 mission is the third phase of the Chinese Lunar Exploration Program and will collect and return lunar samples. After sampling, the Orbiter and the ascent vehicle will rendezvous and dock, and both spacecraft will require high precision orbit navigation. In this paper, we present a novel tracking mode-Four-way lunar Lander-Orbiter tracking that possibly can be employed during the Chang'E-5 mission. The mathematical formulas for the Four-way lunar Lander-Orbiter tracking mode are given and implemented in our newly-designed lunar spacecraft orbit determination and gravity field recovery software, the LUnar Gravity REcovery and Analysis Software/System (LUGREAS). The simulated observables permit analysis of the potential contribution Four-way lunar Lander-Orbiter tracking could make to precision orbit determination for the Orbiter. Our results show that the Four-way lunar Lander-Orbiter Range Rate has better geometric constraint on the orbit, and is more sensitive than the traditional two-way range rate that only tracks data between the Earth station and lunar Orbiter. After combining the Four-way lunar Lander-Orbiter Range Rate data with the traditional two-way range rate data and considering the Lander position error and lunar gravity field error, the accuracy of precision orbit determination for the Orbiter in the simulation was improved significantly, with the biggest improvement being one order of magnitude, and the Lander position could be constrained to sub-meter level. This new tracking mode could provide a reference for the Chang'E-5 mission and have enormous potential for the positioning of future lunar farside Lander due to its relay characteristic.

  16. 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.

  17. Landing site characterization activities for the European Space Agency's Lunar Lander mission

    NASA Astrophysics Data System (ADS)

    De Rosa, D.; Bussey, B.; Cahill, J. T.; Lutz, T.; Crawford, I.; Hackwill, T.; van Gasselt, S.; Neukum, G.; Witte, L.; McGovern, A.; Carpenter, J. D.

    2012-09-01

    The landing sites currently envisaged for the Lunar Lander mission of the European Space Agency have been identified in the South Pole Region (-85° to - 90° latitude) based on favourable illumination conditions, which make it possible to have a longduration mission with conventional power and thermal control subsystems instead of Radioisotope Heating Units. The illumination conditions are simulated based on topographic data from the Lunar Orbiter Laser Altimeter (LOLA), using three independent tools. Risk assessment of the identified sites is also being performed through independent studies, based on LOLA and analysis of Lunar Reconnaissance Orbiter Camera (LROC) images. The preliminary results show that areas with illumination periods of several months (interrupted only by darkness periods of few tens of hours) exist, and that the distributions of hazards in these areas are compatible with the capabilities of the on-board Hazard Detection and Avoidance system.

  18. 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.

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

    PubMed

    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.

  20. LAPIS - LAnder Package Impacting a Seismometer - A Proposal for a Semi-Hard Lander Mission to the Moon

    NASA Astrophysics Data System (ADS)

    Lange, C.

    2009-04-01

    With an increased interest on the moon within the last years, at least with several missions in orbit or under development (SELENE/Japan, Chang'e/China, Chandrayaan/India and others), there is a strong demand within the German science community to participate in this initiative, building-up a national competence regarding lunar exploration. For this purpose, a Phase-0 analysis for a small lunar semi-hard landing scenario has been performed at DLR to foster future lunar exploration missions. This study's scope was to work out a more detailed insight into the design drivers and challenges and their impact on mass and cost budgets for such a mission. LAPIS has been dedicated to the investigation of the seismic activities of the moon, additionally to some other geophysical in-situ measurements at the lunar surface. In fact, the current status of the knowledge and understanding of lunar seismic activities leads to a range of open questions which have not been answered so far by the various Apollo missions in the past and could now possibly be answered by the studied LAPIS mission. Among these are the properties of the lunar core, the origin of deep and shallow moonquakes and the occurrence of micro-meteoroids. Therefore, as proposed first for LAPIS on the LEO mission, a payload of a short period micro-seismometer, based on European and American predevelopments, has been suggested. A staged mission scenario will be described, using a 2-module spacecraft with a propulsion part and a landing part, the so called LAPIS-PROP and LAPIS-LAND. In this scenario, the LAPIS-PROP module will do the cruise, until the spacecraft reaches an altitude of 100 m above the moon, after which the landing module will separate and continue to the actual semi-hard landing, which is based on deformable structures. Further technical details, e.g. considering the subsystem technologies, have been addressed within the performed study. These especially critical and uniquely challenging issues, such

  1. Mobile Payload Element (MPE): Concept study for a sample fetching rover for the ESA Lunar Lander Mission

    NASA Astrophysics Data System (ADS)

    Haarmann, R.; Jaumann, R.; Claasen, F.; Apfelbeck, M.; Klinkner, S.; Richter, L.; Schwendner, J.; Wolf, M.; Hofmann, P.

    2012-12-01

    In late 2010, the DLR Space Administration invited the German industry to submit a proposal for a study about a Mobile Payload Element (MPE), which could be a German national contribution to the ESA Lunar Lander Mission. Several spots in the south polar region of the moon come into consideration as landing site for this mission. All possible spots provide sustained periods of solar illumination, interrupted by darkness periods of several 10 h. The MPE is outlined to be a small, autonomous, innovative vehicle in the 10 kg class for scouting and sampling the environment in the vicinity of the lunar landing site. The novel capabilities of the MPE will be to acquire samples of lunar regolith from surface, subsurface as well as shadowed locations, define their geological context and bring them back to the lander. This will enable access to samples that are not contaminated by the lander descent propulsion system plumes to increase the chances of detecting any indigenous lunar volatiles contained within the samples. Kayser-Threde, as prime industrial contractor for Phase 0/A, has assembled for this study a team of German partners with relevant industrial and institutional competence in space robotics and lunar science. The primary scientific objective of the MPE is to acquire clearly documented samples and to bring them to the lander for analysis with the onboard Lunar Dust Analysis Package (L-DAP) and Lunar Volatile Resources Analysis Package (L-VRAP). Due to the unstable nature of volatiles, which are of particular scientific interest, the MPE design needs to provide a safe storage and transportation of the samples to the lander. The proposed MPE rover concept has a four-wheeled chassis configuration with active suspension, being a compromise between innovation and mass efficiency. The suspension chosen allows a compact stowage of the MPE on the lander as well as precise alignment of the solar generators and instruments. Since therefore no further complex mechanics are

  2. Science Program of Lunar Landers of "Luna-Glob" and "Luna-Resource" Missions

    NASA Astrophysics Data System (ADS)

    Mitrofanov, I. G.; Zelenyi, L. M.; Tret'yakov, V. I.; Dolgopolov, V. P.

    2011-03-01

    Program of scientific investigations is presented for two Russian polar landers: Luna Resource and Luna Glob. This program has to address two tasks: studies of composition of lunar polar regolith and studies of lunar exosphere at both poles.

  3. Characterisation of sites of astrobiology interest for Mars landers and sample return missions

    NASA Astrophysics Data System (ADS)

    Wills, D. E. S.; Monaghan, E. P.; Foing, B. H.

    2009-04-01

    Introduction: The aim of this work is to nominate and assess candidate landing sites for missions of astrobiological interest to Mars. We report in particular on science and technical criteria and our data analysis for sites suitable for an ExoMars-class mission. This includes information from previous missions (such as Mars Express, MGS, Odyssey, MRO and MER rovers) on mineralogical composition, geomorphology, evidence from past water history from imaging and spectroscopic data, and existence of in-situ prior information from landers and rovers (concerning evidences for volatiles, organics and habitability conditions). Science Goals and Objectives: Firstly, we look for morphological evidence of hydrological activity, including sedimentary deposits (deltas, valley networks), areas of ancient hydrothermal activity (spring deposits). Secondly, we look for mineralogical evidence of hydrological activity, such as phyllosilicates (formed by alteration due to water, indicate prolonged exposure to standing water), hydrated sulphates (formed by alteration due to water, not necessarily standing water), other water-containing minerals. Thirdly, we prioritise Noachian terrain (during this epoch, ~3.5 billion years ago, the Martian climate may have been warmer, and liquid water may have been stable on the surface). Finally, we look for sites where the potential for preservation of biosignatures is high (exposed bedrock, subsurface regions, spring sinters). Engineering Constraints: We consider the engineering constraints placed on the ExoMars misson. These include latitude (sufficient insolation for power), landing altitude (sufficient atmosphere for EDL), horizontal winds, shear, and wind turbulence (airbag free fall), radar altimeter reflectivity (for descent and landing control), obstacles and rock distribution (airbag landing), slopes (airbag landing), rover egress, and rover locomotion. The Priority Sites: Out of a short-list of ten proposed locations, we select two top

  4. The method of landing sites selection for Russian lunar lander missions

    NASA Astrophysics Data System (ADS)

    Mitrofanov, Igor; Djachkova, Maya; Litvak, Maxim; Sanin, Anton

    2016-04-01

    Russian space agency is planning to launch two lunar landers in the upcoming years - Luna-Glob (2018) and Luna-Resurs (2021). Instruments installed on board the landers are designed to study volatiles and water ice, lunar exosphere, dust particles and regolith composition. As primary scientific interest is concentrated in the south polar region, the landing sites for both landers will be selected there. Since rugged terrain, conditions of solar illumination at high altitudes and necessity of direct radio communication with the Earth, it is essential to select an optimal landing site for each lander. We present the method of landing sites selection, which is based on geographical information systems (GIS) technologies to perform analysis, based on the criteria of surface suitability for landing, such as slopes, illumination conditions and Earth visibility. In addition, the estimations of hydrogen concentration in regolith based on LEND/LRO data were used to evaluate landing site candidates on possible water ice presence. The method gave us 6 canditates to land. Four of them are located in the impact craters: Simpelius D, Simpelius E, Boguslawsky C, Boussingault, and the other two are located to the north of Schomberger crater and to the north-west of Boguslawsky C crater and associated with probable basin-related materials. The main parameters of these sites will be presented with possible prioritization based on both technical requirements and scientific interest.

  5. In-situ dust measurements by a lunar lander

    NASA Astrophysics Data System (ADS)

    Srama, Ralf; Sternovsky, Zoltan; Horanyi, Mihaly; Gruen, Eberhard; Krueger, Harald; Laufer, Rene; Roeser, Hans-Peter; Postberg, Frank; Kempf, Sascha; Moragas-Klostermeyer, Georg; Mocker, Anna; Fiege, Katherina; Li, Yanwei

    2012-07-01

    Charged dust grains on the lunar surface impact our future exploration of the moon. Serious problems for exploration activities were revealed by the Apollo missions. Dust shows strong adhesion to equipment and clothes and makes breathing difficult within a spacecraft. The micron- and submicron sized grains are embedded in the lunar plasma environment and their physical properties determine their dynamics. The solar wind, UV light and shadows lead to temporal effects in plasma densities and dust grain charging states. The dust populations relevant for the processes on the surface are: interplanetary and interstellar dust, levitated dust and, especially, dust ejecta generated by primary impacts on the surface. A dust instrument on the surface shall distinguish the three populations and characterize their charging state, size, speed and directionality distribution. Dust measurements shall be performed in conjunction with surface plasma and surface electric field characterizations.

  6. A Lunar L2-Farside Exploration and Science Mission Concept with the ORion Multi-Purpose Crew Vehicle and a Teleoperated Lander/Rover

    NASA Technical Reports Server (NTRS)

    Burns, Jack O.; Kring, David; Norris, Scott; Hopkins, Josh; Lazio, Joseph; Kasper, Justin

    2012-01-01

    A novel concept is presented in this paper for a human mission to the lunar L2 (Lagrange) point that would be a proving ground for future exploration missions to deep space while also overseeing scientifically important investigations. In an L2 halo orbit above the lunar farside, the astronauts would travel 15% farther from Earth than did the Apollo astronauts and spend almost three times longer in deep space. Such missions would validate the Orion MPCV's life support systems, would demonstrate the high-speed re-entry capability needed for return from deep space, and would measure astronauts' radiation dose from cosmic rays and solar flares to verify that Orion would provide sufficient protection, as it is designed to do. On this proposed mission, the astronauts would teleoperate landers and rovers on the unexplored lunar farside, which would obtain samples from the geologically interesting farside and deploy a low radio frequency telescope. Sampling the South Pole-Aitkin basin (one of the oldest impact basins in the solar system) is a key science objective of the 2011 Planetary Science Decadal Survey. Observations of the Universe's first stars/galaxies at low radio frequencies are a priority of the 2010 Astronomy & Astrophysics Decadal Survey. Such telerobotic oversight would also demonstrate capability for human and robotic cooperation on future, more complex deep space missions.

  7. NASA's Robotic Lander Takes Flight

    NASA Video Gallery

    On Monday, June 13, the robotic lander mission team was poised and ready when the lander prototype in the adjacent building lifted itself off the ground and rose unrestrained higher and higher. App...

  8. Rationale for a Mars Pathfinder mission to Chryse Planitia and the Viking 1 lander

    NASA Astrophysics Data System (ADS)

    Craddock, Robert A.

    Presently the landing site for Mars Pathfinder will be constrained to latitudes between 0 deg and 30 deg N to facilitate communication with earth and to allow the lander and rover solar arrays to generate the maximum possible power. The reference elevation of the site must also be below 0 km so that the descent parachute, a Viking derivative, has sufficient time to open and slow the lander to the correct terminal velocity. Although Mars has as much land surface area as the continental crust of the earth, such engineering constraints immediately limit the number of possible landing sites to only three broad areas: Amazonis, Chryse, and Isidis Planitia. Of these, both Chryse and Isidis Planitia stand out as the sites offering the most information to address several broad scientific topics.

  9. Quasi-microscope concept for planetary missions. [optically augmented lander camera for high resolution microscopy

    NASA Technical Reports Server (NTRS)

    Huck, F. O.; Burcher, E. E.; Wall, S. D.; Arvidson, R. E.; Giat, O.

    1977-01-01

    Viking lander cameras have returned stereo and multispectral views of the Martian surface with a resolution that approaches 2 mm/lp in the near field. A two-orders-of-magnitude increase in resolution could be obtained for collected surface samples by augmenting these cameras with auxiliary optics that would neither impose special camera design requirements nor limit the cameras field of view of the terrain. Quasi-microscope images would provide valuable data on the physical and chemical characteristics of planetary regoliths.

  10. Viking Lander reliability program

    NASA Technical Reports Server (NTRS)

    Pilny, M. J.

    1978-01-01

    The Viking Lander reliability program is reviewed with attention given to the development of the reliability program requirements, reliability program management, documents evaluation, failure modes evaluation, production variation control, failure reporting and correction, and the parts program. Lander hardware failures which have occurred during the mission are listed.

  11. Evaluation of Viking Lander barometric pressure sensor. [performance related to Viking mission environments

    NASA Technical Reports Server (NTRS)

    Mitchell, M.

    1977-01-01

    Variable reluctance type pressure sensors were evaluated to determine their performance characteristics related to Viking Mission environment levels. Static calibrations were performed throughout the evaluation over the full range of the sensors using two point contact manometer standards. From the beginning of the evaluation to the end of the evaluation, the zero shift in the two sensors was within 0.5 percent, and the sensitivity shift was 0.05 percent. The maximum thermal zero coefficient exhibited by the sensors was 0.032 percent over the temperature range of -28.89 C to 71.11 C. The evaluation results indicated that the sensors are capable of making high accuracy pressure measurements while being exposed to the conditions mentioned.

  12. Geomorphic and geologic settings of the Phoenix Lander mission landing site

    NASA Astrophysics Data System (ADS)

    Heet, T. L.; Arvidson, R. E.; Cull, S. C.; Mellon, M. T.; Seelos, K. D.

    2009-11-01

    The Phoenix Lander touched down on the northern distal flank of the shield volcano Alba Patera in a ˜150 km wide valley underlain by the Scandia region unit. The geomorphology and geology of the landing site is dominated by the ˜0.6 Ga, 11.5 km wide, bowl-shaped impact crater, Heimdal, and its areally extensive ejecta deposits. The Lander is located ˜20 km to the west of the crater and is sitting on a plains surface underlain by partially eroded Heimdal ejecta deposits. Heimdal was produced by a hypervelocity impact into fine-grained, ice-rich material and is inferred to have produced high velocity winds and a ground-hugging ejecta emplacement mode that destroyed or buried preexisting surfaces and rock fields out to ˜10 crater radii. Patterned ground is ubiquitous, with complex polygon patterns and rock rubble piles located on older plains (˜3.3 Ga) to the west of the ejecta deposits. Crater size frequency distributions are complex and represent equilibria between crater production and destruction processes (e.g., aeolian infill, cryoturbation, relaxation of icy substrate). Rock abundances increase near craters for the older plains and rocks with their dark shadows explain the reason for the few percent lower albedo for these plains as opposed to the Heimdal ejecta deposits. Many rocks at the landing site have been reworked by cryoturbation and moved to polygon troughs. The evidence for cryoturbation and the lack of aeolian features imply that the soils sampled by Phoenix are locally derived and mixed with a subordinate amount of windblown dust.

  13. Three Dimensional Rover/Lander/Orbiter Mission-Planning (3D-ROMPS) System: A Modern Approach to Mission Planning

    NASA Technical Reports Server (NTRS)

    Scharfe, Nathan D.

    2005-01-01

    NASA's current mission planning system is based on point design, two-dimensional display, spread sheets, and report technology. This technology does not enable engineers to analyze the results of parametric studies of missions plans. This technology will not support the increased observational complexity and data volume of missions like Cassini, Mars Reconnaissance Orbiter (MRO), Mars Science Laboratory (MSL), and Mars Sample Return (MSR). The goal of the 3D-ROMPS task has been to establish a set of operational mission planning and analysis tools in the Image Processing Laboratory (IPL) Mission Support Area (MSA) that will respond to engineering requirements for planning future Solar System Exploration (SSE) missions using a three-dimensional display.

  14. Performance of the mission critical Electrical Support System (ESS) which handled communications and data transfer between the Rosetta Orbiter and its Lander Philae while en route to and at comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    McKenna-Lawlor, Susan; Rusznyak, Peter; Balaz, Jan; Schmidt, Walter; Fantinati, Cinzia; Kuechemann, Oliver; Geurts, Koen

    2016-08-01

    The Electrical Support System (ESS), which was designed and built in Ireland, handled commands transmitted from the Rosetta spacecraft to the Command and Data Management System (CDMS) aboard its Lander Philae during a ten year Cruise Phase to comet 67P/Churyumov-Gerasimenko as well as at the comet itself. The busy Cruise Phase included three Earth flybys, a fly-by of Mars and visits to two asteroids, Steins and Lutetia. Data originating at the individual Lander experiments measured while en-route to and at the comet were also handled by the ESS which received and reformatted them prior to their transmission by Rosetta to Earth. Since the success of the Lander depended on the acquisition of scientific data, the ESS was defined by the European Space Agency to be Mission Critical Hardware. The electronic design of the ESS and its method of handling communications between the spacecraft and Philae are herein presented. The nominal performance of the ESS during the Cruise Phase and in the course of subsequent surface campaigns is described and the successful fulfilment of the brief of this subsystem to retrieve unique scientific data measured by the instruments of the Philae Lander demonstrated.

  15. Mars lander survey

    NASA Technical Reports Server (NTRS)

    Stump, William R.; Babb, Gus R.; Davis, Hubert P.

    1986-01-01

    The requirements, issues, and design options are reviewed for manned Mars landers. Issues such as high 1/d versus low 1/d shape, parking orbit, and use of a small Mars orbit transfer vehicle to move the lander from orbit to orbit are addressed. Plots of lander mass as a function of Isp, destination orbit, and cargo up and down, plots of initial stack mass in low Earth orbit as a function of lander mass and parking orbit, detailed weight statements, and delta V tables for a variety of options are included. Lander options include a range from minimum landers up to a single stage reusable design. Mission options include conjunction and Venus flyby trajectories using all-cryogenic, hybrid, NERVA, and Mars orbit aerobraking propulsion concepts.

  16. Reconciling the Differences between the Measurements of CO2 Isotopes by the Phoenix and MSL Landers

    NASA Technical Reports Server (NTRS)

    Niles, P. B.; Mahaffy, P. R.; Atreya, S.; Pavlov, A. A.; Trainer, M.; Webster, C. R.; Wong, M.

    2014-01-01

    Precise stable isotope measurements of the CO2 in the martian atmosphere have the potential to provide important constraints for our understanding of the history of volatiles, the carbon cycle, current atmospheric processes, and the degree of water/rock interaction on Mars. There have been several different measurements by landers and Earth based systems performed in recent years that have not been in agreement. In particular, measurements of the isotopic composition of martian atmospheric CO2 by the Thermal and Evolved Gas Analyzer (TEGA) instrument on the Mars Phoenix Lander and the Sample Analysis at Mars (SAM) instrument on the Mars Science Laboratory (MSL) are in stark disagreement. This work attempts to use measurements of mass 45 and mass 46 of martian atmospheric CO2 by the SAM and TEGA instruments to search for agreement as a first step towards reaching a consensus measurement that might be supported by data from both instruments.

  17. Lunar lander conceptual design

    NASA Technical Reports Server (NTRS)

    Lee, Joo Ahn; Carini, John; Choi, Andrew; Dillman, Robert; Griffin, Sean J.; Hanneman, Susan; Mamplata, Caesar; Stanton, Edward

    1989-01-01

    A conceptual design is presented of a Lunar Lander, which can be the primary vehicle to transport the equipment necessary to establish a surface lunar base, the crew that will man the base, and the raw materials which the Lunar Station will process. A Lunar Lander will be needed to operate in the regime between the lunar surface and low lunar orbit (LLO), up to 200 km. This lander is intended for the establishment and operation of a manned surface base on the moon and for the support of the Lunar Space Station. The lander will be able to fulfill the requirements of 3 basic missions: A mission dedicated to delivering maximum payload for setting up the initial lunar base; Multiple missions between LLO and lunar surface dedicated to crew rotation; and Multiple missions dedicated to cargo shipments within the regime of lunar surface and LLO. A complete set of structural specifications is given.

  18. Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Tropical rainfall affects the lives and economics of a majority of the Earth's population. Tropical rain systems, such as hurricanes, typhoons, and monsoons, are crucial to sustaining the livelihoods of those living in the tropics. Excess rainfall can cause floods and great property and crop damage, whereas too little rainfall can cause drought and crop failure. The latent heat release during the process of precipitation is a major source of energy that drives the atmospheric circulation. This latent heat can intensify weather systems, affecting weather thousands of kilometers away, thus making tropical rainfall an important indicator of atmospheric circulation and short-term climate change. Tropical forests and the underlying soils are major sources of many of the atmosphere's trace constituents. Together, the forests and the atmosphere act as a water-energy regulating system. Most of the rainfall is returned to the atmosphere through evaporation and transpiration, and the atmospheric trace constituents take part in the recycling process. Hence, the hydrological cycle provides a direct link between tropical rainfall and the global cycles of carbon, nitrogen, and sulfur, all important trace materials for the Earth's system. Because rainfall is such an important component in the interactions between the ocean, atmosphere, land, and the biosphere, accurate measurements of rainfall are crucial to understanding the workings of the Earth-atmosphere system. The large spatial and temporal variability of rainfall systems, however, poses a major challenge to estimating global rainfall. So far, there has been a lack of rain gauge networks, especially over the oceans, which points to satellite measurement as the only means by which global observation of rainfall can be made. The Tropical Rainfall Measuring Mission (TRMM), jointly sponsored by the National Aeronautics and Space Administration (NASA) of the United States and the National Space Development Agency (NASDA) of

  19. Viking lander spacecraft battery

    NASA Technical Reports Server (NTRS)

    Newell, D. R.

    1976-01-01

    The Viking Lander was the first spacecraft to fly a sterilized nickel-cadmium battery on a mission to explore the surface of a planet. The significant results of the battery development program from its inception through the design, manufacture, and test of the flight batteries which were flown on the two Lander spacecraft are documented. The flight performance during the early phase of the mission is also presented.

  20. Envisaged plasma and magnetic field measurements onboard the Rosetta Lander Philae on comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    Apathy, Istvan; Hilchenbach, Martin; Remizov, Anatoly; Auster, Hans-Ulrich; Berghofer, Gerhard

    Comets are the thinnest cheaters in our solar system. While the comet nucleus extents only up to a few kilometers, the coma can span several hundred million kilometers. ESA's corner stone mission Rosetta will orbit comet 67P/Churyumov-Gerasimenko and deliver the cometary lander Philae onto the comet surface in Novemebr 2014. The instrument ROMAP (Rosetta Lander Magnetometer and Plasma Monitor) onboard Philae consists of a fluxgate magnetometer and a plasma ion and electron sensor. ROMAP will measure for the first time the magnetic field, electron and ion distribution on a cometary surface.
The envisaged science will focuss on the space plasma and magnetic field in the vicinity and on the comet nucleus. We will present the instrument parameters and observation timeline. We will discuss the potential science envisaged from November 2014 onward such as the potential remanent magnetisation of the comet nucleus and what it would mean for the nucleus formation process as well as the envisaged unique solar wind plasma observations on a cometary surface including the transition from day to night side.

  1. Viking Lander Model

    NASA Technical Reports Server (NTRS)

    2007-01-01

    NASA's Viking Project found a place in history when it became the first mission to land a spacecraft successfully on the surface of another planet and return both imaging and non-imaging data over an extended time period. Two identical spacecraft, each consisting of a lander and an orbiter, were built. Each orbiter-lander pair flew together and entered Mars orbit; the landers then separated and descended to the planet's surface.

    The Viking 1 Lander touched down on the western slope of Chryse Planitia (the Plains of Gold) on July 20, 1976, while the Viking 2 lander settled down at Utopia Planitia on September 3, 1976.

    Besides taking photographs and collecting other science data on the Martian surface, the two landers conducted three biology experiments designed to look for possible signs of life. These experiments discovered unexpected and enigmatic chemical activity in the Martian soil, but provided no clear evidence for the presence of living microorganisms in soil near the landing sites. According to scientists, Mars is self-sterilizing. They believe the combination of solar ultraviolet radiation that saturates the surface, the extreme dryness of the soil and the oxidizing nature of the soil chemistry prevent the formation of living organisms in the Martian soil.

    The Viking mission was planned to continue for 90 days after landing. Each orbiter and lander operated far beyond its design lifetime. Viking Orbiter 1 functioned until July 25, 1978, while Viking Orbiter 2 continued for four years and 1,489 orbits of Mars, concluding its mission August 7, 1980. Because of the variations in available sunlight, both landers were powered by radioisotope thermoelectric generators -- devices that create electricity from heat given off by the natural decay of plutonium. That power source allowed long-term science investigations that otherwise would not have been possible. The last data from Viking Lander 2 arrived at Earth on April 11, 1980. Viking Lander

  2. Deployment of a lander on the binary asteroid (175706) 1996 FG3, potential target of the european MarcoPolo-R sample return mission

    NASA Astrophysics Data System (ADS)

    Tardivel, Simon; Michel, Patrick; Scheeres, Daniel J.

    2013-08-01

    The idea of deploying a lander on the secondary body of the binary primitive asteroid (175706) 1996 FG3 is investigated. 1996 FG3 is the backup target of the European sample return space mission MarcoPolo-R under assessment study at the European Space Agency in the framework of the M3 Medium-Class mission competition. The launch will take place in 2022-2024, depending on its selection at the end of 2013. A lander is indicated as an optional payload, depending on mass availability on the spacecraft. Obviously, the possible complexity of a lander deployment is also an important parameter to take into account. Here we demonstrate that, considering worst case scenarios and low requirements on the spacecraft GNC and deployment mechanism, the operations are easy to implement and safe for the main spacecraft. The concept of operations is to deploy a light lander from the L2 Lagrange point of the binary system, on a ballistic trajectory that will impact the secondary asteroid. The fundamental principles of this strategy are briefly presented and a detailed model of 1996 FG3 is considered, to which the strategy is applied. We show that the deployment is successful in 99.94% of cases.

  3. MSFC Robotic Lunar Lander Testbed and Current Status of the International Lunar Network (ILN) Anchor Nodes Mission

    NASA Technical Reports Server (NTRS)

    Cohen, Barbara; Bassler, Julie; Harris, Danny; Morse, Brian; Reed, Cheryl; Kirby, Karen; Eng, Douglas

    2009-01-01

    The lunar lander robotic exploration testbed at Marshall Spaceflight Center provides a test environment for robotic lander test articles, components and algorithms to reduce the risk on the airless body designs during lunar landing. Also included is a chart comparing the two different types of Anchor nodes for the International Lunar Network (ILN): Solar/Battery and the Advanced Stirling Radioisotope generator (ARSG.)

  4. Detection of crustal deformation from the Landers earthquake sequence using continuous geodetic measurements

    NASA Technical Reports Server (NTRS)

    Bock, Yehuda; Agnew, Duncan C.; Fang, Peng; Genrich, Joachim F.; Hager, Bradford H.; Herring, Thomas A.; Hudnut, Kenneth W.; King, Robert W.; Larsen, Shawn; Minster, J.-B.

    1993-01-01

    The first measurements are reported for a major earthquake by a continuously operating GPS network, the permanent GPS Genetic ARRY (PGGA) in southern California. The Landers and Big Bear earthquakes of June 28, 1992 were monitored by daily observations. Ten weeks of measurements indicate significant coseismic motion at all PGGA sites, significant postseismic motion at one site for two weeks after the earthquakes, and no significant preseismic motion. These measurements demonstrate the potential of GPS monitoring for precise detection of precursory and aftershock seismic deformation in the near and far field.

  5. Testing general relativity with Landers on the Martian satellite Phobos

    NASA Technical Reports Server (NTRS)

    Anderson, J. D.; Borderies, N. J.; Campbell, J. K.; Dunne, J. A.; Ellis, J.

    1989-01-01

    A planned experiment to obtain range and Doppler data with the Phobos 2 Lander on the surface of the Martian satellite Phobos is described. With the successful insertion on January 29, 1989 of Phobos 2 into Mars orbit, it is anticipated that the Lander will be placed on the surface of Phobos in April 1989. Depending on the longevity of the Lander, range and Doppler data for a period of from one to several years are expected. Because these data are of value in performing solar-system tests of general relativity, the current accuracy of the relevant relativity tests using Deep Space Network data from the Mariner-9 orbiter of Mars in 1971 and from the Viking Landers in 1976-1982 is reviewed. The expected improvement from data anticipated during the Phobos 2 Lander Mission is also discussed; most important will be an improved sensitivity to any time variation in the gravitational 'constant' as measured in atomic units.

  6. Altair Lunar Lander Consumables Management

    NASA Technical Reports Server (NTRS)

    Polsgrove, Tara; Button, Robert; Linne, Diane

    2009-01-01

    The Altair lunar lander is scheduled to return humans to the moon in the year 2020. Keeping the crew of 4 and the vehicle functioning at their best while minimizing lander mass requires careful budgeting and management of consumables and cooperation with other constellation elements. Consumables discussed here include fluids, gasses, and energy. This paper presents the lander's missions and constraints as they relate to consumables and the design solutions that have been employed in recent Altair conceptual designs.

  7. Robotic Lunar Landers for Science and Exploration

    NASA Technical Reports Server (NTRS)

    Cohen, Barbara A.

    2012-01-01

    The MSFC/APL Robotic Lunar Landing Project (RLLDP) team has developed lander concepts encompassing a range of mission types and payloads for science, exploration, and technology demonstration missions: (1) Developed experience and expertise in lander systems, (2) incorporated lessons learned from previous efforts to improve the fidelity of mission concepts, analysis tools, and test beds Mature small and medium lander designs concepts have been developed: (1) Share largely a common design architecture. (2) Flexible for a large number of mission and payload options. High risk development areas have been successfully addressed Landers could be selected for a mission with much of the concept formulation phase work already complete

  8. Planning and implementation of the on-comet operations of the instrument SD2 onboard the lander Philae of Rosetta mission

    NASA Astrophysics Data System (ADS)

    Di Lizia, P.; Bernelli-Zazzera, F.; Ercoli-Finzi, A.; Mottola, S.; Fantinati, C.; Remetean, E.; Dolives, B.

    2016-08-01

    The lander Philae of the Rosetta mission landed on the surface of the comet 67 P/Churyumov-Gerasimenko on November 12, 2014. Among the specific subsystems and instruments carried on Philae, the sampling, drilling and distribution (SD2) subsystem had the role of providing in-situ operations devoted to soil drilling, sample collection, and their distribution to three scientific instruments. After landing, a first sequence of scientific activities was carried out, relying mainly on the energy stored in the lander primary battery. Due to the limited duration and the communication delay, these activities had to be carried out automatically, with a limited possibility of developing and uploading commands from the ground. Philae's landing was not nominal and SD2 was operated in unexpected conditions: the lander was not anchored to the soil and leant on the comet surface shakily. Nevertheless, one sampling procedure was attempted. This paper provides an overview of SD2 operation planning and on-comet operations, and analyses SD2 achievements during the first science sequence of Philae's on-comet operations.

  9. A MATLAB based Distributed Real-time Simulation of Lander-Orbiter-Earth Communication for Lunar Missions

    NASA Astrophysics Data System (ADS)

    Choudhury, Diptyajit; Angeloski, Aleksandar; Ziah, Haseeb; Buchholz, Hilmar; Landsman, Andre; Gupta, Amitava; Mitra, Tiyasa

    Lunar explorations often involve use of a lunar lander , a rover [1],[2] and an orbiter which rotates around the moon with a fixed radius. The orbiters are usually lunar satellites orbiting along a polar orbit to ensure visibility with respect to the rover and the Earth Station although with varying latency. Communication in such deep space missions is usually done using a specialized protocol like Proximity-1[3]. MATLAB simulation of Proximity-1 have been attempted by some contemporary researchers[4] to simulate all features like transmission control, delay etc. In this paper it is attempted to simulate, in real time, the communication between a tracking station on earth (earth station), a lunar orbiter and a lunar rover using concepts of Distributed Real-time Simulation(DRTS).The objective of the simulation is to simulate, in real-time, the time varying communication delays associated with the communicating elements with a facility to integrate specific simulation modules to study different aspects e.g. response due to a specific control command from the earth station to be executed by the rover. The hardware platform comprises four single board computers operating as stand-alone real time systems (developed by MATLAB xPC target and inter-networked using UDP-IP protocol). A time triggered DRTS approach is adopted. The earth station, the orbiter and the rover are programmed as three standalone real-time processes representing the communicating elements in the system. Communication from one communicating element to another constitutes an event which passes a state message from one element to another, augmenting the state of the latter. These events are handled by an event scheduler which is the fourth real-time process. The event scheduler simulates the delay in space communication taking into consideration the distance between the communicating elements. A unique time synchronization algorithm is developed which takes into account the large latencies in space

  10. A lunar L2-Farside exploration and science mission concept with the Orion Multi-Purpose Crew Vehicle and a teleoperated lander/rover

    NASA Astrophysics Data System (ADS)

    Burns, Jack O.; Kring, David A.; Hopkins, Joshua B.; Norris, Scott; Lazio, T. Joseph W.; Kasper, Justin

    2013-07-01

    A novel concept is presented in this paper for a human mission to the lunar L2 (Lagrange) point that would be a proving ground for future exploration missions to deep space while also overseeing scientifically important investigations. In an L2 halo orbit above the lunar farside, the astronauts aboard the Orion Crew Vehicle would travel 15% farther from Earth than did the Apollo astronauts and spend almost three times longer in deep space. Such a mission would serve as a first step beyond low Earth orbit and prove out operational spaceflight capabilities such as life support, communication, high speed re-entry, and radiation protection prior to more difficult human exploration missions. On this proposed mission, the crew would teleoperate landers/rovers on the unexplored lunar farside, which would obtain samples from the geologically interesting farside and deploy a low radio frequency telescope. Sampling the South Pole-Aitken basin, one of the oldest impact basins in the solar system, is a key science objective of the 2011 Planetary Science Decadal Survey. Observations at low radio frequencies to track the effects of the Universe's first stars/galaxies on the intergalactic medium are a priority of the 2010 Astronomy and Astrophysics Decadal Survey. Such telerobotic oversight would also demonstrate capability for human and robotic cooperation on future, more complex deep space missions such as exploring Mars.

  11. Carbon and Oxygen Stable Isotope Measurements of Martian Atmospheric CO2 by the Phoenix Lander

    NASA Technical Reports Server (NTRS)

    Niles, Paul B.; Boynton, W. V.; Hoffman, J. H.; Ming, D. W.; Hamara, D.

    2010-01-01

    Precise stable isotope measurements of the CO2 in the martian atmosphere have the potential to provide important constraints for our understanding of the history of volatiles, the carbon cycle, current atmospheric processes, and the degree of water/rock interaction on Mars [1]. The isotopic composition of the martian atmosphere has been measured using a number of different methods (Table 1), however a precise value (<1%) has yet to be achieved. Given the elevated Delta(sup 13)C values measured in carbonates in martian meteorites [2-4] it has been proposed that the martian atmosphere was enriched in 13C [8]. This was supported by measurements of trapped CO2 gas in EETA 79001[2] which showed elevated Delta(sup 13)C values (Table 1). More recently, Earth-based spectroscopic measurements of the martian atmosphere have measured the martian CO2 to be depleted in C-13 relative to CO2 in the terrestrial atmosphere[ 7, 9-11]. The Thermal and Evolved Gas Analyzer (TEGA) instrument on the Mars Phoenix Lander [12] included a magnetic-sector mass spectrometer (EGA) [13] which had the goal of measuring the isotopic composition of martian atmospheric CO2 to within 0.5%. The mass spectrometer is a miniature instrument intended to measure both the martian atmosphere as well as gases evolved from heating martian soils.

  12. Detection of crustal deformation from the Landers earthquake sequence using continuous geodetic measurements

    USGS Publications Warehouse

    Bock, Y.; Agnew, D.C.; Fang, P.; Genrich, J.F.; Hager, B.H.; Herring, T.A.; Hudnut, K.W.; King, R.W.; Larsen, S.; Minster, J.-B.; Stark, K.; Wdowinski, S.; Wyatt, F.K.

    1993-01-01

    The measurement of crustal motions in technically active regions is being performed increasingly by the satellite-based Global Positioning System (GPS)1,2, which offers considerable advantages over conventional geodetic techniques3,4. Continuously operating GPS arrays with ground-based receivers spaced tens of kilometres apart have been established in central Japan5,6 and southern California to monitor the spatial and temporal details of crustal deformation. Here we report the first measurements for a major earthquake by a continuously operating GPS network, the Permanent GPS Geodetic Array (PGGA)7,9 in southern California. The Landers (magnitude Mw of 7.3) and Big Bear (Mw 6.2) earthquakes of 28 June 1992 were monitored by daily observations. Ten weeks of measurements, centred on the earthquake events, indicate significant coseismic motion at all PGGA sites, significant post-seismic motion at one site for two weeks after the earthquakes, and no significant preseismic motion. These measurements demonstrate the potential of GPS monitoring for precise detection of precursory and aftershock seismic deformation in the near and far field.

  13. The Global Precipitation Measurement Mission

    NASA Astrophysics Data System (ADS)

    Jackson, Gail

    2014-05-01

    The Global Precipitation Measurement (GPM) mission's Core satellite, scheduled for launch at the end of February 2014, is well designed estimate precipitation from 0.2 to 110 mm/hr and to detect falling snow. Knowing where and how much rain and snow falls globally is vital to understanding how weather and climate impact both our environment and Earth's water and energy cycles, including effects on agriculture, fresh water availability, and responses to natural disasters. The design of the GPM Core Observatory is an advancement of the Tropical Rainfall Measuring Mission (TRMM)'s highly successful rain-sensing package [3]. The cornerstone of the GPM mission is the deployment of a Core Observatory in a unique 65o non-Sun-synchronous orbit to serve as a physics observatory and a calibration reference to improve precipitation measurements by a constellation of 8 or more dedicated and operational, U.S. and international passive microwave sensors. The Core Observatory will carry a Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a multi-channel (10-183 GHz) GPM Microwave Radiometer (GMI). The DPR will provide measurements of 3-D precipitation structures and microphysical properties, which are key to achieving a better understanding of precipitation processes and improving retrieval algorithms for passive microwave radiometers. The combined use of DPR and GMI measurements will place greater constraints on possible solutions to radiometer retrievals to improve the accuracy and consistency of precipitation retrievals from all constellation radiometers. Furthermore, since light rain and falling snow account for a significant fraction of precipitation occurrence in middle and high latitudes, the GPM instruments extend the capabilities of the TRMM sensors to detect falling snow, measure light rain, and provide, for the first time, quantitative estimates of microphysical properties of precipitation particles. The GPM Core Observatory was developed and tested at NASA

  14. Planetary Seismology : Lander- and Wind-Induced Seismic Signals

    NASA Astrophysics Data System (ADS)

    Lorenz, Ralph

    2016-10-01

    Seismic measurements are of interest for future geophysical exploration of ocean worlds such as Europa or Titan, as well as Venus, Mars and the Moon. Even when a seismometer is deployed away from a lander (as in the case of Apollo) lander-generated disturbances are apparent. Such signatures may be usefully diagnostic of lander operations (at least for outreach), and may serve as seismic excitation for near-field propagation studies. The introduction of these 'spurious' events may also influence the performance of event detection and data compression algorithms.Examples of signatures in the Viking 2 seismometer record of lander mechanism operations are presented. The coherence of Viking seismometer noise levels and wind forcing is well-established : some detailed examples are examined. Wind noise is likely to be significant on future Mars missions such as InSight, as well as on Titan and Venus.

  15. Global Precipitation Measurement Mission: Architecture and Mission Concept

    NASA Technical Reports Server (NTRS)

    Bundas, David

    2005-01-01

    The Global Precipitation Measurement (GPM) Mission is a collaboration between the National Aeronautics and Space Administration (NASA) and the Japanese Aerospace Exploration Agency (JAXA), and other partners, with the goal of monitoring the diurnal and seasonal variations in precipitation over the surface of the earth. These measurements will be used to improve current climate models and weather forecasting, and enable improved storm and flood warnings. This paper gives an overview of the mission architecture and addresses some of the key trades that have been completed, including the selection of the Core Observatory s orbit, orbit maintenance trades, and design issues related to meeting orbital debris requirements.

  16. Southern California Permanent GPS Geodetic Array: Continuous measurements of regional crustal deformation between the 1992 Landers and 1994 Northridge earthquakes

    USGS Publications Warehouse

    Bock, Y.; Wdowinski, S.; Fang, P.; Zhang, Jiahua; Williams, S.; Johnson, H.; Behr, J.; Genrich, J.; Dean, J.; Van Domselaar, M.; Agnew, D.; Wyatt, F.; Stark, K.; Oral, B.; Hudnut, K.; King, R.; Herring, T.; Dinardo, S.; Young, W.; Jackson, D.; Gurtner, W.

    1997-01-01

    The southern California Permanent GPS Geodetic Array (PGGA) was established in 1990 across the Pacific-North America plate boundary to continuously monitor crustal deformation. We describe the development of the array and the time series of daily positions estimated for its first 10 sites in the 19-month period between the June 28, 1992 (Mw=7.3), Landers and January 17, 1994 (Mw=6.7), Northridge earthquakes. We compare displacement rates at four site locations with those reported by Feigl et al. [1993], which were derived from an independent set of Global Positioning System (GPS) and very long baseline interferometry (VLBI) measurements collected over nearly a decade prior to the Landers earthquake. The velocity differences for three sites 65-100 km from the earthquake's epicenter are of order of 3-5 mm/yr and are systematically coupled with the corresponding directions of coseismic displacement. The fourth site, 300 km from the epicenter, shows no significant velocity difference. These observations suggest large-scale postseismic deformation with a relaxation time of at least 800 days. The statistical significance of our observations is complicated by our incomplete knowledge of the noise properties of the two data sets; two possible noise models fit the PGGA data equally well as described in the companion paper by Zhang et al. [this issue]; the pre-Landers data are too sparse and heterogeneous to derive a reliable noise model. Under a fractal white noise model for the PGGA data we find that the velocity differences for all three sites are statistically different at the 99% significance level. A white noise plus flicker noise model results in significance levels of only 94%, 43%, and 88%. Additional investigations of the pre-Landers data, and analysis of longer spans of PGGA data, could have an important effect on the significance of these results and will be addressed in future work. Copyright 1997 by the American Geophysical Union.

  17. Phoenix Lander Work Area

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This image shows NASA's Phoenix Mars Lander Robotic Arm work area with an overlay. The pink area is available for digging, the green area is reserved for placing the Thermal and Electrical Conductivity Probe (TECP) instrument. Soil can be dumped in the violet area.

    Images were displayed using NASA Ames 'Viz' visualization software.

    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.

  18. Space Interferometry Mission: Measuring the Universe

    NASA Technical Reports Server (NTRS)

    Marr, James; Dallas, Saterios; Laskin, Robert; Unwin, Stephen; Yu, Jeffrey

    1991-01-01

    The Space Interferometry Mission (SIM) will be the NASA Origins Program's first space based long baseline interferometric observatory. SIM will use a 10 m Michelson stellar interferometer to provide 4 microarcsecond precision absolute position measurements of stars down to 20th magnitude over its 5 yr. mission lifetime. SIM will also provide technology demonstrations of synthesis imaging and interferometric nulling. This paper describes the what, why and how of the SIM mission, including an overall mission and system description, science objectives, general description of how SIM makes its measurements, description of the design concepts now under consideration, operations concept, and supporting technology program.

  19. Planning and Implementation of Pressure and Humidity Measurements on ExoMars 2016 Schiaparelli Lander

    NASA Astrophysics Data System (ADS)

    Nikkanen, T.; Schmidt, W.; Genzer, M.; Komu, M.; Kemppinen, O.; Haukka, H.; Harri, A.-M.

    2014-04-01

    The ExoMars 2016 Schiaparelli lander offers a platform for meteorological and electric field observations ranging from timescales of seconds to Martian days, or sols. In the Finnish Meteorological Institute (FMI), this opportunity has been used to develop a new type of instrument controller unit for the already flight-proven FMI pressure and humidity instruments. The new controller allows for more flexible and autonomous data acquisition processes and planning than the previous FMI designs.

  20. Extended duration lunar lander

    NASA Technical Reports Server (NTRS)

    Babic, Nikola; Carter, Matt; Cosper, Donna; Garza, David; Gonzalez, Eloy; Goodine, David; Hirst, Edward; Li, Ray; Lindsey, Martin; Ng, Tony

    1993-01-01

    Selenium Technologies has been conducting preliminary design work on a manned lunar lander for use in NASA's First Lunar Outpost (FLO) program. The resulting lander is designed to carry a crew of four astronauts to a prepositioned habitat on the lunar surface, remain on the lunar surface for up to 45 days while the crew is living in the habitat, then return the crew to earth via direct reentry and land recovery. Should the need arise, the crew can manually guide the lander to a safe lunar landing site, and live in the lander for up to ten days on the surface. Also, an abort to earth is available during any segment of the mission. The main propulsion system consists of a cluster of four modified Pratt and Whitney RL10 rocket engines that use liquid methane (LCH4) and liquid oxygen (LOX). Four engines are used to provide redundancy and a satisfactory engine out capability. Differences between the new propulsion system and the original system include slightly smaller engine size and lower thrust per engine, although specific impulse remains the same despite the smaller size. Concerns over nozzle ground clearance and engine reliability, as well as more information from Pratt and Whitney, brought about this change. The power system consists of a combination of regenerative fuel cells and solar arrays. While the lander is in flight to or from the moon, or during the lunar night, fuel cells provide all electrical power. During the lunar day, solar arrays are deployed to provide electrical power for the lander as well as electrolyzers, which separate some water back into hydrogen and oxygen for later use by the fuel cells. Total storage requirements for oxygen, hydrogen, and water are 61 kg, 551 kg, and 360 kg, respectively. The lander is a stage-and-a-half design with descent propellant, cargo, and landing gear contained in the descent stage, and the main propulsion system, ascent propellant, and crew module contained in the ascent stage. The primary structure for both

  1. Exploring Triton with Multiple Landers

    NASA Astrophysics Data System (ADS)

    Balint, T. S.

    In our pathway for Outer Planetary Exploration several mission concepts were considered, based on the proposed Jupiter Icy Moons Orbiter (JIMO) mission architecture. This paper describes a JIMO follow-on mission concept to Neptune's largest moon. Triton is a target of interest for outer solar system studies. It has a highly inclined retrograde orbit, suggesting that it may have been a Kuiper Belt object, captured by Neptune. Given this assumption, its composition, which may include organic materials, would be of significant scientific interest. The present concept considers a surface mission architecture with two landers, each powered by a standard multi-mission radioisotope thermoelectric generator (MMRTG). The landers would operate on the surface for several years providing science data, thus expanding our understanding of the environment, the dynamic surface and atmospheric processes, and some of the seasonal variations. A JIMO class orbiter would provide telecommunication link between the landers and Earth, and would be instrumented to observe both Triton and Neptune. In this paper all key aspects of the mission architecture are addressed, including the science instruments, the main subsystems, trade options for the power system, and a conceptual design for the landers.

  2. Airbursts as a viable source of seismic and acoustic energy for the 2016 InSight geophysical lander mission to Mars: analysis using terrestrial analogues

    NASA Astrophysics Data System (ADS)

    Taylor, Jennifer; Wookey, James; Teanby, Nick

    2014-05-01

    The explosion of a bolide as a terminal airburst, before impact into a planetary surface, is a well-documented source of both seismic and acoustic energy[1]. Here we aim to define some diagnostic properties of a recorded airburst time-series and determine detectability criteria for such events for a single station seismo-acoustic station on the Martian surface. In 2016 NASA will launch the InSight geophysical monitoring system. This lander will carry in its SEIS payload two 3-component seismic instruments - the Short Period (SP) and Very Broadband (VBB) seismometers, as well as a micro-barometer for measurement of atmospheric pressure fluctuations. The SEIS and MB packages aboard InSight could potentially be used together for seismo-acoustic detection of impact or airburst events. In past studies, this technique has been used to analyse and model the Washington State Bolide[2] and, more recently, the Chelyabinsk fireball in 2013[3]. Using a multi-station array, it is possible to estimate total kinetic energy of a bolide, its line-of-sight direction and the approximate time of its terminal burst[4]. However, with only a single station, as would be the case on Mars, more creative methods must be employed to extract information from the event. We explore the diagnostic waveform properties of an airburst, including various arrivals from the event. We also show how dominant frequency changes with distance from the event, altitude and yield. Several terrestrial events are analysed, including the 2013 Chelyabinsk fireball. We present theoretical calculations of the likely proportion of bolide terminal bursts on Mars relative to impacts, based on differences in the structure and composition of the Martian atmosphere. We go on to predict the seismic arrivals that may be observed by InSight from the coupling of the acoustic blast into the Martian crust. It is hoped that these diagnostic tools will be useful to identify and quantify bolide terminal bursts on Mars over the

  3. The Lunar Prospector Discovery mission: Mission and measurement description

    SciTech Connect

    Hubbard, G.S.; Binder, A.B.; Feldman, W.

    1998-06-01

    Lunar Prospector, the first competitively selected planetary mission in NASA`s Discovery Program, is described with emphasis on the radiation spectrometer instrumentation and anticipated scientific data return. Scheduled to be launched in January 1998, the mission will conduct a one year orbital survey of the Moon`s composition and structure. The suite of five instruments are outlined: neutron spectrometer, alpha particle spectrometer, gamma-ray spectrometer, electron reflectometer and magnetometer. Scientific requirements and measurement approach to detect water/ice to a sensitivity of 50 ppm (hydrogen), measure key elemental constituents, detect radioactive gas release events and accurately map the Moon`s gravitational and magnetic fields are given. A brief overview of the programmatic accomplishments in meeting a tightly constrained schedule and budget is also provided.

  4. The Phoenix Mars Lander Robotic Arm

    NASA Technical Reports Server (NTRS)

    Bonitz, Robert; Shiraishi, Lori; Robinson, Matthew; Carsten, Joseph; Volpe, Richard; Trebi-Ollennu, Ashitey; Arvidson, Raymond E.; Chu, P. C.; Wilson, J. J.; Davis, K. R.

    2009-01-01

    The Phoenix Mars Lander Robotic Arm (RA) has operated for over 150 sols since the Lander touched down on the north polar region of Mars on May 25, 2008. During its mission it has dug numerous trenches in the Martian regolith, acquired samples of Martian dry and icy soil, and delivered them to the Thermal Evolved Gas Analyzer (TEGA) and the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The RA inserted the Thermal and Electrical Conductivity Probe (TECP) into the Martian regolith and positioned it at various heights above the surface for relative humidity measurements. The RA was used to point the Robotic Arm Camera to take images of the surface, trenches, samples within the scoop, and other objects of scientific interest within its workspace. Data from the RA sensors during trenching, scraping, and trench cave-in experiments have been used to infer mechanical properties of the Martian soil. This paper describes the design and operations of the RA as a critical component of the Phoenix Mars Lander necessary to achieve the scientific goals of the mission.

  5. Robotic Lander Development Project

    NASA Video Gallery

    The Robotic Lander Development Project at the Marshall Center is testing a prototype lander that will aid in the design and development of a new generation of small, smart, versatile robotic lander...

  6. Underneath the Phoenix Lander

    NASA Technical Reports Server (NTRS)

    2008-01-01

    The Robotic Arm Camera on NASA's Phoenix Mars Lander took this image on Oct. 18, 2008, during the 142nd Martian day, or sol, since landing. The flat patch in the center of the image has the informal name 'Holy Cow,' based on researchers' reaction when they saw the initial image of it only a few days after the May 25, 2008 landing. Researchers first saw this flat patch in an image taken by the Robotic Arm Camera on May 30, the fifth Martian day of the mission.

    The Phoenix mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

  7. Rosetta: Comet-Chaser, Comet-Lander, and Comet-Hopper All In One Mission! (Presentation Recording)

    NASA Astrophysics Data System (ADS)

    Chmielewski, Artur B.

    2015-09-01

    Mission to Catch a Comet! Comets have inspired awe and wonder since the dawn of history. Many scientists today believe that comets crashed into Earth in its formative period spewing organic molecules that were crucial to the growth of life. Comets may have formed about the same time as the giant planets of our solar system (Jupiter, Saturn, Uranus, and Neptune) - about 4.6 billion years ago. Some scientists think that comets and planets were both made from the same clumps of dust and ice that spewed from our Sun's birth; others think that these roving time capsules are even older than that, and that they may contain grains of interstellar stuff that is even older than our solar system.

  8. On the possibility of lunar core phase detection using new seismometers for soft-landers in future lunar missions

    NASA Astrophysics Data System (ADS)

    Yamada, Ryuhei; Garcia, Raphael F.; Lognonné, Philippe; Kobayashi, Naoki; Takeuchi, Nozomu; Nébut, Tanguy; Shiraishi, Hiroaki; Calvet, Marie; Ganepain-Beyneix, J.

    2013-06-01

    Information on the lunar central core; size, current state and composition; are key parameters to understand the origin and evolution of the Moon. Recent studies have indicated that possible seismic energies of core-reflected phases can be identified from past Apollo seismic data, and core sizes are determined, but we have still uncertainties to establish the lunar core parameters. We, therefore, plan to detect seismic phases that pass through the interior of the core and/or those reflected from the core-mantle boundary to ensure the parameters using new seismometers for future lunar soft-landing missions such as SELENE-2 and Farside Explorer projects. As the new seismometers, we can apply two types of sensors already developed; they are the Very Broad Band (VBB) seismometer and Short Period (SP) seismometer. We first demonstrate through waveform simulations that the new seismometers are able to record the lunar seismic events with S/N much better than Apollo seismometers. Then, expected detection numbers of core-phases on the entire lunar surface for the two types of seismometers are evaluated for two models of seismic moment distributions of deep moonquakes using the recent interior model (VPREMOON). The evaluation indicates that the VBB has performance to detect reflected S phases (ScS) from the core-mantle boundary mainly on the lunar near-side, and the P phases (PKP) passing through the interior of the core on some areas of the lunar far-side. Then, the SP can also detect PKP phases as first arrival seismic phase on limited regions on the lunar far-side. If appropriate positions of the seismic stations are selected, core-phases can be detected, allowing us to constrain the origin and evolution of the Moon with future lunar soft-landing missions.

  9. Viking Lander 2 Anniversary

    NASA Technical Reports Server (NTRS)

    2002-01-01

    [figure removed for brevity, see original site]

    This portion of a daytime IR image covers the Viking 2 landing site (shown with the X). The second landing on Mars took place September 3, 1976 in Utopia Planitia. The exact location of Lander 2 is not as well established as Lander 1 because there were no clearly identifiable features in the lander images as there were for the site of Lander 1. The Utopia landing site region contains pedestal craters, shallow swales and gentle ridges. The crater Goldstone was named in honor of the Tracking Station in the desert of California. The two Viking Landers operated for over 6 years (nearly four martian years) after landing. This one band IR (band 9 at 12.6 microns) image shows bright and dark textures, which are primarily due to differences in the abundance of rocks on the surface. The relatively cool (dark) regions during the day are rocky or indurated materials, fine sand and dust are warmer (bright). Many of the temperature variations are due to slope effects, with sun-facing slopes warmer than shaded slopes. The dark rings around several of the craters are due to the presence of rocky (cool) material ejected from the crater. These rocks are well below the resolution of any existing Mars camera, but THEMIS can detect the temperature variations they produce. Daytime temperature variations are produced by a combination of topographic (solar heating) and thermophysical (thermal inertia and albedo) effects. Due to topographic heating the surface morphologies seen in THEMIS daytime IR images are similar to those seen in previous imagery and MOLA topography.

    Note: this THEMIS visual image has not been radiometrically nor geometrically calibrated for this preliminary release. An empirical correction has been performed to remove instrumental effects. A linear shift has been applied in the cross-track and down-track direction to approximate spacecraft and planetary motion. Fully calibrated and geometrically projected

  10. Tropical Rainfall Measurement Mission (TRMM) Operation Summary

    NASA Technical Reports Server (NTRS)

    Nio, Tomomi; Saito, Susumu; Stocker, Erich; Pawloski, James H.; Murayama, Yoshifumi; Ohata, Takeshi

    2015-01-01

    The Tropical Rainfall Measurement Mission (TRMM) is a joint U.S. and Japan mission to observe tropical rainfall, which was launched by H-II No. 6 from Tanegashima in Japan at 6:27 JST on November 28, 1997. After the two-month commissioning of TRMM satellite and instruments, the original nominal mission lifetime was three years. In fact, the operations has continued for approximately 17.5 years. This paper provides a summary of the long term operations of TRMM.

  11. Global Precipitation Measurement (GPM) Mission Development Status

    NASA Technical Reports Server (NTRS)

    Azarbarzin, Ardeshir Art

    2011-01-01

    Mission Objective: (1) Improve scientific understanding of the global water cycle and fresh water availability (2) Improve the accuracy of precipitation forecasts (3) Provide frequent and complete sampling of the Earth s precipitation Mission Description (Class B, Category I): (1) Constellation of spacecraft provide global precipitation measurement coverage (2) NASA/JAXA Core spacecraft: Provides a microwave radiometer (GMI) and dual-frequency precipitation radar (DPR) to cross-calibrate entire constellation (3) 65 deg inclination, 400 km altitude (4) Launch July 2013 on HII-A (5) 3 year mission (5 year propellant) (6) Partner constellation spacecraft.

  12. Phoenix Lander on Mars

    NASA Technical Reports Server (NTRS)

    2007-01-01

    NASA's Phoenix Mars Lander monitors the atmosphere overhead and reaches out to the soil below in this artist's depiction of the spacecraft fully deployed on the surface of Mars.

    Phoenix has been assembled and tested for launch in August 2007 from Cape Canaveral Air Force Station, Fla., and for landing in May or June 2008 on an arctic plain of far-northern Mars. The mission responds to evidence returned from NASA's Mars Odyssey orbiter in 2002 indicating that most high-latitude areas on Mars have frozen water mixed with soil within arm's reach of the surface.

    Phoenix will use a robotic arm to dig down to the expected icy layer. It will analyze scooped-up samples of the soil and ice for factors that will help scientists evaluate whether the subsurface environment at the site ever was, or may still be, a favorable habitat for microbial life. The instruments on Phoenix will also gather information to advance understanding about the history of the water in the icy layer. A weather station on the lander will conduct the first study Martian arctic weather from ground level.

    The vertical green line in this illustration shows how the weather station on Phoenix will use a laser beam from a lidar instrument to monitor dust and clouds in the atmosphere. The dark 'wings' to either side of the lander's main body are solar panels for providing electric power.

    The Phoenix mission is led by Principal Investigator Peter H. Smith of the University of Arizona, Tucson, with project management at NASA's Jet Propulsion Laboratory and development partnership with Lockheed Martin Space Systems, Denver. International contributions for Phoenix are provided by the Canadian Space Agency, the University of Neuchatel (Switzerland), the University of Copenhagen (Denmark), the Max Planck Institute (Germany) and the Finnish Meteorological institute. JPL is a division of the California Institute of Technology in Pasadena.

  13. Viking Lander Atlas of Mars

    NASA Technical Reports Server (NTRS)

    Liebes, S., Jr.

    1982-01-01

    Half size reproductions are presented of the extensive set of systematic map products generated for the two Mars Viking landing sites from stereo pairs of images radioed back to Earth. The maps span from the immediate foreground to the remote limits of ranging capability, several hundred meters from the spacecraft. The maps are of two kinds - elevation contour and vertical profile. Background and explanatory material important for understanding and utilizing the map collection included covers the Viking Mission, lander locations, lander cameras, the stereo mapping system and input images to this system.

  14. Common Lunar Lander (CLL) Engineering Study Results

    NASA Technical Reports Server (NTRS)

    Stecklein, Jonette

    1991-01-01

    Information is given in viewgraph form on the Common Lunar Lander (CLL) engineering study results. The mission is to provide a delivery system to soft-land a 200 kg payload set at any given lunar latitude and longitude. Topics covered include the study schedule, mission goals and requirements, the CLL reference mission, costs, CLL options, and two stage performance analysis.

  15. Active Collision Avoidance for Planetary Landers

    NASA Technical Reports Server (NTRS)

    Rickman, Doug; Hannan, Mike; Srinivasan, Karthik

    2014-01-01

    Present day robotic missions to other planets require precise, a priori knowledge of the terrain to pre-determine a landing spot that is safe. Landing sites can be miles from the mission objective, or, mission objectives may be tailored to suit landing sites. Future robotic exploration missions should be capable of autonomously identifying a safe landing target within a specified target area selected by mission requirements. Such autonomous landing sites must (1) 'see' the surface, (2) identify a target, and (3) land the vehicle. Recent advances in radar technology have resulted in small, lightweight, low power radars that are used for collision avoidance and cruise control systems in automobiles. Such radar systems can be adapted for use as active hazard avoidance systems for planetary landers. The focus of this CIF proposal is to leverage earlier work on collision avoidance systems for MSFC's Mighty Eagle lander and evaluate the use of automotive radar systems for collision avoidance in planetary landers.

  16. Robotic Lunar Landers for Science and Exploration

    NASA Technical Reports Server (NTRS)

    Chavers, D. G.; Cohen, B. A.; Bassler, J. A.; Hammond, M. S.; Harris, D. W.; Hill, L. A.; Eng, D.; Ballard, B. W.; Kubota, S. D.; Morse, B. J.; Mulac, B. D.; Holloway, T. A.; Reed, C. L. B.

    2010-01-01

    NASA Marshall Space Flight Center (MSFC) and The Johns Hopkins University Applied Physics Laboratory (APL) have been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. This paper describes some of the lunar lander concepts derived from these studies conducted by the MSFC/APL Robotic Lunar Lander Development Project team. In addition, the results to date of the lunar lander development risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing and combined GN&C and avionics testing will be addressed. The most visible elements of the risk reduction program are two autonomous lander flight test vehicles: a compressed air system with limited flight durations and a second version using hydrogen peroxide propellant to achieve significantly longer flight times and the ability to more fully exercise flight sensors and algorithms.

  17. Resource Prospector Lander: Architecture and Trade Studies

    NASA Technical Reports Server (NTRS)

    Moore, Josh; Calvert, Derek; Frady, Greg; Chavers, Greg; Wayne, Andrew; Hull, Patrick; Lowery, Eric; Farmer, Jeff; Trinh, Huu; Rojdev, Kristina; Piatek, Irene; Ess, Kim; Vitalpur, Sharada; Dunn, Kevin

    2014-01-01

    NASA's Resource Prospector (RP) is a multi-center and multi-institution collaborative project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and is approximately 10 days. The RP vehicle comprises three elements: the Lander, the Rover, and the Payload. The Payload is housed on the Rover and the Rover is on top of the Lander. The focus of this paper is on the Lander element for the RP vehicle. The design of the Lander was requirements driven and focused on a low-cost approach. To arrive at the final configuration, several trade studies were conducted. Of those trade studies, there were six primary trade studies that were instrumental in determining the final design. This paper will discuss each of these trades in further detail and show how these trades led to the final architecture of the RP Lander.

  18. Robotic Lunar Lander Development Status

    NASA Technical Reports Server (NTRS)

    Ballard, Benjamin; Cohen, Barbara A.; McGee, Timothy; Reed, Cheryl

    2012-01-01

    NASA Marshall Space Flight Center and John Hopkins University Applied Physics Laboratory have developed several mission concepts to place scientific and exploration payloads ranging from 10 kg to more than 200 kg on the surface of the moon. The mission concepts all use a small versatile lander that is capable of precision landing. The results to date of the lunar lander development risk reduction activities including high pressure propulsion system testing, structure and mechanism development and testing, and long cycle time battery testing will be addressed. The most visible elements of the risk reduction program are two fully autonomous lander flight test vehicles. The first utilized a high pressure cold gas system (Cold Gas Test Article) with limited flight durations while the subsequent test vehicle, known as the Warm Gas Test Article, utilizes hydrogen peroxide propellant resulting in significantly longer flight times and the ability to more fully exercise flight sensors and algorithms. The development of the Warm Gas Test Article is a system demonstration and was designed with similarity to an actual lunar lander including energy absorbing landing legs, pulsing thrusters, and flight-like software implementation. A set of outdoor flight tests to demonstrate the initial objectives of the WGTA program was completed in Nov. 2011, and will be discussed.

  19. Lunar Polar Coring Lander

    NASA Technical Reports Server (NTRS)

    Angell, David; Bealmear, David; Benarroche, Patrice; Henry, Alan; Hudson, Raymond; Rivellini, Tommaso; Tolmachoff, Alex

    1990-01-01

    Plans to build a lunar base are presently being studied with a number of considerations. One of the most important considerations is qualifying the presence of water on the Moon. The existence of water on the Moon implies that future lunar settlements may be able to use this resource to produce things such as drinking water and rocket fuel. Due to the very high cost of transporting these materials to the Moon, in situ production could save billions of dollars in operating costs of the lunar base. Scientists have suggested that the polar regions of the Moon may contain some amounts of water ice in the regolith. Six possible mission scenarios are suggested which would allow lunar polar soil samples to be collected for analysis. The options presented are: remote sensing satellite, two unmanned robotic lunar coring missions (one is a sample return and one is a data return only), two combined manned and robotic polar coring missions, and one fully manned core retrieval mission. One of the combined manned and robotic missions has been singled out for detailed analysis. This mission proposes sending at least three unmanned robotic landers to the lunar pole to take core samples as deep as 15 meters. Upon successful completion of the coring operations, a manned mission would be sent to retrieve the samples and perform extensive experiments of the polar region. Man's first step in returning to the Moon is recommended to investigate the issue of lunar polar water. The potential benefits of lunar water more than warrant sending either astronauts, robots or both to the Moon before any permanent facility is constructed.

  20. Robotic Lunar Landers for Science and Exploration

    NASA Technical Reports Server (NTRS)

    Cohen, B. A.; Hill, L. A.; Bassler, J. A.; Chavers, D. G.; Hammond, M. S.; Harris, D. W.; Kirby, K. W.; Morse, B. J.; Mulac, B. D.; Reed, C. L. B.

    2010-01-01

    NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory has been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. In 2005, the Robotic Lunar Exploration Program Mission #2 (RLEP-2) was selected as a Exploration Systems Mission Directorate precursor robotic lunar lander mission to demonstrate precision landing and definitively determine if there was water ice at the lunar poles; however, this project was canceled. Since 2008, the team has been supporting NASA s Science Mission Directorate designing small lunar robotic landers for diverse science missions. The primary emphasis has been to establish anchor nodes of the International Lunar Network (ILN), a network of lunar science stations envisioned to be emplaced by multiple nations. This network would consist of multiple landers carrying instruments to address the geophysical characteristics and evolution of the moon. Additional mission studies have been conducted to support other objectives of the lunar science community and extensive risk reduction design and testing has been performed to advance the design of the lander system and reduce development risk for flight projects. This paper describes the current status of the robotic lunar mission studies that have been conducted by the MSFC/APL Robotic Lunar Lander Development team, including the ILN Anchor Nodes mission. In addition, the results to date of the lunar lander development risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing and combined GN&C and avionics testing will be addressed. The most visible elements of the risk reduction program are two autonomous lander test articles: a compressed air system with limited flight durations and a second version using hydrogen peroxide propellant to achieve significantly longer flight times and the ability to

  1. Robotic Lander Prototype

    NASA Video Gallery

    NASA engineers successfully integrated and completed system testing on a new robotic lander recently at Teledyne Brown Engineering’s facility in Huntsville in support of the Robotic Lunar Lander ...

  2. Robotic Lunar Landers for Science and Exploration

    NASA Technical Reports Server (NTRS)

    Cohen, B. A.; Bassler, J. A.; Hammond, M. S.; Harris, D. W.; Hill, L. A.; Kirby, K. W.; Morse, B. J.; Mulac, B. D.; Reed, C. L. B.

    2010-01-01

    The Moon provides an important window into the early history of the Earth, containing information about planetary composition, magmatic evolution, surface bombardment, and exposure to the space environment. Robotic lunar landers to achieve science goals and to provide precursor technology development and site characterization are an important part of program balance within NASA s Science Mission Directorate (SMD) and Exploration Systems Mission Directorate (ESMD). A Robotic Lunar Lan-der mission complements SMD's initiatives to build a robust lunar science community through R&A lines and increases international participation in NASA's robotic exploration of the Moon.

  3. First Results of Plasma And Magnetic Field Measurements Onboard The Rosetta Lander Philae at The Surface of Comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    Auster, H. U.; Apathy, I. N.; Remizov, A.; Berghofer, G.; Hilchenbach, M.; Haerendel, G.; Heinisch, P.; Richter, I.; Glassmeier, K. H.

    2014-12-01

    The ROMAP (Rosetta Lander Magnetometer and Plasma Monitor) suite of sensors onboard the Rosetta lander Philae consists of a fluxgate magnetometer and plasma ion and electron sensors. ROMAP will measure for the first time the magnetic field as well as electron and ion distributions on a cometary surface.
 First magnetic field measurements during the Philae descent and plasma investigations during the first science sequence on the cometary surfce will be presented together with concurrent magnetic field measurements of the Rosetta orbiter. Furthermore, we shall discuss the measurement operation strategy for the long term sequence, for observing the evolution of the plasma environment by measurements with both plasma packages, ROMAP on the surface and RPC onboard the Rosetta Orbiter.

  4. Entry System Design Considerations for Mars Landers

    NASA Technical Reports Server (NTRS)

    Lockwood, Mary Kae; Powell, Richard W.; Graves, Claude A.; Carman, Gilbert L.

    2001-01-01

    The objective for the next generation or Mars landers is to enable a safe landing at specific locations of scientific interest. The 1st generation entry, descent and landing systems, ex. Viking and Pathfinder, provided successful landing on Mars but by design were limited to large scale, 100s of km, landing sites with minimal local hazards. The 2 nd generation landers, or smart landers, will provide scientists with access to previously unachievable landing sites by providing precision landing to less than 10 km of a target landing site, with the ability to perform local hazard avoidance, and provide hazard tolerance. This 2nd generation EDL system can be utilized for a range of robotic missions with vehicles sized for science payloads from the small 25-70 kg, Viking, Pathfinder, Mars Polar Lander and Mars Exploration Rover-class, to the large robotic Mars Sample Return, 300 kg plus, science payloads. The 2nd generation system can also be extended to a 3nd generation EDL system with pinpoint landing, 10's of meters of landing accuracy, for more capable robotic or human missions. This paper will describe the design considerations for 2nd generation landers. These landers are currently being developed by a consortium of NASA centers, government agencies, industry and academic institutions. The extension of this system and additional considerations required for a 3nd generation human mission to Mars will be described.

  5. Global Precipitation Measurement Mission Launch and Commissioning

    NASA Technical Reports Server (NTRS)

    Davis, Nikesha; Deweese, Keith; Vess, Missie; Welter, Gary; O'Donnell, James R., Jr.

    2015-01-01

    During launch and early operation of the Global Precipitation Measurement (GPM) Mission, the Guidance, Navigation and Control (GNC) analysis team encountered four main on orbit anomalies. These include: (1) unexpected shock from Solar Array deployment, (2) momentum buildup from the Magnetic Torquer Bars (MTBs) phasing errors, (3) transition into Safehold due to albedo-induced Course Sun Sensor (CSS) anomaly, and (4) a flight software error that could cause a Safehold transition due to a Star Tracker occultation. This paper will discuss ways GNC engineers identified and tracked down the root causes. Flight data and GNC on board models will be shown to illustrate how each of these anomalies were investigated and mitigated before causing any harm to the spacecraft. On May 29, 2014, GPM was handed over to the Mission Flight Operations Team after a successful commissioning period. Currently, GPM is operating nominally on orbit, collecting meaningful scientific data that will significantly improve our understanding of the Earth's climate and water cycle.

  6. Measuring the Permittivity of the Nucleus of a Comet: the PP-SESAME Experiment on Board the Philae/ROSETTA Lander

    NASA Astrophysics Data System (ADS)

    Lethuillier, A.; Le Gall, A. A.; Hamelin, M.; Ciarletti, V.; Caujolle-Bert, S.; Schmidt, W.; Grard, R.; Seidensticker, K. J.; Fischer, H. H.

    2015-12-01

    The Permittivity Probe (SESAME-PP) on-board the Philae Lander of the ROSETTA mission was designed to constrain the complex permittivity of the first 2 m of the nucleus of comet 67P/Churyumov-Gerasimenko and to monitor its variations with time. Doing so, it is meant to provide a unique insight into the composition of the comet, and in particular, into its water content. PP-SESAME acquired data on November 13, 2015, both during Philae descent to the comet and at the surface of the nucleus. The PP-SESAME instrument is derived from the quadrupole array technique. A sinusoidal electrical current is sent into the ground through a transmitting dipole, and the induced electrical voltage on a receiving dipole is measured. The complex permittivity of the material is inferred from the mutual impedance derived from the measurements. In practice, the influence of both the electronic circuit of the instrument and the conducting elements in its close environment must be accounted for in order to best estimate both the dielectric constant and electrical conductivity of the ground. For that purpose, we have developed a method called the "capacity-influence matrix method". A replica of the instrument was recently built in LATMOS (France) in order to validate this method. In this paper, we will present the tests conducted with the replica in a controlled environment and their comparison to numerical simulations. We will also show simulations relevant to the PP-SESAME experiment on the nucleus of comet 67P/Churyumov-Gerasimenko. These simulations were run for realistic scenarios of the Philae's attitude and environment at its final landing site. We discuss their implications in terms of surface electrical and compositional properties.

  7. NASA'S Robotic Lunar Lander Development Project

    NASA Astrophysics Data System (ADS)

    Cohen, Barbara A.; Chavers, D. Gregory; Ballard, Benjamin W.

    2012-10-01

    Over the last 5 years, NASA has invested in development and risk-reduction activities for a new generation of planetary landers capable of carrying instruments and technology demonstrations to the lunar surface and other airless bodies. The Robotic Lunar Lander Development Project (RLLDP) is jointly implemented by NASA Marshall Space Flight Center (MSFC) and the Johns Hopkins University Applied Physics Laboratory (APL). The RLLDP team has produced mission architecture designs for multiple airless body missions to meet both science and human precursor mission needs. The mission architecture concept studies encompass small, medium, and large landers, with payloads from a few tens of kilograms to over 1000 kg, to the Moon and other airless bodies. To mature these concepts, the project has made significant investments in technology risk reduction in focused subsystems. In addition, many lander technologies and algorithms have been tested and demonstrated in an integrated systems environment using free-flying test articles. These design and testing investments have significantly reduced development risk for airless body landers, thereby reducing overall risk and associated costs for future missions.

  8. Mars Relay Lander and Orbiter Overflight Profile Estimation

    NASA Technical Reports Server (NTRS)

    Wallick, Michael N.; Allard, Daniel A.; Gladden, Roy E.; Peterson, Corey L.

    2012-01-01

    This software allows science and mission operations to view graphs of geometric overflights of satellites and landers within the Mars (or other planetary) networks. It improves on the MaROS Web interface within any modern Web browser, in that it adds new capabilities to the MaROS suite. The profile for an overflight is an important element for selecting communication/ overflight opportunities between the landers and orbiters within the Mars network. Unfortunately, determining these estimates is very computationally expensive and difficult to compute by hand. This software allows the user to select different overflights (via the existing MaROS Web interface) and specify the smoothness of the estimation. Estimates for the geometric relationship between a lander and an orbiter are determined based upon the orbital conditions of the orbiter at the moment the orbiter rises above the horizon from the perspective of the lander. It utilizes 2-body orbital equations to propagate the trajectory through the duration of the view period, and returns profiles that represent the range between the two vehicles, and the elevation and azimuth angles of the orbiter as measured from the lander s position. The algorithms assume a 2-body relationship with an ideal, spherical planetary body, so therefore can see errors less than 2% at polar landing sites on Mars. These algorithms are being implemented to provide rough estimates rapidly for the geometry of a geometric view period where more complete data is unavailable, such as for planning purposes. While other software for this task exists, each at the time of this reporting has been contained within a much more complicated package. This tool allows science and mission operations to view the estimates with a few clicks of the mouse.

  9. The Tropical Rainfall Measuring Mission (TRMM)

    NASA Technical Reports Server (NTRS)

    Theon, John S.

    1994-01-01

    The Tropical Rainfall Measuring Mission (TRMM) is a cooperative effort between National Space Development Agency (NASDA) of Japan and NASA of the USA. TRMM is designed to measure rain rates from space using a combination of high resolution radar, passive microwave radiometer and visible-infrared radiometer measurements from a spacecraft in a rapid precession, 350 km orbit inclined at 35 deg. These measurements, averaged over a 500 km grid for a month, are expected to provide monthly mean rainfall to an accuracy of 10 to 15 percent. TRMM will also make it possible to analyze the diurnal component of the rainfall and to derive the vertical distribution of latent heating. An accurate measure of the oceanic rainfall distribution will provide unprecedented insight into the halocline distribution and the stability of the oceanic surface layers. A status of the program is presented.

  10. The Philae Lander: Science planning and operations

    NASA Astrophysics Data System (ADS)

    Moussi, Aurélie; Fronton, Jean-François; Gaudon, Philippe; Delmas, Cédric; Lafaille, Vivian; Jurado, Eric; Durand, Joelle; Hallouard, Dominique; Mangeret, Maryse; Charpentier, Antoine; Ulamec, Stephan; Fantinati, Cinzia; Geurts, Koen; Salatti, Mario; Bibring, Jean-Pierre; Boehnhardt, Hermann

    2016-08-01

    Rosetta is an ambitious mission launched in March 2004 to study comet 67P/Churyumov-Gerasimenko. It is composed of a space probe (Rosetta) and the Philae Lander. The mission is a series of premieres: among others, first probe to escort a comet, first time a landing site is selected with short turnaround time, first time a lander has landed on a comet nucleus. In November 2014, once stabilized on the comet, Philae has performed its "First Science Sequence". Philae's aim was to perform detailed and innovative in-situ experiments on the comet's surface to characterize the nucleus by performing mechanical, chemical and physical investigations on the comet surface. The main contribution to the Rosetta lander by the French space agency (CNES) is the Science Operation and Navigation Center (SONC) located in Toulouse. Among its tasks is the scheduling of the scientific activities of the 10 lander experiments and then to provide it to the Lander Control Center (LCC) located in DLR Cologne. The teams in charge of the Philae activity scheduling had to cope with considerable constraints in term of energy, data management, asynchronous processes and co-activities or exclusions between instruments. Moreover the comet itself, its environment and the landing conditions remained unknown until separation time. The landing site was selected once the operational sequence was already designed. This paper will explain the specific context of the Rosetta lander mission and all the constraints that the lander activity scheduling had to face to fulfill the scientific objectives specified for Philae. A specific tool was developed by CNES and used to design the complete sequence of activities on the comet with respect to all constraints. The baseline scenario for the lander operation will also be detailed as well as the sequence performed on the comet to highlight the difficulties and challenges that the operational team faced.

  11. Development of An Instrumented, Modular "mole" For In-situ Subsurface Measurements On Planetary Missions

    NASA Astrophysics Data System (ADS)

    Richter, L.; Kochan, H.; Michaelis, H.; Möhlmann, D.; Neuhaus, D.; Popp, J.; Spohn, T.; Stuffler, T.; Tokano, T.; Wernecke, R.

    On the Beagle 2 lander of ESA's Mars Express mission in 2003, a small mechanical "Mole" on a tether will be used to achieve percussive penetration into the Martian regolith to a maximum depth of some 1E1.5 m with the main objective of acquiring subsurface soil samples for analysis on the lander. For future planetary missions it is proposed to develop this concept further in order to accommodate a number of instru- ment sensor heads inside the Mole, enabling different measurements to be performed in the regolith as a function of depth. Such an instrumented, and perhaps even modular, Mole could be utilized to probe the regolith of solar system objects such as Mercury, Mars, the Earth's moon or asteroids. Depending on the mission target, different in- struments to be deployed to the subsurface will be of relevance. Candidates include thermal sensors, volatile detection sensors (including water vapor and adsorbed water for Mars applications), a multispectral imaging sensor head (soil texture and spectral reflectance) and a Raman spectrometer optical head (detailed soil mineralogy). Based on applications on various space missions, most of these instruments are already under development and will be small enough that at least their front ends can be accommo- dated inside a compact cylindrical Mole having an expected internal diameter between 20E35 mm. A particular design challenge is going to be the internal electronics and the electrical/optical interface required to pre-process sensor data and transmit them to the lander above the surface. To minimize the overall mass and length of the instrumented Mole, internal electronics should serve common functions among the accommodated instruments. Another area to be closely studied is temperature rise of the Mole due to its internal dissipation while in the subsurface which could jeopardize thermal mea- surements or could even render internal equipment inoperable. Where the physical integration of sensors is concerned

  12. Dust Storm Moving Near Phoenix Lander

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This series of images show the movement of several dust storms near NASA's Phoenix Mars Lander. These images were taken by the lander's Surface Stereo Imager (SSI) on the 137th Martian day, or sol, of the mission (Oct. 13, 2008).

    These images were taken about 50 seconds apart, showing the formation and movement of dust storms for nearly an hour. Phoenix scientists are still figuring out the exact distances these dust storms occurred from the lander, but they estimate them to be about 1 to 2 kilometers (.6 or 1.2 miles) away.

    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.

  13. Life Support Systems for Lunar Landers

    NASA Technical Reports Server (NTRS)

    Anderson, Molly

    2008-01-01

    Engineers designing life support systems for NASA s next Lunar Landers face unique challenges. As with any vehicle that enables human spaceflight, the needs of the crew drive most of the lander requirements. The lander is also a key element of the architecture NASA will implement in the Constellation program. Many requirements, constraints, or optimization goals will be driven by interfaces with other projects, like the Crew Exploration Vehicle, the Lunar Surface Systems, and the Extravehicular Activity project. Other challenges in the life support system will be driven by the unique location of the vehicle in the environments encountered throughout the mission. This paper examines several topics that may be major design drivers for the lunar lander life support system. There are several functional requirements for the lander that may be different from previous vehicles or programs and recent experience. Some of the requirements or design drivers will change depending on the overall Lander configuration. While the configuration for a lander design is not fixed, designers can examine how these issues would impact their design and be prepared for the quick design iterations required to optimize a spacecraft.

  14. The Tropical Rainfall Measuring Mission (TRMM)

    NASA Technical Reports Server (NTRS)

    Simpson, Joanne; Kummerow, Christian D.; Meneghini, Robert; Hou, Arthur; Adler, Robert F.; Huffman, George; Barkstrom, Bruce; Wielicki, Bruce; Goodman, Steven J.; Christian, Hugh; Einaudi, Franco (Technical Monitor)

    1999-01-01

    Recognizing the importance of rain in the tropics and the accompanying latent heat release, NASA for the U.S. and NASDA for Japan have partnered in the design, construction and flight of an Earth Probe satellite to measure tropical rainfall and calculate the associated heating. Primary mission goals are: 1) the understanding of crucial links in climate variability by the hydrological cycle, 2) improvement in the large-scale models of weather and climate, and 3) improvement in understanding cloud ensembles and their impacts on larger scale circulations. The linkage with the tropical oceans and landmasses are also emphasized. The Tropical Rainfall Measuring Mission (TRMM) satellite was launched in November 1997 with fuel enough to obtain a four to five year data set of rainfall over the global tropics from 37 deg N to 37 deg S. This paper reports progress from launch date through the spring of 1999. The data system and its products and their access is described, as are the algorithms used to obtain the data. Some exciting early results from TRMM are described. Some important algorithm improvements are shown. These will be used in the first total data reprocessing, scheduled to be complete in early 2000. The reader is given information on how to access and use the data.

  15. The Tropical Rainfall Measuring Mission (TRMM)

    NASA Technical Reports Server (NTRS)

    Simpson, Joanne

    1999-01-01

    Recognizing the importance of rain in the tropics and the accompanying latent heat release, NASA for the U.S. and NASDA for Japan have partnered in the design, construction and flight of an Earth Probe satellite to measure tropical rainfall and calculate the associated heating. Primary mission goals are 1) the understanding of crucial links in climate variability by the hydrological cycle, 2) improvement in the large-scale models of weather and climate 3) improvement in understanding cloud ensembles and their impacts on larger scale circulations. The linkage with the tropical oceans and landmasses are also emphasized. The Tropical Rainfall Measuring Mission (TRMM) satellite was launched in November 1997 with fuel enough to obtain a four to five year data set of rainfall over the global tropics from 37 N to 37 S. This paper reports progress from launch date through the spring of 1999. The data system and its products and their access is described, as are the algorithms used to obtain the data. Some exciting early results from TRMM are described. Some important algorithm improvements are shown. These will be used in the first total data reprocessing, scheduled to be complete in early 2000. The reader is given information on how to access and use the data.

  16. Descent Assisted Split Habitat Lunar Lander Concept

    NASA Technical Reports Server (NTRS)

    Mazanek, Daniel D.; Goodliff, Kandyce; Cornelius, David M.

    2008-01-01

    The Descent Assisted Split Habitat (DASH) lunar lander concept utilizes a disposable braking stage for descent and a minimally sized pressurized volume for crew transport to and from the lunar surface. The lander can also be configured to perform autonomous cargo missions. Although a braking-stage approach represents a significantly different operational concept compared with a traditional two-stage lander, the DASH lander offers many important benefits. These benefits include improved crew egress/ingress and large-cargo unloading; excellent surface visibility during landing; elimination of the need for deep-throttling descent engines; potentially reduced plume-surface interactions and lower vertical touchdown velocity; and reduced lander gross mass through efficient mass staging and volume segmentation. This paper documents the conceptual study on various aspects of the design, including development of sortie and outpost lander configurations and a mission concept of operations; the initial descent trajectory design; the initial spacecraft sizing estimates and subsystem design; and the identification of technology needs

  17. A First Look at Carbon and Oxygen Stable Isotope Measurements of Martian Atmospheric C02 by the Phoenix Lander

    NASA Technical Reports Server (NTRS)

    Niles, P.B.; Ming, D.W.; Boynton, W.V.; Hamara, D.; Hoffman, J.H.

    2009-01-01

    Precise stable isotope measurements of the CO2 in the martian atmosphere have the potential to provide important constraints for our understanding of the history of volatiles, the carbon cycle, current atmospheric processes, and the degree of water/rock interaction on Mars. The isotopic composition of the martian atmosphere has been measured using a number of different methods (Table 1), however a precise value (<1%) has yet to be achieved. Given the elevated 13C values measured in carbonates in martian meteorites it has been supposed that the martian atmosphere was enriched in delta(sup 13)C. This was supported by measurements of trapped CO2 gas in EETA 79001[2] which showed elevated delta(sup 13)C values (Table 1). More recently, Earth-based spectroscopic measurements of the martian atmosphere have measured the martian CO2 to be depleted in delta(sup 13)C relative to CO2 in the terrestrial atmosphere. The spectroscopic measurements performed by Krasnopolsky et al. were reported with approx.2% uncertainties which are much smaller than the Viking measurements, but still remain very large in comparison to the magnitude of carbon and oxygen isotope fractionations under martian surface conditions. The Thermal Evolved Gas Analyzer (TEGA) instrument on the Mars Phoenix Lander included a magnetic sector mass spectrometer (EGA) which had the goal of measuring the isotopic composition of martian atmospheric CO2 to within 0.5%. The mass spectrometer is a miniature magnetic sector instrument intended to measure both the martian atmosphere as well as gases evolved from heating martian soils. Ions produced in the ion source are drawn out by a high voltage and focused by a magnetic field onto a set of collector slits. Four specific trajectories are selected to cover the mass ranges, 0.7 - 4, 7 - 35, 14 - 70, and 28 - 140 Da. Using four channels reduces the magnitude of the mass scan and provides simultaneous coverage of the mass ranges. Channel electron multiplier (CEM

  18. ROSETTA lander Philae: Touch-down reconstruction

    NASA Astrophysics Data System (ADS)

    Roll, Reinhard; Witte, Lars

    2016-06-01

    The landing of the ROSETTA-mission lander Philae on November 12th 2014 on Comet 67 P/Churyumov-Gerasimenko was planned as a descent with passive landing and anchoring by harpoons at touch-down. Actually the lander was not fixed at touch-down to the ground due to failing harpoons. The lander internal damper was actuated at touch-down for 42.6 mm with a speed of 0.08 m/s while the lander touch-down speed was 1 m/s. The kinetic energy before touch-down was 50 J, 45 J were dissipated by the lander internal damper and by ground penetration at touch-down, and 5 J kinetic energy are left after touch-down (0.325 m/s speed). Most kinetic energy was dissipated by ground penetration (41 J) while only 4 J are dissipated by the lander internal damper. Based on these data, a value for a constant compressive soil-strength of between 1.55 kPa and 1.8 kPa is calculated. This paper focuses on the reconstruction of the touch-down at Agilkia over a period of around 20 s from first ground contact to lift-off again. After rebound Philae left a strange pattern on ground documented by the OSIRIS Narrow Angle Camera (NAC). The analysis shows, that the touch-down was not just a simple damped reflection on the surface. Instead the lander had repeated contacts with the surface over a period of about 20 s±10 s. This paper discusses scenarios for the reconstruction of the landing sequence based on the data available and on computer simulations. Simulations are performed with a dedicated mechanical multi-body model of the lander, which was validated previously in numerous ground tests. The SIMPACK simulation software was used, including the option to set forces at the feet to the ground. The outgoing velocity vector is mostly influenced by the timing of the ground contact of the different feet. It turns out that ground friction during damping has strong impact on the lander outgoing velocity, on its rotation, and on its nutation. After the end of damping, the attitude of the lander can be

  19. Robotic Lunar Landers For Science And Exploration

    NASA Technical Reports Server (NTRS)

    Cohen, B. A.; Bassler, J. A.; Morse, B. J.; Reed, C. L. B.

    2010-01-01

    NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory have been conducting mission studies and performing risk reduction activities for NASA s robotic lunar lander flight projects. In 2005, the Robotic Lunar Exploration Program Mission #2 (RLEP-2) was selected as an ESMD precursor robotic lander mission to demonstrate precision landing and determine if there was water ice at the lunar poles; however, this project was canceled. Since 2008, the team has been supporting SMD designing small lunar robotic landers for science missions, primarily to establish anchor nodes of the International Lunar Network (ILN), a network of lunar geophysical nodes. Additional mission studies have been conducted to support other objectives of the lunar science community. This paper describes the current status of the MSFC/APL robotic lunar mission studies and risk reduction efforts including high pressure propulsion system testing, structure and mechanism development and testing, long cycle time battery testing, combined GN&C and avionics testing, and two autonomous lander test articles.

  20. Aqueous history of Mars as inferred from landed mission measurements of rocks, soils, and water ice

    NASA Astrophysics Data System (ADS)

    Arvidson, Raymond E.

    2016-09-01

    The missions that have operated on the surface of Mars acquired data that complement observations acquired from orbit and provide information that would not have been acquired without surface measurements. Data from the Viking Landers demonstrated that soils have basaltic compositions, containing minor amounts of salts and one or more strong oxidants. Pathfinder with its rover confirmed that the distal portion of Ares Vallis is the site of flood-deposited boulders. Spirit found evidence for hydrothermal deposits surrounding the Home Plate volcanoclastic feature. Opportunity discovered that the hematite signature on Meridiani Planum as seen from orbit is due to hematitic concretions concentrated on the surface as winds eroded sulfate-rich sandstones that dominate the Burns formation. The sandstones originated as playa muds that were subsequently reworked by wind and rising groundwater. Opportunity also found evidence on the rim of the Noachian Endurance Crater for smectites, with extensive leaching along fractures. Curiosity acquired data at the base of Mount Sharp in Gale Crater that allows reconstruction of a sustained fluvial-deltaic-lacustrine system prograding into the crater. Smectites and low concentrations of chlorinated hydrocarbons have been identified in the lacustrine deposits. Phoenix, landing above the Arctic Circle, found icy soils, along with low concentrations of perchlorate salt. Perchlorate is considered to be a strong candidate for the oxidant found by the Viking Landers. It is also a freezing point depressant and may play a role in allowing brines to exist at and beneath the surface in more modern periods of time on Mars.

  1. The ROSETTA Lander anchoring system

    NASA Astrophysics Data System (ADS)

    Thiel, Markus; Stöcker, Jakob; Rohe, Christian; Kömle, Norbert I.; Kargl, Günter; Hillenmaier, Olaf; Lell, Peter

    2003-09-01

    A major goal of the ESA cornerstone mission ROSETTA is to land a package of scientific instruments known as the ROSETTA Lander on the nucleus of a comet. Due to the low gravity a highly reliable fixation of the ROSETTA Lander to the target comet 67P/Churyumov-Gerasimenko (3rd) is essential. For that purpose a redundant Anchoring System, consisting of two pyrotechnically actuated Anchoring Harpoons and a redundant Control Electronics has been developed, built and qualified at the Max-Planck-Institut für extraterrestrische Physik (MPE), Garching. The pyrotechnical gas generator has been developed jointly by Pyroglobe GmbH and MPE, the procurement of the control electronics has been sub-contracted to Magson GmbH, Berlin. A study to obtain a suitable lubrication method for the commutator of a brushed DC motor has been conducted at the European Space Tribology Laboratory (ESTL; S. D. Lewis et al., 2003).

  2. Global Precipitation Measurement Mission Launch and Commissioning

    NASA Technical Reports Server (NTRS)

    Davis, Nikesha; DeWeese, Keith; Vess, Melissa; O'Donnell, James R., Jr.; Welter, Gary

    2015-01-01

    During launch and early operation of the Global Precipitation Measurement (GPM) Mission, the Guidance, Navigation, and Control (GN&C) analysis team encountered four main on-orbit anomalies. These include: (1) unexpected shock from Solar Array deployment, (2) momentum buildup from the Magnetic Torquer Bars (MTBs) phasing errors, (3) transition into Safehold due to albedo induced Course Sun Sensor (CSS) anomaly, and (4) a flight software error that could cause a Safehold transition due to a Star Tracker occultation. This paper will discuss ways GN&C engineers identified the anomalies and tracked down the root causes. Flight data and GN&C on-board models will be shown to illustrate how each of these anomalies were investigated and mitigated before causing any harm to the spacecraft. On May 29, 2014, GPM was handed over to the Mission Flight Operations Team after a successful commissioning period. Currently, GPM is operating nominally on orbit, collecting meaningful scientific data that will significantly improve our understanding of the Earth's climate and water cycle.

  3. Planetary seismology—Expectations for lander and wind noise with application to Venus

    NASA Astrophysics Data System (ADS)

    Lorenz, Ralph D.

    2012-03-01

    The amplitudes of seismic signals on a planetary surface are discussed in the context of observable physical quantities - displacement, velocity and acceleration - in order to assess the number of events that a sensor with a given detection threshold may capture in a given period. Spacecraft engineers are generally unfamiliar with expected quantities or the language used to describe them, and seismologists are rarely presented with the challenges of accommodation of instrumentation on spacecraft. This paper attempts to bridge this gap, so that the feasibility of attaining seismology objectives on future missions - and in particular, a long-lived Venus lander - can be rationally assessed. For seismometers on planetary landers, the background noise due to wind or lander systems is likely to be a stronger limitation on the effective detection threshold than is the instrument sensitivity itself, and terrestrial data on vehicle noise is assessed in this context. We apply these considerations to investigate scenarios for a long-lived Venus lander mission, which may require a mechanical cooler powered by a Stirling generator. We also consider wind noise: the case for decoupling of a seismometer from a lander is strong on bodies with atmospheres, as is the case for shielding the instrument from wind loads. However, since the atmosphere acts on the elastic ground as well as directly on instruments, the case for deep burial is not strong, but it is important that windspeed and pressure be documented by adequate meteorology measurements.

  4. Low energy neutron measurements aboard encounter missions

    NASA Astrophysics Data System (ADS)

    Vilmer, N.; Maksimovic, M.; Trottet, G.

    Neutrons in the MeV to GeV range are produced by interaction of flare accelerated ions with the solar atmosphere. Because of their lifetime, only high energy neutrons (> 100 MeV) have a high probability to be detected at earth's orbit. So far, around fifteen solar neutron events have been observed either by high energy detectors aboard spacecrafts at 1 AU or by ground based neutron monitors. Neutrons between 10 and 100 MeV have also been detected for a few events through their proton decay. Measurements of solar neutrons closer to the Sun aboard encounter missions will allow to probe for the first time the MeV neutrons which are produced by the nuclear reactions of energetic ions with thresholds around 1 MeV/nuc and will provide information on the accelerated ion spectrum in the energy range between ˜ 1 MeV and 100 MeV/nuc in complementarity with what can be deduced from γ -ray line emission. The close proximity of the Sun would allow to measure neutron events for many more flares opening a new field of solar physics. Combined with near in-situ ion measurements and γ -ray observations, neutrons will bring information on the link between interacting and escaping ions while getting rid of most of the transport effects.

  5. Martian Meteorological Lander

    NASA Astrophysics Data System (ADS)

    Vorontsov, V.; Pichkhadze, K.; Polyakov, A.

    2002-01-01

    much more reliable in comparison with MML of first and second options because their functional diagram is realized by operation of 3-4 (instead of 8-10 for MML of first and second concepts) executive devices. A distinctive moment for MML of last three concepts , namely for variants 3 and 5, is the final stage of landing stipulated by penetration of forebody into the soil. Such a profile of landing was taken into account during the development of one of the landing vehicles for the "MARS-96" SC. This will permit to implement simple technical decisions for putting the meteorological complex into operation and to carry out its further operations on the surface. After comparative analysis of 5 concepts for the more detailed development concepts with parachute system and with IBU and penetration unit have been chosen as most prospective. However, finally, on the next step the new modification of the lander (hybrid version of third and fifth option with inflatable braking device and penetrating unit) has been proposed and chosen for the next step of development. The several small stations should be transported to Mars in frameworks of Scout Mars mission, or Phobos Sample Return mission as piggyback payload.

  6. Northeast View From Pathfinder Lander

    NASA Technical Reports Server (NTRS)

    1997-01-01

    This panorama of the region to the northeast of the lander was constructed to support the Sojourner Rover Team's plans to conduct an 'autonomous traverse' to explore the terrain away from the lander after science objectives in the lander vicinity had been met. The large, relatively bright surface in the foreground, about 10 meters (33 feet) from the spacecraft, in this scene is 'Baker's Bench.' The large, elongated rock left of center in the middle distance is 'Zaphod.'

    This view was produced by combining 8 individual 'Superpan' scenes from the left and right eyes of the IMP camera. Each frame consists of 8 individual frames (left eye) and 7 frames (right eye) taken with different color filters that were enlarged by 500% and then co-added using Adobe Photoshop to produce, in effect, a super-resolution panchromatic frame that is sharper than an individual frame would be.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages the Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is a division of the California Institute of Technology (Caltech). The IMP was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal Investigator.

  7. Looking westward at the lander

    NASA Technical Reports Server (NTRS)

    1997-01-01

    One of the two forward cameras aboard the Sojourner rover took this image of the Sagan Memorial Station on Sol 25. The camera uses a fisheye lens which produces the illumination gradient in the sky on the western horizon. The angular resolution of the camera is about three milliradians (.018 degrees) per pixel, which is why the image appears grainy.

    Features seen on the lander include (from left to right): the Atmospheric Structure Instrument / Meteorology Package (ASI/MET) mast with windsocks; the low-gain antenna mast, the Imager for Mars Pathfinder (IMP) on its mast at center; the disc-shaped high-gain antenna at right, and areas of deflated airbags. The dark circle on the lander body is a filtered vent that allowed air to escape during launch, and allowed the lander to repressurize upon landing. The high-gain antenna is pointed at Earth. The large rock Yogi, which Sojourner has approached and studied, is at the far right of the image.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages and Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is an operating division of the California Institute of Technology (Caltech). The Imager for Mars Pathfinder (IMP) was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal Investigator.

  8. TRMM (Tropical Rainfall Measuring Mission): A satellite mission to measure tropical rainfall

    NASA Technical Reports Server (NTRS)

    Simpson, Joanne (Editor)

    1988-01-01

    The Tropical Rainfall Measuring Mission (TRMM) is presented. TRMM is a satellite program being studied jointly by the United States and Japan which would carry out the systematic study of tropical rainfall required for major strides in weather and climate research. The scientific justification for TRMM is discussed. The implementation process for the scientific community, NASA management, and the other decision-makers and advisory personnel who are expected to evaluate the priority of the project is outlined.

  9. Lander and Mini Matterhorn rock

    NASA Technical Reports Server (NTRS)

    1997-01-01

    One of the two forward cameras aboard the Sojourner rover took this image of the Sagan Memorial Station on Sol 26. The angular resolution of the camera is about three milliradians (.018 degrees) per pixel, which is why the image appears grainy. The field of view of each rover camera is about 127 degrees horizontally and 90 degrees vertically.

    Features seen on the lander include (from left to right): the Atmospheric Structure Instrument/Meteorology Package (ASI/MET) mast with windsocks; the low-gain antenna mast, the Imager for Mars Pathfinder (IMP) on its mast at center; the disc-shaped high-gain antenna at right, and areas of deflated airbags. The dark circle on the lander body is a filtered vent that allowed air to escape during launch, and allowed the lander to repressurize upon landing. The high-gain antenna is pointed at Earth. The large rock Yogi, which Sojourner has approached and studied, as at the far right of the image. Mini Matterhorn is the large rock situated in front of the lander at left.

    The horizontal line at the center of the image is due to differences in light-metering for different portions of the image. The shadow of Sojourner and its antenna are visible at the lower section of the image. The antenna's shadow falls across a light-colored rock.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages and Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is an operating division of the California Institute of Technology (Caltech). The Imager for Mars Pathfinder (IMP) was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal Investigator.

  10. A new Wind Sensor for the Beagle 2 Mars Lander

    NASA Astrophysics Data System (ADS)

    Wilson, C. F.; Calcutt, S. B.; Jones, T. V.

    2001-12-01

    A hot-film anemometer has been developed for Beagle2, a British Mars lander to be launched in 2003. The sensor will measure wind speed (up to 30 m/s) and horizontal component of wind direction. The position of the wind sensor position at the end of Beagle2's motorised arm allows several new possibilities for wind measurement on Mars that were unavailable in previous missions. The height of the wind sensor can be adjusted to any height between ~20 cm and ~110 cm above the lander body, or can be moved laterally at a given height to study the effects of lander interference. Alternatively, the wind sensor may be positioned with its axis horizontal, thus allowing measurements of vertical wind speed. The wind sensor was calibrated in a new wind tunnel facility, in which Martian surface wind conditions are simulated. Wind speeds of 0.5 - 60 m/s can be created in a CO2 or air atmosphere at pressures of 5 - 10 mbar and temperatures of 200 - 300 K. The facility can also be used in its current configuration to simulate stratospheric winds on Earth. >http://www.atm.ox.ac.uk/user/wilson/matacf.html

  11. Exploring Europa with a Surface Lander Powered by a Small Radioisotope Power System (RPS)

    NASA Astrophysics Data System (ADS)

    Abelson, Robert D.; Shirley, James H.

    2005-02-01

    Europa is a high-priority target for future exploration because of the possibility that it may possess a subsurface liquid ocean that could sustain life. Exploring the surface of this Galilean moon, however, represents a formidable technical challenge due to the great distances involved, the high ambient radiation, and the extremely low surface temperatures. A design concept is presented for a Europa Lander Mission (ELM) powered by a small radioisotope power system (RPS) that could fly aboard the proposed Jupiter Icy Moons Orbiter (JIMO). The ELM would perform in-situ science measurements for a minimum of 30 Earth days, equivalent to approximately 8.5 Europa days. The primary science goals for the Europa lander would include astrobiology and geophysics experiments and determination of surface composition. Science measurements would include visual imagery, microseismometry, Raman spectroscopy, Laser Induced Breakdown Spectroscopy (LIBS), and measurements of surface temperature and radiation levels. The ELM spacecraft would be transported to Europa via the JIMO spacecraft as an auxiliary payload with an extended duration cruise phase (up to 13 years). After arriving at Europa, ELM would separate from JIMO and land on the moon's surface to conduct the nominal science mission. In addition to transportation, the JIMO mothership would be used to relay all lander data back to Earth, thus reducing the size and power requirement of the lander communications system. Conventional power sources were evaluated and found to be impractical for this mission due to the extended duration, low level of solar insolation (~3.7% of Earth's), the low surface temperatures (as low as 85K), and the 1.75 days of eclipse every Europa day. In contrast, a small-RPS would enable the ELM mission by powering the lander and keeping all key instrumentation and subsystems warm during the cruise and landed phases of the mission. The conceptual small-RPS is based on the existing General Purpose Heat

  12. Phoenix Lander on Mars (Stereo)

    NASA Technical Reports Server (NTRS)

    2007-01-01

    NASA's Phoenix Mars Lander monitors the atmosphere overhead and reaches out to the soil below in this stereo illustration of the spacecraft fully deployed on the surface of Mars. The image appears three-dimensional when viewed through red-green stereo glasses.

    Phoenix has been assembled and tested for launch in August 2007 from Cape Canaveral Air Force Station, Fla., and for landing in May or June 2008 on an arctic plain of far-northern Mars. The mission responds to evidence returned from NASA's Mars Odyssey orbiter in 2002 indicating that most high-latitude areas on Mars have frozen water mixed with soil within arm's reach of the surface.

    Phoenix will use a robotic arm to dig down to the expected icy layer. It will analyze scooped-up samples of the soil and ice for factors that will help scientists evaluate whether the subsurface environment at the site ever was, or may still be, a favorable habitat for microbial life. The instruments on Phoenix will also gather information to advance understanding about the history of the water in the icy layer. A weather station on the lander will conduct the first study Martian arctic weather from ground level.

    The vertical green line in this illustration shows how the weather station on Phoenix will use a laser beam from a lidar instrument to monitor dust and clouds in the atmosphere. The dark 'wings' to either side of the lander's main body are solar panels for providing electric power.

    The Phoenix mission is led by Principal Investigator Peter H. Smith of the University of Arizona, Tucson, with project management at NASA's Jet Propulsion Laboratory and development partnership with Lockheed Martin Space Systems, Denver. International contributions for Phoenix are provided by the Canadian Space Agency, the University of Neuchatel (Switzerland), the University of Copenhagen (Denmark), the Max Planck Institute (Germany) and the Finnish Meteorological institute. JPL is a division of the California

  13. Selection and Characterization of Landing Sites for Chandrayaan-2 Lander

    NASA Astrophysics Data System (ADS)

    Gopala Krishna, Barla; Amitabh, Amitabh; Srinivasan, T. P.; Karidhal, Ritu; Nagesh, G.; Manjusha, N.

    2016-07-01

    Indian Space Research Organisation has planned the second mission to moon known as Chandrayaan-2, which consists of an Orbiter, a Lander and a Rover. This will be the first soft landing mission of India on lunar surface. The Orbiter, Lander and Rover individually will carry scientific payloads that enhance the scientific objectives of Chandrayaan-2. The Lander soft lands on the lunar surface and subsequently Lander & Rover will carry on with the payload activities on the moon surface. Landing Site identification based on the scientific and engineering constrains of lander plays an important role in success of a mission. The Lander poses some constraints because of its engineering design for the selection of the landing site and on the other hand the landing site / region imparts some constrain on the Lander. The various constraints that have to be considered for the study of the landing site are Local slope, Sun illumination during mission life, Radio communication with the Earth, Global slope towards equator, Boulders size, Crater density and boulder distribution. This paper describes the characterization activities of the different landing locations which have been studied for Chandrayaan-2 Lander. The sites have been studied both in the South Polar and North Polar regions of the moon on the near side. The Engineering Constraints at the sites due to the Lander, Factors that affect mission life (i.e. illumination at the location), Factors influencing communication to earth (i.e. RF visibility) & Shadow movements have been studied at these locations and zones that are favourable for landing have been short listed. This paper gives methodology of these studies along with the results of the characteristics of all the sites and the recommendations for further action in finalizing the landing area.

  14. NASA's Robotic Lunar Lander Development Project

    NASA Technical Reports Server (NTRS)

    Cohen, Barbara A.

    2012-01-01

    Since early 2005, NASA's Robotic Lunar Lander Development (RLLD) office at NASA MSFC, in partnership with the Applied Physics Laboratory (APL), has developed mission concepts and preformed risk-reduction activities to address planetary science and exploration objectives uniquely met with landed missions. The RLLD team developed several concepts for lunar human-exploration precursor missions to demonstrate precision landing and in-situ resource utilization, a multi-node lunar geophysical network mission, either as a stand-alone mission, or as part of the International Lunar Network (ILN), a Lunar Polar Volatiles Explorer and a Mercury lander mission for the Planetary Science decadal survey, and an asteroid rendezvous and landing mission for the Exploration Precursor Robotics Mission (xPRM) office. The RLLD team has conducted an extensive number of risk-reduction activities in areas common to all lander concepts, including thruster testing, propulsion thermal control demonstration, composite deck design and fabrication, and landing leg stability and vibration. In parallel, the team has developed two robotic lander testbeds providing closed-loop, autonomous hover and descent activities for integration and testing of flight-like components and algorithms. A compressed-air test article had its first flight in September 2009 and completed over 150 successful flights. This small test article (107 kg dry/146 kg wet) uses a central throttleable thruster to offset gravity, plus 3 descent thrusters (37lbf ea) and 6 attitude-control thrusters (12lbf ea) to emulate the flight system with pulsed operation over approximately 10s of flight time. The test article uses carbon composite honeycomb decks, custom avionics (COTS components assembled in-house), and custom flight and ground software. A larger (206 kg dry/322 kg wet), hydrogen peroxide-propelled vehicle began flight tests in spring 2011 and fly over 30 successful flights to a maximum altitude of 30m. The monoprop testbed

  15. The Mars Polar Lander undergoes spin test

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers maneuver the Mars Polar Lander onto a spin table for testing. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which is due to be launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  16. The Mars Polar Lander undergoes spin test

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Workers in the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) lift the Mars Polar Lander to move it to a spin table for testing. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which is due to be launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  17. The Mars Polar Lander undergoes spin test

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), the Mars Polar Lander is lowered toward a spin table for testing. The lander, which will be launched on Jan. 3, 1999, is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which is due to be launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  18. Planetary cubesats - mission architectures

    NASA Astrophysics Data System (ADS)

    Bousquet, Pierre W.; Ulamec, Stephan; Jaumann, Ralf; Vane, Gregg; Baker, John; Clark, Pamela; Komarek, Tomas; Lebreton, Jean-Pierre; Yano, Hajime

    2016-07-01

    Miniaturisation of technologies over the last decade has made cubesats a valid solution for deep space missions. For example, a spectacular set 13 cubesats will be delivered in 2018 to a high lunar orbit within the frame of SLS' first flight, referred to as Exploration Mission-1 (EM-1). Each of them will perform autonomously valuable scientific or technological investigations. Other situations are encountered, such as the auxiliary landers / rovers and autonomous camera that will be carried in 2018 to asteroid 1993 JU3 by JAXA's Hayabusas 2 probe, and will provide complementary scientific return to their mothership. In this case, cubesats depend on a larger spacecraft for deployment and other resources, such as telecommunication relay or propulsion. For both situations, we will describe in this paper how cubesats can be used as remote observatories (such as NEO detection missions), as technology demonstrators, and how they can perform or contribute to all steps in the Deep Space exploration sequence: Measurements during Deep Space cruise, Body Fly-bies, Body Orbiters, Atmospheric probes (Jupiter probe, Venus atmospheric probes, ..), Static Landers, Mobile landers (such as balloons, wheeled rovers, small body rovers, drones, penetrators, floating devices, …), Sample Return. We will elaborate on mission architectures for the most promising concepts where cubesat size devices offer an advantage in terms of affordability, feasibility, and increase of scientific return.

  19. The Philae/Rosetta Lander at Comet 67P/Churyumov-Gerasimenko - First Result, on overview

    NASA Astrophysics Data System (ADS)

    Bibring, J. P.; Boehnhardt, H.

    2014-12-01

    The Philae lander onboard ESA Rosetta mission is planned to land November 11, 2014 on comet 67P/Churyumov-Gerasimenko. Before and during landing, descent, touch-down, then the days and weeks thereafter, campaigns of scientific measurements will be performed, involving the 10 instruments onboard, i.e. APXS, CIVA, CONSERT, COSAC, MUPUS, PTOLEMY, ROLIS, ROMAP, SD2 and SESAME. An overview of these activities will be provided and the first results from the Philae instruments presented and discussed.

  20. NASA's Robotic Lunar Lander Development Program

    NASA Technical Reports Server (NTRS)

    Ballard, Benjamin W.; Reed, Cheryl L. B.; Artis, David; Cole, Tim; Eng, Doug S.; Kubota, Sanae; Lafferty, Paul; McGee, Timothy; Morese, Brian J.; Chavers, Gregory; Moore, Joshua; Bassler, Julie A.; Cohen, D. Barbara; Farmer, Jeffrey; Freestone, Todd; Hammond, Monica S.; Hannan, Mike C.; Hill, Lawrence D.; Harris, Danny W.; Holloway, Todd A.; Lowery, John E.; Mulac, Brian D.; Stemple, Cindy

    2012-01-01

    NASA Marshall Space Flight Center and the Johns Hopkins University Applied Physics Laboratory have developed several mission concepts to place scientific and exploration payloads ranging from 10 kg to more than 200 kg on the surface of the moon. The mission concepts all use a small versatile lander that is capable of precision landing. The results to date of the lunar lander development risk reduction activities including high pressure propulsion system testing, structure and mechanism development and testing, and long cycle time battery testing will be addressed. The most visible elements of the risk reduction program are two fully autonomous lander flight test vehicles. The first utilized a high pressure cold gas system (Cold Gas Test Article) with limited flight durations while the subsequent test vehicle, known as the Warm Gas Test Article, utilizes hydrogen peroxide propellant resulting in significantly longer flight times and the ability to more fully exercise flight sensors and algorithms. The development of the Warm Gas Test Article is a system demonstration and was designed with similarity to an actual lunar lander including energy absorbing landing legs, pulsing thrusters, and flight-like software implementation. A set of outdoor flight tests to demonstrate the initial objectives of the WGTA program was completed in Nov. 2011, and will be discussed.

  1. Precipitation Measurements from Space: The Global Precipitation Measurement Mission

    NASA Technical Reports Server (NTRS)

    Hou, Arthur Y.

    2007-01-01

    Water is fundamental to the life on Earth and its phase transition between the gaseous, liquid, and solid states dominates the behavior of the weather/climate/ecological system. Precipitation, which converts atmospheric water vapor into rain and snow, is central to the global water cycle. It regulates the global energy balance through interactions with clouds and water vapor (the primary greenhouse gas), and also shapes global winds and dynamic transport through latent heat release. Surface precipitation affects soil moisture, ocean salinity, and land hydrology, thus linking fast atmospheric processes to the slower components of the climate system. Precipitation is also the primary source of freshwater in the world, which is facing an emerging freshwater crisis in many regions. Accurate and timely knowledge of global precipitation is essential for understanding the behavior of the global water cycle, improving freshwater management, and advancing predictive capabilities of high-impact weather events such as hurricanes, floods, droughts, and landslides. With limited rainfall networks on land and the impracticality of making extensive rainfall measurements over oceans, a comprehensive description of the space and time variability of global precipitation can only be achieved from the vantage point of space. This presentation will examine current capabilities in space-borne rainfall measurements, highlight scientific and practical benefits derived from these observations to date, and provide an overview of the multi-national Global Precipitation Measurement (GPM) Mission scheduled to bc launched in the early next decade.

  2. Phoenix Mars Lander in Testing

    NASA Technical Reports Server (NTRS)

    2006-01-01

    NASA's next Mars-bound spacecraft, the Phoenix Mars Lander, was partway through assembly and testing at Lockheed Martin Space Systems, Denver, in September 2006, progressing toward an August 2007 launch from Florida. In this photograph, spacecraft specialists work on the lander after its fan-like circular solar arrays have been spread open for testing. The arrays will be in this configuration when the spacecraft is active on the surface of Mars.

    Phoenix will land in icy soils near the north polar permanent ice cap of Mars and explore the history of the water in these soils and any associated rocks, while monitoring polar climate. It will dig into the surface, test scooped-up samples for carbon-bearing compounds and serve as NASA's first exploration of a potential modern habitat on Mars.

    mission is led by Principal Investigator Peter H. Smith of the University of Arizona, Tucson, with project management at NASA's Jet Propulsion Laboratory and development partnership with Lockheed Martin Space Systems. International contributions for Phoenix are provided by the Canadian Space Agency, the University of Neuchatel (Switzerland), the University of Copenhagen, and the Max Planck Institute in Germany. JPL is a division of the California Institute of Technology in Pasadena.

  3. A mobile planetary lander utilizing elastic loop suspension

    NASA Technical Reports Server (NTRS)

    Trautwein, W.

    1976-01-01

    Efforts to increase the cost effectiveness of future lunar and planetary rover missions have led to the mobile lander concept, which replaces the landing legs of a soft-lander craft with a compact mobility system of sufficient strength to withstand the landing impact. The results of a mobile lander conceptual design effort based on existing NASA-Viking '75 hardware are presented. The elastic loop concept, developed as a post-Apollo rover technology, is found to meet stringent stowage, traction, power and weight requirements.

  4. NASA's Robotic Lander Takes Flight

    NASA Video Gallery

    On Wednesday, June 8, the lander prototype managed by the Robotic Lunar Lander Development Project at NASA's Marshall Space Flight Center in Huntsville, Ala., hovered autonomously for 15 seconds at...

  5. Low Cost Precision Lander for Lunar Exploration

    NASA Astrophysics Data System (ADS)

    Hoppa, G. V.; Head, J. N.; Gardner, T. G.; Seybold, K. G.

    2004-12-01

    For 60 years the US Defense Department has invested heavily in producing small, low mass, precision-guided vehicles. The technologies matured under these programs include terrain-aided navigation, closed loop terminal guidance algorithms, robust autopilots, high thrust-to-weight propulsion, autonomous mission management software, sensors, and data fusion. These technologies will aid NASA in addressing New Millennium Science and Technology goals as well as the requirements flowing from the Moon to Mars vision articulated in January 2004. Establishing and resupplying a long-term lunar presence will require automated landing precision not yet demonstrated. Precision landing will increase safety and assure mission success. In our lander design, science instruments amount to 10 kg, 16% of the lander vehicle mass. This compares favorably with 7% for Mars Pathfinder and less than 15% for Surveyor. The mission design relies on a cruise stage for navigation and TCMs for the lander's flight to the moon. The landing sequence begins with a solid motor burn to reduce the vehicle speed to 300-450 m/s. At this point the lander is about 2 minutes from touchdown and has 600 to 700 m/s delta-v capability. This allows for about 10 km of vehicle divert during terminal descent. This concept of operations closely mimics missile operational protocol used for decades: the vehicle remains inert, then must execute its mission flawlessly on a moment's notice. The vehicle design uses a propulsion system derived from heritage MDA programs. A redesigned truss provides hard points for landing gear, electronics, power supply, and science instruments. A radar altimeter and a Digital Scene Matching Area Correlator (DSMAC) provide data for the terminal guidance algorithms. This approach leverages the billions of dollars DoD has invested in these technologies, to land useful science payloads precisely on the lunar surface at relatively low cost.

  6. Experiments on asteroids using hard landers

    NASA Technical Reports Server (NTRS)

    Turkevich, A.; Economou, T.

    1978-01-01

    Hard lander missions to asteroids are examined using the Westphal penetrator study as a basis. Imagery and chemical information are considered to be the most significant science to be obtained. The latter, particularly a detailed chemical analysis performed on an uncontaminated sample, may answer questions about the relationships of asteroids to meteorites and the place of asteroids in theories of the formation of the solar system.

  7. Prototype of NASA's Global Precipitation Measurement Mission Ground Validation System

    NASA Technical Reports Server (NTRS)

    Schwaller, M. R.; Morris, K. R.; Petersen, W. A.

    2007-01-01

    NASA is developing a Ground Validation System (GVS) as one of its contributions to the Global Precipitation Mission (GPM). The GPM GVS provides an independent means for evaluation, diagnosis, and ultimately improvement of GPM spaceborne measurements and precipitation products. NASA's GPM GVS consists of three elements: field campaigns/physical validation, direct network validation, and modeling and simulation. The GVS prototype of direct network validation compares Tropical Rainfall Measuring Mission (TRMM) satellite-borne radar data to similar measurements from the U.S. national network of operational weather radars. A prototype field campaign has also been conducted; modeling and simulation prototypes are under consideration.

  8. Mars pathfinder lander deployment mechanisms

    NASA Technical Reports Server (NTRS)

    Gillis-Smith, Greg R.

    1996-01-01

    The Mars Pathfinder Lander employs numerous mechanisms, as well as autonomous mechanical functions, during its Entry, Descent and Landing (EDL) Sequence. This is the first US lander of its kind, since it is unguided and airbag-protected for hard landing using airbags, instead of retro rockets, to soft land. The arrival condition, location, and orientation of the Lander will only be known by the computer on the Lander. The Lander will then autonomously perform the appropriate sequence to retract the airbags, right itself, and open, such that the Lander is nearly level with no airbag material covering the solar cells. This function uses two different types of mechanisms - the Airbag Retraction Actuators and the Lander Petal Actuators - which are designed for the high torque, low temperature, dirty environment and for limited life application. The development of these actuators involved investigating low temperature lubrication, Electrical Discharge Machining (EDM) to cut gears, and gear design for limited life use.

  9. NASA Propulsion Concept Studies and Risk Reduction Activities for Resource Prospector Lander

    NASA Technical Reports Server (NTRS)

    Trinh, Huu P.; Williams, Hunter; Burnside, Chris

    2015-01-01

    The Resource Prospector mission is to investigate the Moon's polar regions in search of volatiles. The government-version lander concept for the mission is composed of a braking stage and a liquid-propulsion lander stage. A propulsion trade study concluded with a solid rocket motor for the braking stage while using the 4th-stage Peacekeeper (PK) propulsion components for the lander stage. The mechanical design of the liquid propulsion system was conducted in concert with the lander structure design. A propulsion cold-flow test article was fabricated and integrated into a lander development structure, and a series of cold flow tests were conducted to characterize the fluid transient behavior and to collect data for validating analytical models. In parallel, RS-34 PK thrusters to be used on the lander stage were hot-fire tested in vacuum conditions as part of risk reduction activities.

  10. Triton Explorer - Neptune Orbiter Mission Study

    NASA Astrophysics Data System (ADS)

    Balint, T. S.; Shirley, J. H.

    2005-12-01

    Triton is larger than the planet Pluto, and its highly inclined, retrograde orbit suggests that it may be a captured object that initially formed somewhere else in the solar system. Its composition (and its inventory of organic materials) is thus of considerable interest. Triton possesses an appreciable atmosphere, and its circulation, like that of Mars, is one of seasonal condensation flow between the southern and northern hemispheres. Although the surface pressure is only ~ 16 microbar, winds of 5-15 m / sec flow toward the equator from the sunlit hemisphere. Voyager 2 detected a number of plumes extending from the surface to approximately 8 km elevation within the atmosphere. Triton exhibits a variety of puzzling surface features; among these are structural features that suggest extensive faulting in the past, together with ice volcanism, and dark streaks that may be associated with the plumes. The Solar System Exploration Decadal Survey (NRC, 2003) lists a Neptune Orbiter / Triton Explorer as a "Deferred High-Priority Flight Mission" that may be considered for the second decade of this century. Likely science objectives for a Triton Lander mission would include a more complete characterization of the composition and circulation of the atmosphere; investigation of the physical processes responsible for plume formation; surface composition measurements; and geophysical monitoring, including seismological measurements that could potentially constrain the physics of plume eruptions. We describe here a conceptual dual-Lander mission to explore Triton's surface. Each of the two Landers would be powered by a standard multi-mission radioisotope thermoelectric generator (MMRTG). These Landers could operate on the surface of Triton for several years. A companion Neptune Orbiter would provide telecommunication links between the Landers and the Earth, and would be instrumented to observe both Triton and Neptune. Although a Jupiter Icy Moons Orbiter (JIMO) follow-on mission

  11. A Discovery-Class Lunette Mission Concept for a Lunar Geophysical Network

    NASA Technical Reports Server (NTRS)

    Elliott, John; Alkalai, Leon

    2010-01-01

    The Lunette mission concept for a network of small, inexpensive lunar landers has evolved over the last three years as the focus of space exploration activities in the US has changed. Originating in a concept for multiple landers launched as a secondary payload capable of regional science and site survey activities, Lunette has recently been developed into a Discovery-class mission concept that offers global lunar coverage enabling network science on a much broader scale. A particular mission concept has been refined by the Lunette team that would result in a low-cost global lunar geophysical network, comprised of two landers widely spaced on the near side of the moon. Each of the two identical landers would carry a suite of instruments that would make continuous measurements of seismic activity, heat flow, and the electromagnetic environment during the full lunar day/night cycle. Each lander would also deploy a next-generation laser retroreflector capable of improving on distance measurement accuracy by an order of magnitude over those emplaced by the previous Apollo and Lunokhod missions. This paper presents a comprehensive overview of the Lunette geophysical network mission concept, including mission and flight system design, as well as the key requirements and constraints that guided them.

  12. The heat shield for the Mars Polar Lander is attached

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers get ready to lift the heat shield for the Mars Polar Lander off the workstand before attaching it to the lander. Scheduled to be launched on Jan. 3, 1999, the lander is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which is due to be launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  13. Aquarius Satellite Salinity Measurement Mission Status, and Science Results from the initial 3-Year Prime Mission

    NASA Astrophysics Data System (ADS)

    Lagerloef, G. S. E.; Kao, H. Y.

    2014-12-01

    The Aquarius satellite microwave sensor, launched June 2011, as part of the US-Argentina joint Aquarius/SAC-D mission, and commenced observations on 25 Aug2011, and completed three years of ocean surface salinity measurements in late August 2014. The Aquarius measurement objectives are to describe unknown features in the sea surface salinity (SSS) field, and document seasonal and interannual variations on regional and basin scales. This presentation will first describe the structure of the mean annual global salinity field compared with the previous in situ climatology and contemporary in situ measurements , including small persistent biases of opposite sign in high latitudes versus low latitudes, currently under intense investigation, as well as global and regional error statistics. Then we summarize highlights of various studies and papers submitted to the JGR-Oceans special section on satellite salinity (2014). The most prominent seasonal variations, most notably the extant and variability of the SSS signature of the Atlantic and Pacific inter-tropical convergence zones, Amazon-Orinoco and other major rivers, and other important regional patterns of seasonal variability. Lastly we will examine the trends observed during the three Sep-Aug measurement years beginning Sep2011, Sep2012 and Sep2013, respectively, in relation to ENSO and other climate indices, as the first step in analyzing interannual SSS variability. An outline for extended mission operations beyond the initial three-year prime mission will be presented.

  14. The Global Precipitation Measurement (GPM) Mission: Overview and Status

    NASA Technical Reports Server (NTRS)

    Hou, Arthur

    2008-01-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission to unify and advance global precipitation measurements from a constellation of dedicated and operational microwave sensors. The GPM concept centers on the deployment of a Core Spacecraft in a non-Sun-synchronous orbit at 65 degrees inclination carrying a dual-frequency precipitation radar (DPR) and a multi-frequency passive microwave radiometer (GMI) with high-frequency capabilities to serve as a precipitation physics observatory and calibration standard for the constellation radiometers. The baseline GPM constellation is envisioned to comprise conical-scanning microwave imagers (e.g., GMI, SSMIS, AMSR, MIS, MADRAS, GPM-Brazil) augmented with cross-track microwave temperature/humidity sounders (e.g., MHS, ATMS) over land. In addition to the Core Satellite, the GPM Mission will contribute a second GMI to be flown in a low-inclination (approximately 40 deg.) non-Sun-synchronous orbit to improve near real-time monitoring of hurricanes. GPM is a science mission with integrated applications goals aimed at (1) advancing the knowledge of the global water/energy cycle variability and freshwater availability and (2) improving weather, climate, and hydrological prediction capabilities through more accurate and frequent measurements of global precipitation. The GPM Mission is currently a partnership between NASA and the Japan Aerospace Exploration Agency (JAXA), with opportunities for additional partners in satellite constellation and ground validation activities. Within the framework of the inter-governmental Group ob Earth Observations (GEO) and Global Earth Observation System of Systems (GEOSS), GPM has been identified as a cornerstone for the Precipitation Constellation (PC) being developed under the auspices of Committee of Earth Observation Satellites (CEOS). The GPM Core Observatory is scheduled for launch in 2013, followed by the launch of the GPM Low-Inclination Observatory in

  15. In Situ Atmospheric Pressure Measurements in the Martian Southern Polar Region: Mars Volatiles and Climate Surveyor Meteorology Package on the Mars Polar Lander

    NASA Technical Reports Server (NTRS)

    Harri, A.-M.; Polkko, J.; Siili, T.; Crisp, D.

    1998-01-01

    Pressure observations are crucial for the success of the Mars Volatiles and Climate Surveyor (MVACS) Meteorology (MET) package onboard the Mars Polar Lander (MPL), due for launch early next year. The spacecraft is expected to land in December 1999 (L(sub s) = 256 degrees) at a high southern latitude (74 degrees - 78 degrees S). The nominal period of operation is 90 sols but may last up to 210 sols. The MVACS/MET experiment will provide the first in situ observations of atmospheric pressure, temperature, wind, and humidity in the southern hemisphere of Mars and in the polar regions. The martian atmosphere goes through a large-scale atmospheric pressure cycle due to the annual condensation/sublimation of the atmospheric CO2. Pressure also exhibits short period variations associated with dust storms, tides, and other atmospheric events. A series of pressure measurements can hence provide us with information on the large-scale state and dynamics of the atmosphere, including the CO2 and dust cycles as well as local weather phenomena. The measurements can also shed light on the shorter time scale phenomena (e.g., passage of dust devils) and hence be important in contributing to our understanding of mixing and transport of heat, dust, and water vapor.

  16. Using Engineering Cameras on Mars Landers and Rovers to Retrieve Atmospheric Dust Loading

    NASA Astrophysics Data System (ADS)

    Wolfe, C. A.; Lemmon, M. T.

    2014-12-01

    Dust in the Martian atmosphere influences energy deposition, dynamics, and the viability of solar powered exploration vehicles. The Viking, Pathfinder, Spirit, Opportunity, Phoenix, and Curiosity landers and rovers each included the ability to image the Sun with a science camera that included a neutral density filter. Direct images of the Sun provide the ability to measure extinction by dust and ice in the atmosphere. These observations have been used to characterize dust storms, to provide ground truth sites for orbiter-based global measurements of dust loading, and to help monitor solar panel performance. In the cost-constrained environment of Mars exploration, future missions may omit such cameras, as the solar-powered InSight mission has. We seek to provide a robust capability of determining atmospheric opacity from sky images taken with cameras that have not been designed for solar imaging, such as lander and rover engineering cameras. Operational use requires the ability to retrieve optical depth on a timescale useful to mission planning, and with an accuracy and precision sufficient to support both mission planning and validating orbital measurements. We will present a simulation-based assessment of imaging strategies and their error budgets, as well as a validation based on archival engineering camera data.

  17. Mars Polar Lander: The Search Begins

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Space Science Systems. This model is illuminated in the same way that sunlight would illuminate the real lander at 2 p.m. local time in December 1999--in other words, the model is illuminated exactly the way it would be if it occurred in the MOC image shown above (left). This figure shows what the Mars Polar Lander would look like if viewed from above by cameras of different resolutions from 1 centimeter (0.4 inch) per pixel in the upper left to 1.5 meters (5 feet) per pixel in the lower right. The 1.5 meters per pixel view is the best resolution that can be achieved by MOC. Note that at MOC resolution, the lander is just a few pixels across.

    The problem of recognizing the lander in MOC images is obvious--all that might be seen is a pattern of a few bright and dark gray pixels. This means that it will be extremely difficult to identify the lander by looking at the relatively noisy MOC images that can be acquired at the landing site--like those shown in the top picture.

    How, then, is the MGS MOC team looking for the lander? Primarily, they are looking for associations of features that, together, would suggest whether or not the Mars landing was successful. For example, the parachute that was used to slow the lander from supersonic speeds to just under 300 km/hr (187 mph) was to have been jettisoned, along with part of the aeroshell that protected the lander from the extreme heat of entry, about 40 seconds before landing. The parachute and aeroshell are likely to be within a kilometer (6 tenths of a mile) of the lander. The parachute and aeroshell are nearly white, so they should stand out well against the red martian soil. The parachute, if lying on the ground in a fully open, flat position, would measure about 6 meters (20 feet)--thus it would cover three or four pixels (at most) in a MOC image. If the parachute can be found, the search for the lander can be narrowed to a small, nearby zone. If, as another example, the landing rockets kicked up a lot of dust and

  18. Rosetta Lander - Philae: Operations on 67P and attempts for Long Term Science

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Biele, Jens; Cozzoni, Barbara; Delmas, Cedric; Fantinati, Cinzia; Geurts, Koen; Jansen, Sven; Jurado, Eric; Küchemann, Oliver; Lommatsch, Valentina; Maibaum, Michael; O'Rourke, Laurence

    2016-04-01

    Philae is a comet Lander, part of Rosetta which is a Cornerstone Mission of the ESA Horizon 2000 programme. Philae successfully landed on comet 67P/Churyumov-Gerasimenko on November 12th, 2014 and performed a First Scientific Sequence, based on the energy stored in it's on board batteries. All ten instruments of the Philae payload have been operated at least once. Due to the fact that the final landing site (after several bounces) was poorly illuminated, Philae went into hibernation on November 15th, and the teams hoped for a wake-up at closer heliocentric distances. Signals from the Lander were indeed received on June 13th when 67P was at a distance of about 1.4 AU from the Sun. Housekeeping values showed that Philae had already been active earlier, but no RF contact with the mothership could be established. Seven more times, signals from Philae were received, the last ones on July 9th, 2015. Unfortunately, no reliable or predictable links could be achieved. The paper will give an overview of the activities with Philae after its hibernation, interpretation of the received housekeeping data and the various strategies to attempt more contacts and long term science measurements. Rosetta is an ESA mission with contributions from its member states and NASA. Rosetta's Philae Lander is provided by a consortium led by DLR, MPS, CNES and ASI with additional contributions from Hungary, UK, Finland, Ireland and Austria.

  19. Mars Phobos and Deimos Survey (M-PADS) - a Martian Moons Orbiter and Phobos Lander

    NASA Astrophysics Data System (ADS)

    Ball, A. J.; Price, M. E.; Walker, R. J.; Dando, G. C.; Wells, N. S.; Zarnecki, J. C.

    We describe a Mars `Micro Mission' for detailed study of the martian satellites Phobos and Deimos. The mission involves two mini-spacecraft equipped with solar electric propulsion to reach Mars orbit. Two spacecraft are stacked for launch: an orbiter for remote investigation of the moons and in situ studies of their environment in Mars orbit, and another carrying a lander for in situ measurements on the surface of Phobos (or alternatively Deimos). Phobos and Deimos remain only partially studied, and Deimos less well than Phobos. Mars has almost always been the primary mission objective, while the more dedicated Phobos project (1988-89) failed to realise its full potential. Many questions remain concerning the moons' origins, evolution, physical nature and composition. Current missions such as Mars Express are due to extend our knowledge of Phobos in some areas but largely neglect Deimos. The objectives of M-PADS focus on: origins and evolution, interactions with Mars, volatiles and interiors, surface features, and differences. The consequent measurement requirements imply both landed and remote sensing payloads. M-PADS is expected to accommodate a 60 kg orbital payload and a 16 kg lander payload.

  20. Mars Phobos and Deimos Survey (M-PADS) A martian Moons orbiter and Phobos lander

    NASA Astrophysics Data System (ADS)

    Ball, Andrew J.; Price, Michael E.; Walker, Roger J.; Dando, Glyn C.; Wells, Nigel S.; Zarnecki, John C.

    2009-01-01

    We describe a Mars ‘Micro Mission’ for detailed study of the martian satellites Phobos and Deimos. The mission involves two ˜330 kg spacecraft equipped with solar electric propulsion to reach Mars orbit. The two spacecraft are stacked for launch: an orbiter for remote investigation of the moons and in situ studies of their environment in Mars orbit, and another carrying a lander for in situ measurements on the surface of Phobos (or alternatively Deimos). Phobos and Deimos remain only partially studied, and Deimos less well than Phobos. Mars has almost always been the primary mission objective, while the more dedicated Phobos project (1988 89) failed to realise its full potential. Many questions remain concerning the moons’ origins, evolution, physical nature and composition. Current missions, such as Mars Express, are extending our knowledge of Phobos in some areas but largely neglect Deimos. The objectives of M-PADS focus on: origins and evolution, interactions with Mars, volatiles and interiors, surface features, and differences. The consequent measurement requirements imply both landed and remote sensing payloads. M-PADS is expected to accommodate a 60 kg orbital payload and a 16 kg lander payload. M-PADS resulted from a BNSC-funded study carried out in 2003 to define candidate Mars Micro Mission concepts for ESA’s Aurora programme.

  1. ARIM-1: The Atmospheric Refractive Index Measurements Sounding Rocket Mission

    NASA Technical Reports Server (NTRS)

    Ruiz, B. Ian (Editor)

    1995-01-01

    A conceptual design study of the ARIM-1 sounding rocket mission, whose goal is to study atmospheric turbulence in the tropopause region of the atmosphere, is presented. The study was conducted by an interdisciplinary team of students at the University of Alaska Fairbanks who were enrolled in a Space Systems Engineering course. The implementation of the ARIM-1 mission will be carried out by students participating in the Alaska Student Rocket Program (ASRP), with a projected launch date of August 1997. The ARIM-1 vehicle is a single stage sounding rocket with a 3:1 ogive nose cone, a payload diameter of 8 in., a motor diameter of 7.6 in., and an overall height of 17.0 ft including the four fins. Emphasis is placed on standardization of payload support systems. The thermosonde payload will measure the atmospheric turbulence by direct measurement of the temperature difference over a distance of one meter using two 3.45-micron 'hot-wire' probes. The recovery system consists of a 6 ft. diameter ribless guide surface drogue chute and a 33 ft. diameter main cross parachute designed to recover a payload of 31 pounds and slow its descent rate to 5 m/s through an altitude of 15 km. This document discusses the science objectives, mission analysis, payload mechanical configuration and structural design, recovery system, payload electronics, ground station, testing plans, and mission implementation.

  2. Program control on the Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    Pennington, Dorothy J.; Majerowicw, Walter

    1994-01-01

    The Tropical Rainfall Measuring Mission (TRMM), an integral part of NASA's Mission to Planet Earth, is the first satellite dedicated to measuring tropical rainfall. TRMM will contribute to an understanding of the mechanisms through which tropical rainfall influences global circulation and climate. Goddard Space Flight Center's (GSFC) Flight Projects Directorate is responsible for establishing a Project Office for the TRMM to manage, coordinate, and integrate the various organizations involved in the development and operation of this complex satellite. The TRMM observatory, the largest ever developed and built inhouse at GSFC, includes state-of-the-art hardware. It will carry five scientific instruments designed to determine the rate of rainfall and the total rainfall occurring between the north and south latitudes of 35 deg. As a secondary science objective, TRMM will also measure the Earth's radiant energy budget and lightning.

  3. ATMOS: Long term atmospheric measurements for mission to planet Earth

    NASA Technical Reports Server (NTRS)

    1992-01-01

    A long-term, space-based measurement program, together with continued balloon and aircraft-borne investigations, is essential to monitor the predicted effects in the atmosphere, to determine to what extent the concentration measurements agree with current models of stratospheric chemistry, and to determine the condition of the ozone layer. The Atmospheric Trace Molecule Spectroscopy (ATMOS) Experiment is currently making comprehensive, global measurements of Earth's atmosphere as part of the Atmospheric Laboratory for Applications and Science (ATLAS) program on the Space Shuttle. Part of NASA's Mission to Planet Earth, ATLAS is a continuing series of missions to study Earth and the Sun and provide a more fundamental understanding of the solar influences on Earth's atmosphere. The ATMOS program, instruments, and science results are presented.

  4. Robotic Lander Prototype Completes Initial Tests

    NASA Video Gallery

    NASA's Robotic Lunar Lander Development Project at Marshall Space Flight Center in Huntsville, Ala., completed an initial series of integrated tests on a new lander prototype. The prototype lander ...

  5. The ExoMars 2016 mission

    NASA Astrophysics Data System (ADS)

    Svedhem, Håkan; Vago, Jorge; de Groot, Rolf

    2015-11-01

    The ExoMars programme is a joint activity by 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, Schiaparelli, and the Exomars 2018 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 for search of subsurface hydrogen. ESA is providing the TGO spacecraft and the Schiaparelli Lander demonstrator and two of the TGO instruments and ROSCOSMOS is providing the launcher and the other two TGO instruments.After the arrival of the ExoMars 2018 mission at the surface of Mars, the TGO will handle the communication between the Earth and the Rover and lander through its UHF communication system. The 2016 mission will be launched by a Russian Proton rocket from Baikonur in January 2016 and will arrive at Mars in October the same year. This presentation will cover a description of the 2016 mission, including the spacecraft, its payload and science and the related plans for scientific operations and measurements.

  6. Science potential from a Europa lander.

    PubMed

    Pappalardo, R T; Vance, S; Bagenal, F; Bills, B G; Blaney, D L; Blankenship, D D; Brinckerhoff, W B; Connerney, J E P; Hand, K P; Hoehler, T M; Leisner, J S; Kurth, W S; McGrath, M A; Mellon, M T; Moore, J M; Patterson, G W; Prockter, L M; Senske, D A; Schmidt, B E; Shock, E L; Smith, D E; Soderlund, K M

    2013-08-01

    The prospect of a future soft landing on the surface of Europa is enticing, as it would create science opportunities that could not be achieved through flyby or orbital remote sensing, with direct relevance to Europa's potential habitability. Here, we summarize the science of a Europa lander concept, as developed by our NASA-commissioned Science Definition Team. The science concept concentrates on observations that can best be achieved by in situ examination of Europa from its surface. We discuss the suggested science objectives and investigations for a Europa lander mission, along with a model planning payload of instruments that could address these objectives. The highest priority is active sampling of Europa's non-ice material from at least two different depths (0.5-2 cm and 5-10 cm) to understand its detailed composition and chemistry and the specific nature of salts, any organic materials, and other contaminants. A secondary focus is geophysical prospecting of Europa, through seismology and magnetometry, to probe the satellite's ice shell and ocean. Finally, the surface geology can be characterized in situ at a human scale. A Europa lander could take advantage of the complex radiation environment of the satellite, landing where modeling suggests that radiation is about an order of magnitude less intense than in other regions. However, to choose a landing site that is safe and would yield the maximum science return, thorough reconnaissance of Europa would be required prior to selecting a scientifically optimized landing site. PMID:23924246

  7. Science potential from a Europa lander.

    PubMed

    Pappalardo, R T; Vance, S; Bagenal, F; Bills, B G; Blaney, D L; Blankenship, D D; Brinckerhoff, W B; Connerney, J E P; Hand, K P; Hoehler, T M; Leisner, J S; Kurth, W S; McGrath, M A; Mellon, M T; Moore, J M; Patterson, G W; Prockter, L M; Senske, D A; Schmidt, B E; Shock, E L; Smith, D E; Soderlund, K M

    2013-08-01

    The prospect of a future soft landing on the surface of Europa is enticing, as it would create science opportunities that could not be achieved through flyby or orbital remote sensing, with direct relevance to Europa's potential habitability. Here, we summarize the science of a Europa lander concept, as developed by our NASA-commissioned Science Definition Team. The science concept concentrates on observations that can best be achieved by in situ examination of Europa from its surface. We discuss the suggested science objectives and investigations for a Europa lander mission, along with a model planning payload of instruments that could address these objectives. The highest priority is active sampling of Europa's non-ice material from at least two different depths (0.5-2 cm and 5-10 cm) to understand its detailed composition and chemistry and the specific nature of salts, any organic materials, and other contaminants. A secondary focus is geophysical prospecting of Europa, through seismology and magnetometry, to probe the satellite's ice shell and ocean. Finally, the surface geology can be characterized in situ at a human scale. A Europa lander could take advantage of the complex radiation environment of the satellite, landing where modeling suggests that radiation is about an order of magnitude less intense than in other regions. However, to choose a landing site that is safe and would yield the maximum science return, thorough reconnaissance of Europa would be required prior to selecting a scientifically optimized landing site.

  8. Northeast View From Pathfinder Lander - Anaglyph

    NASA Technical Reports Server (NTRS)

    1997-01-01

    This panorama of the region to the northeast of the lander was constructed to support the Sojourner Rover Team's plans to conduct an 'autonomous traverse' to explore the terrain away from the lander after science objectives in the lander vicinity had been met. The large, relatively bright surface in the foreground, about 10 meters (33 feet) from the spacecraft, in this scene is 'Baker's Bench.' The large, elongated rock left of center in the middle distance is 'Zaphod.'

    This anaglyph view was produced by combining the left and right eye mosaics (above) by assigning the left eye view to the red color plane and the right eye view to the green and blue color planes (cyan), to produce a stereo anaglyph mosaic. This mosaic can be viewed in 3-D on your computer monitor or in color print form by wearing red-blue 3-D glasses.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages the Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is a division of the California Institute of Technology (Caltech). The IMP was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal Investigator.

    Click below to see the left and right views individually. [figure removed for brevity, see original site] Left [figure removed for brevity, see original site] Right

  9. NASA's Global Precipitation Measurement (GPM) Mission for Science and Society

    NASA Astrophysics Data System (ADS)

    Jackson, Gail

    2016-04-01

    Water is fundamental to life on Earth. Knowing where and how much rain and snow falls globally is vital to understanding how weather and climate impact both our environment and Earth's water and energy cycles, including effects on agriculture, fresh water availability, and responses to natural disasters. The Global Precipitation Measurement (GPM) Mission, launched February 27, 2014, is an international satellite mission to unify and advance precipitation measurements from a constellation of research and operational sensors to provide "next-generation" precipitation products. The joint NASA-JAXA GPM Core Observatory serves as the cornerstone and anchor to unite the constellation radiometers. The GPM Core Observatory carries a Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a multi-channel (10-183 GHz) GPM Microwave Radiometer (GMI). Furthermore, since light rain and falling snow account for a significant fraction of precipitation occurrence in middle and high latitudes, the GPM instruments extend the capabilities of the TRMM sensors to detect falling snow, measure light rain, and provide, for the first time, quantitative estimates of microphysical properties of precipitation particles. As a science mission with integrated application goals, GPM is designed to (1) advance precipitation measurement capability from space through combined use of active and passive microwave sensors, (2) advance the knowledge of the global water/energy cycle and freshwater availability through better description of the space-time variability of global precipitation, and (3) improve weather, climate, and hydrological prediction capabilities through more accurate and frequent measurements of instantaneous precipitation rates and time-integrated rainfall accumulation. Since launch, the instruments have been collecting outstanding precipitation data. New scientific insights resulting from GPM data, an overview of the GPM mission concept and science activities in the United States

  10. Global Precipitation Measurement (GPM) Mission Applications: Activities, Challenges, and Vision

    NASA Technical Reports Server (NTRS)

    Kirschbaum, Dalia; Hou, Arthur

    2012-01-01

    Global Precipitation Measurement (GPM) is an international satellite mission to provide nextgeneration observations of rain and snow worldwide every three hours. NASA and the Japan Aerospace Exploration Agency (JAXA) will launch a "Core" satellite carrying advanced instruments that will set a new standard for precipitation measurements from space. The data they provide will be used to unify precipitation measurements made by an international network of partner satellites to quantify when, where, and how much it rains or snows around the world. The GPM mission will help advance our understanding of Earth's water and energy cycles, improve the forecasting of extreme events that cause natural disasters, and extend current capabilities of using satellite precipitation information to directly benefit society. Building upon the successful legacy of the Tropical Rainfall Measuring Mission (TRMM), GPM's next-generation global precipitation data will lead to scientific advances and societal benefits within a range of hydrologic fields including natural hazards, ecology, public health and water resources. This talk will highlight some examples from TRMM's IS-year history within these applications areas as well as discuss some existing challenges and present a look forward for GPM's contribution to applications in hydrology.

  11. Global Precipitation Measurement (GPM) Mission Applications: Activities, challenges, and vision

    NASA Astrophysics Data System (ADS)

    Kirschbaum, D. B.; Hou, A. Y.

    2012-12-01

    Global Precipitation Measurement (GPM) is an international satellite mission to provide next-generation observations of rain and snow worldwide every three hours. NASA and the Japan Aerospace Exploration Agency (JAXA) will launch a "Core" satellite carrying advanced instruments that will set a new standard for precipitation measurements from space. The data they provide will be used to unify precipitation measurements made by an international network of partner satellites to quantify when, where, and how much it rains or snows around the world. The GPM mission will help advance our understanding of Earth's water and energy cycles, improve the forecasting of extreme events that cause natural disasters, and extend current capabilities of using satellite precipitation information to directly benefit society. Building upon the successful legacy of the Tropical Rainfall Measuring Mission (TRMM), GPM's next-generation global precipitation data will lead to scientific advances and societal benefits within a range of hydrologic fields including natural hazards, ecology, public health and water resources. This talk will highlight some examples from TRMM's 15-year history within these applications areas as well as discuss some existing challenges and present a look forward for GPM's contribution to applications in hydrology.

  12. Lunar lander stage requirements based on the Civil Needs Data Base

    NASA Technical Reports Server (NTRS)

    Mulqueen, John A.

    1992-01-01

    This paper examines the lunar lander stages that will be necessary for the future exploration and development of the Moon. Lunar lander stage sizing is discussed based on the projected lunar payloads listed in the Civil Needs Data Base. Factors that will influence the lander stage design are identified and discussed. Some of these factors are (1) lunar orbiting and lunar surface lander bases; (2) implications of direct landing trajectories and landing from a parking orbit; (3) implications of landing site and parking orbit; (4) implications of landing site and parking orbit selection; (5) the use of expendable and reusable lander stages; and (6) the descent/ascent trajectories. Data relating the lunar lander stage design requirements to each of the above factors and others are presented in parametric form. These data will provide useful design data that will be applicable to future mission model modifications and design studies.

  13. Summary of Global lightning and sprite measurements (GLIMS) mission

    NASA Astrophysics Data System (ADS)

    Ushio, T.; Kikuchi, H.; Sato, M.; Morimoto, T.; Suzuki, M.; Yamazaki, A.; Hobara, Y.; Kikuchi, M.; Adachi, T.; Takahashi, Y.

    2015-12-01

    The Global lightning and sprite measurements (GLIMS) mission aims to study the generation mechanism of lightning-associated transient luminous events (TLEs) and the relationship between lightning and TLEs. Four types of sensors attached to the International Space Station are used to observe a lightning and TLEs. All four types of sensors work synchronously. Two complementary-metal-oxide semiconductor cameras at two different wavelengths (lightning and sprite imager: LSI) are used to capture a position of optical emission from lightning and TLEs. Six photometers at six different wavelengths (PHs) record an optical emission intensity at high temporal resolution. Each photometer works to detect an altitude of optical mission through the use of the optical spectrum that are absorbed by atmospheric gases. A very low frequency (VLF) receiver is used for recording Whistler mode waves from lightning. Very high frequency interferometer (VITF) with two VHF sensors estimates the radiation source direction using phase interference technique. In JEM-GLIMS mission, it is notable that it is possible to conduct a simultaneous observation of optical and radio instruments. The mission has been conducted since November 2012. In this paper, we will show the findings of experimental work conducted during the past 3 years (2013-2015).

  14. The ROSETTA PHILAE Lander damping mechanism as probe for the Comet soil strength.

    NASA Astrophysics Data System (ADS)

    Roll, R.

    2015-10-01

    The ROSETTA Lander is equipped with an one axis damping mechanism to dissipate kinetic energy during the touch down. This damping is necessary to avoid damages to the Lander by a hard landing shock and more important to avoid re-bouncing from ground with high velocity. The damping mechanism works best for perpendicular impact, which means the velocity vector is parallel to the damper axis and all three feet touch the ground at the same time. That is usually not the case. Part of the impact energy can be transferred into rotational energy at ground contact if the impact is not perpendicular. This energy will lift up the Lander from the ground if the harpoons and the hold down thruster fail, as happen in mission. The damping mechanism itself is an electrical generator, driven by a spindle inside a telescopic tube. This tube was extended in mission for landing by 200mm. A maximum damping length of 140mm would be usually required to compensate a landing velocity of 1m/s, if the impact happens perpendicular on hard ground. After landing the potentiometer of the telescopic tube reading shows a total damping length of only 42,5mm. The damping mechanism and the overall mechanical behavior of the Lander at touch down are well tested and characterized and transferred to a multi-body computer model. The incoming and outgoing flightpath of PHILAE allow via computer-simulation the reconstruction of the touch down. It turns out, that the outgoing flight direction is dominated by the local ground slope and that the damping length is strongly dependent on the soil strength. Damping of soft comet ground must be included to fit the damping length measured. Scenario variations of the various feet contact with different local surface features (stone or regolith) and of different soil models finally lead to a restricted range for the soil strength at the touch down area.

  15. Validation procedure for GOCE mission using balloon borne gradient measurements

    NASA Astrophysics Data System (ADS)

    Latka, J.

    2003-04-01

    VALIDATION PROCEDURE FOR GOCE MISSION USING BALLOON BORNE GRADIENT MEASUREMENTS. J.K.Latka (1) (1)Space Research Centre PAS jkl@cbk.waw.pl VALIDATION PROCEDURE FOR GOCE MISSION USING BALLOON BORNE GRADIENT MEASUREMENTS. J.K.Latka (1) (1)Space Research Centre PAS jkl@cbk.waw.pl Amelioration of the global mode of the EARTH gravity field is the aim of the satellite mission GOCE. In order to accomplish such a task,especially careful investigation of experiment itself errors ought to be made. Validation of the results is one of the important tasks. Together with the laboratory calibration they will give the estimation of experiment systematic errors. There are several concepts of a validation process. One of them is the measurement of the gradients using a gradiometer situated on board of a balloon travelling in the Mediterranean area, from Sicily to Spain. Upward continuation procedure should give data for comparisons with GOCE results. In the paper the method of least square collocation is presented as a tool for upward continuation. For calculations one use the simulated values of gradients. The covriance function is based on the models of the Earth gravity field. The models EGM96,OSU81 and their modifications are used.

  16. Rosetta Lander - Philae: First Landing and Operations on a Comet

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Biele, Jens; Delmas, Cedric; Fantinati, Cinzia; Gaudon, Philippe; Geurts, Koen; Jurado, Eric; Lommatsch, Valentina; Maibaum, Michael; Moussi-Soffys, Aurélie; Salatti, Mario

    2015-04-01

    Philae is a comet Lander, part of Rosetta which is a Cornerstone Mission of the ESA Horizon 2000 programme. In August 2014 Rosetta did rendezvous with comet 67P/Churyumov-Gerasimenko (CG) after a 10 year cruise. Both its nucleus and coma have been studied allowing the selection of a landing site for Philae. Philae was separated from the Rosetta main spacecraft on November 12, 2014 and touched the comet surface after seven hours of descent. After several bounces it came to rest and continued to send scientific data to Earth. All ten instruments of its payload have been operated at least once. Due to the fact that the Lander could not be anchored, the originally planned first scientific sequence had to be modified. Philae went into hibernation on November 15th, after its primary battery ran out of energy. Re-activation of the Lander is expected in spring/summer 2015 when CG is closer to the sun and the solar generator of Philae will provide more power. The paper will give an overview of separation, descent and landing, the search for the final landing spot as well as Lander operations after separation. Rosetta is an ESA mission with contributions from its member states and NASA. Rosetta's Philae lander is provided by a consortium led by DLR, MPS, CNES and ASI with additional contributions from Hungary, UK, Finland, Ireland and Austria.

  17. Technology development for long-lived Venus landers.

    NASA Astrophysics Data System (ADS)

    Ekonomov, 1.; Korablev, O.; Zasova, L.

    2007-08-01

    Simultaneously with many successful lander missions on Venus in 1972-1985 Soviet Union began develop long-lived lander on surface of Venus. The basic problem were extreme conditions on a surface: P=10MPa, T=500 C . Then operations have been stopped and have renewed in 2006 already in new Russia. Mission "VENERA (VENUS) - D" is included into the Federal space program of Russia on 2006 - 2015 with launch in 2016. To this date Russia alone can't create a reliable electronics for 500 C, but we have got examples GaN electronics for 350 C. Cooling technology with boiling water is offered for interior devices of lander at pressure 10 MPa and temperature 310 C. As the power source of an electronics we use high-temperature galvanic cells on the base of Li4Si [LiCl, KCl, LiF] FeS2 which are released in Russia as reserve power sources. They are capable to work directly on a surface of Venus without any thermal protection. At lander two kinds of vacuum technology can be used: 1) in multilayer (MLI ) thermal blanket for lander, 2) in electro-vacuum devices, for example transmitter . For creation and maintenance of vacuum at temperature 400-500 C: chemical gas absorbers ( getter materials ) are used, they actively absorb both carbon dioxide and nitrogen .

  18. Phoenix Lander on Mars with Surrounding Terrain, Polar Projection

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This view is a polar projection that combines more than 500 exposures taken by the Surface Stereo Imager camera on NASA's Mars Phoenix Lander and projects them as if looking down from above.

    The black circle on the spacecraft is where the camera itself is mounted on the lander, out of view in images taken by the camera. North is toward the top of the image. The lander's meteorology mast extends above the southwest horzon and is topped by the telltale wind gauge.

    The ground surface around the lander has polygonal patterning similar to patterns in permafrost areas on Earth. The landing site is at 68.22 degrees north latitude, 234.25 degrees east longitude on Mars.

    This view in approximately true color comprises more than 100 different Stereo Surface Imager pointings, with images taken through three different filters at each pointing. The images were taken throughout the period from the 13th Martian day, or sol, after landing to the 47th sol (June 5 through July 12, 2008). The lander's Robotic Arm is cut off in this mosaic view because component images were taken when the arm was out of the frame.

    The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

  19. Multiple asteroid rendezvous missions

    NASA Technical Reports Server (NTRS)

    Bender, D. F.; Friedlander, A. L.

    1979-01-01

    Asteroid missions, centered on multiple asteroid rendezvous missions to main belt asteroids, are discussed and the required solar electric propulsion for these missions as well as the current performance estimates are examined. A brief statistical analysis involving asteroid availability transfer requirements and propulsion system capabilities is given, leading to a prediction that 5 to 8 asteroids can be encountered with a single launch. Measurement techniques include visual imaging, radio tracking, magnetometry, and in the case of landers, seismometry. The spacecraft will be propelled by a solar electric system with a power level of 25 kW to 40 kW and tour possibilities for 13 different asteroids have been developed. Preliminary estimates of asteroid triaxiality are made to calculate the effect of close orbits.

  20. Remote Raman System for Planetary Landers: Data Reduction and Analysis

    NASA Technical Reports Server (NTRS)

    Horton, K. A.; Domergue-Schmidt, N.; Sharma, S. K.; Deb, P.; Lucey, P. G.

    2000-01-01

    Raman spectroscopy is typically envisioned as an in situ analysis technique. Raman spectra measured remotely (10s of meters) from a planetary lander can be calibrated to spectral radiance and the Raman scattering efficiency can be determined.

  1. Initiating the Surface Ops Phase of the Lunar Exploration Architecture with Robotic Landers and Rovers

    NASA Astrophysics Data System (ADS)

    Kring, D. A.; Rademacher, J.

    2007-03-01

    The Lunar Reconnaissance Lander and Lunar Surface Explorer provide low-cost, science- and exploration-rich solutions for multiple mission objectives in a strategy that maximizes the efficiency of the lunar exploration initiative and provides access to the

  2. The Chang'e 3 Mission Overview

    NASA Astrophysics Data System (ADS)

    Li, Chunlai; Liu, Jianjun; Ren, Xin; Zuo, Wei; Tan, Xu; Wen, Weibin; Li, Han; Mu, Lingli; Su, Yan; Zhang, Hongbo; Yan, Jun; Ouyang, Ziyuan

    2015-07-01

    The Chang'e 3 (CE-3) mission was implemented as the first lander/rover mission of the Chinese Lunar Exploration Program (CLEP). After its successful launch at 01:30 local time on December 2, 2013, CE-3 was inserted into an eccentric polar lunar orbit on December 6, and landed to the east of a 430 m crater in northwestern Mare Imbrium (19.51°W, 44.12°N) at 21:11 on December 14, 2013. The Yutu rover separated from the lander at 04:35, December 15, and traversed for a total of 0.114 km. Acquisition of science data began during the descent of the lander and will continue for 12 months during the nominal mission. The CE-3 lander and rover each carry four science instruments. Instruments on the lander are: Landing Camera (LCAM), Terrain Camera (TCAM), Extreme Ultraviolet Camera (EUVC), and Moon-based Ultraviolet Telescope (MUVT). The four instruments on the rover are: Panoramic Camera (PCAM), VIS-NIR Imaging Spectrometer (VNIS), Active Particle induced X-ray Spectrometer (APXS), and Lunar Penetrating Radar (LPR). The science objectives of the CE-3 mission include: (1) investigation of the morphological features and geological structures of and near the landing area; (2) integrated in-situ analysis of mineral and chemical composition of and near the landing area; and (3) exploration of the terrestrial-lunar space environment and lunar-based astronomical observations. This paper describes the CE-3 objectives and measurements that address the science objectives outlined by the Comprehensive Demonstration Report of Phase II of CLEP. The CE-3 team has archived the initial science data, and we describe data accessibility by the science community.

  3. Attitude reconstruction of ROSETTA's Lander PHILAE using two-point magnetic field observations by ROMAP and RPC-MAG

    NASA Astrophysics Data System (ADS)

    Heinisch, Philip; Auster, Hans-Ulrich; Richter, Ingo; Hercik, David; Jurado, Eric; Garmier, Romain; Güttler, Carsten; Glassmeier, Karl-Heinz

    2016-08-01

    As part of the European Space Agency's ROSETTA Mission the Lander PHILAE touched down on comet 67P/Churyumov-Gerasimenko on November 12, 2014. The magnetic field has been measured onboard the orbiter and the lander. The orbiter's tri-axial fluxgate magnetometer RPC-MAG is one of five sensors of the ROSETTA Plasma Consortium. The lander is also equipped with a tri-axial fluxgate magnetometer as part of the ROSETTA Lander Magnetometer and Plasma-Monitor package (ROMAP). This unique setup makes a two point measurement between the two spacecrafts in a relatively small distance of less than 50 km possible. Both magnetometers were switched on during the entire descent, the initial touchdown, the bouncing between the touchdowns and after the final touchdown. We describe a method for attitude determination by correlating magnetic low-frequency waves, which was tested under different conditions and finally used to reconstruct PHILAE's attitude during descent and after landing. In these cases the attitude could be determined with an accuracy of better than ± 5 °. These results were essential not only for PHILAE operations planning but also for the analysis of the obtained scientific data, because nominal sources for this information, like solar panel currents and camera pictures could not provide sufficient information due to the unexpected landing position.

  4. Global Precipitation Measurement (GPM) Mission: Overview and Status

    NASA Technical Reports Server (NTRS)

    Hou, Arthur Y.

    2012-01-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission specifically designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors. NASA and JAXA will deploy a Core Observatory in 2014 to serve as a reference satellite to unify precipitation measurements from the constellation of sensors. The GPM Core Observatory will carry a Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a conical-scanning multi-channel (10-183 GHz) GPM Microwave Radiometer (GMI). The DPR will be the first dual-frequency radar in space to provide not only measurements of 3-D precipitation structures but also quantitative information on microphysical properties of precipitating particles. The DPR and GMI measurements will together provide a database that relates vertical hydrometeor profiles to multi-frequency microwave radiances over a variety of environmental conditions across the globe. This combined database will be used as a common transfer standard for improving the accuracy and consistency of precipitation retrievals from all constellation radiometers. For global coverage, GPM relies on existing satellite programs and new mission opportunities from a consortium of partners through bilateral agreements with either NASA or JAXA. Each constellation member may have its unique scientific or operational objectives but contributes microwave observations to GPM for the generation and dissemination of unified global precipitation data products. In addition to the DPR and GMI on the Core Observatory, the baseline GPM constellation consists of the following sensors: (1) Special Sensor Microwave Imager/Sounder (SSMIS) instruments on the U.S. Defense Meteorological Satellite Program (DMSP) satellites, (2) the Advanced Microwave Scanning Radiometer-2 (AMSR-2) on the GCOM-W1 satellite of JAXA, (3) the Multi-Frequency Microwave Scanning Radiometer (MADRAS) and the multi-channel microwave humidity sounder

  5. Atmospheric Measurements by the 2002 Geoscience Laser Altimeter System Mission

    NASA Technical Reports Server (NTRS)

    Spinhirne, James D.; Starr, David OC. (Technical Monitor)

    2002-01-01

    The NASA Earth Observing System (EOS) program is a multiple platform NASA initiative for the study of global change. As part of the EOS project, the Geoscience Laser Altimeter System (GLAS) was selected as a laser sensor filling complementary requirements for several earth science disciplines including atmospheric and surface applications. Late in 2002, the GaAs instrument is to be launched for a three to five year observational mission. For the atmosphere, the instrument is designed to full fill comprehensive requirements for profiling of radiatively significant cloud and aerosol. Algorithms have been developed to process the cloud and aerosol data and provide standard data products. After launch there will be a three-month project to analyze and understand the system performance and accuracy of the data products. As an EOS mission, the GaAs measurements and data products will be openly available to all investigators. An overview of the instrument, data products and evaluation plan is given.

  6. Ground truth observations for TRMM. [Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    Thiele, Otto W.

    1989-01-01

    Plans to obtain ground truth data for the validation of the Tropical Rainfall Measuring Mission (TRMM) are examined. The experimental rainfall measuring techniques considered for the program are discussed, including optical and Doppler rain gages, satellite beacon attenuation, underwater hydrophones, profilers, microwave attenuation, multiple frequency/polarization radar, and scanning and airborne Doppler radar. The TRMM validation program is considered, noting observations to compare averaged TRMM rainfall data with similar ground truth data and to compare the rainfall and height distribution data from TRMM with instantaneous ground truth data.

  7. NASA's International Lunar Network Anchor Nodes and Robotic Lunar Lander Project Update

    NASA Technical Reports Server (NTRS)

    Cohen, Barbara A.; Bassler, Julie A.; Ballard, Benjamin; Chavers, Greg; Eng, Doug S.; Hammond, Monica S.; Hill, Larry A.; Harris, Danny W.; Hollaway, Todd A.; Kubota, Sanae; Morse, Brian J.; Mulac, Brian D.; Reed, Cheryl L.

    2010-01-01

    NASA Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory have been conducting mission studies and performing risk reduction activities for NASA's robotic lunar lander flight projects. Additional mission studies have been conducted to support other objectives of the lunar science and exploration community and extensive risk reduction design and testing has been performed to advance the design of the lander system and reduce development risk for flight projects.

  8. Command and data management system (CDMS) of the Philae lander

    NASA Astrophysics Data System (ADS)

    Balázs, A.; Baksa, A.; Bitterlich, H.; Hernyes, I.; Küchemann, O.; Pálos, Z.; Rustenbach, J.; Schmidt, W.; Spányi, P.; Sulyán, J.; Szalai, S.; Várhalmi, L.

    2016-08-01

    The paper covers the principal requirements, design concepts and implementation of the hardware and software for the central on-board computer (CDMS) of the Philae lander in the context of the ESA Rosetta space mission, including some technical details. The focus is on the implementation of fault tolerance, autonomous operation and operational flexibility by means of specific linked data structures and code execution mechanisms that can be interpreted as a kind of object oriented model for mission sequencing.

  9. Development of an Audio Microphone for the Mars Surveyor 98 Lander

    NASA Astrophysics Data System (ADS)

    Delory, G. T.; Luhmann, J. G.; Curtis, D. W.; Friedman, L. D.; Primbsch, J. H.; Mozer, F. S.

    1998-01-01

    In December 1999, the next Mars Surveyor Lander will bring the first microphone to the surface of Mars. The Mars Microphone represents a joint effort between the Planetary Society and the University of California at Berkeley Space Sciences Laboratory and is riding on the lander as part of the LIDAR instrument package provided by the Russian Academy of Sciences in Moscow. The inclusion of a microphone on the Mars Surveyor Lander represents a unique opportunity to sample for the first time the acoustic environment on the surface, including both natural and lander-generated sounds. Sounds produced by martian meteorology are among the signals to be recorded, including wind and impacts of sand particles on the instrument. Photographs from the Viking orbiters as well as Pathfinder images show evidence of small tornado-like vortices that may be acoustically detected, along with noise generated by static discharges possible during sandstorms. Lander-generated sounds that will be measured include the motion and digging of the lander arm as it gathers soil samples for analysis. Along with these scientific objectives, the Mars Microphone represents a powerful tool for public outreach by providing sound samples on the Internet recorded during the mission. The addition of audio capability to the lander brings us one step closer to a true virtual presence on the Mars surface by complementing the visual capabilities of the Mars Surveyor cameras. The Mars Microphone is contained in a 5 x 5 x 1 cm box, weighs less than 50 g, and uses 0.1 W of power during its most active times. The microphone used is a standard hearing-aid electret. The sound sampling and processing system relies on an RSC-164 speech processor chip, which performs 8-bit A/ D sampling and sound compression. An onboard flight program enables several modes for the instrument, including varying sample ranges of 5 kHz and 20 kHz, and a selectable gain setting with 64x dynamic range. The device automatically triggers on

  10. Battery and Fuel Cell Development Goals for the Lunar Surface and Lander

    NASA Technical Reports Server (NTRS)

    Mercer, Carolyn R.

    2008-01-01

    NASA is planning a return to the moon and requires advances in energy storage technology for its planned lunar lander and lunar outpost. This presentation describes NASA s overall mission goals and technical goals for batteries and fuel cells to support the mission. Goals are given for secondary batteries for the lander s ascent stage and suits for extravehicular activity on the lunar surface, and for fuel cells for the lander s descent stage and regenerative fuel cells for outpost power. An overall approach to meeting these goals is also presented.

  11. Scientific preparations for lunar exploration with the European Lunar Lander

    NASA Astrophysics Data System (ADS)

    Carpenter, J. D.; Fisackerly, R.; De Rosa, D.; Houdou, B.

    2012-12-01

    Recent Lunar missions and new scientific results in multiple disciplines have shown that working and operating in the complex lunar environment and exploiting the Moon as a platform for scientific research and further exploration poses major challenges. Underlying these challenges are fundamental scientific unknowns regarding the Moon's surface, its environment, the effects of this environment and the availability of potential resources. The European Lunar Lander is a mission proposed by the European Space Agency to prepare for future exploration. The mission provides an opportunity to address some of these key unknowns and provide information of importance for future exploration activities. Areas of particular interest for investigation on the Lunar Lander include the integrated plasma, dust, charge and radiation environment and its effects, the properties of lunar dust and its physical effects on systems and physiological effects on humans, the availability, distribution and potential application of in situ resources for future exploration. A model payload has then been derived, taking these objectives to account and considering potential payloads proposed through a request for information, and the mission's boundary conditions. While exploration preparation has driven the definition there is a significant synergy with investigations associated with fundamental scientific questions. This paper discusses the scientific objectives for the ESA Lunar Lander Mission, which emphasise human exploration preparatory science and introduces the model scientific payload considered as part of the on-going mission studies, in advance of a formal instrument selection.

  12. Life Sciences Investigations for ESA's First Lunar Lander

    NASA Astrophysics Data System (ADS)

    Carpenter, J. D.; Angerer, O.; Durante, M.; Linnarson, D.; Pike, W. T.

    2010-12-01

    Preparing for future human exploration of the Moon and beyond is an interdisciplinary exercise, requiring new technologies and the pooling of knowledge and expertise from many scientific areas. The European Space Agency is working to develop a Lunar Lander, as a precursor to future human exploration activities. The mission will demonstrate new technologies and perform important preparatory investigations. In the biological sciences the two major areas requiring investigation in advance of human exploration are radiation and its effects on human physiology and the potential toxicity of lunar dust. This paper summarises the issues associated with these areas and the investigations planned for the Lunar Lander to address them.

  13. Earthquake-Lightning Signature Probed by Tropical Rainfall Measuring Mission

    NASA Astrophysics Data System (ADS)

    Lee, Hao; Liu, Jann-Yenq Tiger

    2016-04-01

    The lightning activity is one of the key parameters to understand the atmospheric electric fields near the Earth's surface and the lithosphere-atmosphere-ionosphere coupling during the earthquake preparation period. A statistical study shows more lightning before magnitude M>=5.0 earthquakes in Taiwan during 1993-2004. In this paper, the Lightning Imaging Sensor (LIS) onboard Tropical Rainfall Measuring Mission (TRMM) is used to statistically exam the lightning activity 30 days before and after 198 M>=7.0 earthquakes in the tropical area of the globe during the 17-year period of 1988-2014. The statistical results show that lightning activities over epicenter significantly enhance before the earthquakes.

  14. Connecting the Dots: Lander, Heat Shield, Parachute

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This enhanced-color image from Mars Reconnaissance Orbiter's High Resolution Imaging Science Experiment (HiRISE) camera shows the Phoenix landing area viewed from orbit. The spacecraft appears more blue than it would in reality. From top to bottom are the Phoenix lander with its solar panels deployed on the Martian surface, the heat shield and bounce mark the heat shield made on the Martian surface, and the top of the Phoenix parachute attached to the bottom of the back shell.

    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.

  15. Testing Phoenix Mars Lander Parachute in Idaho

    NASA Technical Reports Server (NTRS)

    2008-01-01

    NASA's Phoenix Mars Lander will parachute for nearly three minutes as it descends through the Martian atmosphere on May 25, 2008. Extensive preparations for that crucial period included this drop test near Boise, Idaho, in October 2006.

    The parachute used for the Phoenix mission is similar to ones used by NASA's Viking landers in 1976. It is a 'disk-gap-band' type of parachute, referring to two fabric components -- a central disk and a cylindrical band -- separated by a gap.

    Although the Phoenix parachute has a smaller diameter (11.8 meters or 39 feet) than the parachute for the 2007 Mars Pathfinder landing (12.7 meters or 42 feet), its Viking configuration results in slightly larger drag area. The smaller physical size allows for a stronger system because, given the same mass and volume restrictions, a smaller parachute can be built using higher strength components. The Phoenix parachute is approximately 1.5 times stronger than Pathfinder's. Testing shows that it is nearly two times stronger than the maximum opening force expected during its use at Mars.

    Engineers used a dart-like weight for the drop testing in Idaho. On the Phoenix spacecraft, the parachute is attached the the backshell. The backshell is the upper portion of a capsule around the lander during the flight from Earth to Mars and protects Phoenix during the initial portion of the descent through Mars' atmosphere.

    Phoenix will deploy its parachute at about 12.6 kilometers (7.8 miles) in altitude and at a velocity of 1.7 times the speed of sound. A mortar on the spacecraft fires to deploy the parachute, propelling it away from the backshell into the supersonic flow. The mortar design for Phoenix is essentially the same as Pathfinder's. The parachute and mortar are collectively called the 'parachute decelerator system.' Pioneer Aerospace, South Windsor, Conn., produced this system for Phoenix. The same company provided the parachute decelerator systems for Pathfinder, Mars Polar

  16. Low Cost Precision Lander for Lunar Exploration

    NASA Astrophysics Data System (ADS)

    Head, J. N.; Gardner, T. G.; Hoppa, G. V.; Seybold, K. G.

    2004-12-01

    For 60 years the US Defense Department has invested heavily in producing small, low mass, precision guided vehicles. The technologies matured under these programs include terrain-aided navigation, closed loop terminal guidance algorithms, robust autopilots, high thrust-to-weight propulsion, autonomous mission management software, sensors, and data fusion. These technologies will aid NASA in addressing New Millennium Science and Technology goals as well as the requirements flowing from the Vision articulated in January 2004. Establishing and resupplying a long term lunar presence will require automated landing precision not yet demonstrated. Precision landing will increase safety and assure mission success. In the DOD world, such technologies are used routinely and reliably. Hence, it is timely to generate a point design for a precise planetary lander useful for lunar exploration. In this design science instruments amount to 10 kg, 16% of the lander vehicle mass. This compares favorably with 7% for Mars Pathfinder and less than 15% for Surveyor. The mission design flies the lander in an inert configuration to the moon, relying on a cruise stage for navigation and TCMs. The lander activates about a minute before impact. A solid booster reduces the vehicle speed to 300-450 m/s. The lander is now about 2 minutes from touchdown and has 600 to 700 m/s delta-v capability, allowing for about 10 km of vehicle divert during terminal descent. This concept of operations is chosen because it closely mimics missile operational timelines used for decades: the vehicle remains inert in a challenging environment, then must execute its mission flawlessly on a moment's notice. The vehicle design consists of a re-plumbed propulsion system, using propellant tanks and thrusters from exoatmospheric programs. A redesigned truss provides hard points for landing gear, electronics, power supply, and science instruments. A radar altimeter and a Digital Scene Matching Area Correlator (DSMAC

  17. Morpheus Lander Hot Fire Test

    NASA Video Gallery

    This video shows a successful "hot fire" test of the Morpheus lander on February 27, 2012, at the VTB Flight Complex at NASA's Johnson Space Center. The engine burns for an extended period of time ...

  18. Rosetta Lander - Philae: preparations for landing on comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    Ulamec, S.; Biele, J.; Jurado, E.; Gaudon, P.; Geurts, K.

    2013-12-01

    Rosetta is a Cornerstone Mission of the ESA Horizon 2000 programme. It is going to rendezvous with comet 67P/Churyumov-Gerasimenko after a ten year cruise and will study both its nucleus and coma with an orbiting spacecraft as well as with a Lander, Philae, that has been designed to land softly on the comet nucleus. Aboard Philae, a payload consisting of ten scientific instruments will perform in-situ studies of the cometary material. Philae will be separated from the mother spacecraft from a dedicated delivery trajectory. It then descends, ballistically, to the surface of the comet, stabilized with an internal flywheel. At touch-down anchoring harpoons will be fired and a damping mechanism within the landing gear will provide the lander from re-bouncing. Currently the characteristics of the nucleus of the comet are hardly known. Mapping with the orbiter cameras (shape, slopes, surface roughness) and essential measurements like gravity field, state of rotation or outgassing parameters can only be performed after arrival of the main spacecraft, between May and October 2014. These data will be used for selecting a landing site and defining the detailed landing strategy. Landing is foreseen for November 2014 at a heliocentric distance of 3 AU. The paper describes the Rosetta Lander system and its payload, but emphasizes on the preparations for landing, the landing site selection process and the planned operational timeline.

  19. Analysis of TRMM Microphysical Measurements: Tropical Rainfall Measuring Mission (TRMM)

    NASA Technical Reports Server (NTRS)

    2004-01-01

    SPEC Incorporated participated in three of the four TRMM field campaigns (TEFLUN-A, TEFLUN-B and KWAJEX), installing and operating a cloud particle imager (CPI) and a high volume precipitation spectrometer (HVPS) on the SPEC Learjet in TEFLUN-A, the University of North Dakota Citation in TEFLUN-B and KWAJEX, and a CPI on the NASA DC-8 in KWAJEX. This report presents and discusses new software tools and algorithms that were developed to analyze microphysical data collected during these field campaigns, as well as scientific interpretations of the data themselves. Software algorithms were developed to improve the analysis of microphysical measurements collected by the TRMM aircraft during the field campaigns. Particular attention was paid to developing and/or improving algorithms used to compute particle size distributions and ice water content. Software was also developed in support of production of the TRMM Common Microphysical Product (CMP) data files. CMP data files for TEFLUN-A field campaign were produced and submitted to the DAAC. Typical microphysical properties of convective and stratiform regions from TEFLUN-A and KWAJEX clouds were produced. In general, it was found that in the upper cloud region near -20 to -25 C, stratiform clouds contain very high (greater than 1 per cubic centimeter) concentrations of small ice particles, which are suspected to be a residual from homogeneous freezing and sedimentation of small drops in a convective updraft. In the upper cloud region near -20 to -25 C, convective clouds contain aggregates, which are not found lower in the cloud. Stratiform clouds contain aggregates at all levels, with the majority in the lowest levels. Convective cloud regions contain much higher LWC and drop concentrations than stratiform regions at all levels, and higher LWC in the middle and upper regions. Stratiform clouds contain higher IWC than convective clouds only at the lowest level. Irregular shaped ice particles are found in very high

  20. Mars Polar Lander is mated with Boeing Delta II rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Workers mate the Mars Polar Lander (top) to the Boeing Delta II rocket at Launch Complex 17B, Cape Canaveral Air Station. The rocket is scheduled to launch Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern- most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars Surveyor '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  1. Mars Polar Lander is mated with Boeing Delta II rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Inside the gantry at Launch Complex 17B, Cape Canaveral Air Station, the Mars Polar Lander spacecraft is lowered to mate it with the Boeing Delta II rocket that will launch it on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars Surveyor'98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  2. The heat shield for the Mars Polar Lander is attached

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers lower the heat shield onto the Mars Polar Lander. Scheduled to be launched on Jan. 3, 1999, the lander is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which is due to be launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  3. Mars Polar Lander is mated with Boeing Delta II rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    At Launch Complex 17B, Cape Canaveral Air Station, workers get ready to remove the protective wrapping on the Mars Polar Lander to be launched aboard a Boeing Delta II rocket on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars Surveyor'98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  4. Mars Polar Lander arrives at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The Mars Polar Landerspacecraft is lifted off the trailer of that transported it to the gantry at Launch Complex 17B, Cape Canaveral Air Station. The lander, which will be launched aboard a Boeing Delta II rocket on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  5. MetBaro - Pressure Instrument for Mars MetNet Lander

    NASA Astrophysics Data System (ADS)

    Polkko, J.; Haukka, H.; Harri, A.-M.; Schmidt, W.; Leinonen, J.; Mäkinen, T.

    2009-04-01

    THE METNET MISSION FOCUSED ON THE Martian atmospheric science is based on a new semihard landing vehicle called the MetNet Lander (MNL). The MNL will have a versatile science payload focused on the atmospheric science of Mars. The scientific payload of the MetNet Mission encompasses separate instrument packages for the atmospheric entry and descent phase and for the surface operation phase. MetBaro is the pressure instrument of MetNet Lander designed to work on Martian surface. It is based on Barocap® technology developed by Vaisala, Inc. MetBaro is a capacitic type of sensing device where capasitor plates are moved by ambient pressure. MetBaro device consists of two pressure transducers including a total of 6 Barocap® sensor heads of high-stability and high-resolution types. The long-term stability of MetBaro is in order of 20…50 µBar and resolution a few µBar. MetBaro is small, lightweighed and has low power consumption. It weighs about 50g without wires and controlling FPGA, and consumes 15 mW of power. A similar device has successfully flown in Phoenix mission, where it performed months of measurements on Martian ground. Another device is also part of the Mars Science Laboratory REMS instrument (to be launched in 2011).

  6. Morpheus Lander Testing Campaign

    NASA Technical Reports Server (NTRS)

    Hart, Jeremy J.; Mitchell, Jennifer D.

    2011-01-01

    NASA s Morpheus Project has developed and tested a prototype planetary lander capable of vertical takeoff and landing designed to serve as a testbed for advanced spacecraft technologies. The Morpheus vehicle has successfully performed a set of integrated vehicle test flights including hot-fire and tether tests, ultimately culminating in an un-tethered "free-flight" This development and testing campaign was conducted on-site at the Johnson Space Center (JSC), less than one year after project start. Designed, developed, manufactured and operated in-house by engineers at JSC, the Morpheus Project represents an unprecedented departure from recent NASA programs and projects that traditionally require longer development lifecycles and testing at remote, dedicated testing facilities. This paper documents the integrated testing campaign, including descriptions of test types (hot-fire, tether, and free-flight), test objectives, and the infrastructure of JSC testing facilities. A major focus of the paper will be the fast pace of the project, rapid prototyping, frequent testing, and lessons learned from this departure from the traditional engineering development process at NASA s Johnson Space Center.

  7. The Tropical Rainfall Measuring Mission (TRMM) Progress Report

    NASA Technical Reports Server (NTRS)

    Simpson, Joanne; Meneghini, Robert; Kummerow, Christian D.; Meneghini, Robert; Hou, Arthur; Adler, Robert F.; Huffman, George; Barkstrom, Bruce; Wielicki, Bruce; Goodman, Steve

    1999-01-01

    Recognizing the importance of rain in the tropics and the accompanying latent heat release, NASA for the U.S. and NASDA for Japan have partnered in the design, construction and flight of an Earth Probe satellite to measure tropical rainfall and calculate the associated heating. Primary mission goals are 1) the understanding of crucial links in climate variability by the hydrological cycle, 2) improvement in the large-scale models of weather and climate 3) Improvement in understanding cloud ensembles and their impacts on larger scale circulations. The linkage with the tropical oceans and landmasses are also emphasized. The Tropical Rainfall Measuring Mission (TRMM) satellite was launched in November 1997 with fuel enough to obtain a four to five year data set of rainfall over the global tropics from 37'N to 37'S. This paper reports progress from launch date through the spring of 1999. The data system and its products and their access is described, as are the algorithms used to obtain the data. Some exciting early results from TRMM are described. Some important algorithm improvements are shown. These will be used in the first total data reprocessing, scheduled to be complete in early 2000. The reader is given information on how to access and use the data.

  8. Development of a prototype fluid volume measurement system. [for urine volume measurement on space missions

    NASA Technical Reports Server (NTRS)

    Poppendiek, H. F.; Sabin, C. M.; Meckel, P. T.

    1974-01-01

    The research is reported in applying the axial fluid temperature differential flowmeter to a urine volume measurement system for space missions. The fluid volume measurement system is described along with the prototype equipment package. Flowmeter calibration, electronic signal processing, and typical void volume measurements are also described.

  9. Experimental Enhanced Upper Stage (XEUS): An affordable large lander system

    NASA Astrophysics Data System (ADS)

    Scotkin, J.; Masten, D.; Powers, J.; O'Konek, N.; Kutter, B.; Stopnitzky, B.

    The Experimental Enhanced Upper Stage (XEUS) offers a path to reduce costs and development time to sustainable activity beyond LEO by equipping existing large cryogenic propulsion stages with MSS VTVL propulsion and GNC to create a large, multi-thrust axis lander. Conventional lander designs have been driven by the assumption that a single, highly reliable, and efficient propulsion system should conduct the entire descent, approach, and landing. Compromises in structural, propulsion, and operational efficiency result from this assumption. System reliability and safety also suffer. The result is often an iterative series of optimizations, making every subsystem mission-unique and expensive. The XEUS multi-thrust axis lander concept uniquely addresses the programmatic and technical challenges of large-mass planetary landing by taking advantage of proven technologies and decoupling the deorbit and descent propulsion system from the landing propulsion system. Precise control of distributed, multi-thrust axis landing propulsion units mounted on the horizontal axis of a Centaur stage will ultimately enable the affordable deployment of large planetary rovers, uncrewed base infrastructure and manned planetary expeditions. The XEUS lander has been designed to offer a significantly improved mass fraction and mass to surface capability over conventional lander designs, while reducing airlock/payload to surface distances and distributing plume effects by using multiple gimbaled landing thrusters. In utilizing a proven cryogenic propulsion stage, XEUS reduces development costs required for development of new cryogenic propulsion stages and fairings and builds upon the strong heritage of successful Centaur and MSS RLV flights.

  10. Lunar Lander Structural Design Studies at NASA Langley

    NASA Technical Reports Server (NTRS)

    Wu, K. Chauncey; Antol, Jeffrey; Watson, Judith J.; Flick, John J.; Saucillo, Rudolph J.; Mazanek, Daniel D.; North, David D.

    2007-01-01

    The National Aeronautics and Space Administration is currently developing mission architectures, vehicle concepts and flight hardware to support the planned human return to the Moon. During Phase II of the 2006 Lunar Lander Preparatory Study, a team from the Langley Research Center was tasked with developing and refining two proposed Lander concepts. The Descent-Assisted, Split Habitat Lander concept uses a disposable braking stage to perform the lunar orbit insertion maneuver and most of the descent from lunar orbit to the surface. The second concept, the Cargo Star Horizontal Lander, carries ascent loads along its longitudinal axis, and is then rotated in flight so that its main engines (mounted perpendicular to the vehicle longitudinal axis) are correctly oriented for lunar orbit insertion and a horizontal landing. Both Landers have separate crew transport volumes and habitats for surface operations, and allow placement of large cargo elements very close to the lunar surface. As part of this study, lightweight, efficient structural configurations for these spacecraft were proposed and evaluated. Vehicle structural configurations were first developed, and preliminary structural sizing was then performed using finite element-based methods. Results of selected structural design and trade studies performed during this activity are presented and discussed.

  11. Successes with the Global Precipitation Measurement (GPM) Mission

    NASA Technical Reports Server (NTRS)

    Skofronick-Jackson, Gail; Huffman, George; Stocker, Erich; Petersen, Walter

    2016-01-01

    Water is essential to our planet Earth. Knowing when, where and how precipitation falls is crucial for understanding the linkages between the Earth's water and energy cycles and is extraordinarily important for sustaining life on our planet during climate change. The Global Precipitation Measurement (GPM) Core Observatory spacecraft launched February 27, 2014, is the anchor to the GPM international satellite mission to unify and advance precipitation measurements from a constellation of research and operational sensors to provide "next-generation" precipitation products. GPM is currently a partnership between NASA and the Japan Aerospace Exploration Agency (JAXA). Status and successes in terms of spacecraft, instruments, retrieval products, validation, and impacts for science and society will be presented. Precipitation, microwave, satellite

  12. The Philae Science Mission - A Preview

    NASA Astrophysics Data System (ADS)

    Boehnhardt, H.; Bibring, J.-P.

    2014-04-01

    The PHILAE Science Mission is based on measurements from 10 scientific instruments, i.e. the α-particle and X-ray spectrometer APXS, the visible camera and near-infrared spectrometer CIVA, the radio sounding experiment CONSERT, the molecule mass spectrometer and gas chromatograph COSAC, the accelerometer and thermal probe MUPUS, the light elements and isotope mass spectrometer and gas chromatograph PTOLEMY, the down-looking camera ROLIS, the magnetometer and plasma package ROMAP, the drill system SD2, and the acoustic and electric probe and dust impact sensor SESAME. The measurements are performed during 4 mission phase, i.e. during the pre-landing phase (PDCS) while the lander is still attached to the ROSETTA orbiter, during the separation, descent and landing phase (SDL), during the First Science Sequence (FSS) within about 3 days after landing and during a Long-Term Science phase (LTS) which follows the FSS immediately or after a short hibernation period depending on the landing site and the related power situation of the lander. The PDCS and SDL phase only a subset of the lander instruments will be active with scientific measurements, i.e. CIVA, CONSERT, PTOLEMY, ROMAP and SESAME during PDCS and CIVA, CONSERT, ROLIS, and ROMAP during SDL. The FSS and LTS phases will utilize all 10 PHILAE instruments for science. The presentations provides an overview of the PHILAE observations during the various mission phases, outlines the expected results and comments on the impact of the landing sites for the PHILAE science.

  13. Multibody Modeling and Simulation for the Mars Phoenix Lander Entry, Descent and Landing

    NASA Technical Reports Server (NTRS)

    Queen, Eric M.; Prince, Jill L.; Desai, Prasun N.

    2008-01-01

    A multi-body flight simulation for the Phoenix Mars Lander has been developed that includes high fidelity six degree-of-freedom rigid-body models for the parachute and lander system. The simulation provides attitude and rate history predictions of all bodies throughout the flight, as well as loads on each of the connecting lines. In so doing, a realistic behavior of the descending parachute/lander system dynamics can be simulated that allows assessment of the Phoenix descent performance and identification of potential sensitivities for landing. This simulation provides a complete end-to-end capability of modeling the entire entry, descent, and landing sequence for the mission. Time histories of the parachute and lander aerodynamic angles are presented. The response of the lander system to various wind models and wind shears is shown to be acceptable. Monte Carlo simulation results are also presented.

  14. Saturn orbiter dual probe mission

    NASA Technical Reports Server (NTRS)

    Rudd, R. P.

    1978-01-01

    The described Saturn orbiter dual probe mission and spacecraft combines three systems into a multi-purpose Saturn exploration package. The spacecraft consists of: (1) Saturn orbiter; (2) Saturn probe; and (3) Titan probe or lander. This single spacecraft provides the capability to conduct in situ measurements of the Saturn and Titan atmospheres, and, possibly the Titan surface, as well as a variety of remote sensing measurements. The remote sensing capabilities will be used to study the surfaces, interiors and environments of Saturn's satellites, the rings of Saturn, Saturn's magnetosphere, and synoptic properties of Saturn's atmosphere.

  15. Lunar lander ground support system

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The design of the Lunar Lander Ground Support System (LLGSS) is examined. The basic design time line is around 2010 to 2030 and is referred to as a second generation system, as lunar bases and equipment would have been present. Present plans for lunar colonization call for a phased return of personnel and materials to the moons's surface. During settlement of lunar bases, the lunar lander is stationary in a very hostile environment and would have to be in a state of readiness for use in case of an emergency. Cargo and personnel would have to be removed from the lander and transported to a safe environment at the lunar base. An integrated system is required to perform these functions. These needs are addressed which center around the design of a lunar lander servicing system. The servicing system could perform several servicing functions to the lander in addition to cargo servicing. The following were considered: (1) reliquify hydrogen boiloff; (2) supply power; and (3) remove or add heat as necessary. The final design incorporates both original designs and existing vehicles and equipment on the surface of the moon at the time considered. The importance of commonality is foremost in the design of any lunar machinery.

  16. Phoenix Mars Lander with Solar Arrays Open

    NASA Technical Reports Server (NTRS)

    2006-01-01

    NASA's next Mars-bound spacecraft, the Phoenix Mars Lander, was partway through assembly and testing at Lockheed Martin Space Systems, Denver, in September 2006, progressing toward an August 2007 launch from Florida. In this photograph, spacecraft specialists work on the lander after its fan-like circular solar arrays have been spread open for testing. The arrays will be in this configuration when the spacecraft is active on the surface of Mars.

    Phoenix will land in icy soils near the north polar permanent ice cap of Mars and explore the history of the water in these soils and any associated rocks, while monitoring polar climate. It will dig into the surface, test scooped-up samples for carbon-bearing compounds and serve as NASA's first exploration of a potential modern habitat on Mars.

    The Phoenix mission is led by Principal Investigator Peter H. Smith of the University of Arizona, Tucson, with project management at NASA's Jet Propulsion Laboratory and development partnership with Lockheed Martin Space Systems. International contributions for Phoenix are provided by the Canadian Space Agency, the University of Neuchatel (Switzerland), the University of Copenhagen, and the Max Planck Institute in Germany. JPL is a division of the California Institute of Technology in Pasadena.

  17. Charge measurements for an asteroid sample return mission

    NASA Astrophysics Data System (ADS)

    Macfaden, A.; Aplin, K. L.; Bowles, N. E.

    2013-09-01

    Photoelectric charging of asteroid regolith material influences particle motion and escape. Differing spacecraft and asteroid charges may also affect sample return on missions such as Marco Polo-R. To study this, bespoke 2D particle-in-cell code simulating the behaviour of photoelectrons trapped near a photoemitting surface (photosheath) has been written and implemented. The spacecraft- photosheath system reaches equilibrium in 1 ms, which is rapid compared to the descent timescale. Equilibria reached in simulations are therefore assumed representative of the dynamic spacecraft environment. Predicted potentials at different heightsand with different solar zenith angle are presented, so that an instrument to measure the potential difference across the spacecraft can be defined. The distorting effect of the spacecraft significantly modifies the potential difference and displacement currents during the terminal descent, by introducing an equipotential body, creating a shadow, and photoemitting itself. By considering the distortion from different parts of the spacecraft, optimal locations for a set of electrodes to measure the potential difference are suggested. Potential differences of about 100 mV are expected to be generated across the electrodes, which should be representative of the electrical environment. The results demonstrate that a simple set of electrodes can measure the asteroid's surface electric field during sample collection.

  18. Spaceship Discovery's Crew and Cargo Lander Module Designs for Human Exploration of Mars

    NASA Astrophysics Data System (ADS)

    Benton, Mark G.

    2008-01-01

    The Spaceship Discovery design was first presented at STAIF 2006. This conceptual design space vehicle architecture for human solar system exploration includes two types of Mars exploration lander modules: A piloted crew lander, designated Lander Module 2 (LM2), and an autonomous cargo lander, designated Lander Module 3 (LM3). The LM2 and LM3 designs were first presented at AIAA Space 2007. The LM2 and LM3 concepts have recently been extensively redesigned. The specific objective of this paper is to present these revised designs. The LM2 and LM3 landers are based on a common design that can be configured to carry either crew or cargo. They utilize a combination of aerodynamic reentry, parachutes, and propulsive braking to decelerate from orbital velocity to a soft landing. The LM2 crew lander provides two-way transportation for a nominal three-person crew between Mars orbit and the surface, and provides life support for a 30-day contingency mission. It contains an ascent section to return the crew to orbit after completion of surface operations. The LM3 cargo lander provides one-way, autonomous transportation of cargo from Mars orbit to the surface and can be configured to carry a mix of consumables and equipment, or equipment only. Lander service life and endurance is based on the Spaceship Discovery conjunction-class Design Reference Mission 2. The LM3 is designed to extend the surface stay for three crew members in an LM2 crew lander such that two sets of crew and cargo landers enable human exploration of the surface for the bulk of the 454 day wait time at Mars, in two shifts of three crew members each. Design requirements, mission profiles, mass properties, performance data, and configuration layouts are presented for the LM2 crew and LM3 cargo landers. These lander designs are a proposed solution to the problem of safely transporting a human crew from Mars orbit to the surface, sustaining them for extended periods of time on the surface, and returning them

  19. Investigation of Mars Rotational Dynamics Using Earth-based Radio Tracking of Mars Landers

    NASA Technical Reports Server (NTRS)

    Edwards, C. D., Jr.; Folkner, W. M.; Kahn, R. D.; Preston, R. A.

    1993-01-01

    The development of space geodetic techniques over the past two decades has made it possible to measure the rotational dynamics of the Earth at the milliarcsecond level, improving our geophysical models of the Earth 's interior and the interactions between the solid Earth and its atmosphere. We have found that the rotational dynamics of Mars can be determined to nearly the same level of accuracy by acquiring Earth-based two-way radio tracking observations of three or more landers globally distributed on the surface of Mars. Our results indicate that the precession and long-term obliquity changes of the Mars pole direction can be determined to an angular accuracy corresponding to about 15 cm/yr at the planet's surface. In addition, periodic nutations of the pole and seasonal variations in the spin rate of the planet can be determined to 10 cm or less. Measuring the rotation of Mars at this accuracy would greatly improve the determination of the planet' s moment of inertia and would resolve the size of a planetary fluid core, providing a valuable constraint on Mars interior models. Detecting seasonal variations in the spin rate of Mars would provide global constraints on atmospheric angular momentum changes due to sublimation of the Mars CO2 polar ice caps. Finally, observation of quasisecular changes in Mars obliquity would have significant implications for understanding long-term climatic change. The key to achieving these accuracies is a globally distributed network of Mars landers with stable, phase-coherent radio transponders. By simultaneously acquiring coherent two-way carrier phase observations between a single Earth tracking station and multiple Mars landers, Earth media errors are essentially eliminated, providing an extremely sensitive measure of changes in the differential path lengths between the Earth tracking station and the Mars landers due to Mars rotation. Time variability of the instrumental phase delay through the radio transponder may represent

  20. Space acceleration measurement system description and operations on the First Spacelab Life Sciences Mission

    NASA Technical Reports Server (NTRS)

    Delombard, Richard; Finley, Brian D.

    1991-01-01

    The Space Acceleration Measurement System (SAMS) project and flight units are briefly described. The SAMS operations during the STS-40 mission are summarized, and a preliminary look at some of the acceleration data from that mission are provided. The background and rationale for the SAMS project is described to better illustrate its goals. The functions and capabilities of each SAMS flight unit are first explained, then the STS-40 mission, the SAMS's function for that mission, and the preparation of the SAMS are described. Observations about the SAMS operations during the first SAMS mission are then discussed. Some sample data are presented illustrating several aspects of the mission's microgravity environment.

  1. Imaging experiment: The Viking Lander

    USGS Publications Warehouse

    Mutch, T.A.; Binder, A.B.; Huck, F.O.; Levinthal, E.C.; Morris, E.C.; Sagan, C.; Young, A.T.

    1972-01-01

    The Viking Lander Imaging System will consist of two identical facsimile cameras. Each camera has a high-resolution mode with an instantaneous field of view of 0.04??, and survey and color modes with instantaneous fields of view of 0.12??. Cameras are positioned one meter apart to provide stereoscopic coverage of the near-field. The Imaging Experiment will provide important information about the morphology, composition, and origin of the Martian surface and atmospheric features. In addition, lander pictures will provide supporting information for other experiments in biology, organic chemistry, meteorology, and physical properties. ?? 1972.

  2. Development of a Compact, Deep-Penetrating Heat Flow Instrument for Lunar Landers: In-Situ Thermal Conductivity System

    NASA Technical Reports Server (NTRS)

    Nagihara, S.; Zacny, K.; Hedlund, M.; Taylor, P. T.

    2012-01-01

    Geothermal heat flow is obtained as a product of the geothermal gradient and the thermal conductivity of the vertical soil/rock/regolith interval penetrated by the instrument. Heat flow measurements are a high priority for the geophysical network missions to the Moon recommended by the latest Decadal Survey and previously the International Lunar Network. One of the difficulties associated with lunar heat flow measurement on a robotic mission is that it requires excavation of a relatively deep (approx 3 m) hole in order to avoid the long-term temporal changes in lunar surface thermal environment affecting the subsurface temperature measurements. Such changes may be due to the 18.6-year-cylcle lunar precession, or may be initiated by presence of the lander itself. Therefore, a key science requirement for heat flow instruments for future lunar missions is to penetrate 3 m into the regolith and to measure both thermal gradient and thermal conductivity. Engineering requirements are that the instrument itself has minimal impact on the subsurface thermal regime and that it must be a low-mass and low-power system like any other science instrumentation on planetary landers. It would be very difficult to meet the engineering requirements, if the instrument utilizes a long (> 3 m) probe driven into the ground by a rotary or percussive drill. Here we report progress in our efforts to develop a new, compact lunar heat flow instrumentation that meets all of these science and engineering requirements.

  3. Robotic Lander Completes Multiple Outdoor Flight

    NASA Video Gallery

    NASA’s Robotic Lander Development Project in Huntsville, Ala., has successfully completed seven autonomous outdoor flight tests of a lander prototype, dubbed Mighty Eagle. On Oct. 14, Mighty Eagl...

  4. Phoenix Lander on Mars with Surrounding Terrain, Vertical Projection

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This view is a vertical projection that combines more than 500 exposures taken by the Surface Stereo Imager camera on NASA's Mars Phoenix Lander and projects them as if looking down from above.

    The black circle on the spacecraft is where the camera itself is mounted on the lander, out of view in images taken by the camera. North is toward the top of the image. The height of the lander's meteorology mast, extending toward the southwest, appears exaggerated because that mast is taller than the camera mast.

    This view in approximately true color covers an area about 30 meters by 30 meters (about 100 feet by 100 feet). The landing site is at 68.22 degrees north latitude, 234.25 degrees east longitude on Mars.

    The ground surface around the lander has polygonal patterning similar to patterns in permafrost areas on Earth.

    This view comprises more than 100 different Stereo Surface Imager pointings, with images taken through three different filters at each pointing. The images were taken throughout the period from the 13th Martian day, or sol, after landing to the 47th sol (June 5 through July 12, 2008). The lander's Robotic Arm is cut off in this mosaic view because component images were taken when the arm was out of the frame.

    The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

  5. MetHumi - Humidity Instrument for Mars MetNet Lander

    NASA Astrophysics Data System (ADS)

    Polkko, J.; Genzer, M.; Harri, A.-M.; Schmidt, W.; Leinonen, J.; Mäkinen, T.

    2009-04-01

    THE METNET MISSION FOCUSED ON THE Martian atmospheric science is based on a new semihard landing vehicle called the MetNet Lander (MNL). The MNL will have a versatile science payload focused on the atmospheric science of Mars. The scientific payload of the MetNet Mission encompasses separate instrument packages for the atmospheric entry and descent phase and for the surface operation phase. MetHumi is the humidity instrument of MetNet Lander designed to work on Martian surface. It is based on Humicap® technology developed by Vaisala, Inc. MetHumi is a capacitic type of sensing device where an active polymer film changes capacitance as function of relative humidity. One MetHumi device package consists of one humidity transducer including three Humicap® sensor heads, an accurate temperature sensor head (Thermocap® by Vaisala, Inc.) and constant reference channels. MetHumi is very small, lightweighed and has low power consumption. It weighs only about 15 g without wires, and consumes 15 mW of power. MetHumi can make meaningful relative humidity measurements in range of 0 - 100%RH down to -70°C ambient temperature, but it survives even -135°C ambient temperature. Similar device is part of the Mars Science Laboratory REMS -instrument (to be launched 2011).

  6. Chandrayaan-2: India's First Soft-landing Mission to Moon

    NASA Astrophysics Data System (ADS)

    Mylswamy, Annadurai; Krishnan, A.; Alex, T. K.; Rama Murali, G. K.

    2012-07-01

    latitude location is preferred from scientific interest. Multiple communication links involving Rover-Lander-Earth, Orbiter-Earth and Rover-Orbiter will be implemented. Scientific Payloads:, The scientific payloads on orbiter include a Terrain Mapping Camera (TMC-2), an Imaging Infra-Red Spectrometer (IIRS), a Dual Band (L&S-Band) Synthetic Aperture Radar (SAR), a Collimated Large Area Soft x-ray Spectrometer (CLASS), and a Chandra's Atmospheric Composition Explorer(ChACE-2). TMC with two cameras will provide 3D imaging and DEM, while the IIRS will cover the 0.8-5 micron region at high spectral resolution using a grating spectrograph coupled to an active cooler based MCT array detector. It will provide information on mineral composition and detect OH and H2O and also measure thermal emission from the lunar surface. CLASS is an improved version of C1XS flown on Chandrayaan-1 and will employ swept charge detector (SCD) for detection of X-rays from lunar surface during solar flares.ChACE-2 is a modified version of ChACE-1, one of the instruments on Moon Impact Probe (MIP) that provided hints for the presence of water molecule in lunar exosphere. The Synthetic Aperture Radar will include both L (1.25 GHz) and S (2.5 GHz) bands with selectable resolution of up to a few meters. A radiating patch arrangement is designed for the integrated L-band and S-band antenna. There will be two payloads on the Rover: an Alpha Particle induced X-ray Spectrometer (APXS) and a Laser Induced Breakdown Spectroscopy (LIBS) for studies of chemical composition and volatiles present in lunar surface material near the landing site. The Lander Craft will have suite of instruments to study both physical and chemical properties of the landing site. It will have direct communication link to Earth Stations. The Lander will also act as the relay for communication with the Rover. The design and development of the various mission elements as well as of the scientific payloads are currently in progress both in

  7. The Planning of Lander Science Observations after ROSETTA Deep Space Hibernation

    NASA Astrophysics Data System (ADS)

    Barthelemy, Maud; Ulamec, Stephan; Gaudon, Philippe; Biele, Jens; Pätz, Brigitte; Ashman, Mike

    2014-05-01

    After 10 years of its interplanetary journey, Rosetta has woken up from hibernation to meet Churyumov-Gerasimenko comet in the second term of 2014. The Rosetta spacecraft is composed of an Orbiter and a Lander part. The spacecraft will deliver the Lander, named Philae, to land on the surface of the comet in November 2014. During the Cruise Phase, the Lander, attached to the Orbiter, participated in several commissioning and payload checkout observations. In April 2014, after almost 3 years of hibernation, the Lander and the Orbiter will enter a commissioning phase to check the health of all instruments. Then, from May to November, Prelanding science activities can be planned, although the priority will go to those observations that help to select the landing site. The Lander project has, in much the same way as the Orbiter, its own ground segment: the Rosetta Lander Ground Segment (RLGS). The RLGS is composed of the Science Operations and Navigation Center - SONC - at CNES in Toulouse and the Lander Control Center - LCC - at DLR in Cologne. There are 10 instruments on board of Philae trying to conduct science observations during the life of the Lander. As the comet travels closer to the sun the temperature will eventually become too hot for Philae. The Orbiter, however, is planned to operate for much longer, until end of 2015, passing perihelion. Each of the 10 instruments is represented by a principal investigator. The Lander project also has Lead Scientists, who make sure that the science objectives of the Lander are fulfilled and are on hand to solve any eventual conflicts in this regard. To plan their observations, the Lander team listed their science objectives and ranked them. From these objectives, Specific On-Comet Operation Plan (SOCOP) documents are written by LCC describing the proposed observations. Then, at SONC, the MOST (Mission Operation Scheduling Tool) is used to generate a science experiment plan. This plan is confirmed by the PIs and the Lead

  8. Mars Polar Lander is mated with Boeing Delta II rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    At Launch Complex 17B, Cape Canaveral Air Station, the protective covering on the Mars Polar Lander is lifted up and out of the way. The lander, in the opening below, is being mated to the Boeing Delta II rocket that will launch it on Jan. 3, 1999. The lander is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars Surveyor'98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  9. Design, calibration and operation of Mars lander cameras

    NASA Astrophysics Data System (ADS)

    Bos, Brent Jon

    2002-09-01

    In the 45 years since the dawn of the space age, there have only been two Mars lander camera designs to successfully operate on the Martian surface. Therefore information on Mars imager design and operation issues is limited. In addition, good examples of Mars lander imager calibration work are almost non-existent. This work presents instrument calibration results for a Mars lander camera originally designed to fly as an instrument onboard the 2001 Mars Surveyor lander as a robotic arm camera (RAC). Test procedures and results are described as well as techniques for improving the accuracy of the calibration data. In addition we describe camera algorithms and operations research results for optimizing imager operations on the Martian surface. Finally, the lessons learned from the 2001 RAC are applied to the preliminary design of a new Mars camera for the Artemis Mars Scout mission. The design utilizes a Bayer color mosaic filter, white light LED's and includes an optical system operating at f/13 with a maximum resolution of 0.11 mrad/pixel. It is capable of imaging in several modes including: stereo, microscopic and panoramic at a mass of 0.3 kg. It will provide planetary geologists with an unprecedented view of the Martian surface.

  10. Measurements of Aged Aircraft Exhaust in the ACCENT Mission

    NASA Technical Reports Server (NTRS)

    Friedl, R.; Ross, A.

    2000-01-01

    The Atmospheric Chemistry of Combustion Emissions Near the Tropopause (ACCENT) mission is a multi-agency sponsored effort to evaluate the roles of aircraft and rocket exhaust in perturbing ozone chemistry and modifying aerosols and clouds.

  11. Chemistry Lab for Phoenix Mars Lander

    NASA Technical Reports Server (NTRS)

    2007-01-01

    The science payload of NASA's Phoenix Mars Lander includes a multi-tool instrument named the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The instrument's wet chemistry laboratory, prominent in this photograph, will measure a range of chemical properties of Martian soil samples, such as the presence of dissolved salts and the level of acidity or alkalinity. Other tools that are parts of the instrument are microscopes that will examine samples' mineral grains and a probe that will check the soil's thermal and electrical properties.

  12. A Wind Tunnel Study on the Mars Pathfinder (MPF) Lander Descent Pressure Sensor

    NASA Technical Reports Server (NTRS)

    Soriano, J. Francisco; Coquilla, Rachael V.; Wilson, Gregory R.; Seiff, Alvin; Rivell, Tomas

    2001-01-01

    The primary focus of this study was to determine the accuracy of the Mars Pathfinder lander local pressure readings in accordance with the actual ambient atmospheric pressures of Mars during parachute descent. In order to obtain good measurements, the plane of the lander pressure sensor opening should ideally be situated so that it is parallel to the freestream. However, due to two unfavorable conditions, the sensor was positioned in locations where correction factors are required. One of these disadvantages is due to the fact that the parachute attachment point rotated the lander's center of gravity forcing the location of the pressure sensor opening to be off tangent to the freestream. The second and most troublesome factor was that the lander descends with slight oscillations that could vary the amplitude of the sensor readings. In order to accurately map the correction factors required at each sensor position, an experiment simulating the lander descent was conducted in the Martian Surface Wind Tunnel at NASA Ames Research Center. Using a 115 scale model at Earth ambient pressures, the test settings provided the necessary Reynolds number conditions in which the actual lander was possibly subjected to during the descent. In the analysis and results of this experiment, the readings from the lander sensor were converted to the form of pressure coefficients. With a contour map of pressure coefficients at each lander oscillatory position, this report will provide a guideline to determine the correction factors required for the Mars Pathfinder lander descent pressure sensor readings.

  13. Mars Dynamics from Earth-Based Tracking of the Mars Pathfinder Lander

    NASA Technical Reports Server (NTRS)

    Folkner, W. M.; Kahn, R. D.; Preston, R. A.; Yoder, C. F.; Standish, E. M.; Williams, J. G.; Edwards, C. D.; Hellings, R. W.; Eubanks, T. M.; Bills, B. G.

    1997-01-01

    Measurements of Mars' rotational variations can be conducted via Earth-based radio tracking observations of the Mars Pathfinder lander during an extended mission. Two-way range measurements between an Earth tracking station and the lander will enable precise monitoring of the planet's orientation, allowing details of Mars' internal structure and global surface/atmosphere interactions to be determined. An analysis has been performed to investigate the accuracy with which key physical parameters of Mars can be determined using the Earth-based radio tracking measurements. Acquisition of such measurements over one Martian year should enable determination of Mars' polar moment of inertia to 1% or better, providing a strong constraint on radial density profiles (and hence on the iron content of the core and mantle) and on long-term variations of the obliquity, which influences the climate. Variations in Mars length of day and polar motion should also be detectable, and will yield information on the seasonal cycling of carbon dioxide between the atmosphere and the surface.

  14. The Asteroid Impact Mission (AIM): Studying the geophysics of small binaries, measuring asteroid deflection and studying impact physics

    NASA Astrophysics Data System (ADS)

    Kueppers, Michael; Michel, Patrick; AIM team

    2016-10-01

    Binary asteroids and their formation mechanisms are of particular interest for understanding the evolution of the small bodies in the solar system. Also, hazards to Earth from impact of near-Earth asteroids and their mitigation have drawn considerable interest over the last decades.Those subjects are both addressed by ESA's Asteroid Impact mission, which is part of the Asteroid Impact & Deflection Assessment (AIDA) currently under study in collaboration between NASA and ESA. NASA's DART mission will impact a projectile into the minor component of the binary near-Earth asteroid (65803) Didymos in 2022. The basic idea is to demonstrate the effect of the impact on the orbital period of the secondary around the primary. ESA's AIM will monitor the Didymos system for several months around the DART impact time.AIM will be launched in aurumn 2020. It is foreseen to arrive at Didymos in April 2022. The mission takes advantage of a close approach of Didymos to Earth. The next opportunity would arise in 2040 only.AIM will stay near Didymos for approximately 6 months. Most of the time it will be placed on the illuminated side of the system, at distances of approximately 35 km and 10 km. AIM is expected to move away from Didymos for some time around the DART impact.The reference payload for AIM includes two visual imagers, a hyperspectral camera, a lidar, a thermal infrared imager, a monostatic high frequency radar, and a bistatic low frequency radar. In addition, AIM will deploy a small lander on the secondary asteroid, and two cubesats that will be used for additional, more risky investigations close to or on the surface of the asteroid.Major contributions from AIM are expected in the study of the geophysics of small asteroids (including for the first time, radar measurements of an interior structure), the formation of binary asteroids, the momentum enhancement factor from the DART impact (through measuring the mass and the change of orbit of the seondary), and impact physics

  15. Geomorphic Map of Region Around Phoenix Mars Lander

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This map shows shows a color-coded interpretation of geomorphic units categories based on surface textures and contours in the region where NASA's Phoenix Mars Lander has studied an arctic Martian plain. It covers an area about 65 kilometers by 65 kilometers (40 miles by 40 miles).

    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.

  16. Non-Cooled Power System for Venus Lander

    NASA Technical Reports Server (NTRS)

    Salazar, Denise; Landis, Geoffrey A.; Colozza, Anthony J.

    2014-01-01

    The Planetary Science Decadal Survey of 2013-2022 stated that the exploration of Venus is of significant interest. Studying the seismic activity of the planet is of particular importance because the findings can be compared to the seismic activity of Earth. Further, the geological and atmospheric properties of Venus will shed light into the past and future of Earth. This paper presents a radioisotope power system (RPS) design for a small low-power Venus lander. The feasibility of the new power system is then compared to that of primary batteries. A requirement for the power source system is to avoid moving parts in order to not interfere with the primary objective of the mission - to collect data about the seismic activity of Venus using a seismometer. The target mission duration of the lander is 117 days, a significant leap from Venera 13, the longest-lived lander on the surface of Venus, which survived for 2 hours. One major assumption for this mission design is that the power source system will not provide cooling to the other components of the lander. This assumption is based on high-temperature electronics technology that will enable the electronics and components of the lander to operate at Venus surface temperature. For the proposed RPS, a customized General Purpose Heat Source Radioisotope Thermoelectric Generator (GPHSRTG) is designed and analyzed. The GPHS-RTG is chosen primarily because it has no moving parts and it is capable of operating for long duration missions on the order of years. This power system is modeled as a spherical structure for a fundamental thermal analysis. The total mass and electrical output of the system are calculated to be 24 kilograms and 26 Watts, respectively. An alternative design for a battery-based power system uses Sodium Sulfur batteries. To deliver a similar electrical output for 117 days, the battery mass is calculated to be 234 kilograms. Reducing mission duration or power required will reduce the required battery mass

  17. 1998 Mars Missions Science Briefing

    NASA Technical Reports Server (NTRS)

    1998-01-01

    NASA executives gathered together for an interview to discuss the 1998 Mars Mission. A simulated overview of the Lander Mission is presented. Also presented are views of pre-launch activities, countdown, and launch of the spacecraft, burnouts of the first, second, and third engines, and the probe separating from the spacecraft. During this mission the Lander performs in situ investigations that address the science theme "Volatiles and Climate History" on Mars. The purpose of this mission is to study the following: climate; life; water; carbon dioxide; and dust particles.

  18. Attitude-Reconstruction of ROSETTA's lander PHILAE using two-point observations by ROMAP and RPC-MAG

    NASA Astrophysics Data System (ADS)

    Heinisch, Philip; Auster, Hans-Ulrich; Richter, Ingo; Berghofer, Gerhard; Fornacon, Karl-Heinz; Glassmeier, Karl-Heinz

    2015-04-01

    As part of the European Space Agency's ROSETTA Mission the lander PHILAE touched down on comet 67P/Churyumov-Gerasimenko on November 12, 2014. The lander is equipped with a tri-axial fluxgate magnetometer as part of the Rosetta Lander Magnetometer and Plasma-Monitor package (ROMAP). This magnetometer was switched on during descent, the bouncing between the touchdowns and after the final touchdown, which made it possible to reconstruct not only PHILAE's rotation and nutation during flight, but also to determine the exact touchdown times. Together with the tri-axial fluxgate magnetometer of the Rosetta Plasma Consortium (RPC-MAG) onboard the ROSETTA orbiter, simultaneous measurements during the descent and after the touchdowns were used to determine PHILAE's absolute attitude. This was done by correlating magnetic low-frequency waves below 60 mHz simultaneously observed on PHILAE and in orbit by RPC-MAG, which was made possible by the relatively small distance between the two spacecraft's of less than 50km. The results gained from this method are consistent with the illumination patterns of PHILAE's solar arrays and the RF-link periods.

  19. Viking Lander Mosaics of Mars

    NASA Technical Reports Server (NTRS)

    Morris, E. C.

    1985-01-01

    The Viking Lander 1 and 2 cameras acquired many high-resolution pictures of the Chryse Planitia and Utopia Planitia landing sites. Based on computer-processed data of a selected number of these pictures, eight high-resolution mosaics were published by the U.S. Geological Survey as part of the Atlas of Mars, Miscellaneous Investigation Series. The mosaics are composites of the best picture elements (pixels) of all the Lander pictures used. Each complete mosaic extends 342.5 deg in azimuth, from approximately 5 deg above the horizon to 60 deg below, and incorporates approximately 15 million pixels. Each mosaic is shown in a set of five sheets. One sheet contains the full panorama from one camera taken in either morning or evening. The other four sheets show sectors of the panorama at an enlarged scale; when joined together they make a panorama approximately 2' X 9'.

  20. Europa Surface Radiation Environment for Lander Assessment

    NASA Technical Reports Server (NTRS)

    Cooper, John F.; Sturner, Steven J.

    2006-01-01

    The Jovian magnetospheric particle environment at Europa's surface is critical to assessment of landed astrobiological experiments in three respects: (1) the landing site must be chosen for the best prospects for detectable organic or inorganic signs of Life, e.g. regions of freshly emergent flows from the subsurface; (2) lander systems must reach the surface through the Jovian magnetospheric environment and operate long enough on the surface to return useful data; (3) lander instrumentation must be capable of detecting signs of life in the context of the local environmental radiation and associated chemistry. The Galileo, Voyager, and Pioneer missions have provided a wealth of data on energetic particle intensities throughout the Jovian magnetosphere including from many flybys of Europa. cumulative radiation dosages for spacecraft enroute to Europa can be well characterized, but knowledge of the surface radiation environment is very limited. Energetic electrons should primarily impact the trailing hemisphere with decreasing intensity towards the center of the leading hemisphere and are the most significant radiation component down to meter depths in the surface regolith due to secondary interactions. Observed surface distribution for sulfates is suggestive of electron irradiation but may have alternative interpretations. Having much-larger magnetic gyroradii than electrons, energetic protons and heavier ions irradiate more of the global surface. The particular orientations of electron, proton, and ion gyromotion would project into corresponding directional (e.g., east-west) anisotropies of particle flu into the surface. Particular topographic features at the landing site may therefore offer shielding from part of the incident radiation.

  1. Preliminary design of a universal Martian lander

    NASA Astrophysics Data System (ADS)

    Norman, Timothy L.; Gaskin, David E.; Adkins, Sean; Gunawan, Mary; Johnson, Raquel; Macdonnell, David; Parlock, Andrew; Sarick, John; Bodwell, Charles; Hashimoto, Kouichi

    In the next 25 years, mankind will be undertaking yet another giant leap forward in the exploration of the solar system: a manned mission to Mars. This journey will provide important information on the composition and history of both Mars and the Solar System. A manned mission will also provide the opportunity to study how humans can adapt to long term space flight conditions and the Martian environment. As part of the NASA/USRA program, nineteen West Virginia University students conducted a preliminary design of a manned Universal Martian Lander (UML). The UML's design will provide a 'universal' platform, consisting of four modules for living and laboratory experiments and a liquid-fuel propelled Manned Ascent Return Vehicle (MARV). The distinguishing feature of the UML is the 'universal' design of the modules which can be connected to form a network of laboratories and living quarters for future missions thereby reducing development and production costs. The WVU design considers descent to Mars from polar orbit, a six month surface stay, and ascent for rendezvous. The design begins with an unmanned UML landing at Elysium Mons followed by the manned UML landing nearby. During the six month surface stay, the eight modules will be assembled to form a Martian base where scientific experiments will be performed. The mission will also incorporate hydroponic plant growth into a Controlled Ecological Life Support System (CELSS) for water recycling, food production, and to counteract psychological effects of living on Mars. In situ fuel production for the MARV will be produced from gases in the Martian atmosphere. Following surface operations, the eight member crew will use the MARV to return to the Martian Transfer Vehicle (MTV) for the journey home to Earth.

  2. Preliminary design of a universal Martian lander

    NASA Technical Reports Server (NTRS)

    Norman, Timothy L.; Gaskin, David E.; Adkins, Sean; Gunawan, Mary; Johnson, Raquel; Macdonnell, David; Parlock, Andrew; Sarick, John; Bodwell, Charles; Hashimoto, Kouichi

    1993-01-01

    In the next 25 years, mankind will be undertaking yet another giant leap forward in the exploration of the solar system: a manned mission to Mars. This journey will provide important information on the composition and history of both Mars and the Solar System. A manned mission will also provide the opportunity to study how humans can adapt to long term space flight conditions and the Martian environment. As part of the NASA/USRA program, nineteen West Virginia University students conducted a preliminary design of a manned Universal Martian Lander (UML). The UML's design will provide a 'universal' platform, consisting of four modules for living and laboratory experiments and a liquid-fuel propelled Manned Ascent Return Vehicle (MARV). The distinguishing feature of the UML is the 'universal' design of the modules which can be connected to form a network of laboratories and living quarters for future missions thereby reducing development and production costs. The WVU design considers descent to Mars from polar orbit, a six month surface stay, and ascent for rendezvous. The design begins with an unmanned UML landing at Elysium Mons followed by the manned UML landing nearby. During the six month surface stay, the eight modules will be assembled to form a Martian base where scientific experiments will be performed. The mission will also incorporate hydroponic plant growth into a Controlled Ecological Life Support System (CELSS) for water recycling, food production, and to counteract psychological effects of living on Mars. In situ fuel production for the MARV will be produced from gases in the Martian atmosphere. Following surface operations, the eight member crew will use the MARV to return to the Martian Transfer Vehicle (MTV) for the journey home to Earth.

  3. Rest In Peace Mars Polar Lander

    NASA Technical Reports Server (NTRS)

    2002-01-01

    [figure removed for brevity, see original site]

    Three years ago (December 3, 1999) Mars Polar Lander (MPL) was set to touchdown on the enigmatic layered terrain located near the South Pole. Unfortunately, communications with the spacecraft were lost and never regained. The Mars Program Independent Assessment Team concluded that this loss was most likely due to premature retrorocket shutdown resulting in the crash of the lander. The image primarily shows what appears to be a ridged surface with some small isolated hills.

    Historically, exploration has and will continue to be a very hard and risky endeavor and sometimes you lose. But the spirit of exploration and discovery has served mankind well throughout the ages and it has now driven us to the far reaches of space. Therefore, with this in mind the THEMIS Team today is releasing an image of the region where MPL was set to land in memory of this mission and the unquenchable spirit of exploration. It is hoped that in the near future we will once again attempt another landing in the Martian polar regions.

    Note: this THEMIS visual image has not been radiometrically nor geometrically calibrated for this preliminary release. An empirical correction has been performed to remove instrumental effects. A linear shift has been applied in the cross-track and down-track direction to approximate spacecraft and planetary motion. Fully calibrated and geometrically projected images will be released through the Planetary Data System in accordance with Project policies at a later time.

    NASA's Jet Propulsion Laboratory manages the 2001 Mars Odyssey mission for NASA's Office of Space Science, Washington, D.C. The Thermal Emission Imaging System (THEMIS) was developed by Arizona State University, Tempe, in collaboration with Raytheon Santa Barbara Remote Sensing. The THEMIS investigation is led by Dr. Philip Christensen at Arizona State University. Lockheed Martin Astronautics, Denver, is the prime contractor for the

  4. Rosetta Lander - Philae on Comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    Biele, J.; Ulamec, S.; Cozzoni, B.; Fantinati, C.; Gaudon, P.; Geurts, K.; Jurado, E.; Küchemann, O.; Lommatsch, V.; Finke, F.; Maibaum, M.; Moussi-Soffys, A.; Salatti, M.

    2015-10-01

    Rosetta is a Cornerstone Mission of the ESA Horizon 2000 programme. In August 2014 it reached comet 67P/Churyumov-Gerasimenko after a 10 year cruise. Both its nucleus and coma have been studied with its orbiter payload of eleven PI instruments, allowing the selection of a landing site for Philae. The landing on the comet nucleus successfully took place on November 12th 2014. Philae touched the comet surface seven hours after ejection from the orbiter. After several bounces it came to rest and continued to send scientific data to Earth. All ten instruments of its payload have been operated at least once. Due to the fact that the Lander could not be anchored, the originally planned first scientific sequence had to be modified. Philae went into hibernation on November 15th, after its primary battery ran out of energy. Re-activation of the Lander is expected in spring/summer 2015 (before the conference) when CG is closer to the sun and the solar generator of Philae will provide more power. The presentation will give an overview of the activities of Philae on the comet, including a status report on the re-activation after hibernation. Rosetta is an ESA mission with contributions from its member states and NASA. Rosetta's Philae lander is provided by a consortium led by DLR, MPS, CNES and ASI with additional contributions from Hungary, UK, Finland, Ireland and Austria.

  5. Phoenix Lander Self Portrait on Mars, Vertical Projection

    NASA Technical Reports Server (NTRS)

    2008-01-01

    This view is a vertical projection that combines hundreds of exposures taken by the Surface Stereo Imager camera on NASA's Mars Phoenix Lander and projects them as if looking down from above.

    The black circle is where the camera itself is mounted on the lander, out of view in images taken by the camera. North is toward the top of the image.

    This view comprises more than 100 different Stereo Surface Imager pointings, with images taken through three different filters at each pointing. The images were taken throughout the period from the 13th Martian day, or sol, after landing to the 47th sol (June 5 through July 12, 2008). The lander's Robotic Arm appears cut off in this mosaic view because component images were taken when the arm was out of the frame.

    The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

  6. Lunar transit telescope lander design

    NASA Technical Reports Server (NTRS)

    Omar, Husam A.

    1992-01-01

    The Program Development group at NASA's Marshall Space Flight Center has been involved in studying the feasibility of placing a 16 meter telescope on the lunar surface to scan the skies using visible/ Ultraviolet/ Infrared light frequencies. The precursor telescope is now called the TRANSIT LUNAR TELESCOPE (LTT). The Program Development Group at Marshall Space Flight Center has been given the task of developing the basic concepts and providing a feasibility study on building such a telescope. The telescope should be simple with minimum weight and volume to fit into one of the available launch vehicles. The preliminary launch date is set for 2005. A study was done to determine the launch vehicle to be used to deliver the telescope to the lunar surface. The TITAN IV/Centaur system was chosen. The engineering challenge was to design the largest possible telescope to fit into the TITAN IV/Centaur launch system. The telescope will be comprised of the primary, secondary and tertiary mirrors and their supporting system in addition to the lander that will land the telescope on the lunar surface and will also serve as the telescope's base. The lunar lander should be designed integrally with the telescope in order to minimize its weight, thus allowing more weight for the telescope and its support components. The objective of this study were to design a lander that meets all the constraints of the launching system. The basic constraints of the TITAN IV/Centaur system are given.

  7. Lunar transit telescope lander design

    NASA Technical Reports Server (NTRS)

    Omar, Husam A.

    1991-01-01

    The Program Development group at NASA's Marshall Space Flight Center has been involved in studying the feasibility of placing a 16 meter telescope on the lunar surface to scan the skies using visible/ Ultraviolet/ Infrared light frequencies. The precursor telescope is now called the TRANSIT LUNAR TELESCOPE (LTT). The Program Development Group at Marshall Space Flight Center has been given the task of developing the basic concepts and providing a feasibility study on building such a telescope. The telescope should be simple with minimum weight and volume to fit into one of the available launch vehicles. The preliminary launch date is set for 2005. A study was done to determine the launch vehicle to be used to deliver the telescope to the lunar surface. The TITAN IV/Centaur system was chosen. The engineering challenge was to design the largest possible telescope to fit into the TITAN IV/Centaur launch system. The telescope will be comprised of the primary, secondary and tertiary mirrors and their supporting system in addition to the lander that will land the telescope on the lunar surface and will also serve as the telescope's base. The lunar lander should be designed integrally with the telescope in order to minimize its weight, thus allowing more weight for the telescope and its support components. The objective of this study were to design a lander that meets all the constraints of the launching system. The basic constraints of the TITAN IV/Centaur system are given.

  8. A sophisticated lander for scientific exploration of Mars: scientific objectives and implementation of the Mars-96 Small Station.

    PubMed

    Linkin, V; Harri, A M; Lipatov, A; Belostotskaja, K; Derbunovich, B; Ekonomov, A; Khloustova, L; Kremnev, R; Makarov, V; Martinov, B; Nenarokov, D; Prostov, M; Pustovalov, A; Shustko, G; Jarvinen, I; Kivilinna, H; Korpela, S; Kumpulainen, K; Lehto, A; Pellinen, R; Pirjola, R; Riihela, P; Salminen, A; Schmidt, W; McKay, C P

    1998-01-01

    A mission to Mars including two Small Stations, two Penetrators and an Orbiter was launched at Baikonur, Kazakhstan, on 16 November 1996. This was called the Mars-96 mission. The Small Stations were expected to land in September 1997 (Ls approximately 178 degrees), nominally to Amazonis-Arcadia region on locations (33 N, 169.4 W) and (37.6 N, 161.9 W). The fourth stage of the Mars-96 launcher malfunctioned and hence the mission was lost. However, the state of the art concept of the Small Station can be applied to future Martian lander missions. Also, from the manufacturing and performance point of view, the Mars-96 Small Station could be built as such at low cost, and be fairly easily accommodated on almost any forthcoming Martian mission. This is primarily due to the very simple interface between the Small Station and the spacecraft. The Small Station is a sophisticated piece of equipment. With the total available power of approximately 400 mW the Station successfully supports an ambitious scientific program. The Station accommodates a panoramic camera, an alpha-proton-x-ray spectrometer, a seismometer, a magnetometer, an oxidant instrument, equipment for meteorological observations, and sensors for atmospheric measurement during the descent phase, including images taken by a descent phase camera. The total mass of the Small Station with payload on the Martian surface, including the airbags, is only 32 kg. Lander observations on the surface of Mars combined with data from Orbiter instruments will shed light on the contemporary Mars and its evolution. As in the Mars-96 mission, specific science goals could be exploration of the interior and surface of Mars, investigation of the structure and dynamics of the atmosphere, the role of water and other materials containing volatiles and in situ studies of the atmospheric boundary layer processes. To achieve the scientific goals of the mission the lander should carry a versatile set of instruments. The Small Station

  9. Miniature GC-Minicell Ion Mobility Spectrometer (IMS) for In Situ Measurements in Astrobiology Planetary Missions

    NASA Technical Reports Server (NTRS)

    Kojiro, Daniel R.; Stimac, Robert M.; Kaye, William J.; Holland, Paul M.; Takeuchi, Norishige

    2006-01-01

    Astrobiology flight experiments require highly sensitive instrumentation for in situ analysis of volatile chemical species and minerals present in the atmospheres and surfaces of planets, moons, and asteroids. The complex mixtures encountered place a heavy burden on the analytical instrumentation to detect and identify all species present. The use of land rovers and balloon aero-rovers place additional emphasis on miniaturization of the analytical instrumentation. In addition, smaller instruments, using tiny amounts of consumables, allow the use of more instrumentation and/or ionger mission life for stationary landers/laboratories. The miniCometary Ice and Dust Experiment (miniCIDEX), which combined Gas Chromatography (GC) with helium Ion Mobility Spectrometry (IMS), was capable of providing the wide range of analytical information required for Astrobiology missions. The IMS used here was based on the PCP model 111 IMS. A similar system, the Titan Ice and Dust Experiment (TIDE), was proposed as part of the Titan Orbiter Aerorover Mission (TOAM). Newer GC systems employing Micro Electro- Mechanical System (MEMS) based technology have greatly reduced both the size and resource requirements for space GCs. These smaller GCs, as well as the continuing miniaturization of Astrobiology analytical instruments in general, has highlighted the need for smaller, dry helium IMS systems. We describe here the development of a miniature, MEMS GC-IMS system (MEMS GC developed by Thorleaf Research Inc.), employing the MiniCell Ion Mobility Spectrometer (IMS), from Ion Applications Inc., developed through NASA's Astrobiology Science and Technology Instrument Development (ASTID) Program and NASA s Small Business Innovative Research (SBIR) Program.

  10. (abstract) MEASURE-Jupiter: Low Cost Missions to Explore Jupiter in the Post-Galileo Era

    NASA Technical Reports Server (NTRS)

    Wallace, R. A.; Stern, S. A.; Ayon, J. A.; Lane, A. L.; Nunez, C. L.; Sauer, C. G.; Stetson, D. G.; West, R. A.

    1994-01-01

    MEASURE-Jupiter is a new mission concept for the exploration of giant planets, with initial application to Jupiter. By flying sets of lightweight spacecraft with highly focused measurement objectives, it is designed to break the apparent impass in giant planet exploration beyond Cassini. The MEASURE-Jupiter concept is characterized by: 1) intensive exploration of a giant planet system, 2) multiple small missions flown in focused waves using spacecraft costing $100M to $200M, and 3) mission sets launched every 2 to 3 years. Why Jupiter? Jupiter is the most complex planetary system in the Solar System with many scientifically intriguing bodies and phenomena to explore. The Galileo mission will scratch the surface of the exploration of Jupiter, posing many questions for the MEASURE-Jupiter missions to address. Jupiter is also the easiest planet in the Outer Solar System to reach, making possible flight times of 2 years and total mission durations of 3 years or less. Concept design studies have uncovered a number of scientifically rewarding, simple, low-cost mission options. These options have the additional attraction of being able to launch on 2-year trajectories to Jupiter with low-cost Delta II expendable launch vehicles. A partial list of mission concepts studied to date include: Io Very Close Flyby, Jupiter Close Polar Pass, Mini-Orbiters, and Galilean Satellite Penetrators. Key to the realization of the MEASURE-Jupiter missions is the judicious use of the new low power consuming advanced technology and applicable systems from the Pluto Fast Flyby mission spacecraft design. Foremost of the new technologies planned for inclusion are the elements of hybrid solar array/battery power systems which make it possible to perform the identified missions without the need for Radioactive Thermoelectric Generators (RTGs). This relieves the mission design of the attendant programmatic complexities, cost, and constraints attendant with the use of RTGs.

  11. Human Mars Lander Design for NASA's Evolvable Mars Campaign

    NASA Technical Reports Server (NTRS)

    Polsgrove, Tara; Chapman, Jack; Sutherlin, Steve; Taylor, Brian; Fabisinski, Leo; Collins, Tim; Cianciolo Dwyer, Alicia; Samareh, Jamshid; Robertson, Ed; Studak, Bill; Vitalpur, Sharada; Lee, Allan Y.; Rakow, Glenn

    2016-01-01

    Landing humans on Mars will require entry, descent, and landing capability beyond the current state of the art. Nearly twenty times more delivered payload and an order of magnitude improvement in precision landing capability will be necessary. To better assess entry, descent, and landing technology options and sensitivities to future human mission design variations, a series of design studies on human-class Mars landers has been initiated. This paper describes the results of the first design study in the series of studies to be completed in 2016 and includes configuration, trajectory and subsystem design details for a lander with Hypersonic Inflatable Aerodynamic Decelerator (HIAD) entry technology. Future design activities in this series will focus on other entry technology options.

  12. Heat capacity mapping mission. [satellite for earth surface temperature measurement

    NASA Technical Reports Server (NTRS)

    Price, J. C.

    1978-01-01

    A Heat Capacity Mapping Mission (HCMM), part of a series of Applications Explorers Missions, is designed to provide data on surface heating as a response to solar energy input. The data is obtained by a two channel scanning radiometer, with one channel covering the visible and near-IR band between 0.5 and 1.1 micrometers, and the other covering the thermal-IR between 10.5 and 12.5 micrometers. The temperature range covered lies between 260 and 340 K, in 0.3 deg steps, with an accuracy at 280 K of plus or minus 0.5 K. Nominal altitude is 620 km, with a ground swath 700 km wide.

  13. Errors in Viking Lander Atmospheric Profiles Discovered Using MOLA Topography

    NASA Technical Reports Server (NTRS)

    Withers, Paul; Lorenz, R. D.; Neumann, G. A.

    2002-01-01

    Each Viking lander measured a topographic profile during entry. Comparing to MOLA (Mars Orbiter Laser Altimeter), we find a vertical error of 1-2 km in the Viking trajectory. This introduces a systematic error of 10-20% in the Viking densities and pressures at a given altitude. Additional information is contained in the original extended abstract.

  14. MUPUS on the Rosetta Lander Philae: First Results

    NASA Astrophysics Data System (ADS)

    Spohn, T.; Joerg, K.

    2014-12-01

    The Rosetta lander Philae is planned to land on he nucleus of comet Churyumov-Gerasimenko on Nov 11 2014 and start its battery powered first science sequence. The "MUlti-PUrpose probe for surface and sub-surface Science" MUPUS will measure the temperature profile up to a depth of 30cm and the thermal conductivity using a self-penetrating needle-probe, the surface brightness temperature using a radiometer, the hardness of the comet soil by measuring the progress of insertion of the probe and the deceleration of the two anchors that will be shot to fix the lander. The anchors are equipped with an accelerometer and a temperature sensor each. The self-penetrating needle-probe, or penetrator for short, has an electro-magnetically driven hammer mechanism on top and a rod of about 1cm diameter and 32cm length equipped with 16 temperature sensors that can also be heated with controlled power of up to 2W to measure the thermal conductivity. MUPUS is stored on the lander but will be deployed to a distance of about 1m from the lander using a motor driven deployment device that extends from the lander balcony. The science goals of the instrument are to measure the temperature profile in the near surface layers of the comet and the heat flow into the comet nucleus to complement the surface energy balance of the nucleus with a quantity that is difficult to measure remotely or to estimate. The thermal conductivity can be further used to characterize the near surface layers and possibly determine the depth to pristine ice. The first science sequence will allow for insertion of the probe and for a first series of temperature and thermal conductivity measurements. MUPUS is looking at the long-term science sequence to complement these data. At the AGU fall meeting - assuming a successful landing and installation of the probe - we will report on results from the first science sequence.

  15. Technician Checks Soil Sampler on Viking Lander

    NASA Technical Reports Server (NTRS)

    1971-01-01

    A technician checks the soil sampler of the Viking lander. An arm will scoop up a sample of the Martian soil, empty it into a hopper on the lander which will route the sample to each of the three scientific instruments, biology, gas chromatograph/mass spectrometer and water analysis. NASA's Viking Lander was designed, fabricated, and tested by the Martin Marietta Corp. of Denver, Colorado, under the direction of the Viking Progect Office at Langley Research Center, Hampton, Virginia. The Lander drew heavily on the experience gained from the Ranger, Surveyor and the Apollo Programs in the areas of radar, altimeters, facsimile, cameras, soil samplers, landing gear, etc.

  16. Measuring Staff Perceptions of University Identity and Activities: The Mission and Values Inventory

    ERIC Educational Resources Information Center

    Ferrari, Joseph R.; Velcoff, Jessica

    2006-01-01

    Higher education institutions need to ascertain whether their stakeholders understand the school's mission, vision, and values. In the present study, the psychometric properties of a mission identity and activity measure were investigated with two staff samples. Using a principal component factor analysis (varimax rotation), respondents in Sample…

  17. The Camera of the MASCOT Asteroid Lander on Board Hayabusa 2

    NASA Astrophysics Data System (ADS)

    Jaumann, R.; Schmitz, N.; Koncz, A.; Michaelis, H.; Schroeder, S. E.; Mottola, S.; Trauthan, F.; Hoffmann, H.; Roatsch, T.; Jobs, D.; Kachlicki, J.; Pforte, B.; Terzer, R.; Tschentscher, M.; Weisse, S.; Mueller, U.; Perez-Prieto, L.; Broll, B.; Kruselburger, A.; Ho, T.-M.; Biele, J.; Ulamec, S.; Krause, C.; Grott, M.; Bibring, J.-P.; Watanabe, S.; Sugita, S.; Okada, T.; Yoshikawa, M.; Yabuta, H.

    2016-06-01

    The MASCOT Camera (MasCam) is part of the Mobile Asteroid Surface Scout (MASCOT) lander's science payload. MASCOT has been launched to asteroid (162173) Ryugu onboard JAXA's Hayabusa 2 asteroid sample return mission on Dec 3rd, 2014. It is scheduled to arrive at Ryugu in 2018, and return samples to Earth by 2020. MasCam was designed and built by DLR's Institute of Planetary Research, together with Airbus-DS Germany. The scientific goals of the MasCam investigation are to provide ground truth for the orbiter's remote sensing observations, provide context for measurements by the other lander instruments (radiometer, spectrometer and magnetometer), the orbiter sampling experiment, and characterize the geological context, compositional variations and physical properties of the surface (e.g. rock and regolith particle size distributions). During daytime, clear filter images will be acquired. During night, illumination of the dark surface is performed by an LED array, equipped with 4×36 monochromatic light-emitting diodes (LEDs) working in four spectral bands. Color imaging will allow the identification of spectrally distinct surface units. Continued imaging during the surface mission phase and the acquisition of image series at different sun angles over the course of an asteroid day will contribute to the physical characterization of the surface and also allow the investigation of time-dependent processes and to determine the photometric properties of the regolith. The MasCam observations, combined with the MASCOT hyperspectral microscope (MMEGA) and radiometer (MARA) thermal observations, will cover a wide range of observational scales and serve as a strong tie point between Hayabusa 2's remote-sensing scales ( 103- 10^{-3} m) and sample scales ( 10^{-3}- 10^{-6} m). The descent sequence and the close-up images will reveal the surface features over a broad range of scales, allowing an assessment of the surface's diversity and close the gap between the orbital

  18. Unlocking the secrets of the universe, Rosetta lander named Philae

    NASA Astrophysics Data System (ADS)

    2004-02-01

    Philae is the island in the river Nile on which an obelisk was found that had a bilingual inscription including the names of Cleopatra and Ptolemy in Egyptian hieroglyphs. This provided the French historian Jean-François Champollion with the final clues that enabled him to decipher the hieroglyphs of the Rosetta Stone and unlock the secrets of the civilisation of ancient Egypt. Just as the Philae Obelisk and the Rosetta Stone provided the keys to an ancient civilisation, the Philae lander and the Rosetta orbiter aim to unlock the mysteries of the oldest building blocks of our Solar System - comets. Germany, France, Italy and Hungary are the main contributors to the lander, working together with Austria, Finland, Ireland and the UK. The main contributors held national competitions to select the most appropriate name. Philae was proposed by 15-year-old Serena Olga Vismara from Arluno near Milan, Italy. Her hobbies are reading and surfing the internet, where she got the idea of naming the lander Philae. Her prize will be a visit to Kourou to attend the Rosetta launch. Study of Comet Churyumov-Gerasimenko will allow scientists to look back 4600 million years to an epoch when no planets existed and only a vast swarm of asteroids and comets surrounded the Sun. On arrival at the comet in 2014, Philae will be commanded to self-eject from the orbiter and unfold its three legs, ready for a gentle touchdown. Immediately after touchdown, a harpoon will be fired to anchor Philae to the ground and prevent it escaping from the comet's extremely weak gravity. The legs can rotate, lift or tilt to return Philae to an upright position. Philae will determine the physical properties of the comet's surface and subsurface and their chemical, mineralogical and isotopic composition. This will complement the orbiter's studies of the overall characterisation of the comet's dynamic properties and surface morphology. Philae may provide the final clues enabling the Rosetta mission to unlock

  19. Mars Sample Return mission: Two alternate scenarios

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Two scenarios for accomplishing a Mars Sample Return mission are presented herein. Mission A is a low cost, low mass scenario, while Mission B is a high technology, high science alternative. Mission A begins with the launch of one Titan IV rocket with a Centaur G' upper stage. The Centaur performs the trans-Mars injection burn and is then released. The payload consists of two lander packages and the Orbital Transfer Vehicle, which is responsible for supporting the landers during launch and interplanetary cruise. After descending to the surface, the landers deploy small, local rovers to collect samples. Mission B starts with 4 Titan IV launches, used to place the parts of the Planetary Transfer Vehicle (PTV) into orbit. The fourth launch payload is able to move to assemble the entire vehicle by simple docking routines. Once complete, the PTV begins a low thrust trajectory out from low Earth orbit, through interplanetary space, and into low Martian orbit. It deploys a communication satellite into a 1/2 sol orbit and then releases the lander package at 500 km altitude. The lander package contains the lander, the Mars Ascent Vehicle (MAV), two lighter than air rovers (called Aereons), and one conventional land rover. The entire package is contained with a biconic aeroshell. After release from the PTV, the lander package descends to the surface, where all three rovers are released to collect samples and map the terrain.

  20. Terrestrial outgoing radiation measurements with small satellite mission

    NASA Astrophysics Data System (ADS)

    Zhu, Ping; Dewitte, Steven; Karatekin, Ozgur; Chevalier, André; Conscience, Christian

    2015-04-01

    The solar force is the main driver of the Earth's climate. For a balanced climate system, the incoming solar radiation is equal to the sum of the reflected visible and reemitted thermal radiation at top of the atmosphere (TOA). Thus the energy imbalance plays an important role to diagnose the health of nowadays climate. However it remains a challenge to directly track the small Energy imbalance in Earth's Radiation Budget (EIERB) from space due to the complicities of the Earth's climate system and the limitation on long term stability of space instrument. The terrestrial outgoing radiation (TOR) has been recoded with a Bolometric Oscillation Sensor onboard PICAD microsatellite. In this presentation, we will report the three years TOR observed with PICARD-BOS and its further comparison with the CERES product. However the data acquired from this mission is still not enough to derive the EIERB. But the heritage gained from this experiment shields a light on the EIERB tracking with the small satellite even a cubesat mission.

  1. SELENE mission: mathematical model for SST Doppler measurements

    NASA Astrophysics Data System (ADS)

    Ping, J.; Kono, Y.; Kawano, N.; Hanada, H.; Matsumoto, K.

    2001-09-01

    Japanese lunar exploration mission, SELENE, has been planned to be launched into space by using H II-a rocket in the Summer of 2004. This mission is composed of 3 subsatellites, a main lunar orbiter, a relay satellite and a free flying VLBI radio source. One of its main scientific objectives is the estimation of high order and degree spherical harmonic coefficients for the lunar gravity field. Different tracking methods will be employed in SELENE. The key tracking method is 4 way Satellite-to-Satellite Tracking (SST) technique. By this way, the tracking data can be obtained through the relay when the low altitude main orbiter is flying at the far-side of the Moon and can not be "seen" from the Earth. To success the historical tracking data, a complete coverage of Doppler tracking from an orbiter at sufficiently low altitude with high tracking accuracy can be obtained. The 4 way SST has various configurations. For SELENE, the SST tracking mode is introduced here, the mathematical relation between range rate and 4 way Doppler count number is established, and a data processing stream frame by using GEODYN II is suggested.

  2. Future instrumentation and missions for measurements of tropospheric trace species from space: Workshop recommendations

    NASA Technical Reports Server (NTRS)

    1987-01-01

    It was recommended that gas filter correlation radiometry and high-resolution interferometry be exploited and expanded for measurements of the distribution of tropospheric trace gases. Instruments and missions were identified and discussed. Several instrument/measurement/mission feasibility studies were recommended, including: a three-layer measurement of carbon monoxide, using a nadir-viewing gas filter correlation radiometer; a lower or middle tropospheric measurement of methane, using a nadir-viewing gas filter correlation radiometer; and a survey of lower, middle, and upper tropospheric trace gases using a nadir-viewing high-resolution interferometer operating in the thermal emission mode. It was also concluded that lidar systems appear to have the potential of obtaining measurments of tropospheric trace gases and aerosols from space. In addition to the specific instrument/mission recommendations, the panels made several general recommendations that may lead to future spaceborne instruments, techniques, and missions for tropospheric research.

  3. NEXT-Lunar Lander -an Opportunity for a Close Look at the Lunar South Pole

    NASA Astrophysics Data System (ADS)

    Homeister, Maren; Thaeter, Joachim; Scheper, Marc; Apeldoorn, Jeffrey; Koebel, David

    The NEXT-Lunar Lander mission, as contracted by ESA and investigated by OHB-System and its industrial study team, has two main purposes. The first is technology demonstration for enabling technologies like propulsion-based soft precision landing for future planetary landing missions. This involves also enabling technology experiments, like fuel cell, life science and life support, which are embedded in the stationary payload of the lander. The second main and equally important aspect is the in-situ investigation of the surface of the Moon at the lunar South Pole by stationary payload inside the Lander, deployable payload to be placed in the vicinity of the lander and mobile payload carried by a rover. The currently assessed model payload includes 15 instruments on the lander and additional five on the rover. They are addressing the fields geophysics, geochemistry, geology and radio astronomy preparation. The mission is currently under investigation in frame of a phase A mission study contract awarded by ESA to two independent industrial teams, of which one is led by OHB-System. The phase A activities started in spring 2008 and were conducted until spring 2010. A phase B is expected shortly afterwards. The analysed mission architectures range from a Soyuz-based mission to a Shared-Ariane V class mission via different transfer trajectories. Depending on the scenario payload masses including servicing of 70 to 150 kg can be delivered to the lunar surface. The lander can offer different services to the payload. The stationary payload is powered and conditioned by the lander. Examples for embarked payloads are an optical camera system, a Radio Science Experiment and a radiation monitor. The lander surface payload is deployed to the lunar surface by a 5 DoF robotic arm and will be powered by the Lander. To this group of payloads belong seismometers, a magnetometer and an instrumented Mole. The mobile payload will be carried by a rover. The rover is equipped with its own

  4. Rosetta Lander - Philae: activities after hibernation and landing preparations

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Biele, Jens; Sierks, Holger; Blazquez, Alejandro; Cozzoni, Barbara; Fantinati, Cinzia; Gaudon, Philippe; Geurts, Koen; Jurado, Eric; Paetz, Brigitte.; Maibaum, Michael

    Rosetta is a Cornerstone Mission of the ESA Horizon 2000 programme. It is going to rendezvous with comet 67P/Churyumov-Gerasimenko after a ten year cruise and will study both its nucleus and coma with an orbiting spacecraft as well as with a Lander, Philae. Aboard Philae, a payload consisting of ten scientific instruments will perform in-situ studies of the cometary material. Rosetta and Philae have been in hibernation until January 20, 2014. After the successful wakeup they will undergo a post hibernation commissioning. The orbiter instruments (like e.g. the OSIRIS cameras) are to characterize the target comet to allow landing site selection and the definition of a separation, descent and landing (SDL) strategy for the Lander. By August 2014 our currently very poor knowledge of the characteristics of the nucleus of the comet will have increased dramatically. The paper will report on the latest updates in Separation-Descent-Landing (SDL) planning. Landing is foreseen for November 2014 at a heliocentric distance of 3 AU. Philae will be separated from the mother spacecraft from a dedicated delivery trajectory. It then descends ballistically to the surface of the comet, stabilized with an internal flywheel. At touch-down anchoring harpoons will be fired and a damping mechanism within the landing gear will provide the lander from re-bouncing. The paper will give an overview of the Philae system, the operational activities after hibernation and the latest status on the preparations for landing.

  5. Mars Polar Lander mated with third stage of rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The Mars Polar Lander is suspended from a crane in the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) before being lowered to a workstand. There it will be mated to the third stage of the Boeing Delta II rocket before it is transported to Launch Pad 17B, Cape Canaveral Air Station. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  6. Mars Polar Lander mated with third stage of rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), the Mars Polar Lander is lowered onto the third stage of the Boeing Delta II rocket before it is transported to Launch Pad 17B, Cape Canaveral Air Station. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  7. Mars Polar Lander mated with third stage of rocket

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers mate the Mars Polar Lander to the third stage of the Boeing Delta II rocket before it is transported to Launch Pad 17B, Cape Canaveral Air Station. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  8. MASCOT- A Lightweight Multi-Purpose Lander Platform

    NASA Astrophysics Data System (ADS)

    Lange, M.,; Huhne, C.; Mierheim, O.; Braukhane, A.; Ho, T.-M.; Lange, C.; Wagenbach, S.; Witte, L.

    2012-07-01

    The Mobile Asteroid Surface Scout (MASCOT) is a small box shaped ~ 9 kg lander, developed to support and enhance larger S/C's scientific possibilities. Its P/L compartment includes currently 3 experiments of in total 3 kg. Further a mobility mechanism is on board which allows hopping manoeuvres on the asteroid. The system consist of two structures, a lander unit and a mechanical I/F structure. Both are designed as framework structures made of solid CFRP and CFRP- foam sandwich respectively. By designing consequently under the use of the materials orthotropic properties and additional design features (e.g. insertless) a very lightweight and stiff structure has been realised. With respect to a fully aluminium design a save of 75% structural mass for the lander unit was achieved and the structure is ready to enter Phase C. Being part of JAXA's Hayabusa 2 mission the launch date will be in December 2014 heading to the C-class asteroid 1999JU3.

  9. On the Tropical Rainfall Measuring Mission (TRMM): Bringing NASA's Earth System Science Program to the Classroom

    NASA Technical Reports Server (NTRS)

    Shepherd, J. Marshall

    1998-01-01

    The Tropical Rainfall Measuring Mission is the first mission dedicated to measuring tropical and subtropical rainfall using a variety of remote sensing instrumentation, including the first spaceborne rain-measuring radar. Since the energy released when tropical rainfall occurs is a primary "fuel" supply for the weather and climate "engine"; improvements in computer models which predict future weather and climate states may depend on better measurements of global tropical rainfall and its energy. In support of the STANYS conference theme of Education and Space, this presentation focuses on one aspect of NASA's Earth Systems Science Program. We seek to present an overview of the TRMM mission. This overview will discuss the scientific motivation for TRMM, the TRMM instrument package, and recent images from tropical rainfall systems and hurricanes. The presentation also targets educational components of the TRMM mission in the areas of weather, mathematics, technology, and geography that can be used by secondary school/high school educators in the classroom.

  10. Rosetta Lander - Landing and operations on comet 67P/Churyumov-Gerasimenko

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Fantinati, Cinzia; Maibaum, Michael; Geurts, Koen; Biele, Jens; Jansen, Sven; Küchemann, Oliver; Cozzoni, Barbara; Finke, Felix; Lommatsch, Valentina; Moussi-Soffys, Aurelie; Delmas, Cedric; O´Rourke, Laurence

    2016-08-01

    The Rosetta Lander Philae is part of the ESA Rosetta Mission which reached comet 67P/Churyumov-Gerasimenko after a 10 year cruise in August 2014. Since then, Rosetta has been studying both its nucleus and coma with instruments aboard the Orbiter. On November 12th, 2014 the Lander, Philae, was successfully delivered to the surface of the comet and operated for approximately 64 h after separation from the mother spacecraft. Since the active cold gas system aboard the Lander as well as the anchoring harpoons did not work, Philae bounced after the first touch-down at the planned landing site "Agilkia". At the final landing site, "Abydos", a modified First Scientific Sequence was performed. Due to the unexpectedly low illumination conditions and a lack of anchoring the sequence had to be adapted in order to minimize risk and maximize the scientific output. All ten instruments could be activated at least once, before Philae went into hibernation. In June 2015, the Lander contacted Rosetta again having survived successfully a long hibernation phase. This paper describes the Lander operations around separation, during descent and on the surface of the comet. We also address the partly successful attempts to re-establish contact with the Lander in June/July, when the internal temperature & power received were sufficient for Philae to become active again.

  11. Design of a Thermal and Micrometeorite Protection System for an Unmanned Lunar Cargo Lander

    NASA Technical Reports Server (NTRS)

    Hernandez, Carlos A.; Sunder, Sankar; Vestgaard, Baard

    1989-01-01

    The first vehicles to land on the lunar surface during the establishment phase of a lunar base will be unmanned lunar cargo landers. These landers will need to be protected against the hostile lunar environment for six to twelve months until the next manned mission arrives. The lunar environment is characterized by large temperature changes and periodic micrometeorite impacts. An automatically deployable and reconfigurable thermal and micrometeorite protection system was designed for an unmanned lunar cargo lander. The protection system is a lightweight multilayered material consisting of alternating layers of thermal and micrometeorite protection material. The protection system is packaged and stored above the lander common module. After landing, the system is deployed to cover the lander using a system of inflatable struts that are inflated using residual fuel (liquid oxygen) from the fuel tanks. Once the lander is unloaded and the protection system is no longer needed, the protection system is reconfigured as a regolith support blanket for the purpose of burying and protecting the common module, or as a lunar surface garage that can be used to sort and store lunar surface vehicles and equipment. A model showing deployment and reconfiguration of the protection system was also constructed.

  12. Planetary Lake Lander - A Robotic Sentinel to Monitor a Remote Lake

    NASA Technical Reports Server (NTRS)

    Pedersen, Liam; Smith, Trey; Lee, Susan; Cabrol, Nathalie; Rose, Kevin

    2012-01-01

    The Planetary Lake Lander Project is studying the impact of rapid deglaciation at a high altitude alpine lake in the Andes, where disrupted environmental, physical, chemical, and biological cycles result in newly emerging natural patterns. The solar powered Lake Lander robot is designed to monitor the lake system and characterize both baseline characteristics and impacts of disturbance events such as storms and landslides. Lake Lander must use an onboard adaptive science-on-the-fly approach to return relevant data about these events to mission control without exceeding limited energy and bandwidth resources. Lake Lander carries weather sensors, cameras and a sonde that is winched up and down the water column to monitor temperature, dissolved oxygen, turbidity and other water quality parameters. Data from Lake Lander is returned via satellite and distributed to an international team of scientists via web-based ground data systems. Here, we describe the Lake Lander Project scientific goals, hardware design, ground data systems, and preliminary data from 2011. The adaptive science-on-the-fly system will be described in future papers.

  13. Brake Failure from Residual Magnetism in the Mars Exploration Rover Lander Petal Actuator

    NASA Technical Reports Server (NTRS)

    Jandura, Louise

    2004-01-01

    In January 2004, two Mars Exploration Rover spacecraft arrived at Mars. Each safely delivered an identical rover to the Martian surface in a tetrahedral lander encased in airbags. Upon landing, the airbags deflated and three Lander Petal Actuators opened the three deployable Lander side petals enabling the rover to exit the Lander. Approximately nine weeks prior to the scheduled launch of the first spacecraft, one of these mission-critical Lander Petal Actuators exhibited a brake stuck-open failure during its final flight stow at Kennedy Space Center. Residual magnetism was the definitive conclusion from the failure investigation. Although residual magnetism was recognized as an issue in the design, the lack of an appropriately specified lower bound on brake drop-out voltage inhibited the discovery of this problem earlier in the program. In addition, the brakes had more unit-to-unit variation in drop-out voltage than expected, likely due to a larger than expected variation in the magnetic properties of the 15-5 PH stainless steel brake plates. Failure analysis and subsequent rework of two other Lander Petal Actuators with marginal brakes was completed in three weeks, causing no impact to the launch date.

  14. Rock Moved by Mars Lander Arm, Stereo View

    NASA Technical Reports Server (NTRS)

    2008-01-01

    The robotic arm on NASA's Phoenix Mars Lander slid a rock out of the way during the mission's 117th Martian day (Sept. 22, 2008) to gain access to soil that had been underneath the rock.The lander's Surface Stereo Imager took the two images for this stereo view later the same day, showing the rock, called 'Headless,' after the arm pushed it about 40 centimeters (16 inches) from its previous location.

    'The rock ended up exactly where we intended it to,' said Matt Robinson of NASA's Jet Propulsion Laboratory, robotic arm flight software lead for the Phoenix team.

    The arm had enlarged the trench near Headless two days earlier in preparation for sliding the rock into the trench. The trench was dug to about 3 centimeters (1.2 inches) deep. The ground surface between the rock's prior position and the lip of the trench had a slope of about 3 degrees downward toward the trench. Headless is about the size and shape of a VHS videotape.

    The Phoenix science team sought to move the rock in order to study the soil and the depth to subsurface ice underneath where the rock had been.

    This left-eye and right-eye images for this stereo view were taken at about 12:30 p.m., local solar time on Mars. The scene appears three-dimensional when seen through blue-red glasses.The view is to the north northeast of the lander.

    The Phoenix Mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is by JPL, Pasadena, Calif. Spacecraft development was by Lockheed Martin Space Systems, Denver.

  15. Prediction of Viking lander camera image quality

    NASA Technical Reports Server (NTRS)

    Huck, F. O.; Burcher, E. E.; Jobson, D. J.; Wall, S. D.

    1976-01-01

    Formulations are presented that permit prediction of image quality as a function of camera performance, surface radiance properties, and lighting and viewing geometry. Predictions made for a wide range of surface radiance properties reveal that image quality depends strongly on proper camera dynamic range command and on favorable lighting and viewing geometry. Proper camera dynamic range commands depend mostly on the surface albedo that will be encountered. Favorable lighting and viewing geometries depend mostly on lander orientation with respect to the diurnal sun path over the landing site, and tend to be independent of surface albedo and illumination scattering function. Side lighting with low sun elevation angles (10 to 30 deg) is generally favorable for imaging spatial details and slopes, whereas high sun elevation angles are favorable for measuring spectral reflectances.

  16. Robotic Lunar Lander Development Project Status

    NASA Technical Reports Server (NTRS)

    Hammond, Monica; Bassler, Julie; Morse, Brian

    2010-01-01

    This slide presentation reviews the status of the development of a robotic lunar lander. The goal of the project is to perform engineering tests and risk reduction activities to support the development of a small lunar lander for lunar surface science. This includes: (1) risk reduction for the flight of the robotic lander, (i.e., testing and analyzing various phase of the project); (2) the incremental development for the design of the robotic lander, which is to demonstrate autonomous, controlled descent and landing on airless bodies, and design of thruster configuration for 1/6th of the gravity of earth; (3) cold gas test article in flight demonstration testing; (4) warm gas testing of the robotic lander design; (5) develop and test landing algorithms; (6) validate the algorithms through analysis and test; and (7) tests of the flight propulsion system.

  17. Radiation dosimetry measurements during U.S. Space Shuttle missions with the RME-III.

    PubMed

    Golightly, M J; Hardy, K; Quam, W

    1994-01-01

    Time-resolved radiation dosimetry measurements inside the crew compartment have been made during recent Shuttle missions with the U.S. Air Force Radiation Monitoring Equipment-III (RME-III), a portable battery-powered four-channel tissue equivalent proportional counter. Results from the first six missions are presented and discussed. Half of the missions had orbital inclinations of 28.5 degrees with the remainder at inclinations of 57 degrees or greater; altitudes ranged from 300 to 600 km. The determined dose equivalent rates ranged from 70 to 5300 microSv/day. The RME-III measurements are in good agreement with other dosimetry measurements made aboard the vehicles. Measurements indicate that medium- and high-LET particles contribute less than 2% of the particle fluence for all missions, but up to 50% of the dose equivalent, depending on the spacecraft's altitude and orbital inclination. Isocontours of fluence, dose and dose equivalent rate have been developed from measurements made during the STS-28 mission. The drift rate of the South Atlantic Anomaly is estimated to be 0.49 degrees W/yr and 0.12 degrees N/yr. The calculated trapped proton and GCR dose for the STS-28 mission was significantly lower than the measured values.

  18. CE-4 Mission and Future Journey to Lunar

    NASA Astrophysics Data System (ADS)

    Zou, Yongliao; Wang, Qin; Liu, Xiaoqun

    2016-07-01

    Chang'E-4 mission, being undertaken by phase two of China Lunar Exploration Program, represents China's first attempt to explore farside of lunar surface. Its probe includes a lander, a rover and a telecommunication relay which is scheduled to launch in around 2018. The scientific objectives of CE-4 mission will be implemented to investigate the lunar regional geological characteristics of landing and roving area, and also will make the first radio-astronomy measurements from the most radio-quiet region of near-earth space. The rover will opreate for at least 3 months, the lander for half a year, and the relay for no less than 3 years. Its scinetific instruments includes Cameras, infrared imaging spectrometer, Penetrating Radar onboard the rover in which is the same as the paylads on board the CE-3 rover, and a Dust-analyzer, a Temperature-instrument and a Wide Band Low Frequency Digital Radio Astronomical Station will be installed on board the lander. Our scientific goals of the future lunar exploration will aim at the lunar geology, resources and surface environments. A series of exploraion missions such as robotic exploration and non-manned lunar scientific station is proposed in this paper.

  19. TAGS 85/2N RTG Power for Viking Lander Capsule

    DOE R&D Accomplishments Database

    1969-08-01

    Results of studies performed by Isotopes, Inc., Nuclear Systems Division, to optimize and baseline a TAGS 85/2N RTG for the Viking Lander Capsule prime electrical power source are presented. These studies generally encompassed identifying the Viking RTG mission profile and design requirements, and establishing a baseline RTG design consistent with these requirements.

  20. System Analysis Applied to Autonomy: Application to Human-Rated Lunar/Mars Landers

    NASA Technical Reports Server (NTRS)

    Young, Larry A.

    2006-01-01

    System analysis is an essential technical discipline for the modern design of spacecraft and their associated missions. Specifically, system analysis is a powerful aid in identifying and prioritizing the required technologies needed for mission and/or vehicle development efforts. Maturation of intelligent systems technologies, and their incorporation into spacecraft systems, are dictating the development of new analysis tools, and incorporation of such tools into existing system analysis methodologies, in order to fully capture the trade-offs of autonomy on vehicle and mission success. A "system analysis of autonomy" methodology will be outlined and applied to a set of notional human-rated lunar/Mars lander missions toward answering these questions: 1. what is the optimum level of vehicle autonomy and intelligence required? and 2. what are the specific attributes of an autonomous system implementation essential for a given surface lander mission/application in order to maximize mission success? Future human-rated lunar/Mars landers, though nominally under the control of their crew, will, nonetheless, be highly automated systems. These automated systems will range from mission/flight control functions, to vehicle health monitoring and prognostication, to life-support and other "housekeeping" functions. The optimum degree of autonomy afforded to these spacecraft systems/functions has profound implications from an exploration system architecture standpoint.

  1. NASA's International Lunar Network Anchor Nodes and Robotic Lunar Lander Project Update

    NASA Technical Reports Server (NTRS)

    Morse, Brian J.; Reed, Cheryl L. B.; Kirby, Karen W.; Cohen, Barbara A.; Bassler, Julie A.; Harris, Danny W.; Chavers, D. Gregory

    2010-01-01

    In early 2008, NASA established the Lunar Quest Program, a new lunar science research program within NASA s Science Mission Directorate. The program included the establishment of the anchor nodes of the International Lunar Network (ILN), a network of lunar science stations envisioned to be emplaced by multiple nations. This paper describes the current status of the ILN Anchor Nodes mission development and the lander risk-reduction design and test activities implemented jointly by NASA s Marshall Space Flight Center and The Johns Hopkins University Applied Physics Laboratory. The lunar lander concepts developed by this team are applicable to multiple science missions, and this paper will describe a mission combining the functionality of an ILN node with an investigation of lunar polar volatiles.

  2. Laboratory measurements of dielectric properties of compact and granular materials, in relation with Rosetta mission.

    NASA Astrophysics Data System (ADS)

    Brouet, Y.; Levasseur-Regourd, A. C.; Encrenaz, P.; Gheudin, M.; Ciarletti, V.; Gulkis, S.; Jambon, A.; Ruffié, G.; Prigent, C.

    2012-04-01

    The European Rosetta spacecraft (s/c), launched in 2004, will be the first s/c to orbit a comet and place a lander module on its surface. In 2014, the s/c will rendezvous with the comet 67P/Churyumov-Gerasimenko and place the lander on its surface thereby allowing in situ and remote sensing of the comet nucleus. Two radio experiments, one passive (MIRO [1]) and one active (CONSERT [2]), are aboard the Rosetta s/c. MIRO, composed of two radiometers, with center band frequencies at 190 GHz and at 563 GHz to determine the brightness temperatures of the target surfaces and sub-surfaces, has already observed asteroids (2867) Steins [3] and (21) Lutetia [4]. CONSERT will investigate the deep interior of the nucleus using 90 MHz radio-waves transmitted from the orbiter through the nucleus and returned to the orbiter from the lander. To support interpretations of MIRO and CONSERT observations, a program of dielectric properties measurements is under development on a large range of frequencies encompassing those of the above-mentioned experiments. Several instruments for dielectric constant determination are available at IMS laboratory (Bordeaux, France): impedance analyzer, coaxial sensor, resonant cavities (measuring respectively at 100 MHz, 0.5-6 GHz, 1.2-13.4 GHz). Millimeter benches are available at both IMS and LERMA laboratories (measuring respectively at 30-110 GHz and 70-230 GHz). Taking into account the possible presence of regolith layers on the surface of asteroids or nuclei and the very low density of cometary nuclei [5], the dependence of the dielectric constant on the structure and porosity of given granular materials needs also to be investigated (while the thermal and hygrometric conditions are carefully monitored). We have already reported measurements obtained on various meteorites, possibly representative of some asteroid surfaces [6, 7]. We will also report systematic measurements obtained on a large sample of pyroclastic deposits from Etna, providing

  3. Exploring Triton with multiple landers

    NASA Technical Reports Server (NTRS)

    Balint, Tibor S.

    2005-01-01

    In our pathway for Outer Planetary Exploration several mission concepts were considered, based on the proposed JIMO mission architecture. This paper describes a JIMO follow-on mission concept to Neptunes largest moon. Triton is a target of interest for outer solar system studies. It has a highly inclined retrograde orbit, suggesting that it may have been a Kuiper Belt object captured by Neptune. Given this assumption its composition, which may include organic materials, would be of significant scientific interest.

  4. Rosetta Lander - Philae: Landing preparations

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Biele, Jens; Blazquez, Alejandro; Cozzoni, Barbara; Delmas, Cedric; Fantinati, Cinzia; Gaudon, Philippe; Geurts, Koen; Jurado, Eric; Küchemann, Oliver; Lommatsch, Valentina; Maibaum, Michael; Sierks, Holger; Witte, Lars

    2015-02-01

    Rosetta and Philae have been in hibernation until January 20, 2014. After the successful wakeup they underwent a post-hibernation commissioning. The orbiter instruments (like e.g. the OSIRIS cameras, VIRTIS, MIRO, Alice and ROSINA) characterized the target comet and its environment to allow landing site selection and the definition of a separation, descent and landing (SDL) strategy for the Lander. By September 2014 our previously poor knowledge of the characteristics of the nucleus of the comet has increased drastically and the nominal and backup landing could be selected. The nominal site, as well as the corresponding descent strategy have been confirmed in mid-October, one month before the landing. The paper summarizes the selection process for a landing site and the planning for Separation-Descent-Landing (SDL).

  5. Declining Sunshine for Phoenix Lander

    NASA Technical Reports Server (NTRS)

    2008-01-01

    The yellow line on this graphic indicates the number of hours of sunlight each sol, or Martian day, at the Phoenix landing site's far-northern latitude, beginning with the entire Martian day (about 24 hours and 40 minutes) for the first 90 sols, then declining to no sunlight by about sol 300. The blue tick mark indicates that on Sol 124 (Sept. 29, 2008), the sun is above the horizon for about 20 hours.

    The brown vertical bar represents the period from Nov. 18 to Dec. 24, 2008, around the 'solar conjunction,' when the sun is close to the line between Mars and Earth, affecting communications.

    The green vertical rectangle represents the period from February to November 2009 when the Phoenix lander is expected to be encased in carbon-dioxide ice.

  6. Science, Measurement, and Technology Requirements for Infrared Climate Benchmark Missions

    NASA Technical Reports Server (NTRS)

    Johnson, David G.; Mlynczak, Martin G.

    2011-01-01

    Quantifying climate change in the presence of natural variability requires highly accurate global measurements covering more than a decade. Instrument design considerations for trending terrestrial emitted radiance are described.

  7. Conclusion of Viking Lander Imaging Investigation: Picture catalog of experiment data record

    NASA Technical Reports Server (NTRS)

    Wall, S. D.; Ashmore, T. C.

    1985-01-01

    The images returned by the two Viking landers during the Viking Survey Mission are presented in this report. Listing of supplemental information which describe the conditions under which the images were acquired are included. Subsets of the images are listed in a variety of sequences to aid in locating images of interest. The format and organization of the digital magnetic tape storage of the images are described. A brief description of the mission and the camera system is also included.

  8. Phoenix Lander's Thermal Evolved Gas Analyzer: Differential Scanning Calorimeter and Mass Spectrometer Database Development

    NASA Technical Reports Server (NTRS)

    Sutter, B.; Lauer, H. V.; Golden, D. C.; Ming, D. W.; Boynton, W. V.

    2008-01-01

    The Mars Scout Phoenix lander will land in the north polar region of Mars in May, 2008. One objective of the Phoenix lander is to search for evidence of past life in the form of molecular organics that may be preserved in the subsurface soil. The Thermal Evolved Gas Analyzer (TEGA) was developed to detect these organics by coupling a simultaneous differential thermal analyzer (SDTA) with a mass spectrometer. Martian soil will be heated to approx.1000 C and potential organic decomposition products such as CO2, CH4 etc. will be examined for with the MS. TEGA s SDTA will also assess the presence of endothermic and exothermic reactions that are characteristic of soil organics and minerals as the soil is heated. The MS in addition to detecting organic decompositon products, will also assess the levels of soil inorganic volatiles such as H2O, SO2, and CO2. Organic detection has a high priority for this mission; however, TEGA has the ability to provide valuable insight into the mineralogical composition of the soil. The overall goal of this work is to develop a TEGA database of minerals that will serve as a reference for the interpretation of Phoenix-TEGA. Previous databases for the ill-fated Mars Polar Lander (MPL)-TEGA instrument only went to 725 C. Furthermore, the MPL-TEGA could only detect CO2 and H2O while the Phoenix-TEGA MS can examine up to 144 atomic mass units. The higher temperature Phoenix-TEGA SDTA coupled with the more capable MS indicates that a higher temperature database is required for TEGA interpretation. The overall goal of this work is to develop a differential scanning calorimeter (DSC) database of minerals along with corresponding MS data of evolved gases that can used to interpret TEGA data during and after mission operations. While SDTA and DSC measurement techniques are slightly different (SDTA does not use a reference pan), the results are fundamentally similar and thus DSC is a useful technique in providing comparative data for the TEGA

  9. Mars Polar Lander Landing Zone Compared With JPL

    NASA Technical Reports Server (NTRS)

    1999-01-01

    What will Mars Polar Lander find when it reaches the red planet on December 3, 1999? The Mars Global Surveyor (MGS) Mars Orbiter Camera (MOC)--currently operating in Mars orbit since September 1997--is providing some of our highest-resolution views of the planet ever obtained. MOC, in fact, can see objects the size of automobiles with its 1.5 meter (5 ft) per pixel capability.

    To give some sense of the nature of polar terrain in the vicinity of Mars Polar Lander's 76oS, 195oW landing zone, very high resolution MOC images are here compared with the 'main campus' of the Jet Propulsion Laboratory (JPL). JPL is located in Pasadena, California, and is part of the California Institute of Technology (Caltech). Together with partners Lockheed Martin Astronautics (Denver, CO), University of California-Los Angeles, The Planetary Society (Pasadena, CA), and Malin Space Science Systems (San Diego, CA), JPL is operating and managing the Mars Polar Lander and Deep Space 2 missions under contract from NASA.

    The three MOC images shown next to each view of JPL represent the three most abundant terrain types seen in the Mars Polar Lander landing ellipse--ridges and small knobs, ridges and gullies, and ridges and pits. Each is shown at the same scale as the buildings of the Jet Propulsion Laboratory (1.5 m/pixel). Each image is about 400 meters (437 yards) across and is illuminated by sunlight from the lower right. Mars Polar Lander Landing Zone Compared With JPL The picture on the left is a MOC image taken in mid-November 1999 near the west edge of Mars Polar Lander's landing ellipse. Many small, bright pinnacles or knobs are visible amid a few circular features and dark patches. The picture on the right shows a portion of the Jet Propulsion Laboratory at the same scale. Note that buildings and some trees can be discerned in the JPL photo. Ridges and Gullies Compared to Features of Similar Scale Taken in November 1999 after the winter frost had finally cleared away, this

  10. Findings from the PP-SESAME experiment on board the Philae/ROSETTA lander on the surface of comet 67P

    NASA Astrophysics Data System (ADS)

    Lethuillier, A.; Le Gall, A.; Hamelin, M.; Ciarletti, V.; Caujolle-Bert, S.; Schmidt, W.; Grard, R.; Fischer, H.; Seidensticker, K.

    2015-10-01

    The Permittivity Probe (PP-SESAME [1]) on-board the Philae Lander of the ROSETTA mission was designed to constrain the complex permittivity of the first 2 meters of the nucleus of comet 67P/Churyumov- Gerasimenko and to monitor its variations with time. Doing so, it is meant to provide unique insight into the composition (and activity if data could have been acquired longer) of the comet. In this paper, we present the analysis of the PP-SESAME measurements acquired during the first science sequence, on November 13, 2014, on the surface of the comet.

  11. Solving the color calibration problem of Martian lander images

    NASA Astrophysics Data System (ADS)

    Levin, Ron L.; Levin, Gilbert V.

    2004-02-01

    The color of published Viking and Pathfinder images varies greatly in hue, saturation and chromaticity. True color is important for interpretation of physical, chemical, geological and, possibly, biological information about Mars. The weak link in the imaging process for both missions was the reliance on imaging color charts reflecting Martian ambient light. While the reflectivity of the charts is well known, the spectrum of their illumination on Mars is not. "Calibrated" images are usually reddish, attributed to atmospheric dust, but hues range widely because of the great uncertainty in the illumination spectrum. Solar black body radiation, the same on Mars as on Earth, is minimally modified by the atmosphere of either planet. For red dust to change the spectrum significantly, reflected light must exceed the transmitted light. Were this the case, shadows would be virtually eliminated. Viking images show prominent shadows. Also, Pathfinder"s solar cells, activated by blue light, would have failed under the predominately red spectrum generally attributed to Mars. Accordingly, no consensus has emerged on the colors of the soil, rocks and sky of Mars. This paper proposes two techniques to eliminate color uncertainty from future images, and also to allow recalibration of past images: 1. Calibration of cameras at night through minimal atmospheric paths using light sources brought from Earth, which, used during the day, would permit calculation of red, green and blue intensities independent of scene illumination; 2. Use of hyperspectral imaging to measure the complete spectrum of each pixel. This paper includes a calibration of a NASA Viking lander image based on its color chart as it appears on Earth. The more realistic Martian colors become far more interesting, showing blue skies, brownish soil and rocks, both with yellow, olive, and greenish areas.

  12. The Asteroid Impact Mission

    NASA Astrophysics Data System (ADS)

    Carnelli, Ian; Galvez, Andres; Mellab, Karim

    2016-04-01

    The Asteroid Impact Mission (AIM) is a small and innovative mission of opportunity, currently under study at ESA, intending to demonstrate new technologies for future deep-space missions while addressing planetary defense objectives and performing for the first time detailed investigations of a binary asteroid system. It leverages on a unique opportunity provided by asteroid 65803 Didymos, set for an Earth close-encounter in October 2022, to achieve a fast mission return in only two years after launch in October/November 2020. AIM is also ESA's contribution to an international cooperation between ESA and NASA called Asteroid Impact Deflection Assessment (AIDA), consisting of two mission elements: the NASA Double Asteroid Redirection Test (DART) mission and the AIM rendezvous spacecraft. The primary goals of AIDA are to test our ability to perform a spacecraft impact on a near-Earth asteroid and to measure and characterize the deflection caused by the impact. The two mission components of AIDA, DART and AIM, are each independently valuable but when combined they provide a greatly increased scientific return. The DART hypervelocity impact on the secondary asteroid will alter the binary orbit period, which will also be measured by means of lightcurves observations from Earth-based telescopes. AIM instead will perform before and after detailed characterization shedding light on the dependence of the momentum transfer on the asteroid's bulk density, porosity, surface and internal properties. AIM will gather data describing the fragmentation and restructuring processes as well as the ejection of material, and relate them to parameters that can only be available from ground-based observations. Collisional events are of great importance in the formation and evolution of planetary systems, own Solar System and planetary rings. The AIDA scenario will provide a unique opportunity to observe a collision event directly in space, and simultaneously from ground-based optical and

  13. Onboard Processing of Electromagnetic Measurements for the Luna - Glob Mission

    NASA Astrophysics Data System (ADS)

    Hruska, F.; Kolmasova, I.; Santolik, O.; Skalski, A.; Pronenko, V.; Belyayev, S.; Lan, R.; Uhlir, L.

    2013-12-01

    The LEMRA-L instrument (Long-wavelength Electro-Magnetic Radiation Analyzer) will be implemented on the LUNA-GLOB spacecraft. It will analyze the data of the three-axial flux gate (DC - 10Hz) and searchcoil (1Hz - 10kHz) magnetometers LEMI. It will measure intensity, polarization, and coherence properties of waves in plasmas of the solar wind, in the lunar wake and its boundaries, and study the magnetic anomalies. We will use new modern robust onboard analysis methods to estimate the wave coherence, sense of polarization, ellipticity, and wave-vector direction, and thus substantially compress the transmitted data volumes, while conserving the important scientific information. In the burst mode data set intended for studying nonlinear phenomena, we will conserve the continuous flux-gate magnetometer data and discrete snapshots of three axial waveform measurements. In the survey-mode data set, continuous flux-gate magnetometer data will be transmitted together with onboard analyzed and averaged spectral matrices from the higher-frequency wave measurements or with onboard calculated propagation and polarization parameters.

  14. An Autonomous Instrument Package for Providing 'Pathfinder' Network Measurements on the Surface of Mars

    NASA Technical Reports Server (NTRS)

    Banerdt, W. B.; Lognonne, Ph.

    2003-01-01

    The investigations of the interior and atmosphere of Mars have been identified as high scientific priorities in most planetary exploration strategy document since the time of Viking. Most recently, the National Academy of Sciences has recommended a long-lived Mars network mission as its second highest scientific priority for Mars (after sample return) for the purpose of performing seismological investigations of the interior and studying the activity and composition of the atmosphere. Despite consistent recommendations by advisory groups, Mars network missions (MESUR, Marsnet, InterMarsnet, NetLander/MSR 05, NetLander/Premier 07, NetLander/?? 09) have undergone a strikingly consistent 'Phoenix' cycle of death and rebirth over the past 15 years, and there are still no confirmed plans to address the interior and atmosphere of Mars. The latest attempt is the NetLander mission. The objective of NetLander is to place a network of four landers on Mars to perform detailed measurements of the seismicity and atmospheric pressure, temperature, wind, humidity, and opacity (as well as provide images, subsurface radar sounding profiles, and electric/magnetic field measurements). However, this mission has recently encountered major programmatic difficulties within CNES and NASA. NASA has already cancelled its participation and the mission itself is facing imminent cancellation if CNES cannot solve programmatic issues associated with launching the mission in 2009. In this presentation we will describe an approach that could move us closer to realizing the goals of a Mars network mission and will secure at least one geophysical and meteorological observatory in 2009.

  15. Novel Architecture for a Long-Life, Lightweight Venus Lander

    SciTech Connect

    Bugby, D.; Seghi, S.; Kroliczek, E.; Pauken, M.

    2009-03-16

    This paper describes a novel concept for an extended lifetime, lightweight Venus lander. Historically, to operate in the 480 deg. C, 90 atm, corrosive, mostly CO{sub 2} Venus surface environment, previous landers have relied on thick Ti spherical outer shells and thick layers of internal insulation. But even the most resilient of these landers operated for only about 2 hours before succumbing to the environment. The goal on this project is to develop an architecture that extends lander lifetime to 20-25 hours and also reduces mass compared to the Pioneer Venus mission architecture. The idea for reducing mass is to: (a) contain the science instruments within a spherical high strength lightweight polymer matrix composite (PMC) tank; (b) surround the PMC tank with an annular shell of high performance insulation pre-pressurized to a level that (after landing) will exceed the external Venus surface pressure; and (c) surround the insulation with a thin Ti outer shell that contains only a net internal pressure, eliminating buckling overdesign mass. The combination of the PMC inner tank and thin Ti outer shell is lighter than a single thick Ti outer shell. The idea for extending lifetime is to add the following three features: (i) an expendable water supply that is placed within the insulation or is contained in an additional vessel within the PMC tank; (ii) a thin spherical evaporator shell placed within the insulation a short radial distance from the outer shell; and (iii) a thin heat-intercepting liquid cooled shield placed inboard of the evaporator shell. These features lower the temperature of the insulation below what it would have been with the insulation alone, reducing the internal heat leak and lengthening lifetime. The use of phase change materials (PCMs) inside the PMC tank is also analyzed as a lifetime-extending design option. The paper describes: (1) analytical modeling to demonstrate reduced mass and extended life; (2) thermal conductivity testing of high

  16. Logistics impacts on lunar and Mars lander design

    NASA Technical Reports Server (NTRS)

    Donahue, Benjamin

    1991-01-01

    The results of trade studies and evaluations done to determine the impact of accommodation and unloading of cargo on spacecraft design are reviewed. It is concluded that the effectiveness of the surface mission to moon or Mars is best accomplished by providing for undivided cargo delivery and for cargo unloading indirectly to earth surface without the aid of a surface system unloader, for immediate cargo drop during descent abort to orbit, for immediate cargo drop in case of need for an emergency ascent from the surface, and for contiguous placement of cab and surface habitat modules. For exploration architectures that include multiple site visits within as much as several hundred km of each other, use of excursion vehicles capable of short suborbital hops to secondary sites is much less expensive in terms of IMLEO than a strategy of using multiple landers or multiple missions.

  17. Stereochemical investigation of cometary matter onboard the Rosetta Lander.

    PubMed

    Meierhenrich, U J; Thiemann, W H; Rosenbauer, H

    2001-01-01

    At present the European Space Agency is working on one of its Cornerstone Missions, named "Rosetta", to be launched in January 2003 for a visit to comet 46P/Wirtanen2 in 2011. The Rosetta spacecraft will carry a small subsatellite, the Rosetta Lander3 (RoLand), to be detached from the orbiter and land on the surface of the comet's nucleus. One of our main scientific interests is to find out whether chiral organic compounds in cometary matter brought to the Earth by cometary impacts might have had, due to corresponding enantiomeric excesses, a seed function in determining the handedness which is characteristic of homochiral compounds employed by life on Earth. For this reason we have developed an Experiment for the ROSETTA mission, named Cometary Sampling and Composition Experiment (COSAC).

  18. Summary Report of Mission Acceleration Measurement for STS-87, Launched November 19, 1997

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; Hrovat, Kenneth; McPherson, Kevin; DeLombard, Richard; Reckart, Timothy

    1999-01-01

    Two accelerometer systems, the Orbital Acceleration Research Experiment and the Space Acceleration Measurement System, were used to measure and record the microgravity environment of the Orbiter Columbia during the STS-87 mission in November-December 1997. Data from two separate Space Acceleration Measurement System units were telemetered to the ground during the mission and data plots were displayed for investigators of the Fourth United States Microgravity Payload experiments in near real-time using the World Wide Web. Plots generated using Orbital Acceleration Research Experiment data (telemetered to the ground using a tape delay) were provided to the investigators using the World Wide Web approximately twelve hours after data recording. Disturbances in the microgravity environment as recorded by these instruments are grouped by source type: Orbiter systems, on-board activities, payload operations, and unknown sources. The environment related to the Ku-band antenna dither, Orbiter structural modes, attitude deadband collapses, water dump operations, crew sleep, and crew exercise was comparable to the effects of these sources on previous Orbiter missions. Disturbances related to operations of the Isothermal Dendritic Growth Experiment and Space Acceleration Measurement Systems that were not observed on previous missions are detailed. The effects of Orbiter cabin and airlock depressurization and extravehicular activities are also reported for the first time. A set of data plots representing the entire mission is included in the CD-ROM version of this report.

  19. Carbon cycle relevant measurements with the TROPOMI instrument on the Sentinel 5 Precursor mission

    NASA Astrophysics Data System (ADS)

    Aben, I.; aan de Brugh, J.; Hu, H.; Borsdorff, T.; Scheepmaker, R. A.; van Hees, R.; Krijger, M.; Tol, P.; Hoogeveen, R.; Butz, A.; Frankenberg, C.; Guanter, L.; Koehler, P.; Houweling, S.; Hasekamp, O. P.; Veefkind, P.; Landgraf, J.

    2015-12-01

    In 2016 Q2 the Sentinel 5 Precursor (S5P) mission will be launched with the TROPOMI instrument as its single instrument payload. It comprises global measurements of the atmospheric composition for air quality and climate application as part of the Copernicus atmospheric services. To this purpose it will perform nadir observations in the UV-VIS (270 - 500 nm), NIR (675-725 nm), and SWIR (2305-2385 nm) measuring key species such as O3, NO2, CO, CH4, CH2O, SO2. TROPOMI is a push broom grating spectrometer combining a large swath (~2600 km) with high spatial resolution (7x7km2 in nadir) measurements, and has heritage from OMI and SCIAMACHY. The S5P will extend the data records from these missions, as well as being a preparatory (precursor) mission for the Sentinel-5 missions planned for 2020 onward. In this presentation we will address the Carbon cycle relevant SWIR products from TROPOMI (CH4, CO) as well as a fluorescence product from the NIR. In particular, this presentation will focus on the potential for CH4 measurements also in respect to other existing missions.

  20. Summary Report of Mission Acceleration Measurement for STS-87: Launched November 19, 1997

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; Hrovat, Kenneth; McPherson, Kevin; DeLombard, Richard; Reckart, Timothy

    1999-01-01

    Two accelerometer systems, the Orbital Acceleration Research Experiment and the Space Acceleration Measurement System, were used to measure and record the microgravity environment of the Orbiter Columbia during the STS-87 mission in November-December 1997. Data from two separate Space Acceleration Measurement System units were telemetered to the ground during the mission and data plots were displayed for investigators of the Fourth United States Microgravity Payload experiments in near real-time using the World Wide Web. Plots generated using Orbital Acceleration Research Experiment data (telemetered to the ground using a tape delay) were provided to the investigators using the World Wide Web approximately twelve hours after data recording. Disturbances in the microgravity environment as recorded by these instruments are grouped by source type: Orbiter systems, on-board activities, payload operations, and unknown sources. The environment related to the Ku-band antenna dither, Orbiter structural modes, attitude deadband collapses, water dump operations, crew sleep, and crew exercise was comparable to the effects of these sources on previous Orbiter missions. Disturbances related to operations of the Isothermal Dendritic Growth Experiment and Space Acceleration Measurement Systems that were not observed on previous missions are detailed. The effects of Orbiter cabin and airlock depressurization and extravehicular activities are also reported for the first time. A set of data plots representing the entire mission is included in the CD-ROM version of this report.

  1. Robotic Landers: Small With Big Benefits

    NASA Video Gallery

    NASA and the Johns Hopkins University Applied Physics Laboratory are creating a new generation of smart, versatile robotic landers. for exploring the moon, asteroids, and other airless bodies in ou...

  2. Robotic Lander Gets Sideways During Test

    NASA Video Gallery

    During a recent test at NASA’s Marshall Space Flight Center inHuntsville, Ala., the robotic lander prototype, known as Mighty Eagle,performed a hover test flying up to three feet and then trans...

  3. Two-Dimensional Planetary Surface Lander

    NASA Astrophysics Data System (ADS)

    Hemmati, H.; Sengupta, A.; Castillo, J.; McElrath, T.; Roberts, T.; Willis, P.

    2014-06-01

    A systems engineering study was conducted to leverage a new two-dimensional (2D) lander concept with a low per unit cost to enable scientific study at multiple locations with a single entry system as the delivery vehicle.

  4. The Lunar Lander "HabiTank" Concept

    NASA Technical Reports Server (NTRS)

    Kennedy, Kriss J.

    2007-01-01

    This paper will summarize the study that was conducted under the auspices of the National Aeronautics and Space Administration (NASA), lead by Johnson Space Center s Engineering Directorate in support of the Lunar Lander Preparatory Study (LLPS) as sponsored by the Constellation Program Office (CxPO), Advanced Projects Office (APO). The lunar lander conceptual design and analysis is intended to provide an understanding of requirements for human space exploration of the Moon using the Advanced Projects Office Pre-Lander Project Office selected "HabiTank" Lander concept. In addition, these analyses help identify system "drivers," or significant sources of cost, performance, risk, and schedule variation along with areas needing technology development. Recommendations, results, and conclusions in this paper do not reflect NASA policy or programmatic decisions. This paper is an executive summary of this study.

  5. The environs of viking 2 lander.

    PubMed

    Shorthill, R W; Moore, H J; Hutton, R E; Scott, R F; Spitzer, C R

    1976-12-11

    Forty-six days after Viking 1 landed, Viking 2 landed in Utopia Planitia, about 6500 kilometers away from the landing site of Viking 1. Images show that in the immediate vicinity of the Viking 2 landing site the surface is covered with rocks, some of which are partially buried, and fine-grained materials. The surface sampler, the lander cameras, engineering sensors, and some data from the other lander experiments were used to investigate the properties of the surface. Lander 2 has a more homogeneous surface, more coarse-grained material, an extensive crust, small rocks or clods which seem to be difficult to collect, and more extensive erosion by the retro-engine exhaust gases than lander 1. A report on the physical properties of the martian surface based on data obtained through sol 58 on Viking 2 and a brief description of activities on Viking 1 after sol 36 are given.

  6. Mars Polar Lander arrives at KSC

    NASA Technical Reports Server (NTRS)

    1998-01-01

    At the Shuttle Landing Facility, the Mars Polar Lander is loaded onto a truck after its flight aboard an Air Force C-17 cargo plane that carried it from the Lockheed Martin Astronautics plant in Denver, CO. The lander is being transported to the Spacecraft Assembly and Encapsulation Facility-2(SAEF-2) in the KSC Industrial Area for testing, including a functional test of the science instruments and the basic spacecraft subsystems. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. The Mars Polar Lander spacecraft is planned for launch from Cape Canaveral Air Station aboard a Delta II rocket on Jan. 3, 1999.

  7. Space qualification of an automotive microcontroller for the DREAMS-P/H pressure and humidity instrument on board the ExoMars 2016 Schiaparelli lander

    NASA Astrophysics Data System (ADS)

    Nikkanen, T.; Schmidt, W.; Harri, A.-M.; Genzer, M.; Hieta, M.; Haukka, H.; Kemppinen, O.

    2015-10-01

    Finnish Meteorological Institute (FMI) has developed a novel kind of pressure and humidity instrument for the Schiaparelli Mars lander, which is a part of the ExoMars 2016 mission of the European Space Agency (ESA) [1]. The DREAMS-P pressure instrument and DREAMS-H humidity instrument are part of the DREAMS science package on board the lander. DREAMS-P (seen in Fig. 1 and DREAMS-H were evolved from earlier planetary pressure and humidity instrument designs by FMI with a completely redesigned control and data unit. Instead of using the conventional approach of utilizing a space grade processor component, a commercial off the shelf microcontroller was selected for handling the pressure and humidity measurements. The new controller is based on the Freescale MC9S12XEP100 16-bit automotive microcontroller. Coordinated by FMI, a batch of these microcontroller units (MCUs) went through a custom qualification process in order to accept the component for spaceflight on board a Mars lander.

  8. Permittivity Probe on the Rosetta Lander Philae: Preparation for On-Comet-Phase

    NASA Astrophysics Data System (ADS)

    Schmidt, Walter; Grard, Réjean; Hamelin, Michel; Ciarletti, Valerie; Le Gall, Alice; Caujolle-Bert, Sylvain; Kargl, Günther

    2013-04-01

    Mid of November 2014 the ESA Rosetta spacecraft will send its Lander Philae to the surface of the comet 67P/Churyumov-Gerasimenko. The three landing gear feet carry sensors of the Surface Electrical, Seismic and Acoustic Monitoring Experiments (SESAME), among them the Permittivity Probe (PP) [1]. Together with sensors attached to the MUPUS PEN and the APXS detector lid, PP features three transmitter electrodes and 2 receiver electrodes. Using any combination of two transmitters the quadrupole arrangement can measure the electrical properties of the comet surface material at different depths between 50 cm and about 2 m. The instrument is optimized for the detection of water ice inside the observed volume, its purity and temperature. For PP a critical mission phase is the descent towards the comet surface as after separation from the spacecraft and unfolding of the landing gear the instrument is for the first time in the real measurement configuration while the vacuum condition of space provides a known reference. This phase will be used for calibration of all signal disturbances like stray capacitances caused by cable connections, structure elements and other instruments. During the past year a special test scenario was developed and tested combining the operational requirements from several instruments into an integrated time line. Together with laboratory measurements using flight-equivalent material the electrical properties of the PP instrument network will be modeled. The results set the framework for the analysis of the on-comet observations under different electrode-combinations and geometry conditions. An observation sequence for the first days after landing was defined taking the different observational requirements into account. Reference: [1] Seidensticker, K.J., Thiel, K. and Schmidt, W., 2004: The Rosetta Lander Experiment SESAME and the new Target Comet 67P/Churyumov-Gerasimenko. Astrophys. Space Sci., 311,297-307.

  9. Mars planetary geodesy using earth-based observations of Mars landers

    NASA Technical Reports Server (NTRS)

    Edwards, C. D., Jr.; Kahn, R. D.; Folkner, W. M.; Preston, R. A.

    1992-01-01

    The potential for earth-based radiometric observations of a network of Mars surface landers to provide accurate determination of the Mars rotational orientation in inertial space is investigated. An error budget is presented for the carrier phase data type and related to system requirements for the surface landers. Differencing the carrier phase observations for a pair of Mars landers can provide extremely high precision due to common-mode error cancellation. Results of a covariance analysis are presented which show that Mars orientation can be determined to better than 10 milliarcsec, corresponding to decimeter distances at the planet surface. Recommendations on how to incorporate these concepts into future Mars missions, such as the Mars Environmental Survey, are discussed.

  10. Long-Lived Venus Lander Conceptual Design: How To Keep It Cool

    NASA Technical Reports Server (NTRS)

    Dyson, Ridger W.; Schmitz, Paul C.; Penswick, L. Barry; Bruder, Geoffrey A.

    2009-01-01

    Surprisingly little is known about Venus, our neighboring sister planet in the solar system, due to the challenges of operating in its extremely hot, corrosive, and dense environment. For example, after over two dozen missions to the planet, the longest-lived lander was the Soviet Venera 13, and it only survived two hours on the surface. Several conceptual Venus mission studies have been formulated in the past two decades proposing lander architectures that potentially extend lander lifetime. Most recently, the Venus Science and Technology Definition Team (STDT) was commissioned by NASA to study a Venus Flagship Mission potentially launching in the 2020- 2025 time-frame; the reference lander of this study is designed to survive for only a few hours more than Venera 13 launched back in 1981! Since Cytherean mission planners lack a viable approach to a long-lived surface architecture, specific scientific objectives outlined in the National Science Foundation Decadal Survey and Venus Exploration Advisory Group final report cannot be completed. These include: mapping the mineralogy and composition of the surface on a planetary scale determining the age of various rock samples on Venus, searching for evidence of changes in interior dynamics (seismometry) and its impact on climate and many other key observations that benefit with time scales of at least a full Venus day (Le. daylight/night cycle). This report reviews those studies and recommends a hybrid lander architecture that can survive for at least one Venus day (243 Earth days) by incorporating selective Stirling multi-stage active cooling and hybrid thermoacoustic power.

  11. Design of Small Impact-Resistant RTGs for Global Network of Unmanned Mars Landers

    SciTech Connect

    Schock, Alfred

    1991-06-26

    Ongoing studies by the National Aeronautics and Space Administration (NASA) for the robotic exploration of Mars contemplate a network of at least twenty small and relatively inexpensive landers distributed over both low and high latitudes of the Martian globe. They are intended to explore the structural, mineralogical, and chemical characteristics of the Martian soil, search for possible subsurface trapped ice, and collect long-term seismological and meteorological data over a period of ten years. They can also serve as precursors for later unmanned and manned Mars missions.; The collected data will be transmitted periodically, either directly to Earth or indirectly via an orbiting relay. The choice of transmission will determine the required power, which is currently expected to be between 2 and 12 watts(e) per lander. This could be supplied either by solar arrays or by Radioisotope Thermoelectric Generators (RTGs). Solar-powered landers could only be used for low Martian latitudes, but RTG-powered landers can be used for both low and high latitudes. Moreover, RTGs are less affected by Martian sandstorms and can be modified to resist high-G-load impacts. High impact resistance is a critical goal. It is desired by the mission designers, to minimize the mass and complexity of the system needed to decelerate the landers to a survivable impact velocity.; To support the NASA system studies, the U.S. Department of Energy's Office of Special Applications (DOE/OSA) asked Fairchild to perform RTG design studies for this mission. The key problem in designing these RTGs is how to enable the generators to tolerate substantially higher G-loads than those encountered on previous RTG missions.; The Fairchild studies resulted in designs of compact RTGs based on flight-proven and safety-qualified heat source components, with a number of novel features designed to provide the desired high impact tolerance. The present paper describes those designs and their rationale, and a

  12. NASA Propulsion Sub-System Concept Studies and Risk Reduction Activities for Resource Prospector Lander

    NASA Technical Reports Server (NTRS)

    Trinh, Huu P.

    2015-01-01

    NASA's exploration roadmap is focused on developing technologies and performing precursor missions to advance the state of the art for eventual human missions to Mars. One of the key components of this roadmap is various robotic missions to Near-Earth Objects, the Moon, and Mars to fill in some of the strategic knowledge gaps. The Resource Prospector (RP) project is one of these robotic precursor activities in the roadmap. RP is a multi-center and multi-institution project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and is approximately 10 days, assuming a five day direct Earth to Moon transfer. Because of the mission cost constraint, a trade study of the propulsion concepts was conducted with a focus on available low-cost hardware for reducing cost in development, while technical risk, system mass, and technology advancement requirements were also taken into consideration. The propulsion system for the lander is composed of a braking stage providing a high thrust to match the lander's velocity with the lunar surface and a lander stage performing the final lunar descent. For the braking stage, liquid oxygen (LOX) and liquid methane (LCH4) propulsion systems, derived from the Morpheus experimental lander, and storable bi-propellant systems, including the 4th stage Peacekeeper (PK) propulsion components and Space Shuttle orbital maneuvering engine (OME), and a solid motor were considered for the study. For the lander stage, the trade study included miniaturized Divert Attitude Control System (DACS) thrusters (Missile Defense Agency (MDA) heritage), their enhanced thruster versions, ISE-100 and ISE-5, and commercial-off-the-shelf (COTS) hardware. The lowest cost configuration of using the solid motor and the PK components while meeting the requirements was selected. The reference concept of the lander is shown in Figure 1. In the current reference configuration, the solid stage is the primary provider of delta

  13. Self-unloading, reusable, lunar lander project

    NASA Technical Reports Server (NTRS)

    Arseculeratne, Ruwan; Cavazos, Melissa; Euker, John; Ghavidel, Fred; Hinkel, Todd J.; Hitzfelder, John; Leitner, Jesse; Nevik, James; Paynter, Scott; Zolondek, Allen

    1990-01-01

    In the early 21st century, NASA will return to the Moon and establish a permanent base. To achieve this goal safely and economically, B&T Engineering has designed an unmanned, reusable, self-unloading lunar lander. The lander is designed to deliver 15,000 kg payloads from an orbit transfer vehicle (OTV) in a low lunar polar orbit and an altitude of 200 km to any location on the lunar surface.

  14. Global precipitation measurement (GPM) mission and its application for flood monitoring

    NASA Astrophysics Data System (ADS)

    Kachi, Misako; Oki, Riko; Shimizu, Shuji; Kojima, Masahiro

    2006-12-01

    The Global Precipitation Measurement (GPM) mission is an expanded follow-on mission of the current Tropical Rainfall Measuring Mission (TRMM). The concept of GPM is, 1) TRMM-like, non-sun-synchronous core satellite carrying the Dual-frequency Precipitation Radar (DPR) to be developed by Japan and a microwave radiometer to be developed by United States, and 2) constellation of satellites in polar orbit, each carrying a microwave radiometer provided by international partner. The constellation system of GPM will make it possible every three-hour global precipitation measurement. Because of its concept on focusing high-accurate and high-frequent global precipitation observation, GPM has a unique position among future Earth observation missions. GPM international partnerships will embody concept of GEOSS. Observation data acquired by the GPM mission are expected to be used for both Earth environmental research and various societal benefit areas. One of most expected application fields is weather prediction. Use of high-frequent observation in numerical weather prediction models will improve weather forecasting especially for extreme events such as tropical cyclones and heavy rain. Another example is application to flood monitoring and forecasting. Recent increasing needs of real-time flood information required from many countries especially in Asia will strongly support operational application of GPM products in this field.

  15. DXL: A sounding rocket mission measuring Solar Wind Charge eXchange properties

    NASA Astrophysics Data System (ADS)

    Galeazzi, Massimiliano

    2016-04-01

    Solar Wind interacts with the interstellar neutrals via charge exchange mechanism to produce spatially and temporally varying x-rays making it difficult to separate from other diffuse sources. The Diffuse X-rays from the Local Galaxy (DXL) mission measured the spatial signature of Solar Wind Charge eXchange (SWCX) emission due to the helium focusing cone. The mission used 2 large area proportional counters and was able to separate the SWCX contribution from Local Hot Bubble emission. The data from the mission provide a robust estimate of the SWCX contribution to the ROSAT maps, measuring the compound SWCX cross section with He in all ROSAT bands. The results showed that the total SWCX contribution in the ¼ keV band is, on average, ~27%. A new mission, DXL-2, was launched on December 4, 2015 with two new counters for a better understanding of the energy distribution of heliospheric SWCX photons, by using a multi-band approach. A dedicated scan to accurately measure the cone position and solve the IBEX controversy was also performed. The talk will discuss the DXL mission, the results from the first flight, and the preliminary results from the latest flight.Submitted for the DXL Collaboration

  16. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander is lifted to a vertical position on Pad 17B, Cape Canaveral Air Station. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  17. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander is lifted to the top of the gantry on Pad 17B, Cape Canaveral Air Station. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  18. The SRBs for the Delta II rocket carrying the Mars Polar Lander arrive on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, a solid rocket booster is raised to a vertical position for mating with the Delta II rocket carrying the Mars Polar Lander. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  19. The SRBs for the Delta II rocket carrying the Mars Polar Lander arrive on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, the gantry holding the solid rocket boosters is moved into place next to the Delta II rocket carrying the Mars Polar Lander. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  20. The SRBs for the Delta II rocket carrying the Mars Polar Lander arrive on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, a solid rocket booster hangs in place between two other rocket boosters waiting to be mated with the Delta II rocket carrying the Mars Polar Lander. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  1. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Inside the gantry on Pad 17B, Cape Canaveral Air Station, the fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander waits to be lowered into the white room. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  2. The SRBs for the Delta II rocket carrying the Mars Polar Lander arrive on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, workers monitor the solid rocket booster before its being lifted to mate with the Delta II rocket carrying the Mars Polar Lander. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  3. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    The fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander arrives at Pad 17B, Cape Canaveral Air Station. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern- most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  4. The SRBs for the Delta II rocket carrying the Mars Polar Lander arrive on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, a solid rocket booster waits for mating with the Delta II rocket (in background) carrying the Mars Polar Lander. The rocket will be used to launch the Mars Polar Lander on Jan. 3, 1999. The lander is a solar- powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  5. A Plan for Measuring Climatic Scale Global Precipitation Variability: The Global Precipitation Mission

    NASA Technical Reports Server (NTRS)

    Smith, Eric A.; Einaudi, Franco (Technical Monitor)

    2000-01-01

    The outstanding success of the Tropical Rainfall Measuring Mission (TRMM) stemmed from a near flawless launch and deployment, a highly successful measurement campaign, achievement of all original scientific objectives before the mission life had ended, and the accomplishment of a number of unanticipated but important additional scientific advances. This success and the realization that satellite rainfall datasets are now a foremost tool in the understanding of decadal climate variability has helped motivate a comprehensive global rainfall measuring mission, called 'The Global Precipitation Mission' (GPM). The intent of this mission is to address looming scientific questions arising in the context of global climate-water cycle interactions, hydrometeorology, weather prediction, the global carbon budget, and atmosphere-biosphere-cryosphere chemistry. This paper addresses the status of that mission currently planed for launch in the early 2007 time frame. The GPM design involves a nine-member satellite constellation, one of which will be an advanced TRMM-like 'core' satellite carrying a dual-frequency Ku-Ka band radar (df-PR) and a TMI-like radiometer. The other eight members of the constellation can be considered drones to the core satellite, each carrying some type of passive microwave radiometer measuring across the 10.7-85 GHz frequency range, likely based on both real and synthetic aperture antenna technology and to include a combination of new lightweight dedicated GPM drones and both co-existing operational and experimental satellites carrying passive microwave radiometers (i.e., SSM/l, AMSR, etc.). The constellation is designed to provide a minimum of three-hour sampling at any spot on the globe using sun-synchronous orbit architecture, with the core satellite providing relevant measurements on internal cloud precipitation microphysical processes. The core satellite also enables 'training' and 'calibration' of the drone retrieval process. Additional

  6. The Global Precipitation Measurement (GPM) Mission: Overview and U.S. Science Status

    NASA Technical Reports Server (NTRS)

    Hou, Arthur

    2007-01-01

    The Global Precipitation Measurement (GPM) Mission, an international satellite mission to unify and advance space-based precipitation measurements around the globe, is a science mission with integrated application goals. The mission is designed to (1) advance the knowledge of the global water cycle and freshwater availability, and (2) improve weather, climate, and hydrological prediction capabilities through more accurate and frequent measurements of global precipitation. The cornerstone of GPM is the deployment of a Core Spacecraft in a unique 65 deg-inclined orbit to serve as a physics observatory and a calibration reference to improve the accuracy of precipitation measurements by a heterogeneous constellation of dedicated and operational passive microwave sensors. The Core Spacecraft will carry a dual-frequency (Ku-Ka band) radar and a multi-channel microwave radiometer with high-frequency capabilities to provide measurements of 3-D precipitation structures and microphysical properties, which are key to achieving a better understanding of precipitation processes and improved retrieval algorithms for passive microwave radiometers. The GPM constellation is envisioned to comprise 5 or more conical-scanning microwave radiometers provided by partners, augmented by cross-track microwave sounders on operational satellites such as the National Polar-orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP), POES, NPOESS, and MetOp satellites for improved sampling over land. The GPM Mission is currently a partnership between NASA and the Japan Aerospace Exploration Agency (JAXA), with opportunities for additional international partners in constellation satellites and ground validation. An overview of the GPM mission concept and science activities in the United States will be presented.

  7. Altair Lander Life Support: Design Analysis Cycles 4 and 5

    NASA Technical Reports Server (NTRS)

    Anderson, Molly; Curley, Su; Rotter, Henry; Stambaugh, Imelda; Yagoda, Evan

    2011-01-01

    Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.

  8. Altair Lander Life Support: Design Analysis Cycles 4 and 5

    NASA Technical Reports Server (NTRS)

    Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan

    2010-01-01

    Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.

  9. 3D Visualization for Phoenix Mars Lander Science Operations

    NASA Technical Reports Server (NTRS)

    Edwards, Laurence; Keely, Leslie; Lees, David; Stoker, Carol

    2012-01-01

    Planetary surface exploration missions present considerable operational challenges in the form of substantial communication delays, limited communication windows, and limited communication bandwidth. A 3D visualization software was developed and delivered to the 2008 Phoenix Mars Lander (PML) mission. The components of the system include an interactive 3D visualization environment called Mercator, terrain reconstruction software called the Ames Stereo Pipeline, and a server providing distributed access to terrain models. The software was successfully utilized during the mission for science analysis, site understanding, and science operations activity planning. A terrain server was implemented that provided distribution of terrain models from a central repository to clients running the Mercator software. The Ames Stereo Pipeline generates accurate, high-resolution, texture-mapped, 3D terrain models from stereo image pairs. These terrain models can then be visualized within the Mercator environment. The central cross-cutting goal for these tools is to provide an easy-to-use, high-quality, full-featured visualization environment that enhances the mission science team s ability to develop low-risk productive science activity plans. In addition, for the Mercator and Viz visualization environments, extensibility and adaptability to different missions and application areas are key design goals.

  10. Summary report of mission acceleration measurements for Spacehab-01, STS-57 launched 21 June 1993

    NASA Technical Reports Server (NTRS)

    Finley, Brian; Grodsinsky, Carlos; Delombard, Richard

    1994-01-01

    The maiden voyage of the commercial Spacehab laboratory module onboard the STS-57 mission was integrated with several accelerometer packages, one of which was the Space Acceleration Measurement System (SAMS). The June 21st 1993, launch was the seventh successful mission for the Office of Life and Microgravity Sciences and Application's (OLMSA) SAMS unit. This flight was also complemented by a second accelerometer system. The Three Dimensional Microgravity Accelerometer (3-DMA), a Code C funded acceleration measurement system, offering an on-orbit residual calibration as a reference for the unit's four triaxial accelerometers. The SAMS accelerometer unit utilized three remote triaxial sensor heads mounted on the forward Spacehab module bulkhead and on one centrally located experiment locker door. These triaxial heads had filter cut-offs set to 5, 50, and 1000 Hz. The mission also included other experiment specific accelerometer packages in various locations.

  11. Summary report of mission acceleration measurements for Spacehab-01, STS-57 launched 21 June 1993

    NASA Astrophysics Data System (ADS)

    Finley, Brian; Grodsinsky, Carlos; Delombard, Richard

    1994-03-01

    The maiden voyage of the commercial Spacehab laboratory module onboard the STS-57 mission was integrated with several accelerometer packages, one of which was the Space Acceleration Measurement System (SAMS). The June 21st 1993, launch was the seventh successful mission for the Office of Life and Microgravity Sciences and Application's (OLMSA) SAMS unit. This flight was also complemented by a second accelerometer system. The Three Dimensional Microgravity Accelerometer (3-DMA), a Code C funded acceleration measurement system, offering an on-orbit residual calibration as a reference for the unit's four triaxial accelerometers. The SAMS accelerometer unit utilized three remote triaxial sensor heads mounted on the forward Spacehab module bulkhead and on one centrally located experiment locker door. These triaxial heads had filter cut-offs set to 5, 50, and 1000 Hz. The mission also included other experiment specific accelerometer packages in various locations.

  12. Summary Report of Mission Acceleration Measurements for STS-78. Launched June 20, 1996

    NASA Technical Reports Server (NTRS)

    Hakimzadeh, Roshanak; Hrovat, Kenneth; McPherson, Kevin M.; Moskowitz, Milton E.; Rogers, Melissa J. B.

    1997-01-01

    The microgravity environment of the Space Shuttle Columbia was measured during the STS-78 mission using accelerometers from three different instruments: the Orbital Acceleration Research Experiment, the Space Acceleration Measurement System and the Microgravity Measurement Assembly. The quasi-steady environment was also calculated in near real-time during the mission by the Microgravity Analysis Workstation. The Orbital Acceleration Research Experiment provided investigators with real-time quasi-steady acceleration measurements. The Space Acceleration Measurement System recorded higher frequency data on-board for post-mission analysis. The Microgravity Measurement Assembly provided investigators with real-time quasi-steady and higher frequency acceleration measurements. The Microgravity Analysis Workstation provided calculation of the quasi-steady environment. This calculation was presented to the science teams in real-time during the mission. The microgravity environment related to several different Orbiter, crew and experiment operations is presented and interpreted in this report. A radiator deploy, the Flight Control System checkout, and a vernier reaction control system reboost demonstration had minimal effects on the acceleration environment, with excitation of frequencies in the 0.01 to 10 Hz range. Flash Evaporator System venting had no noticeable effect on the environment while supply and waste water dumps caused excursions of 2 x lO(exp -6) to 4 x 10(exp -6) g in the Y(sub b) and Z(sub b) directions. Crew sleep and ergometer exercise periods can be clearly seen in the acceleration data, as expected. Accelerations related to the two Life Science Laboratory Equipment Refrigerator/Freezers were apparent in the data as are accelerations caused by the Johnson Space Center Projects Centrifuge. As on previous microgravity missions, several signals are present in the acceleration data for which a source has not been identified. The causes of these accelerations

  13. Global Precipitation Measurement (GPM) Mission: Precipitation Processing System (PPS) GPM Mission Gridded Text Products Provide Surface Precipitation Retrievals

    NASA Technical Reports Server (NTRS)

    Stocker, Erich Franz; Kelley, O.; Kummerow, C.; Huffman, G.; Olson, W.; Kwiatkowski, J.

    2015-01-01

    In February 2015, the Global Precipitation Measurement (GPM) mission core satellite will complete its first year in space. The core satellite carries a conically scanning microwave imager called the GPM Microwave Imager (GMI), which also has 166 GHz and 183 GHz frequency channels. The GPM core satellite also carries a dual frequency radar (DPR) which operates at Ku frequency, similar to the Tropical Rainfall Measuring Mission (TRMM) Precipitation Radar, and a new Ka frequency. The precipitation processing system (PPS) is producing swath-based instantaneous precipitation retrievals from GMI, both radars including a dual-frequency product, and a combined GMIDPR precipitation retrieval. These level 2 products are written in the HDF5 format and have many additional parameters beyond surface precipitation that are organized into appropriate groups. While these retrieval algorithms were developed prior to launch and are not optimal, these algorithms are producing very creditable retrievals. It is appropriate for a wide group of users to have access to the GPM retrievals. However, for researchers requiring only surface precipitation, these L2 swath products can appear to be very intimidating and they certainly do contain many more variables than the average researcher needs. Some researchers desire only surface retrievals stored in a simple easily accessible format. In response, PPS has begun to produce gridded text based products that contain just the most widely used variables for each instrument (surface rainfall rate, fraction liquid, fraction convective) in a single line for each grid box that contains one or more observations.This paper will describe the gridded data products that are being produced and provide an overview of their content. Currently two types of gridded products are being produced: (1) surface precipitation retrievals from the core satellite instruments GMI, DPR, and combined GMIDPR (2) surface precipitation retrievals for the partner constellation

  14. Mechanical Properties of the Surface Material of Comet 67P/Churyumov-Gerasimenko Measured By the Casse Instrument Onboard the Philae Lander

    NASA Astrophysics Data System (ADS)

    Knapmeyer, M.; Fischer, H. H.; Seidensticker, K. J.; Arnold, W.; Faber, C.; Möhlmann, D.; Thiel, K.

    2014-12-01

    Satellite remote sensing of ocean color is a critical tool for assessing the productivity of marine ecosystems and monitoring changes resulting from climatic or environmental influences. Yet water-leaving radiance comprises less than 10% of the signal measured from space, making correction for absorption and scattering by the intervening atmosphere imperative. Traditional ocean color retrieval algorithms utilize a standard set of aerosol models and the assumption of negligible water-leaving radiance in the near-infrared. Modern improvements have been developed to handle absorbing aerosols such as urban particulates in coastal areas and transported desert dust over the open ocean, where ocean fertilization can impact biological productivity at the base of the marine food chain. Even so, imperfect knowledge of the absorbing aerosol optical properties or their height distribution results in well-documented sources of error. In the UV, the problem of UV-enhanced absorption and nonsphericity of certain aerosol types are amplified due to the increased Rayleigh and aerosol optical depth, especially at off-nadir view angles. Multi-angle spectro-polarimetric measurements have been advocated as an additional tool to better understand and retrieve the aerosol properties needed for atmospheric correction for ocean color retrievals. The central concern of the work to be described is the assessment of the effects of absorbing aerosol properties on water leaving radiance measurement uncertainty by neglecting UV-enhanced absorption of carbonaceous particles and by not accounting for dust nonsphericity. In addition, we evaluate the polarimetric sensitivity of absorbing aerosol properties in light of measurement uncertainties achievable for the next generation of multi-angle polarimetric imaging instruments, and demonstrate advantages and disadvantages of wavelength selection in the UV/VNIR range. The phase matrices for the spherical smoke particles were calculated using a standard

  15. Lessons learned from planetary entry probe missions

    NASA Astrophysics Data System (ADS)

    Niemann, Hasso; Atreya, Sushil K.; Kasprzak, Wayne

    Probing the atmospheres and surfaces of the planets and their moons with fast moving entry probes has been a very useful and essential technique to obtain in situ or quasi in situ scientific data (ground truth) which could not otherwise be obtained from fly by or orbiter only missions and where balloon, aircraft or lander missions are too complex and too costly. Planetary entry probe missions have been conducted successfully on Venus, Mars, Jupiter and Titan after having been first demonstrated in the Earth's atmosphere. Future planetary missions should also include more entry probe missions back to Venus and to the outer planets. The success of and science returns from past missions, the need for more and unique data, and a continuously advancing technology generate confidence that future missions will be even more successful with respect to science return and technical performance. There are, however, unique challenges associated with entry probe missions and with building instruments for an entry probe, as compared to orbiters, landers, or rovers. Conditions during atmospheric entry are extreme. There are operating time constraints due to the usually short duration of the probe descent, and the instruments experience rapid environmental changes in temperature and pressure. In addition, there are resource limitations, i.e. mass, power, size and bandwidth. Because of the protective heat shield and the high acceleration the probe experiences during entry, the ratio of payload to total probe mass is usually much smaller than in other missions. Finally, the demands on the instrument design are determined in large part by conditions (pressure, temperature, composition) unique to the particular body under study, and as a result, there is no one-size-fits-all instrument for an atmospheric probe. Many of these requirements are more easily met by miniaturizing the probe instrumentation and consequently reducing the required size of the probe. Improved heat shield

  16. Landing on small bodies: From the Rosetta Lander to MASCOT and beyond

    NASA Astrophysics Data System (ADS)

    Philae; MASCOT Teams; Ulamec, Stephan; Biele, Jens; Bousquet, Pierre-W.; Gaudon, Philippe; Geurts, Koen; Ho, Tra-Mi; Krause, Christian; Lange, Caroline; Willnecker, Rainer; Witte, Lars

    2014-01-01

    Recent planning for science and exploration missions has emphasized the high interest in the close investigation of small bodies in the Solar System. In particular in-situ observations of asteroids and comets play an important role in this field and will contribute substantially to our understanding of the formation and history of the Solar System.The first dedicated comet Lander is Philae, an element of ESA's Rosetta mission to comet 67/P Churyumov-Gerasimenko. Rosetta was launched in 2004. After more than 7 years of cruise (including three Earth and one Mars swing-by as well as two asteroid flybys) the spacecraft has gone into a deep space hibernation in June 2011. When approaching the target comet in early 2014, Rosetta will be re-activated. The cometary nucleus will be characterized remotely to prepare for Lander delivery, currently foreseen for November 2014.The Rosetta Lander was developed and manufactured, similar to a scientific instrument, by a consortium consisting of international partners. Project management is located at DLR in Cologne/Germany, with co-project managers at CNES (France) and ASI (Italy). The scientific lead is at the Max Planck Institute for Solar System Science (Lindau, Germany) and the Institut d'Astrophysique Spatiale (Paris).Mainly scientific institutes provided the subsystems, instruments and the complete, qualified lander system. Operations are performed in two dedicated centers, the Lander Control Center (LCC) at DLR-MUSC and the Science Operations and Navigation Center (SONC) at CNES. This concept was adopted to reduce overall cost of the project and is foreseen also to be applied for development and operations of future small bodies landers.A mission profiting from experience gained during Philae development and operations is MASCOT, a surface package for the Japanese Hayabusa 2 mission. MASCOT is a small (˜10kg) mobile device, delivered to the surface of asteroid 1999JU3. There it will operate for about 16h. During this time a

  17. Landing on small bodies: From the Rosetta Lander to MASCOT and beyond

    NASA Astrophysics Data System (ADS)

    Ulamec, Stephan; Biele, Jens; Bousquet, Pierre-W.; Gaudon, Philippe; Geurts, Koen; Ho, Tra-Mi; Krause, Christian; Lange, Caroline; Willnecker, Rainer; Witte, Lars; The Philae; Mascot Teams

    2014-01-01

    Recent planning for science and exploration missions has emphasized the high interest in the close investigation of small bodies in the Solar System. In particular in-situ observations of asteroids and comets play an important role in this field and will contribute substantially to our understanding of the formation and history of the Solar System. The first dedicated comet Lander is Philae, an element of ESA's Rosetta mission to comet 67/P Churyumov-Gerasimenko. Rosetta was launched in 2004. After more than 7 years of cruise (including three Earth and one Mars swing-by as well as two asteroid flybys) the spacecraft has gone into a deep space hibernation in June 2011. When approaching the target comet in early 2014, Rosetta will be re-activated. The cometary nucleus will be characterized remotely to prepare for Lander delivery, currently foreseen for November 2014. The Rosetta Lander was developed and manufactured, similar to a scientific instrument, by a consortium consisting of international partners. Project management is located at DLR in Cologne/Germany, with co-project managers at CNES (France) and ASI (Italy). The scientific lead is at the Max Planck Institute for Solar System Science (Lindau, Germany) and the Institut d'Astrophysique Spatiale (Paris). Mainly scientific institutes provided the subsystems, instruments and the complete, qualified lander system. Operations are performed in two dedicated centers, the Lander Control Center (LCC) at DLR-MUSC and the Science Operations and Navigation Center (SONC) at CNES. This concept was adopted to reduce overall cost of the project and is foreseen also to be applied for development and operations of future small bodies landers. A mission profiting from experience gained during Philae development and operations is MASCOT, a surface package for the Japanese Hayabusa 2 mission. MASCOT is a small (˜10 kg) mobile device, delivered to the surface of asteroid 1999JU3. There it will operate for about 16 h. During this

  18. Airborne Measurements in Support of the NASA Atmospheric Carbon and Transport - America (ACT-America) Mission

    NASA Astrophysics Data System (ADS)

    Meadows, B.; Davis, K.; Barrick, J. D. W.; Browell, E. V.; Chen, G.; Dobler, J. T.; Fried, A.; Lauvaux, T.; Lin, B.; McGill, M. J.; Miles, N. L.; Nehrir, A. R.; Obland, M. D.; O'Dell, C.; Sweeney, C.; Yang, M. M.

    2015-12-01

    NASA announced the research opportunity Earth Venture Suborbital - 2 (EVS-2) mission in support of the NASA's science strategic goals and objectives in 2013. Penn State University, NASA Langley Research Center (LaRC), and other academic institutions, government agencies, and industrial companies together formulated and proposed the Atmospheric Carbon and Transport - America (ACT - America) suborbital mission, which was subsequently selected for implementation. The airborne measurements that are part of ACT-America will provide a unique set of remote and in-situ measurements of CO2 over North America at spatial and temporal scales not previously available to the science community and this will greatly enhance our understanding of the carbon cycle. ACT - America will consist of five airborne campaigns, covering all four seasons, to measure regional atmospheric carbon distributions and to evaluate the accuracy of atmospheric transport models used to assess carbon sinks and sources under fair and stormy weather conditions. This coordinated mission will measure atmospheric carbon in the three most important regions of the continental US carbon balance: Northeast, Midwest, and South. Data will be collected using 2 airborne platforms (NASA Wallops' C-130 and NASA Langley's B-200) with both in-situ and lidar instruments, along with instrumented ground towers and under flights of the Orbiting Carbon Observatory (OCO-2) satellite. This presentation provides an overview of the ACT-America instruments, with particular emphasis on the airborne CO2 and backscatter lidars, and the, rationale, approach, and anticipated results from this mission.

  19. Airborne Measurements in Support of the NASA Atmospheric Carbon and Transport - America (ACT-America) Mission

    NASA Technical Reports Server (NTRS)

    Meadows, Byron; Davis, Ken; Barrick, John; Browell, Edward; Chen, Gao; Dobler, Jeremy; Fried, Alan; Lauvaux, Thomas; Lin, Bing; McGill, Matt; Miles, Natasha; Nehrir, Amin; Obland, Michael; O'Dell, Chris; Sweeney, Colm; Yang, Melissa

    2015-01-01

    NASA announced the research opportunity Earth Venture Suborbital -2 (EVS-2) mission in support of the NASA's science strategic goals and objectives in 2013. Penn State University, NASA Langley Research Center (LaRC), and other academic institutions, government agencies, and industrial companies together formulated and proposed the Atmospheric Carbon and Transport -America (ACT -America) suborbital mission, which was subsequently selected for implementation. The airborne measurements that are part of ACT-America will provide a unique set of remote and in-situ measurements of CO2 over North America at spatial and temporal scales not previously available to the science community and this will greatly enhance our understanding of the carbon cycle. ACT -America will consist of five airborne campaigns, covering all four seasons, to measure regional atmospheric carbon distributions and to evaluate the accuracy of atmospheric transport models used to assess carbon sinks and sources under fair and stormy weather conditions. This coordinated mission will measure atmospheric carbon in the three most important regions of the continental US carbon balance: Northeast, Midwest, and South. Data will be collected using 2 airborne platforms (NASA Wallops' C-130 and NASA Langley's B-200) with both in-situ and lidar instruments, along with instrumented ground towers and under flights of the Orbiting Carbon Observatory (OCO-2) satellite. This presentation provides an overview of the ACT-America instruments, with particular emphasis on the airborne CO2and backscatter lidars, and the, rationale, approach, and anticipated results from this mission.

  20. The high-LET radiation component measured during the EUROMIR-94 mission.

    PubMed

    Leugner, D; Streibel, T; Rocher, H; Reitz, G; Heinrich, W

    1998-01-01

    Stacks of CR-39 plastic nuclear track detectors were mounted inside the MIR-station during the EUROMIR-94-mission. We present LET-spectra determined separately for long range cosmic ray heavy ions and for short range target fragments produced in nuclear interactions of cosmic rays and measured charge distributions for relativistic and stopping particles.

  1. Operating the Dual-Orbiter GRAIL Mission to Measure the Moon's Gravity

    NASA Technical Reports Server (NTRS)

    Beerer, Joseph G.; Havens, Glen G.

    2012-01-01

    NASA's mission to measure the Moon's gravity and determine the interior structure, from crust to core, has almost completed its 3-month science data collection phase. The twin orbiters of the Gravity Recovery and Interior Laboratory (GRAIL) mission were launched from Florida on September 10, 2011, on a Delta-II launch vehicle. After traveling for nearly four months on a low energy trajectory to the Moon, they were inserted into lunar orbit on New Year's Eve and New Year's Day. In January 2012 a series of circularization maneuvers brought the orbiters into co-planar near-circular polar orbits. In February a distant (75- km) rendezvous was achieved and the science instruments were turned on. A dual- frequency (Ka and S-band) inter-orbiter radio link provides a precise orbiter-to-orbiter range measurement that enables the gravity field estimation. NASA's Jet Propulsion Laboratory in Pasadena, CA, manages the GRAIL project. Mission management, mission planning and sequencing, and navigation are conducted at JPL. Lockheed Martin, the flight system manufacturer, operates the orbiters from their control center in Denver, Colorado. The orbiters together have performed 28 propulsive maneuvers to reach and maintain the science phase configuration. Execution of these maneuvers, as well as the payload checkout and calibration activities, has gone smoothly due to extensive pre-launch operations planning and testing. The key to the operations success has been detailed timelines for product interchange between the operations teams and proven procedures from previous JPL/LM planetary missions. Once in science phase, GRAIL benefitted from the payload operational heritage of the GRACE mission that measures the Earth's gravity.

  2. Radio Telescopes to Keep Sharp Eye on Mars Lander

    NASA Astrophysics Data System (ADS)

    2008-05-01

    As NASA's Phoenix Mars Lander descends through the Red Planet's atmosphere toward its landing on May 25, its progress will be scrutinized by radio telescopes from the National Radio Astronomy Observatory (NRAO). At NRAO control rooms in Green Bank, West Virginia, and Socorro, New Mexico, scientists, engineers and technicians will be tracking the faint signal from the lander, 171 million miles from Earth. The GBT Robert C. Byrd Green Bank Telescope CREDIT: NRAO/AUI/NSF To make a safe landing, Phoenix must make a risky descent, slowing down from nearly 13,000 mph at the top of the Martian atmosphere to only 5 mph in the final seconds before touchdown. NASA officials point out that fewer than half of all Mars landing missions have been successful, but the scientific rewards of success are worth the risk. Major events in the spacecraft's atmospheric entry, descent and landing will be marked by changes in the Doppler Shift in the frequency of the vehicle's radio signal. Doppler Shift is the change in frequency caused by relative motion between the transmitter and receiver. At Green Bank, NRAO and NASA personnel will use the giant Robert C. Byrd Green Bank Telescope (GBT) to follow the Doppler changes and verify that the descent is going as planned. The radio signal from Phoenix is designed to be received by other spacecraft in Mars orbit, then relayed to Earth. However, the GBT, a dish antenna with more than two acres of collecting surface and highly-sensitive receivers, can directly receive the transmissions from Phoenix. "We'll see the frequency change as Phoenix slows down in the Martian atmosphere, then there will be a big change when the parachute deploys," said NRAO astronomer Frank Ghigo. When the spacecraft's rocket thrusters slow it down for its final, gentle touchdown, its radio frequency will stabilize, Ghigo said. "We'll have confirmation of these major events through our direct reception several seconds earlier than the controllers at NASA's Jet Propulsion

  3. Near-field postseismic deformation associated with the 1992 Landers and 1999 Hector Mine, California, earthquakes

    USGS Publications Warehouse

    Savage, J.C.; Svarc, J.L.; Prescott, W.H.

    2003-01-01

    After the Landers earthquake (Mw = 7.3, 1992.489) a linear array of 10 monuments extending about 30 km N50??E on either side of the earthquake rupture plus a nearby offtrend reference monument were surveyed frequently by GPS until 2003.2. The array also spans the rupture of the subsequent Hector Mine earthquake (Mw = 7.1, 1999.792 . The pre-Landers velocities of monuments in the array relative to interior North America were estimated from earlier trilateration and very long baseline interferometry measurements. Except at the reference monument, the post-Landers velocities of the individual monuments in the array relaxed to their preseismic values within 4 years. Following the Hector Mine earthquake the velocities of the monuments relaxed to steady rates within 1 year. Those steady rates for the east components are about equal to the pre-Landers rates as is the steady rate for the north component of the one monument east of the Hector Mine rupture. However, the steady rates for the north components of the 10 monuments west of the rupture are systematically ???10 mm yr1 larger than the pre-Landers rates. The relaxation to a steady rate is approximately exponential with decay times of 0.50 ?? 0.10 year following the Landers earthquake and 0.32 ?? 0.18 year following the Hector Mine earthquake. The postearthquake motions of the Landers array following the Landers earthquake are not well approximated by the viscoelastic-coupling model of Pollitz et al. [2000]. A similar viscoelastic-coupling model [Pollitz et al., 2001] is more successful in representing the deformation after the Hector Mine earthquake.

  4. Spacecraft Conceptual Design Compared to the Apollo Lunar Lander

    NASA Technical Reports Server (NTRS)

    Young, C.; Bowie, J.; Rust, R.; Lenius, J.; Anderson, M.; Connolly, J.

    2011-01-01

    Future human exploration of the Moon will require an optimized spacecraft design with each sub-system achieving the required minimum capability and maintaining high reliability. The objective of this study was to trade capability with reliability and minimize mass for the lunar lander spacecraft. The NASA parametric concept for a 3-person vehicle to the lunar surface with a 30% mass margin totaled was considerably heavier than the Apollo 15 Lunar Module "as flown" mass of 16.4 metric tons. The additional mass was attributed to mission requirements and system design choices that were made to meet the realities of modern spaceflight. The parametric tool used to size the current concept, Envision, accounts for primary and secondary mass requirements. For example, adding an astronaut increases the mass requirements for suits, water, food, oxygen, as well as, the increase in volume. The environmental control sub-systems becomes heavier with the increased requirements and more structure was needed to support the additional mass. There was also an increase in propellant usage. For comparison, an "Apollo-like" vehicle was created by removing these additional requirements. Utilizing the Envision parametric mass calculation tool and a quantitative reliability estimation tool designed by Valador Inc., it was determined that with today?s current technology a Lunar Module (LM) with Apollo capability could be built with less mass and similar reliability. The reliability of this new lander was compared to Apollo Lunar Module utilizing the same methodology, adjusting for mission timeline changes as well as component differences. Interestingly, the parametric concept's overall estimated risk for loss of mission (LOM) and loss of crew (LOC) did not significantly improve when compared to Apollo.

  5. Altair Lander Life Support: Requirements Analysis Cycles 1 and 2

    NASA Technical Reports Server (NTRS)

    Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan

    2010-01-01

    Life support systems are a critical part of human exploration beyond low earth orbit. NASA's Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally -functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper'. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair's life support system.

  6. Altair Lander Life Support: Requirement Analysis Cycles 1 and 2

    NASA Technical Reports Server (NTRS)

    Anderson, Molly; Curley, Su; Rotter, Henry; Yagoda, Evan

    2009-01-01

    Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally-functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair s life support system.

  7. Altair Lunar Lander Development Status: Enabling Lunar Exploration

    NASA Technical Reports Server (NTRS)

    Laurini, Kathleen C.; Connolly, John F.

    2009-01-01

    As a critical part of the NASA Constellation Program lunar transportation architecture, the Altair lunar lander will return humans to the moon and enable a sustained program of lunar exploration. The Altair is to deliver up to four crew to the surface of the moon and return them to low lunar orbit at the completion of their mission. Altair will also be used to deliver large cargo elements to the lunar surface, enabling the buildup of an outpost. The Altair Project initialized its design using a "minimum functionality" approach that identified critical functionality required to meet a minimum set of Altair requirements. The Altair team then performed several analysis cycles using risk-informed design to selectively add back components and functionality to increase the vehicle's safety and reliability. The analysis cycle results were captured in a reference Altair design. This design was reviewed at the Constellation Lunar Capabilities Concept Review, a Mission Concept Review, where key driving requirements were confirmed and the Altair Project was given authorization to began Phase A project formulation. A key objective of Phase A is to revisit the Altair vehicle configuration, to better optimize it to complete its broad range of crew and cargo delivery missions. Industry was invited to partner with NASA early in the design to provide their insights regarding Altair configuration and key engineering challenges. NASA intends to continue to seek industry involvement in project formulation activities. This paper will update the international coimmunity on the status of the Altair Project as it addresses the challenges of project formulation, including optinuzing a vehicle configuration based on the work of the NASA Altair Project team, industry inputs and the plans going forward in designing the Altair lunar lander.

  8. Phoenix Mars Lander: Vortices and Dust Devils at the Landing Site

    NASA Astrophysics Data System (ADS)

    Ellehoj, M. D.; Taylor, P. A.; Gunnlaugsson, H. P.; Gheynani, B. T.; Drube, L.; von Holstein-Rathlou, C.; Whiteway, J.; Lemmon, M.; Madsen, M. B.; Fisher, D.; Volpe, R.; Smith, P.

    2008-12-01

    Near continuous measurements of temperatures and pressure on the Phoenix Mars Lander are used to identify the passage of vertically oriented vortex structures at the Phoenix landing site (126W, 68N) on Mars. Observations: During the Phoenix mission the pressure and temperature sensors frequently detected features passing over or close to the lander. Short duration (order 20 s) pressure drops of order 1-2 Pa, and often less, were observed relatively frequently, accompanied by increases in temperature. Similar features were observed from the Pathfinder mission, although in that case the reported pressure drops were often larger [1]. Statistics of the pressure drop features over the first 102 sols of the Phoenix mission shows that most of the events occur between noon and 15:00 LMST - the hottest part of the sol. Dust Raising: By assuming the concept of a vortex in cyclostrophic flow as well as various assumptions about the atmosphere, we obtain a pressure drop of 1.9 - 3.2 Pa if dust is to be raised. We only saw few pressure drops this large in Sols 0-102. However, the features do not need to pass directly over the lander and the pressures could be lower than the minima we measure. Furthermore, the response time of the pressure sensor is of order 3-5 s so it may not capture peak pressure perturbations. Thus, more dust devils may have occurred near the Phoenix site, but most of our detected vortices would be ghostly, dustless devils. Modelling: Using a Large Eddy Simulation model, we can simulate highly convective boundary layers on Mars [2]. The typical vortex has a diameter of 150 m, and extends up to 1 km. Further calculations give an incidence of 11 vortex events per day that could be compatible with the LES simulations. Deeper investigation of this is planned -but the numbers are roughly compatible. If the significant pressure signatures are limited to the center of the vortex then 5 per sol might be appropriate. The Phoenix mission has collected a unique set of

  9. The International Lunar Network (ILN) and the US Anchor Nodes Mission

    NASA Technical Reports Server (NTRS)

    Cohen, Barbara A.; Bessler, J. A.; Harris, D. W.; Hill, L.; Hammond, M. S.; McDougal, J. M.; Morse, B. J.; Red, C. L. B.; Kirby, K. W.

    2009-01-01

    This presentation reviews the International Lunar Network (ILN) mission, a cooperative effort designed to coordinate individual lunar landers in a geophysical network on the lunar surface. The presentation also includes information on the geophysical network, mission operations, and recent accomplishments.

  10. Combined Infrared Stereo and Laser Ranging Cloud Measurements from Shuttle Mission STS-85

    NASA Technical Reports Server (NTRS)

    Lancaster, R. S.; Spinhirne, J. D.; Manizade, K. F.

    2004-01-01

    Multiangle remote sensing provides a wealth of information for earth and climate monitoring, such as the ability to measure the height of cloud tops through stereoscopic imaging. As technology advances so do the options for developing spacecraft instrumentation versatile enough to meet the demands associated with multiangle measurements. One such instrument is the infrared spectral imaging radiometer, which flew as part of mission STS-85 of the space shuttle in 1997 and was the first earth- observing radiometer to incorporate an uncooled microbolometer array detector as its image sensor. Specifically, a method for computing cloud-top height with a precision of +/- 620 m from the multispectral stereo measurements acquired during this flight has been developed, and the results are compared with coincident direct laser ranging measurements from the shuttle laser altimeter. Mission STS-85 was the first space flight to combine laser ranging and thermal IR camera systems for cloud remote sensing.

  11. Tropical Rainfall Measuring Mission (TRMM). Phase B: Data capture facility definition study

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The National Aeronautics and Aerospace Administration (NASA) and the National Space Development Agency of Japan (NASDA) initiated the Tropical Rainfall Measuring Mission (TRMM) to obtain more accurate measurements of tropical rainfall then ever before. The measurements are to improve scientific understanding and knowledge of the mechanisms effecting the intra-annual and interannual variability of the Earth's climate. The TRMM is largely dependent upon the handling and processing of the data by the TRMM Ground System supporting the mission. The objective of the TRMM is to obtain three years of climatological determinations of rainfall in the tropics, culminating in data sets of 30-day average rainfall over 5-degree square areas, and associated estimates of vertical distribution of latent heat release. The scope of this study is limited to the functions performed by TRMM Data Capture Facility (TDCF). These functions include capturing the TRMM spacecraft return link data stream; processing the data in the real-time, quick-look, and routine production modes, as appropriate; and distributing real time, quick-look, and production data products to users. The following topics are addressed: (1) TRMM end-to-end system description; (2) TRMM mission operations concept; (3) baseline requirements; (4) assumptions related to mission requirements; (5) external interface; (6) TDCF architecture and design options; (7) critical issues and tradeoffs; and (8) recommendation for the final TDCF selection process.

  12. Location and Geologic Setting for the Three U.S. Mars Landers

    NASA Technical Reports Server (NTRS)

    Parker, T. J.; Kirk, R. L.

    1999-01-01

    Super resolution of the horizon at both Viking landing sites has revealed "new" features we use for triangulation, similar to the approach used during the Mars Pathfinder Mission. We propose alternative landing site locations for both landers for which we believe the confidence is very high. Super resolution of VL-1 images also reveals some of the drift material at the site to consist of gravel-size deposits. Since our proposed location for VL-2 is NOT on the Mie ejecta blanket, the blocky surface around the lander may represent the meter-scale texture of "smooth palins" in the region. The Viking Lander panchromatic images typically offer more repeat coverage than does the IMP on Mars Pathfinder, due to the longer duration of these landed missions. Sub-pixel offsets, necessary for super resolution to work, appear to be attributable to thermal effects on the lander and settling of the lander over time. Due to the greater repeat coverage (particularly in the near and mid-fields) and all-panchromatic images, the gain in resolution by super resolution processing is better for Viking than it is with most IMP image sequences. This enhances the study of textural details near the lander and enables the identification rock and surface textures at greater distances from the lander. Discernment of stereo in super resolution im-ages is possible to great distances from the lander, but is limited by the non-rotating baseline between the two cameras and the shorter height of the cameras above the ground compared to IMP. With super resolution, details of horizon features, such as blockiness and crater rim shapes, may be better correlated with Orbiter images. A number of horizon features - craters and ridges - were identified at VL-1 during the misison, and a few hils and subtle ridges were identified at VL-2. We have added a few "new" horizon features for triangulation at the VL-2 landing site in Utopia Planitia. These features were used for independent triangulation with features

  13. History of satellite missions and measurements of the Earth Radiation Budget (1957-1984)

    NASA Technical Reports Server (NTRS)

    House, F. B.; Gruber, A.; Hunt, G. E.; Mecherikunnel, A. T.

    1986-01-01

    The history of satellite missions and their measurements of the earth radiation budget from the beginning of the space age until the present time are reviewed. The survey emphasizes the early struggle to develop instrument systems to monitor reflected shortwave and emitted long-wave exitances from the earth, and the problems associated with the interpretation of these observations from space. In some instances, valuable data sets were developed from satellite measurements whose instruments were not specifically designed for earth radiation budget observations.

  14. A GNM mission and system design proposal

    NASA Technical Reports Server (NTRS)

    Bailey, Stephen

    1990-01-01

    Here, the author takes an advocacy position for the proposed Mars Global Network Mission (GNM); it is not intended to be an objective review, although both pros and cons are presented in summary. The mission consists of launches from earth in the '96, '98, and '01 opportunities on Delta-class launch vehicles (approx. 1000 kg injected to Mars in 8 to 10 ft diameter shroud). The trans Mars boost stage injects a stack of small independent, aeroshelled spacecraft. The stack separates from the boost stage and each rigid (as opposed to deployable) aeroshell flies to Mars on its own, performing midcourse maneuvers as necessary. Each spacecraft flies a unique trajectory which is targeted to achieve approach atmospheric interface at the desired latitude and lighting conditions; arrival times may vary by a month or more. A direct entry is performed, there is no propulsive orbit capture. The aeroshelled rough-landers are targeted to achieve a desired attitude and entry flight path angle, and then follow a passive ballistic trajectory until terminal descent. Based on sensed acceleration (integrated to deduce altitude), the aft aeroshell skirt is jettisoned; a short later a supersonic parachute is deployed. The ballistic coefficient of the parachute is sized to achieve terminal velocity at about 8 km. However the parachute is not deployed until a few Km above the surface to minimize wind-induced drift. The nose cap descent imaging begins, a laser altimeter also measures true altitude. Based on range and range rate to the surface, the parachute is jettisoned and the lander uses descent engines to achieve touchdown velocity. A contact sensor shuts down the motors to avoid cratering, and the lander rough-lands at less than 5 m/sec. The remaining aeroshell and a deployable bladder attenuate landing loads and minimize the possibility of tip over. Science instruments are deployed and activated, and the network is established.

  15. The ESA Lunar Lander and the search for Lunar Volatiles

    NASA Astrophysics Data System (ADS)

    Morse, A. D.; Barber, S. J.; Pillinger, J. M.; Sheridan, S.; Wright, I. P.; Gibson, E. K.; Merrifield, J. A.; Waltham, N. R.; Waugh, L. J.; Pillinger, C. T.

    2011-10-01

    Following the Apollo era the moon was considered a volatile poor body. Samples collected from the Apollo missions contained only ppm levels of water formed by the interaction of the solar wind with the lunar regolith [1]. However more recent orbiter observations have indicated that water may exist as water ice in cold polar regions buried within craters at concentrations of a few wt. % [2]. Infrared images from M3 on Chandrayaan-1 have been interpreted as showing the presence of hydrated surface minerals with the ongoing hydroxyl/water process feeding cold polar traps. This has been supported by observation of ephemeral features termed "space dew" [3]. Meanwhile laboratory studies indicate that water could be present in appreciable quantities in lunar rocks [4] and could also have a cometary source [5]. The presence of sufficient quantities of volatiles could provide a resource which would simplify logistics for long term lunar missions. The European Space Agency (ESA's Directorate of Human Spaceflight and Operations) have provisionally scheduled a robotic mission to demonstrate key technologies to enable later human exploration. Planned for launch in 2018, the primary aim is for precise automated landing, with hazard avoidance, in zones which are almost constantly illuminated (e.g. at the edge of the Shackleton crater at the lunar south pole). These regions would enable the solar powered Lander to survive for long periods > 6 months, but require accurate navigation to within 200m. Although landing in an illuminated area, these regions are close to permanently shadowed volatile rich regions and the analysis of volatiles is a major science objective of the mission. The straw man payload includes provision for a Lunar Volatile and Resources Analysis Package (LVRAP). The authors have been commissioned by ESA to conduct an evaluation of possible technologies to be included in L-VRAP which can be included within the Lander payload. Scientific aims are to demonstrate the

  16. Relationship of Global Precipitation Measurement (GPM) Mission to Global Change Research

    NASA Technical Reports Server (NTRS)

    Smith, Eric A.; Starr, David OC. (Technical Monitor)

    2002-01-01

    In late 2001, the Global Precipitation Measurement (GPM) mission was approved as a new start by the National Aeronautics and Space Administration (NASA). This new mission is motivated by a number of scientific questions that are posed over a range of space and time scales that generally fall within the discipline of the global water and energy cycle (GWEC). Recognizing that satellite rainfall datasets are now a foremost tool for understanding global climate variability out to decadal scales and beyond, for improving weather forecasting, and for producing better predictions of hydrometeorological processes including short-term hazardous flooding and seasonal fresh water resources assessment, a comprehensive and internationally sanctioned global measuring strategy has led to the GPM mission. The GPM mission plans to expand the scope of rainfall measurement through use of a multi-member satellite constellation that will be contributed by a number of world nations. This talk overviews the GPM scientific research program that has been fostered within NASA, then focuses on scientific progress that is being made in various research areas in the course of the mission formulation phase that are of interest to the global change scientific community. This latter part of the talk addresses research issues that have become central to the GPM science implementation plan concerning: (1) the rate of global water cycling through the atmosphere and surface and the relationship of precipitation variability to the sustained rate of the water cycle; (2) the relationship between climate change and cloud macrophysical- microphysical processes; and (3) the general improvement in measuring precipitation at the fundamental microphysical level that will take place during the GPM era and an explanation of how these improvements are expected to come about.

  17. Explosive propulsion applications. [to future unmanned missions

    NASA Technical Reports Server (NTRS)

    Nakamura, Y.; Varsi, G.; Back, L. H.

    1974-01-01

    The feasibility and application of an explosive propulsion concept capable of supporting future unmanned missions in the post-1980 era were examined and recommendations made for advanced technology development tasks. The Venus large lander mission was selected as the first in which the explosive propulsion concept can find application. A conceptual design was generated and its performance, weight, costs, and interaction effects determined. Comparisons were made with conventional propulsion alternatives. The feasibility of the explosive propulsion system was verified for planetology experiments within the dense atmosphere of Venus as well as the outer planets. Additionally, it was determined that the Venus large lander mission could be augmented ballistically with a significant delivery margin.

  18. The ExoMars 2016 Mission

    NASA Astrophysics Data System (ADS)

    Svedhem, Håkan; Vago, Jorge; de Groot, Rolf; McCoy, Don

    2016-04-01

    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 2018 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 2018 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. The 2016 mission will be launched by a Russian Proton rocket from Baikonur in March 2016 (launch window 14-25 March) and will arrive at Mars on 19 October. This presentation will cover a description of the 2016 mission, including the spacecraft

  19. Mars Polar Lander arrives at KSC

    NASA Technical Reports Server (NTRS)

    1998-01-01

    At the Shuttle Landing Facility, the Mars Polar Lander is rolled from the Air Force C-17 cargo plane that carried it from the Lockheed Martin Astronautics plant in Denver, CO. The Mars Polar Lander is targeted for launch from Cape Canaveral Air Station aboard a Delta II rocket on Jan. 3, 1999. The solar-powered spacecraft is designed to touch down on the Martian surface near the northern-most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere.

  20. Summary Report of Mission Acceleration Measurements for STS-65, Launched 8 July 1994

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; Delombard, Richard

    1995-01-01

    The second flight of the International Microgravity Laboratory (IML-2) payload on board the STS-65 mission was supported by three accelerometer instruments: The Orbital Acceleration Research Experiment (OARE) located close to the orbiter center of mass; the Quasi-Steady Acceleration Measurement experiment, and the Space Acceleration Measurement System (SAMS), both in the Spacelab module. A fourth accelerometer, the Microgravity Measuring Device recorded data in the middeck in support of exercise isolation tests.Data collected by OARE and SAMS during IML-2 are displayed in this report. The OARE data represent the microgravity environment below 1 Hz. The SAMS data represent the environment in the 0.01 Hz to 100 Hz range. Variations in the environment caused by unique activities are presented. Specific events addressed are: crew activity, crew exercise, experiment component mixing activities, experiment centrifuge operations, refrigerator/freezer operations and circulation pump operations. The analyses included in this report complement analyses presented in other mission summary reports.

  1. The Global Precipitation Measurement (GPM) Mission: U.S. Program and Science Status

    NASA Astrophysics Data System (ADS)

    Hou, A.; Azarbarzin, A.; Kakar, R.; Neeck, S.

    2009-04-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors to provide next-generation precipitation data products for scientific research and societal applications. NASA and JAXA will deploy the GPM Core Observatory carrying an advanced radar-radiometer system to serve as a physics observatory and calibration reference for constellation radiometers. NASA will deploy the GPM Low-Inclination Observatory to enhance the near real-time monitoring of hurricanes and mid-latitude storms, and JAXA will contribute data from the Global Change Observation Mission-Water (GCOM-W) satellite. Partnerships are under development to include additional conical-scanning microwave imagers on the French-Indian Megha-Tropiques satellite and U.S. Defense Meteorological Satellite Program (DMSP) satellites, as well as cross-track scanning humidity sounders on operational satellites such as the National Polar-orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP), POES, NPOESS, and European MetOp satellites, which are used to improve the precipitation sampling over land. In addition, Brazil has in its national space plan for a GPM low-inclination radiometer, and data from Chinese and Russian microwave radiometers could potentially become available through international collaboration under the auspices of the Committee on Earth Observation Satellites (CEOS) and Group on Earth Observations (GEO). As a science mission with integrated application goals, GPM is expected to (1) provide new measurement standards for precipitation estimation from space, (2) improve understanding of precipitation physics, the global water cycle variability, and freshwater availability, and (3) advance weather/climate/hydrological prediction capabilities to directly benefit the society. An overview of the GPM mission concept, program

  2. Science and Measurement Requirements for a Plant Physiology and Functional Types Mission: Measuring the Composition, Function and Health of Global Land and Coastal Ocean Ecosystems

    NASA Technical Reports Server (NTRS)

    Green, Robert O.; Rogez, Francois; Green, Rob; Ungar, Steve; Knox, Robert; Asner, Greg; Muller-Karger, Frank; Bissett, Paul; Chekalyuk, Alex; Dierssen, Heidi; Gamon, John; Hook, Simon; Meister, Gerhard; Middleton, Betsy; Ollinger, Scott; Roberts, Dar; Siegel, Dave; Townsend, Phil; Saatchi, Sassan; Unstin, Susan; Turner, Woody; Wickland, Diane; Bontempi, Paula; Emanuel, Bill

    2007-01-01

    This slide presentation reviews the proposed Plant Physiology and Functional Types (PPFT) Mission. The National Academy of Sciences Decadal Survey, placed a critical priority on a Mission to observe distribution and changes in ecosystem functions. The PPFT satellite mission provides the essential measurements needed to assess drivers of change in biodiversity and ecosystem services that affect human welfare. The presentation reviews the science questions that the mission will be designed to answer, the science rationale, the science measurements, the mission concept, the planned instrumentation, the calibration method, and key signal to noise ratios and uniformity requirements.

  3. 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.

  4. Towards the Development of a Global Precipitation Measurement (GPM) Mission Concept

    NASA Technical Reports Server (NTRS)

    Shepherd, Marshall; Starr, David OC. (Technical Monitor)

    2001-01-01

    The scientific success of the Tropical Rainfall Measuring Mission (TRMM) and additional satellite-focused precipitation retrieval projects have paved the way for a more advanced global precipitation mission. A comprehensive global measuring strategy is currently under study - Global Precipitation Measurement (GPM). The GPM study could ultimately lead to the development of the Global Precipitation Mission. The intent of GPM is to address looming scientific questions arising in the context of global climate-water cycle interactions, hydrometeorology, weather prediction and prediction of freshwater resources, the global carbon cycle, and biogeochemical cycles. This talk overviews the status and scientific agenda of this proposed mission currently planned for launch in the 2007-2008 time frame. GPM is planning to expand the scope of precipitation measurement through the use of a constellation of 6-10 satellites, one of which will be an advanced TRMM-like "core" satellite carry dual-frequency Ku-Ka band radar and a microwave radiometer (e.g. TMI-like). The other constellation members will likely include new lightweight satellites and co-existing operational/research satellites carrying passive microwave radiometers. The goal behind the constellation is to achieve no worse than 3-hour sampling at any spot on the globe. The constellation's orbit architecture will consist of a mix of sun-synchronous and non-su n -synchronous satellites with the "core" satellite providing measurement of cloud-precipitation microphysical processes plus "training calibrating" information to be used with the retrieval algorithms for the constellation satellite measurements. The GPM is organized internationally, currently involving a partnership between NASA in the US, NASDA in Japan, and ESA in Europe (representing the European community). The program is expected to involve additional international partners, other federal agencies, and a diverse collection of scientists from academia

  5. Big Crater as Viewed by Pathfinder Lander

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The 'Big Crater' is actually a relatively small Martian crater to the southeast of the Mars Pathfinder landing site. It is 1500 meters (4900 feet) in diameter, or about the same size as Meteor Crater in Arizona. Superimposed on the rim of Big Crater (the central part of the rim as seen here) is a smaller crater nicknamed 'Rimshot Crater.' The distance to this smaller crater, and the nearest portion of the rim of Big Crater, is 2200 meters (7200 feet). To the right of Big Crater, south from the spacecraft, almost lost in the atmospheric dust 'haze,' is the large streamlined mountain nicknamed 'Far Knob.' This mountain is over 450 meters (1480 feet) tall, and is over 30 kilometers (19 miles) from the spacecraft. Another, smaller and closer knob, nicknamed 'Southeast Knob' can be seen as a triangular peak to the left of the flanks of the Big Crater rim. This knob is 21 kilometers (13 miles) southeast from the spacecraft.

    The larger features visible in this scene - Big Crater, Far Knob, and Southeast Knob - were discovered on the first panoramas taken by the IMP camera on the 4th of July, 1997, and subsequently identified in Viking Orbiter images taken over 20 years ago. The scene includes rocky ridges and swales or 'hummocks' of flood debris that range from a few tens of meters away from the lander to the distance of South Twin Peak. The largest rock in the nearfield, just left of center in the foreground, nicknamed 'Otter', is about 1.5 meters (4.9 feet) long and 10 meters (33 feet) from the spacecraft.

    This view of Big Crater was produced by combining 6 individual 'Superpan' scenes from the left and right eyes of the IMP camera. Each frame consists of 8 individual frames (left eye) and 7 frames (right eye) taken with different color filters that were enlarged by 500% and then co-added using Adobe Photoshop to produce, in effect, a super-resolution panchromatic frame that is sharper than an individual frame would be.

    Mars Pathfinder is the second in NASA

  6. New estimates of the Martian landers and rovers coordinates by combining Doppler data and topography model

    NASA Astrophysics Data System (ADS)

    Le Maistre, Sebastien

    2015-11-01

    We propose here a new method to determine the three coordinates of a spacecraft landed on Mars with a high accuracy as early as the very beginning of the mission. The method consists of determining first the in-equatorial plane coordinates with Doppler data only and then inferring the Z-coordinate (along the polar axis) using the MOLA topography model. The method is applied to several landed missions, providing good estimate of the Z-coordinate of Viking lander 1, Pathfinder and Spirit, but failing to improve the Z of Opportunity and Viking lander 2. Finally, the method is applied in the InSight landing ellipse showing the high probability to get InSight’s Z coordinate with a precision better than 10m after only a couple of days of observations.

  7. Reflectance characteristics of the Viking lander camera reference test charts

    NASA Technical Reports Server (NTRS)

    Wall, S. D.; Burcher, E. E.; Jabson, D. J.

    1975-01-01

    Reference test charts provide radiometric, colorimetric, and spatial resolution references for the Viking lander cameras on Mars. Reflectance measurements of these references are described, including the absolute bidirectional reflectance of the radiometric references and the relative spectral reflectance of both radiometric and colorimetric references. Results show that the bidirection reflectance of the radiometric references is Lambertian to within + or - 7% for incidence angles between 20 deg and 60 deg, and that their spectral reflectance is constant with wavelength to within + or - 5% over the spectral range of the cameras. Estimated accuracy of the measurements is + or - 0.05 in relative spectral reflectance.

  8. Airbags to Martian Landers: Analyses at Sandia National Laboratories

    SciTech Connect

    Gwinn, K.W.

    1994-03-01

    A new direction for the national laboratories is to assist US business with research and development, primarily through cooperative research and development agreements (CRADAs). Technology transfer to the private sector has been very successful as over 200 CRADAs are in place at Sandia. Because of these cooperative efforts, technology has evolved into some new areas not commonly associated with the former mission of the national laboratories. An example of this is the analysis of fabric structures. Explicit analyses and expertise in constructing parachutes led to the development of a next generation automobile airbag; which led to the construction, testing, and analysis of the Jet Propulsion Laboratory Mars Environmental Survey Lander; and finally led to the development of CAD based custom garment designs using 3D scanned images of the human body. The structural analysis of these fabric structures is described as well as a more traditional example Sandia with the test/analysis correlation of the impact of a weapon container.

  9. The Preliminary Design of a Universal Martian Lander

    NASA Technical Reports Server (NTRS)

    Norman, Timothy L.; Gaskin, David; Adkins, Sean; MacDonnell, David; Ross, Enoch; Hashimoto, Kouichi; Miller, Loran; Sarick, John; Hicks, Jonathan; Parlock, Andrew; Swalley, Frank (Technical Monitor)

    1993-01-01

    As part of the NASA/USRA program, nineteen West Virginia University students conducted a preliminary design of a manned Universal Martian Lander (UML). The WVU design considers descent to Mars from polar orbit, a six month surface stay, and ascent for rendezvous. The design begins with an unmanned UML landing at Elysium Mons followed by the manned UML landing nearby. During the six month surface stay, the eight modules are assembled to form a Martian base where scientific experiments are performed. The mission also incorporates hydroponic plant growth into a Controlled Ecological Life Support System (CELSS) for water recycling, food production, and to counteract psycho-logical effects of living on Mars. In situ fuel production for the Martian Ascent and Rendezvous Vehicle (MARV) is produced From gases in the Martian atmosphere. Following surface operations, the eight member crew uses the MARV to return to the Martian Transfer Vehicle (MTV) for the journey home to Earth.

  10. Radiometric performance of the Viking Mars lander cameras

    NASA Technical Reports Server (NTRS)

    Huck, F. O.; Burcher, E. E.; Taylor, E. J.; Wall, S. D.

    1975-01-01

    The Viking lander cameras feature an array of 12 silicon photodiodes for electronic focus selection and multispectral imaging. Comparisons of absolute radiometric calibrations of the four cameras selected for the mission to Mars with performance predictions based on their design data revealed minor discrepancies. These discrepancies were caused primarily by the method used to calibrate the photosensor array and apparently also from light reflections internal to the array. The sensitivity and dynamic range of all camera channels are found to be sufficient for high quality pictures, providing that the commandable gains and offsets can be optimized for the scene radiance; otherwise, the quantization noise may be too high or the dynamic range too low for an adequate characterization of the scene.

  11. A rover's-eye view of the lander

    NASA Technical Reports Server (NTRS)

    1997-01-01

    One of Sojourner's two front cameras took this image of the Sagan Memorial Station on Sol 6. The lander and its deployed rear ramp are at upper left, while several large rocks appear at center. Sojourner was near the large rock Yogi when this image was taken.

    Mars Pathfinder is the second in NASA's Discovery program of low-cost spacecraft with highly focused science goals. The Jet Propulsion Laboratory, Pasadena, CA, developed and manages the Mars Pathfinder mission for NASA's Office of Space Science, Washington, D.C. JPL is an operating division of the California Institute of Technology (Caltech). The Imager for Mars Pathfinder (IMP) was developed by the University of Arizona Lunar and Planetary Laboratory under contract to JPL. Peter Smith is the Principal Investigator.

  12. Common Lunar Lander vehicle propulsion system conceptual design

    NASA Technical Reports Server (NTRS)

    Hyatt, C. D.; Riccio, Joseph R.; Moore, Landon

    1993-01-01

    The Common Lunar Lander (CLL) is a concept for a small, unpiloted vehicle which would provide a low-cost capability to land any of a variety of payloads in the 200 kg class at any point on the surface of the moon. Initiated as a precursor mission for the First Lunar Outpost, it also has considerable potential for use by the scientific community at large. A series of studies has been conducted at the NASA Johnson Space Center to define initial requirements and to initiate the design process. This paper describes the propulsion subsystem design as it existed at the CLL System Design Review. The propulsion subsystem design is described in detail along with the planned operations concept, including the unique concept of using pulsing of main engines for thrust modulation. Design options and trades considered and the verification process philosophy which was being planned for the program are discussed.

  13. Study of a quasi-microscope design for planetary landers

    NASA Technical Reports Server (NTRS)

    Giat, O.; Brown, E. B.

    1973-01-01

    The Viking Lander fascimile camera, in its present form, provides for a minimum object distance of 1.9 meters, at which distance its resolution of 0.0007 radian provides an object resolution of 1.33 millimeters. It was deemed desirable, especially for follow-on Viking missions, to provide means for examing Martian terrain at resolutions considerably higher than that now provided. This led to the concept of quasi-microscope, an attachment to be used in conjunction with the fascimile camera to convert it to a low power microscope. The results are reported of an investigation to consider alternate optical configurations for the quasi-microscope and to develop optical designs for the selected system or systems. Initial requirements included consideration of object resolutions in the range of 2 to 50 micrometers, an available field of view of the order of 500 pixels, and no significant modifications to the fascimile camera.

  14. The Global Precipitation Measurement (GPM) Mission: Overview and U.S. Status

    NASA Technical Reports Server (NTRS)

    Hou, Arthur Y.

    2010-01-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors. NASA and JAXA will deploy the GPM Core Observatory carrying an advanced radar-radiometer system to serve as a physics observatory and a transfer standard for inter-calibration of constellation radiometers. The GPM Core Observatory is scheduled for launch in July 2013. NASA will provide a second radiometer to be flown on a partner-provided GPM Low-Inclination Observatory to enhance the near real-time monitoring of hurricanes and mid-latitude storms. JAXA will also contribute data from the Global Change Observation Mission-Water (GCOM-W) satellite. Additional partnerships are under development to include microwave radiometers on the French-Indian Megha-Tropiques satellite and U.S. Defense Meteorological Satellite Program (DMSP) satellites, as well as cross-track scanning humidity sounders on operational satellites such as the NPP, POES, JPSS, and MetOp satellites, which are used to improve the precipitation sampling over land. Brazil has in its national space plan for a GPM low-inclination radiometer, and data from Chinese and Russian microwave radiometers could potentially become available through international collaboration under the auspices of the Committee on Earth Observation Satellites (CEOS) and Group on Earth Observations (GEO). The current generation of global rainfall products combines observations from a network of uncoordinated satellite missions using a variety of merging techniques. GPM will provide "next-generation" precipitation data products characterized by: (1) more accurate instantaneous precipitation measurement (especially for light rain and cold-season solid precipitation), (2) more frequent sampling by an expanded constellation of microwave radiometers including operational humidity sounders over land, (3) intercalibrated microwave

  15. The Global Precipitation Measurement (GPM) Mission: U.S. Program and Science Status

    NASA Astrophysics Data System (ADS)

    Hou, Arthur; Azarbarzin, Ardeshir; Kakar, Ramesh; Neeck, Steven

    2010-05-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors. NASA and JAXA will deploy the GPM Core Observatory carrying an advanced radar-radiometer system to serve as a physics observatory and a transfer standard for inter-calibration of constellation radiometers. The GPM Core Observatory is scheduled for launch in July 2013. In addition, NASA will provide a second radiometer to be flown on a partner-provided GPM Low-Inclination Observatory to enhance the near real-time monitoring of hurricanes and mid-latitude storms. JAXA will also contribute data from the Global Change Observation Mission-Water (GCOM-W) satellite. Additional partnerships are under development to include conical-scanning microwave imagers on the French-Indian Megha-Tropiques satellite and U.S. Defense Meteorological Satellite Program (DMSP) satellites, as well as cross-track scanning humidity sounders on operational satellites such as the National Polar-orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP), POES, NPOESS, and European MetOp satellites, which are used to improve the precipitation sampling over land. Currently, Brazil has in its national space plan for a GPM low-inclination radiometer, and data from Chinese and Russian microwave radiometers could potentially become available through international collaboration under the auspices of the Committee on Earth Observation Satellites (CEOS) and Group on Earth Observations (GEO). The current generation of global rainfall products combines observations from a network of uncoordinated satellite missions using a variety of merging techniques. GPM will provide "next-generation" precipitation data products characterized by: (1) more accurate instantaneous precipitation measurement (especially for light rain and cold-season solid precipitation), (2) more

  16. Observing System Simulations for the NASA ASCENDS Lidar CO2 Mission Concept: Substantiating Science Measurement Requirements

    NASA Technical Reports Server (NTRS)

    Kawa, Stephan R.; Baker, David Frank; Schuh, Andrew E.; Abshire, James Brice; Browell, Edward V.; Michalak, Anna M.

    2012-01-01

    The NASA ASCENDS mission (Active Sensing of Carbon Emissions, Nights, Days, and Seasons) is envisioned as the next generation of dedicated, space-based CO2 observing systems, currently planned for launch in about the year 2022. Recommended by the US National Academy of Sciences Decadal Survey, active (lidar) sensing of CO2 from space has several potentially significant advantages, in comparison to current and planned passive CO2 instruments, that promise to advance CO2 measurement capability and carbon cycle understanding into the next decade. Assessment and testing of possible lidar instrument technologies indicates that such sensors are more than feasible, however, the measurement precision and accuracy requirements remain at unprecedented levels of stringency. It is, therefore, important to quantitatively and consistently evaluate the measurement capabilities and requirements for the prospective active system in the context of advancing our knowledge of carbon flux distributions and their dependence on underlying physical processes. This amounts to establishing minimum requirements for precision, relative accuracy, spatial/temporal coverage and resolution, vertical information content, interferences, and possibly the tradeoffs among these parameters, while at the same time framing a mission that can be implemented within a constrained budget. Here, we present results of observing system simulation studies, commissioned by the ASCENDS Science Requirements Definition Team, for a range of possible mission implementation options that are intended to substantiate science measurement requirements for a laser-based CO2 space instrument.

  17. Drop Size Distribution Measurements Supporting the NASA Global Precipitation Measurement Mission: Infrastructure and Preliminary Results

    NASA Technical Reports Server (NTRS)

    Petersen, Walter A.; Carey, Lawerence D.; Gatlin, Patrick N.; Wingo, Matthew; Tokay, Ali; Wolff, David B.; Bringi, V. N.

    2011-01-01

    Global Precipitation Measurement Mission (GPM) retrieval algorithm validation requires datasets that characterize the 4-D structure, variability, and correlation properties of hydrometeor particle size distributions (PSD) and accumulations over satellite fields of view (5 -- 50 km). Key to this process is the combined use of disdrometer and polarimetric radar platforms. Here the disdrometer measurements serve as a reference for up-scaling dual-polarimetric radar observations of the PSD to the much larger volumetric sampling domain of the radar. The PSD observations thus derived provide a much larger data set for assessing DSD variability, and satellite-based precipitation retrieval algorithm assumptions, in all three spatial dimensions for a range of storm types and seasons. As one component of this effort, the GPM Ground Validation program recently acquired five 3rd generation 2D Video disdrometers as part of its Disdrometer and Radar Observations of Precipitation Facility (DROP), currently hosted in northern Alabama by the NASA Marshall Space Flight Center and the University of Alabama in Huntsville. These next-generation 2DVDs were operated and evaluated in different phases of data collection under the scanning domain of the UAH ARMOR C-band dual-polarimetric radar. During this period approximately 7500 minutes of PSD data were collected and processed to create gamma size distribution parameters using a truncated method of moments approach. After creating the gamma parameter datasets the DSDs were then used as input to T-matrix code for computation of polarimetric radar moments at C-band. The combined dataset was then analyzed with two basic objectives in mind: 1) the investigation of seasonal variability in the rain PSD parameters as observed by the 2DVDs; 2) the use of combined polarimetric moments and observed gamma distribution parameters in a functional form to retrieve PSD parameters in 4-D using the ARMOR radar for precipitation occurring in different

  18. 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.

  19. 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. PMID:16010756

  20. Measurement of precipitation induced FUV emission and Geocoronal Lyman Alpha from the IMI mission

    NASA Technical Reports Server (NTRS)

    Mende, Stephen B.; Fuselier, S. A.; Rairden, R. L.

    1995-01-01

    This final report describes the activities of the Lockheed Martin Palo Alto Research Laboratory in studying the measurement of ion and electron precipitation induced Far Ultra-Violet (FUV) emissions and Geocoronal Lyman Alpha for the NASA Inner Magnetospheric Imager (IMI) mission. this study examined promising techniques that may allow combining several FUV instruments that would separately measure proton aurora, electron aurora, and geocoronal Lyman alpha into a single instrument operated on a spinning spacecraft. The study consisted of two parts. First, the geocoronal Lyman alpha, proton aurora, and electron aurora emissions were modeled to determine instrument requirements. Second, several promising techniques were investigated to determine if they were suitable for use in an IMI-type mission. Among the techniques investigated were the Hydrogen gas cell for eliminating cold geocoronal Lyman alpha emissions, and a coded aperture spectrometer with sufficient resolution to separate Doppler shifted Lyman alpha components.

  1. Assimilation of Precipitation Measurement Missions Microwave Radiance Observations With GEOS-5

    NASA Technical Reports Server (NTRS)

    Jin, Jianjun; Kim, Min-Jeong; McCarty, Will; Akella, Santha; Gu, Wei

    2015-01-01

    The Global Precipitation Mission (GPM) Core Observatory satellite was launched in February, 2014. The GPM Microwave Imager (GMI) is a conically scanning radiometer measuring 13 channels ranging from 10 to 183 GHz and sampling between 65 S 65 N. This instrument is a successor to the Tropical Rainfall Measurement Mission (TRMM) Microwave Imager (TMI), which has observed 9 channels at frequencies ranging 10 to 85 GHz between 40 S 40 N since 1997. This presentation outlines the base procedures developed to assimilate GMI and TMI radiances in clear-sky conditions, including quality control methods, thinning decisions, and the estimation of, observation errors. This presentation also shows the impact of these observations when they are incorporated into the GEOS-5 atmospheric data assimilation system.

  2. Compact Low Power DPU for Plasma Instrument LINA on the Russian Luna-Glob Lander

    NASA Astrophysics Data System (ADS)

    Schmidt, Walter; Riihelä, Pekka; Kallio, Esa

    2013-04-01

    The Swedish Institute for Space Physics in Kiruna is bilding a Lunar Ions and Neutrals Analyzer (LINA) for the Russian Luna-Glob lander mission and its orbiter, to be launched around 2016 [1]. The Finnish Meteorological Institute is responsible for designing and building the central data processing units (DPU) for both instruments. The design details were optimized to serve as demonstrator also for a similar instrument on the Jupiter mission JUICE. To accommodate the originally set short development time and to keep the design between orbiter and Lander as similar as possible, the DPU is built around two re-programmable flash-based FPGAs from Actel. One FPGA contains a public-domain 32-bit processor core identical for both Lander and orbiter. The other FPGA handles all interfaces to the spacecraft system and the detectors, somewhat different for both implementations. Monitoring of analog housekeeping data is implemented as an IP-core from Stellamar inside the interface FPGA, saving mass, volume and especially power while simplifying the radiation protection design. As especially on the Lander the data retention before transfer to the orbiter cannot be guaranteed under all conditions, the DPU includes a Flash-PROM containing several software versions and data storage capability. With the memory management implemented inside the interface FPGA, one of the serial links can also be used as test port to verify the system, load the initial software into the Flash-PROM and to control the detector hardware directly without support by the processor and a ready developed operating system and software. Implementation and performance details will be presented. Reference: [1] http://www.russianspaceweb.com/luna_glob_lander.html.

  3. 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.

  4. CLAIRE: a Canadian Small Satellite Mission for Measurement of Greenhouse Gases

    NASA Astrophysics Data System (ADS)

    Sloan, James; Grant, Cordell; Germain, Stephane; Durak, Berke; McKeever, Jason; Latendresse, Vincent

    2016-07-01

    CLAIRE, a Canadian mission operated by GHGSat Inc. of Montreal, is the world's first satellite designed to measure greenhouse gas emissions from single targeted industrial facilities. Claire was launched earlier this year into a 500 km polar sun-synchronous orbit selected to provide an acceptable balance between return frequency and spatial resolution. Extensive simulations of oil & gas facilities, power plants, hydro reservoirs and even animal feedlots were used to predict the mission performance. The principal goal is to measure the emission rates of carbon dioxide and methane from selected targets with greater precision and lower cost than ground-based alternatives. CLAIRE will measure sources having surface areas less than 10 x 10 km2 with a spatial resolution better than 50 m, thereby providing industrial site operators and government regulators with the information they need to understand, manage and ultimately to reduce greenhouse gas emissions more economically. The sensor is based on a Fabry-Perot interferometer, coupled with a 2D InGaAs focal plane array operating in the short-wave infrared with a spectral resolution of about 0.1 nm. The patented, high étendue, instrument design provides signal to noise ratios that permit quantification of emission rates with accuracies adequate for most regulatory reporting thresholds. The very high spatial resolution of the density maps produced by the CLAIRE mission resolves plume shapes and emitter locations so that advanced dispersion models can derive accurate emission rates of multiple sources within the field of view. The satellite bus, provided by the University of Toronto's Space Flight Laboratory, is based on the well-characterized NEMO architecture, including hardware that has significant spaceflight heritage. The mission is currently undergoing initial test and validation measurements in preparation for commercial operation later this year.

  5. An Intercomparison of Lidar Ozone and Temperature Measurements From the SOLVE Mission With Predicted Model Values

    NASA Technical Reports Server (NTRS)

    Burris, John; McGee, Thomas J.; Hoegy, Walt; Lait, Leslie; Sumnicht, Grant; Twigg, Larry; Heaps, William

    2000-01-01

    Temperature profiles acquired by Goddard Space Flight Center's AROTEL lidar during the SOLVE mission onboard NASA's DC-8 are compared with predicted values from several atmospheric models (DAO, NCEP and UKMO). The variability in the differences between measured and calculated temperature fields was approximately 5 K. Retrieved temperatures within the polar vortex showed large regions that were significantly colder than predicted by the atmospheric models.

  6. Piezoelectric composite transducers, ultrasonic materials characterization, and the ROSETTA Comet mission

    NASA Astrophysics Data System (ADS)

    Arnold, W.; Gebhardt, W.; Licht, R.; Kröning, M.

    2001-04-01

    In 2003 the ROSETTA space mission to Comet 46P/Wirtanen will be launched by the European Space Agency (ESA). On board of the spacecraft will be a lander in order to carry out measurements on the comet surface. The so-called CASSE experiment aims to investigate the surface of the comet by transmitting, receiving and passively monitoring acoustic waves at frequencies from a few hundred to several kilohertz. The knowledge of the IZFP in modeling of NDT problems, in wave propagation in complex materials, and in the design of advanced transducers eventually led to its involvement in the ROSETTA mission. .

  7. Mission Simulation of Space Lidar Measurements for Seasonal and Regional CO2 Variations

    NASA Technical Reports Server (NTRS)

    Kawa, Stephan; Collatz, G. J.; Mao, J.; Abshire, J. B.; Sun, X.; Weaver, C. J.

    2010-01-01

    Results of mission simulation studies are presented for a laser-based atmospheric [82 sounder. The simulations are based on real-time carbon cycle process modeling and data analysis. The mission concept corresponds to the Active Sensing of [82 over Nights, Days, and Seasons (ASCENDS) recommended by the US National Academy of Sciences Decadal Survey of Earth Science and Applications from Space. One prerequisite for meaningful quantitative sensor evaluation is realistic CO2 process modeling across a wide range of scales, i.e., does the model have representative spatial and temporal gradients? Examples of model comparison with data will be shown. Another requirement is a relatively complete description of the atmospheric and surface state, which we have obtained from meteorological data assimilation and satellite measurements from MODIS and [ALIPS0. We use radiative transfer model calculations, an instrument model with representative errors ' and a simple retrieval approach to complete the cycle from "nature" run to "pseudo-data" CO2, Several mission and instrument configuration options are examined/ and the sensitivity to key design variables is shown. We use the simulation framework to demonstrate that within reasonable technological assumptions for the system performance, relatively high measurement precision can be obtained, but errors depend strongly on environmental conditions as well as instrument specifications. Examples are also shown of how the resulting pseudo - measurements might be used to address key carbon cycle science questions.

  8. Short and long term efficiencies of debris risk reduction measures: Application to a European LEO mission

    NASA Astrophysics Data System (ADS)

    Lang, T.; Kervarc, R.; Bertrand, S.; Carle, P.; Donath, T.; Destefanis, R.; Grassi, L.; Tiboldo, F.; Schäfer, F.; Kempf, S.; Gelhaus, J.

    2015-01-01

    Recent numerical studies indicate that the low Earth orbit (LEO) debris environment has reached a point such that even if no further space launches were conducted, the Earth satellite population would remain relatively constant for only the next 50 years or so. Beyond that, the debris population would begin to increase noticeably, due to the production of collisional debris (Liou and Johnson, 2008). Measures to be enforced play thus a major role to preserve an acceptable space mission risk and ensure sustainable space activities. The identification of such measures and the quantification of their efficiency over time for LEO missions is of prime concern in the decision-making process, as it has been investigated for the last few decades by the Inter-Agency Space Debris Coordination Committee (IADC). This paper addresses the final results of a generic methodology and the characteristics of a tool developed to assess the efficiency of the risk reduction measures identified for the Sentinel-1 (S1) mission. This work is performed as part of the 34-month P2-ROTECT project (Prediction, Protection & Reduction of OrbiTal Exposure to Collision Threats), funded by the European Union within the Seventh Framework Programme. Three ways of risk reduction have been investigated, both in short and long-term, namely: better satellite protection, better conjunction prediction, and cleaner environment. According to our assumptions, the S1 mission vulnerability evaluations in the long term (from 2093 to 2100) show that full compliance to the mitigation measures leads to a situation twice safer than that induced by an active debris removal of 5 objects per year in a MASTER2009 Business-As-Usual context. Because these measures have visible risk reduction effects in the long term, complementary measures with short response time are also studied. In the short term (from 2013 to 2020), a better prediction of the conjunctions is more efficient than protecting the satellite S1 itself. By

  9. Low-cost unmanned lunar lander

    NASA Technical Reports Server (NTRS)

    Daniel, Walter K.

    1992-01-01

    Two student groups designed unmanned landers to deliver 200 kilogram payloads to the lunar surface. Payloads could include astronomical telescopes, small lunar rovers, and experiments related to future human exploration. Requirements include the use of existing hardware where possible, use of a medium-class launch vehicle, an unobstructed view of the sky for the payload, and access to the lunar surface for the payload. The projects were modeled after Artemis, a project that the NASA Office of Exploration is pursuing with a planned first launch in 1996. The Lunar Scout design uses a Delta 2 launch vehicle with a Star 48 motor for insertion into the trans-lunar trajectory. During the transfer, the solar panels will be folded inward and the spacecraft will be powered by rechargeable nickel-cadmium batteries. The lander will use a combination of a solid rocket motor and hydrazine thrusters for the descent to the lunar surface. The solar arrays will be deployed after landing. The lander will provide power for operations to the payload during the lunar day; batteries will provide 'stay-alive' power during the lunar night. A horn antenna on the lander will provide communications between the payload and the earth.

  10. Lunar lander configuration study and parametric performance analysis

    NASA Technical Reports Server (NTRS)

    Donahue, Benjamin B.; Fowler, C. R.

    1993-01-01

    Future Lunar exploration plans will call for delivery of significant mounts or cargo to provide for crew habitation, surface tansportation, and scientific exploration activities. Minimization of costly surface based infrastructure is in large part directly related to the design of the cargo delivery/landing craft. This study focused on evaluating Lunar lander concepts from a logistics oriented perspective, and outlines the approach used in the development of a preferred configuration, sets forth the benefits derived from its utilization and describes the missions and system considered. Results indicate that only direct-to-surface downloading of payloads provides for unassisted cargo removal operations imperative to efficient and low risk site buildup, including the emplacement of Space Station derivative surface habitat modules, immediate cargo jettison for both descent abort and emergency surface ascent essential to piloted missions carrying cargo, and short habitat egress/ingress paths necessary to productive surface work tours for crew members carrying hand held experiments, tools and other bulky articles. Accommodating cargo in a position underneath the vehicles structural frame, landing craft described herein eliminate altogether the necessity for dedicated surface based off-loading vehicles, the operations and maintenance associated with their operation, and the precipitous ladder climbs to and from the surface that are inherent to traditional designs. Parametric evaluations illustrate performance and mass variation with respect to mission requirements.

  11. Synthetic Vision Displays for Planetary and Lunar Lander Vehicles

    NASA Technical Reports Server (NTRS)

    Arthur, Jarvis J., III; Prinzel, Lawrence J., III; Williams, Steven P.; Shelton, Kevin J.; Kramer, Lynda J.; Bailey, Randall E.; Norman, Robert M.

    2008-01-01

    Aviation research has demonstrated that Synthetic Vision (SV) technology can substantially enhance situation awareness, reduce pilot workload, improve aviation safety, and promote flight path control precision. SV, and related flight deck technologies are currently being extended for application in planetary exploration vehicles. SV, in particular, holds significant potential for many planetary missions since the SV presentation provides a computer-generated view for the flight crew of the terrain and other significant environmental characteristics independent of the outside visibility conditions, window locations, or vehicle attributes. SV allows unconstrained control of the computer-generated scene lighting, terrain coloring, and virtual camera angles which may provide invaluable visual cues to pilots/astronauts, not available from other vision technologies. In addition, important vehicle state information may be conformally displayed on the view such as forward and down velocities, altitude, and fuel remaining to enhance trajectory control and vehicle system status. The paper accompanies a conference demonstration that introduced a prototype NASA Synthetic Vision system for lunar lander spacecraft. The paper will describe technical challenges and potential solutions to SV applications for the lunar landing mission, including the requirements for high-resolution lunar terrain maps, accurate positioning and orientation, and lunar cockpit display concepts to support projected mission challenges.

  12. Lunar lander configuration study and parametric performance analysis

    NASA Astrophysics Data System (ADS)

    Donahue, Benjamin B.; Fowler, C. R.

    1993-06-01

    Future Lunar exploration plans will call for delivery of significant mounts or cargo to provide for crew habitation, surface tansportation, and scientific exploration activities. Minimization of costly surface based infrastructure is in large part directly related to the design of the cargo delivery/landing craft. This study focused on evaluating Lunar lander concepts from a logistics oriented perspective, and outlines the approach used in the development of a preferred configuration, sets forth the benefits derived from its utilization and describes the missions and system considered. Results indicate that only direct-to-surface downloading of payloads provides for unassisted cargo removal operations imperative to efficient and low risk site buildup, including the emplacement of Space Station derivative surface habitat modules, immediate cargo jettison for both descent abort and emergency surface ascent essential to piloted missions carrying cargo, and short habitat egress/ingress paths necessary to productive surface work tours for crew members carrying hand held experiments, tools and other bulky articles. Accommodating cargo in a position underneath the vehicles structural frame, landing craft described herein eliminate altogether the necessity for dedicated surface based off-loading vehicles, the operations and maintenance associated with their operation, and the precipitous ladder climbs to and from the surface that are inherent to traditional designs. Parametric evaluations illustrate performance and mass variation with respect to mission requirements.

  13. The Global Precipitation Measurement (GPM) Mission contributions to terrestrial hydrology and societal applications

    NASA Astrophysics Data System (ADS)

    Kirschbaum, D.; Skofronick Jackson, G.; Huffman, G. J.

    2015-12-01

    Too much or too little rain can serve as a tipping point for triggering catastrophic flooding and landslides or widespread drought. Knowing when, where and how much rain is falling globally is vital to understanding how vulnerable areas may be more or less impacted by these disasters. The Global Precipitation Measurement (GPM) mission is an international constellation of satellites coordinated through a partnership with NASA and the Japan Aerospace Exploration Agency (JAXA) to provide next-generation global observations of rain and snow. The GPM mission centers on the deployment of a Core Observatory satellite that serves as a reference standard to unify precipitation measurements from a constellation of research and operational satellites. This satellite launched from Tanegashima Space Complex in Japan on January 28th, 2014 and carries advanced instruments setting a new standard for precipitation measurements from space. The GPM Core Observatory satellite measures rain and snow using two science instruments: the GPM Microwave Imager (GMI) and the Dual-frequency Precipitation Radar (DPR). The GMI captures precipitation intensities and horizontal patterns, while the DPR provides insights into the three dimensional structure of precipitating particles. Together these two instruments provide a database of measurements against which other partner satellites' microwave observations can be meaningfully compared and combined to make a global precipitation dataset. GPM has already provided unprecedented views of typhoons, extratropical systems, light rain, snow storms and extreme precipitation. Through improved measurements of precipitation globally, the GPM mission provides new insights into measuring the fluxes of Earth's water cycle. This presentation will outline new findings and advancements of GPM in understanding and modeling of Earth's water and energy cycles, improving forecasting of extreme events that cause natural hazards and disasters, and extending current

  14. Mars' rotational state and tidal deformations from radio interferometry of a network of landers.

    NASA Astrophysics Data System (ADS)

    Iess, L.; Giuliani, S.; Dehant, V.

    2012-04-01

    The precise determination of the rotational state of solar system bodies is one of the main tools to investigate their interior structure. Unfortunately the accuracies required for geophysical interpretations are very stringent, and generally unattainable from orbit using optical or radar tracking of surface landmarks. Radio tracking of a lander from ground or from a spacecraft orbiting the planet offers substantial improvements, especially if the lander lifetime is adequately long. The optimal configuration is however attained when two or more landers can be simultaneously tracked from a ground antenna in an interferometric mode. ESA has been considering a network of landers on Mars since many years, and recently this concept has been revived by the study of the Mars Network Science Mission (MNSM). The scientific rationale of MNSM is the investigation of the Mars' interior and atmosphere by means of a network of two or three landers, making it especially suitable for interferometric observations. In order to synthesize an interferometer, the MNSN landers must be tracked simultaneously from a single ground antenna in a coherent two-way mode. The uplink radio signal (at X- or Ka-band) is received by the landers' transponders and retransmitted to ground in the same frequency band. The signals received at ground station are then recorded (typically at few tens of kHz) and beaten against each other to form the output of the interferometer, a complex phasor. The differential phase retain information on Mars' rotational parameters and tidal deformations. A crucial aspect of the interferometric configuration is the rejection of common noise and error sources. Errors in the station location, Earth orientation parameters and ephemerides, path delays due to the Earth troposphere and ionosphere, and, to a good extent, interplanetary plasma are cancelled out. The main residual errors are due to differential path delays from Mars' atmosphere and differential drifts of the

  15. Eight years of OMI measurements and what we can learn from these for the Sentinel missions

    NASA Astrophysics Data System (ADS)

    Levelt, Pieternel; Veefkind, Pepijn; Bhartia, Pawan; Joiner, Joanna; Taminen, Johanna; Omi Science Team

    2013-04-01

    Eight years of OMI measurements and what we can learn from these for the Sentinel missions P.F. Levelt, P. Veefkind, PK Bhartia, J. Joiner, J. Tamminen, OMI Science Team The Ozone Monitoring Instrument (OMI) is an UV/VIS nadir solar backscatter imaging spectrometer, which provides nearly global coverage in one day with a spatial resolution of 13 x 24 km2. OMI measures solar irradiance and Earth radiances in the wavelength range of 270 to 500 nm with a spectral resolution of about 0.5 nm. The OMI instrument was launched at July 15, 2004 on NASA's EOS-Aura satellite. OMI is a third party mission of ESA. OMI's unique capabilities rely in measuring tropospheric trace gases with a small footprint and daily global coverage. The unprecedented spatial resolution of the instrument revealed for the first time tropospheric pollution maps on a daily basis with urban scale resolution, and also enables research improving our understanding of air pollutants and aerosols in the interaction between air quality and climate change. The data are used for obtaining emission maps using inverse modelling or related techniques. The sentinel missions (S5p/TROPOMI and Sentinel 4 and 5) will have an even better spatial resolution than OMI. In order to exploit their capability for tropospheric research and actual monitoring of emission sources the calibration and validation of these instruments and their data products are of high importance. In this presentation new findings of OMI will be presented and what we can learn from that for the preparation of the Sentinel missions, their validation and their scientific exploitation. Also lessons learned from the NASA methodology for OMI validation will be discussed and results of validation campaigns that supported OMI validation (i.e. SAUNA, DANDELIONS, CINDI, DISCOVER AQ, etc etc) will be shown.

  16. Rosetta Mission Status Update

    NASA Astrophysics Data System (ADS)

    Taylor, M. G.; Altobelli, N.; Alexander, C. J.; Schwehm, G. H.; Jansen, F.; Küppers, M.; O'Rourke, L.; Barthelemy, M.; Geiger, B.; Grieger, B.; Moissl, R.; Vallat, C.

    2014-12-01

    The Rosetta Mission is the third cornerstone mission the ESA programme Horizon 2000. The aim of the mission is to map the comet 67-P/Churyumov-Gerasimenko by remote sensing, to examine its environment insitu and its evolution in the inner solar system. The lander Philae will be the first device to land on a comet and perform in-situ science on the surface. Nearly 10 years after launch in 2004, on 20th January 2014 at 10:00 UTC the spacecraft woke up from hibernation. Following successful instrument commissioning, at the time of writing the spacecraft is about to rendez-vous with the comet. The rest of 2014 will involve careful mapping and characterisation of the nucleus and its environs, for science and to identify a landing site for the lander Philae in November. This presentation will provide a brief overview of the mission up to date and where we stand in early part of the escort phase of the mission which runs until end of 2015.

  17. The Mars Pathfinder Mission and Science Results

    NASA Astrophysics Data System (ADS)

    Golombek, M. P.

    1999-01-01

    Mars Pathfinder, the first low-cost, quick Discovery class mission to be completed, successfully landed on the surface of Mars on July 4, 1997, deployed and navigated a small rover, and collected data from 3 science instruments and 10 technology experiments. The mission operated on Mars for 3 months and returned 2.3 Gbits of new data, including over 16,500 lander and 550 rover images, 16 chemical analyses of rocks and soil, and 8.5 million individual temperature, pressure and wind measurements. The rover traversed 100 m clockwise around the lander, exploring about 200 square meters of the surface. The mission captured the imagination of the public, and garnered front page headlines during the first week. A total of about 566 million internet "hits" were registered during the first month of the mission, with 47 million "hits" on July 8th alone, making the Pathfinder landing by far the largest internet event in history at the time. Pathfinder was the first mission to deploy a rover on Mars. It carried a chemical analysis instrument, to characterize the rocks and soils in a landing area over hundreds of square meters on Mars, which provided a calibration point or "ground truth" for orbital remote sensing observations. The combination of spectral imaging of the landing area by the lander camera, chemical analyses aboard the rover, and close-up imaging of colors, textures and fabrics with the rover cameras offered the potential of identifying rocks (petrology and mineralogy). With this payload, a landing site in Ares Vallis was selected because it appeared acceptably safe and offered the prospect of analyzing a variety of rock types expected to be deposited by catastrophic floods, which enabled addressing first-order scientific questions such as differentiation of the crust, the development of weathering products, and the nature of the early Martian environment and its subsequent evolution. The 3 instruments and rover allowed seven areas of scientific investigation: the

  18. Geoscience Laser Altimeter System (GLAS) on the ICESat Mission: Science Measurement Performance since Launch

    NASA Technical Reports Server (NTRS)

    Sun, Xiao-Li; Abshire, James B.; Riris, Haris; McGarry, Jan; Sirota, Marcos

    2004-01-01

    The Geoscience Laser Altimeter System is the primary space lidar on NASA's ICESat mission. Since launch in January 2003 GLAS has produced about 544 million measurements of the Earth's surface and atmosphere. It has made global measurements of the Earth's icesheets, land topography and atmosphere with unprecedented vertical resolution and accuracy. GLAS was first activated for science measurements in February 2003. Since then its operation and performance has confirmed many pre-launch expectations and exceed a few of the most optimistic expectations in vertical resolution. However GLAS also suffered an unexpected failure of its first laser, and the GLAS measurements have yielded some surprises in other areas. The talk will give a post launch assessment of the science measurement performance of the GLAS instrument, and compare the science measurements and engineering operation to pre-launch expectations. It also will address some of what has been learned from the GLAS operations and data, which may benefit future space lidar.

  19. In-Situ Missions for the Exploration of Titan's Lakes

    NASA Technical Reports Server (NTRS)

    Elliott, John O.; Waite, J. Hunter

    2011-01-01

    The lakes of Titan represent an increasingly tantalizing target for future exploration. As Cassini continues to reveal more details the lakes appear to offer a particularly rich reservoir of knowledge that could provide insights to Titan's formation and evolution, as well as an ideal location to explore Titan's potential for pre-biotic chemistry. A recent study of Titan Lake Probe missions was undertaken as one of several dozen studies commissioned by the National Research Council (NRC) Planetary Decadal Survey to explore the technical readiness, feasibility and affordability of scientifically promising mission scenarios. This in-depth study focused on an in-situ examination of a hydrocarbon lake on the Saturnian moon Titan--a target that presents unique scientific opportunities as well as several unique engineering challenges (e.g., submersion systems and cryogenic sampling) to enable those measurements. Per direction from the NRC Planetary Decadal Survey Satellites Panel, and after an initial trade-space examination, study architectures focused on three possible New Frontiers-class missions and a more ambitious Flagship-class lander intended as the in-situ portion of a larger collaborative mission. Detailed point designs were developed to explore these four potential mission options, including consideration of flight system and mission designs, as well as operations on and under the lake's surface and scenarios for data return. In this paper we present an overview of the science objectives of the missions, the mission architecture and surface.

  20. Atmospheric Airborne Pressure Measurements Using the Oxygen A Band for the ASCENDS Mission

    NASA Technical Reports Server (NTRS)

    Riris, Haris; Rodriguez, Mike; Stephen, Mark; Hasselbrack, William; Allan, Graham; Mao, Jianping; Kawa, Stephen R.; Weaver, Clark J.

    2010-01-01

    We report on airborne atmospheric pressure measurements using new fiber-based laser technology and the oxygen A-band at 765 nm. Remote measurements of atmospheric temperature and pressure are required for a number of NASA Earth science missions and specifically for the Active Sensing of CO2 Emissions Over Nights, Days, and Seasons (ASCENDS) mission. Accurate measurements of tropospheric CO2 on a global scale are very important in order to better understand its sources and sinks and to improve predictions on any future climate change. The ultimate goal of a CO2 remote sensing mission, such as ASCENDS, is to derive the CO2 concentration in the atmosphere in terms of mole fraction in unit of parts-per-million (ppmv) with regard to dry air. Therefore, both CO2 and the dry air number of molecules in the atmosphere are needed in deriving this quantity. O2 is a stable molecule and uniformly mixed in the atmosphere. Measuring the O2 absorption in the atmosphere can thus be used to infer the dry air number of molecules and then used to calculate CO2 concentration. With the knowledge of atmospheric water vapor, we can then estimate the total surface pressure needed for CO2 retrievals. Our work, funded by the ESTO IIP program, uses fiber optic technology and non-linear optics to generate 765 nm laser radiation coincident with the Oxygen A-band. Our pulsed, time gated technique uses several on- and off-line wavelengths tuned to the O2 absorption line. The choice of wavelengths allows us to measure the pressure by using two adjacent O2 absorptions in the Oxygen A-band. Our retrieval algorithm fits the O2 lineshapes and derives the pressure. Our measurements compare favorably with a local weather monitor mounted outside our laboratory and a local weather station.

  1. Atmospheric Airborne Pressure Measurements Using the Oxygen A Band for the ASCENDS Mission

    NASA Technical Reports Server (NTRS)

    Riris, Haris; Rodriguez, Mike; Stephen, Mark; Hasselbrack, William; Allan, Graham; Mao, Jiamping,; Kawa, Stephan R.; Weaver, Clark J.

    2011-01-01

    We report on airborne atmospheric pressure measurements using new fiber-based laser technology and the oxygen A-band at 765 nm. Remote measurements of atmospheric temperature and pressure are required for a number of NASA Earth science missions and specifically for the Active Sensing of CO2 Emissions Over Nights, Days, and Seasons (ASCENDS) mission. Accurate measurements of tropospheric CO2 on a global scale are very important in order to better understand its sources and sinks and to improve predictions on any future climate change. The ultimate goal of a CO2 remote sensing mission, such as ASCENDS, is to derive the CO2 concentration in the atmosphere in terms of mole fraction in unit of parts-per-million (ppmv) with regard to dry air. Therefore, both CO2 and the dry air number of molecules in the atmosphere are needed in deriving this quantity. O2 is a stable molecule and uniformly mixed in the atmosphere. Measuring the O2 absorption in the atmosphere can thus be used to infer the dry air number of molecules and then used to calculate CO2 concentration. With the knowledge of atmospheric water vapor, we can then estimate the total surface pressure needed for CO2 retrievals. Our work, funded by the ESTO IIP program, uses fiber optic technology and non-linear optics to generate 765 nm laser radiation coincident with the Oxygen A-band. Our pulsed, time gated technique uses several on- and off-line wavelengths tuned to the O2 absorption line. The choice of wavelengths allows us to measure the pressure by using two adjacent O2 absorptions in the Oxygen A-band. Our retrieval algorithm fits the O2 lineshapes and derives the pressure. Our measurements compare favorably with a local weather monitor mounted outside our laboratory and a local weather station.

  2. Concept of Operations for Deploying a Lander on the Secondary Body of Binary Asteroid 1996 FG3

    NASA Astrophysics Data System (ADS)

    Tardivel, Simon; Michel, P.; Scheeres, D.

    2012-10-01

    The European Space Agency is currently performing an assessment study of the MarcoPolo-R space mission, in the framework of the M3 class competition of its Cosmic Vision Program. MarcoPolo-R is a sample return mission to a primitive asteroid, whose baseline target is the binary asteroid 1996FG3. The baseline mission, including the sample, is focused on the primary of the binary system. To date, little has yet been considered for the investigation of the secondary, apart from remote observations from the spacecraft. However, MarcoPolo-R may carry an optional lander, and if such a lander could be accommodated it may be relevant to use it for a more detailed investigation of the secondary. This poster presents a strategy for deploying a lander using an unpowered trajectory towards the secondary. This ballistic deployment allows for the design of a light lander with minimum platform overhead and maximum payload. The deployment operations are shown to be very simple and require minimum preparation. The main spacecraft is set on an orbit that reaches a specific point near the binary system L2 Lagrange Point facing the far side of the secondary, about 220 meters from the secondary surface, with a relative speed of about 10cm/s. The lander is then jettisoned using a spring-release mechanism that sets it on an impact trajectory that robustly intersects with the secondary surface. On impact, the lander only needs to dissipate a small amount of kinetic energy in order to ensure that it is energetically and dynamically trapped on the surface. Considering errors on spacecraft GNC and on the spring-release mechanism, and very large uncertainties on the gravity field of the asteroids, the strategy presented here yields a successful landing in more than 99.9% of cases, while ensuring the absolute safety of the spacecraft before, during and after deployment operations.

  3. NanoSWARM - A nano-satellite mission to measure particles and fields around the Moon

    NASA Astrophysics Data System (ADS)

    Garrick-Bethell, Ian; Russell, Christopher; Pieters, Carle; Weiss, Benjamin; Halekas, Jasper; Poppe, Andrew; Larson, Davin; Lawrence, David; Elphic, Richard; Hayne, Paul; Blakely, Richard; Kim, Khan-Hyuk; Choi, Young-Jun; Jin, Ho; Hemingway, Doug; Nayak, Michael; Puig-Suari, Jordi; Jaroux, Belgacem; Warwick, Steven

    2015-04-01

    The NanoSWARM mission concept uses a fleet of cubesats around the Moon to address a number of open problems in planetary science: 1) The mechanisms of space weathering, 2) The origins of planetary magnetism, 3) The origins, distributions, and migration processes of surface water on airless bodies, and 4) The physics of small-scale magnetospheres. To accomplish these goals, NanoSWARM targets scientifically rich features on the Moon known as swirls. Swirls are high-albedo features correlated with strong magnetic fields and low surface-water. NanoSWARM cubesats will make the first near-surface (<500 m altitude) measurements of solar wind flux and magnetic fields at swirls. NanoSWARM cubesats will also perform low-altitude neutron measurements to provide key constraints on the distribution of polar hydrogen concentrations, which are important volatile sinks in the lunar water cycle. To release its cubesats, NanoSWARM uses a high-heritage mother ship in a low altitude, polar, circular orbit. NanoSWARM's results will have direct applications to the geophysics, volatile distribution, and plasma physics of numerous other bodies, in particular asteroids and the terrestrial planets. The technologies and methods used by NanoSWARM will enable many new cubesat missions in the next decade, and expand the cubesat paradigm into deep space. NanoSWARM will be proposed as a NASA Discovery mission in early 2015.

  4. NanoSWARM: A Nano-satellite Mission to Measure Particles and Fields Around the Moon

    NASA Astrophysics Data System (ADS)

    Garrick-Bethell, I.

    2015-12-01

    The NanoSWARM mission concept uses a fleet of cubesats around the Moon to address a number of open problems in planetary science: 1) The mechanisms of space weathering, 2) The origins of planetary magnetism, 3) The origins, distributions, and migration processes of surface water on airless bodies, and 4) The physics of small-scale magnetospheres. To accomplish these goals, NanoSWARM targets scientifically rich features on the Moon known as swirls. Swirls are high-albedo features correlated with strong magnetic fields and low surface-water. NanoSWARM cubesats will make the first near-surface (<1 km altitude) measurements of solar wind flux and magnetic fields at swirls. NanoSWARM cubesats will also perform low-altitude neutron measurements to provide key constraints on the distribution of polar hydrogen concentrations, which are important volatile sinks in the lunar water cycle. To release its cubesats, NanoSWARM uses a high-heritage mother ship in a low altitude, polar, circular orbit. NanoSWARM's results will have direct applications to the geophysics, volatile distribution, and plasma physics of numerous other bodies, in particular asteroids and the terrestrial planets. The technologies and methods used by NanoSWARM will enable many new cubesat missions in the next decade. NanoSWARM was proposed as a NASA Discovery mission in February 2015.

  5. Design and Performance of Tropical Rainfall Measuring Mission (TRMM) Super NiCd Batteries

    NASA Technical Reports Server (NTRS)

    Ahmad, Anisa J.; Rao, Gopalakrishna M.; Jallice, Doris E.; Moran Vickie E.

    1999-01-01

    The Tropical Rainfall Measuring Mission (TRMM) is a joint mission between NASA and the National Space Development Agency (NASDA) of Japan. The observatory is designed to monitor and study tropical rainfall and the associated release of energy that helps to power the global atmospheric circulation shaping both weather and climate around the globe. The spacecraft was launched from Japan on November 27,1997 via the NASDA H-2 launch vehicle. The TRMM Power Subsystem is a Peak Power Tracking system that can support the maximum TRMM load of 815 watts at the end of its three year life. The Power Subsystem consists of two 50 Ampere Hour Super NiCd batteries, Gallium Arsenide Solar Array and the Power System Electronics. This paper describes the TRMM Power Subsystem, battery design, cell and battery ground test performance, and in-orbit battery operations and performance.

  6. Summary Report of mission acceleration measurements for STS-66. Launched November 3, 1994

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; Delombard, Richard

    1995-01-01

    Experiments flown in the middeck of Atlantis during the STS-66 mission were supported by the Space Acceleration Measurement System (SAMS). In particular, the three triaxial SAMS sensor heads collected data in support of protein crystal growth experiments. Data collected during STS-66 are reviewed in this report. The STS-66 SAMS data represent the microgravity environment in the 0.01 Hz to 10 Hz range. Variations in the environment related to differing levels of crew activity are discussed in the report. A comparison is made among times when the crew was quiet during a public affairs conference, working quietly, and exercising. These levels of activity are also compared to levels recorded by a SAMS unit in the Spacelab on Columbia during the STS-65 mission.

  7. Mission Design Overview for the Phoenix Mars Scout Mission

    NASA Technical Reports Server (NTRS)

    Garcia, Mark D.; Fujii, Kenneth K.

    2007-01-01

    The Phoenix mission "follows the water" by landing in a region where NASA's Mars Odyssey orbiter has discovered evidence of ice-rich soil very near the Martian surface. For three months after landing, the fixed Lander will perform in-situ and remote sensing investigations that will characterize the chemistry of the materials at the local surface, sub-surface, and atmosphere, and will identify potential provenance of key indicator elements of significance to the biological potential of Mars, including potential organics and any accessible water ice. The Lander will employ a robotic arm to dig to the ice layer, and will analyze the acquired samples using a suite of deck-mounted, science instruments. The development of the baseline strategy to achieve the objectives of this mission involves the integration of a variety of elements into a coherent mission plan.

  8. Water vapor and cloud water measurements over Darwin during the STEP 1987 tropical mission

    SciTech Connect

    Kelly, K.K.; Proffitt, M.H. ); Chan, K.R.; Loewenstein, M.; Podolske, J.R. ); Strahan, S.E. ); Wilson, J.C. ); Kley, D. )

    1993-05-20

    The authors report results of total water, and water vapor measurements made in the upper troposphere and stratosphere during the Stratosphere-Troposphere Exchange Project (STEP) Tropical mission over Darwin, Australia. Measurements were made from an ER-2 aircraft by lyman-[alpha] hygrometers. The average lower stratosphere water vapor was 2.4 parts per million by volume (ppmv), at a potential temperature of 375 K. This level is lower than the 3 to 4 ppmv water vapor level typical of the stratosphere.

  9. The eXtra Small Analyzer for Neutrals (XSAN) instrument on-board of the Lunar-Glob lander

    NASA Astrophysics Data System (ADS)

    Wieser, Martin; Barabash, Stas

    A large fraction of up to 20 precent of the solar wind impinging onto the lunar surface is reflected back to space as energetic neutral atoms. The SARA instrument on the Chandrayaan-1 mission provided a comprehensive coverage of the lunar surface of this interaction by mapping it from a 100 - 200 km orbit. The micro-physics of this reflection process is unexplored however. With the eXtra Small Analyzer for Neutrals instrument (XSAN) placed on the Lunar-Glob lander, we will directly investigate the production process of energetic neutral atoms from a vantage point of only meters from the surface for the first time. The XSAN design is based on the Solar Wind Monitor (SWIM) family of instruments originally flown on the Indian Chandrayaan-1 mission and with derivatives built e.g. for ESA's BepiColombo Mission to Mercury or for Phobos-Grunt. XSAN extends the functionality of this instrument family by adding a neutral atom to ion conversion surface in its entrance system. This will make it possible to measure detailed energy spectra and mass composition of the energetic neutral atoms originating from the lunar surface. We present an overview of the XSAN instrument and its science and report on latest developments.

  10. Improved coordinates of features in the vicinity of the Viking lander site on Mars

    NASA Technical Reports Server (NTRS)

    Davies, M. E.; Dole, S. H.

    1980-01-01

    The measurement of longitude of the Viking 1 landing site and the accuracy of the coordinates of features in the area around the landing site are discussed. The longitude must be measured photogrammatically from the small crater, Airy 0, which defines the 0 deg meridian on Mars. The computer program, GIANT, which was used to perform the analytical triangulations, and the photogrammetric computation of the longitude of the Viking 1 lander site are described. Improved coordinates of features in the vicinity of the Viking 1 lander site are presented.

  11. The prime meridian of Mars and the longitudes of the Viking landers

    NASA Technical Reports Server (NTRS)

    Davies, M. E.

    1977-01-01

    A planetwide control net of Mars has been computed by a single large-block analytical triangulation derived from 17,224 measurements of 3,037 control points on 928 Mariner 9 pictures. The computation incorporated the Viking-determined direction of the spin axis and rotation rate of Mars. The angle measured from the vernal equinox to the prime meridian (areocentric right ascension) of Mars was determined to be 148.368 deg + 350.891986 deg (JD - 2433282.5), where JD refers to the Julian date. The prime meridian of Mars passes through the center of the small crater Airy-O. The longitudes of the Viking landers are 47.82 + or - 0.1 deg for Lander 1 and 225.59 + or - 0.1 deg for Lander 2.

  12. MNSM - A Future Mars Network Science Mission

    NASA Astrophysics Data System (ADS)

    Chicarro, A. F.

    2012-04-01

    Following ESA' s successful Mars Express mission, European efforts in Mars Exploration are now taking place within the joint ESA-NASA Mars Exploration Programme, starting in 2016 with the Trace Gases Orbiter (TGO) focusing on atmospheric trace gases and in particular methane, and with the Entry and Descent Module (EDM). In 2018, a joint NASA-ESA rover will perform sample caching as well as geological, geochemical and exobiological measurements of the surface and the subsurface of Mars. A number of missions for 2020 and beyond are currently under study. Among those, a possible candidate is a Mars Network Science Mission (MNSM) of 3-6 surface stations, to investigate the interior of the planet, its rotational parameters and its atmospheric dynamics. These important science goals have not been fully addressed by Mars exploration so far and can only be achieved with simultaneous measurements from a number of landers located on the surface of the planet such as a Mars Network mission. In addition, the geology, mineralogy and astrobiological significance of each landing site would be addressed, as three new locations on Mars would be reached. Such Mars Network Science Mission has been considered a significant priority by the planetary science community worldwide for the past two decades. In fact, a Mars Network mission concept has a long heritage, as it was studied a number of times by ESA, NASA and CNES (e.g., Marsnet, Intermarsnet, Netlander and MarsNEXT mission studies) since 1990. Study work has been renewed in ESA recently with MNSM Science and Engineering Teams being set up to update the scientific objectives of the mission and to evaluate its technical feasibility, respectively. The current mission baseline includes three ESA-led small landers with a robotic arm to be launched with a Soyuz rocket and direct communications to Earth (no need of a dedicated orbiter). However, a larger network could be put in place through international collaboration, as several

  13. Combined Infrared Stereo and Laser Ranging Cloud Measurements from Shuttle Mission STS-85

    NASA Technical Reports Server (NTRS)

    Lancaster, Redgie S.; Spinhirne, James D.; OCStarr, David (Technical Monitor)

    2001-01-01

    Multi-angle remote sensing provides a wealth of information for earth and climate monitoring. And, as technology advances so do the options for developing instrumentation versatile enough to meet the demands associated with these types of measurements. In the current work, the multiangle measurement capability of the Infrared Spectral Imaging Radiometer is demonstrated. This instrument flew as part of mission STS-85 of the space shuttle Columbia in 1997 and was the first earth-observing radiometer to incorporate an uncooled microbolometer array detector as its image sensor. Specifically, a method for computing cloud-top height from the multi-spectral stereo measurements acquired during this flight has been developed and the results demonstrate that a vertical precision of 10.6 km was achieved. Further, the accuracy of these measurements is confirmed by comparison with coincident direct laser ranging measurements from the Shuttle Laser Altimeter. Mission STS-85 was the first space flight to combine laser ranging and thermal IR camera systems for cloud remote sensing.

  14. DopSCAT: A mission concept for simultaneous measurements of marine winds and surface currents

    NASA Astrophysics Data System (ADS)

    Fois, Franco; Hoogeboom, Peter; Le Chevalier, François; Stoffelen, Ad; Mouche, Alexis

    2015-12-01

    A radar scatterometer operates by transmitting a pulse of microwave energy toward the ocean's surface and measuring the normalized (per-unit-surface) radar backscatter coefficient (σ°). The primary application of scatterometry is the measurement of near-surface ocean winds. By combining σ° measurements from different azimuth angles, the 10 m vector wind can be determined through a Geophysical Model Function (GMF), which relates wind and backscatter. This paper proposes a mission concept for the measurement of both oceanic winds and surface currents, which makes full use of earlier C-band radar remote sensing experience. For the determination of ocean currents, in particular, the novel idea of using two chirps of opposite slope is introduced. The fundamental processing steps required to retrieve surface currents are given together with their associated accuracies. A detailed description of the mission proposal and comparisons between real and retrieved surface currents are presented. The proposed ocean Doppler scatterometer can be used to generate global surface ocean current maps with accuracies better than 0.2 m/s at a spatial resolution better than 25 km (i.e., 12.5 km spatial sampling) on a daily basis. These maps will allow gaining some insights on the upper ocean mesoscale dynamics. The work lies at a frontier, given that the present inability to measure ocean currents from space in a consistent and synoptic manner represents one of the greatest weaknesses in ocean remote sensing.

  15. 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.

  16. Measuring Earth's radiation imbalance with RAVAN: A CubeSat mission to measure the driver of global climate change

    NASA Astrophysics Data System (ADS)

    Swartz, W. H.; Dyrud, L. P.; Wiscombe, W. J.; Lorentz, S. R.; Papadakis, S.; Summers, R. A.; Smith, A. W.; Wu, D. L.; Deglau, D. M.; Arnold, S. P.

    2013-12-01

    The Earth radiation imbalance (ERI) is the single most important quantity for predicting the course of climate change over the next century. It is also the single most important metric for any geo-engineering scheme. We review the current scientific understanding of ERI and present a recently funded CubeSat mission, the Radiometer Assessment using Vertically Aligned Nanotubes (RAVAN), that will demonstrate an affordable, accurate radiometer that directly measures Earth-leaving fluxes of total and solar-reflected radiation. Coupled with knowledge of the incoming radiation from the Sun, RAVAN directly gives ERI. The objective of RAVAN is to demonstrate that a compact spaceborne radiometer that is absolutely accurate to NIST-traceable standards can be built for low cost. The key technologies that enable a radiometer with all these attributes are: a gallium fixed-point blackbody as a built-in calibration source and a vertically aligned carbon nanotube (VACNT) absorber. VACNTs are the blackest known substance, making them ideal radiometer absorbers with order-of-magnitude improvements in spectral flatness and stability over the existing art. The Johns Hopkins University Applied Physics Laboratory heritage 3U Multi-Mission Nanosat will host RAVAN, providing the reliability, agility, and resources needed. RAVAN will pave the way for a constellation Earth radiation budget mission that can provide the measurements needed to enable vastly superior predictions of future climate change.

  17. Cost effectiveness as applied to the Viking Lander systems-level thermal development test program

    NASA Technical Reports Server (NTRS)

    Buna, T.; Shupert, T. C.

    1974-01-01

    The economic aspects of thermal testing at the systems-level as applied to the Viking Lander Capsule thermal development program are reviewed. The unique mission profile and pioneering scientific goals of Viking imposed novel requirements on testing, including the development of a simulation technique for the Martian thermal environment. The selected approach included modifications of an existing conventional thermal vacuum facility, and improved test-operational techniques that are applicable to the simulation of the other mission phases as well, thereby contributing significantly to the cost effectiveness of the overall thermal test program.

  18. New Mission to Measure Global Lightning from the International Space Station (ISS)

    NASA Astrophysics Data System (ADS)

    Blakeslee, R. J.; Christian, H. J., Jr.; Mach, D. M.; Buechler, D. E.; Koshak, W. J.; Walker, T. D.; Bateman, M. G.; Stewart, M. F.; O'Brien, S.; Wilson, T. O.; Pavelitz, S. D.; Coker, C.

    2015-12-01

    Over the past 20 years, the NASA Marshall Space Flight Center, the University of Alabama in Huntsville, and their partners developed and demonstrated the effectiveness and value of space-based lightning observations as a remote sensing tool for Earth science research and applications, and, in the process, established a robust global lightning climatology. The observations included measurements from the Lightning Imaging Sensor (LIS) on the Tropical Rainfall Measuring Mission (TRMM) that acquired global observations of total lightning (i.e., intracloud and cloud-to-ground discharges) from November 1997 to April 2015 between 38° N/S latitudes, and its Optical Transient Detector predecessor that acquired observation from May 1995 to April 2000 over 75° N/S latitudes. In February 2016, as an exciting follow-on to these prior missions, a space-qualified LIS built as a flight-spare for TRMM will be delivered to the International Space Station (ISS) for a 2 year or longer mission, flown as a hosted payload on the Department of Defense Space Test Program-Houston 5 (STP-H5) mission. The LIS on ISS will continue observations of the amount, rate, and radiant energy of total lightning over the Earth. More specifically, LIS measures lightning during both day and night, with storm scale resolution (~4 km), millisecond timing, and high, uniform detection efficiency, without any land-ocean bias. Lightning is a direct and most impressive response to intense atmospheric convection. ISS LIS lightning observations will continue to provide important gap-filling inputs to pressing Earth system science issues across a broad range of disciplines. This mission will also extend TRMM time series observations, expand the latitudinal coverage to 54° latitude, provide real-time lightning data to operational users, espically over data sparse oceanic regions, and enable cross-sensor observations and calibrations that includes the new GOES-R Geostationary Lightning Mapper (GLM) and the Meteosat

  19. Austere Human Missions to Mars

    NASA Technical Reports Server (NTRS)

    Price, Hoppy; Hawkins, Alisa; Radcliffe, Torrey

    2009-01-01

    This slide presentation reviews a possible mission architecture for a more austere Mars mission, than the one developed by NASA outlined in the Design Reference Architecture 5 (DRA 5). "Austere" architecture is scaled back from DRA 5 and might offer lower development cost, lower flight cost, and lower development risk. This approach will not meet all the DRA 5 mission requirements. Included in the presentation are the elements of an Austere mission, diagrams of the trans-Mars injection (TMI), cruise, and Mars Orbital Insertion for various phases of the mission, the entry descent landing (EDL) concept. The key features of the Transit Habitat (TransHab), the Earth Departure Stage (EDS), the landers, are reviewed. A chart shows the Mass in tons, of the conceptual types of Mars Landers. The EDL concept, EDL Phase diagrams for the Mars Lander are reviewed. New technologies that would be required are also reviewed. Flight test programs for the various parts of the architecture and a flight schedule are reviewed.

  20. Summary report of mission acceleration measurements for STS-60, SPACEHAB2, launched 11 February 1994

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; Delombard, Richard

    1994-01-01

    The STS-60 mission, which launched on 11 February 1994, carried seven accelerometer systems. This report describes the configuration of each of these systems, where they were located on the Orbiter and the name of a contact person for each system. The Space Acceleration Measurement System (SAMS) was one of the accelerometer systems on-board and this mission marked its eighth successful flight. Acceleration data are provided here for SAMS which flew under an agreement between the NASA Microgravity Science and Applications division and the NASA office of Advanced Concepts and Technology. Acceleration data for the other accelerometer systems are not presented here. SAMS was located in the commercial SPACEHAB laboratory, on its second flight. The SAMS system was configured with three triaxial sensor heads with filter cut-offs of 5, 10, and 50 Hz. The acceleration environment related to an experiment centrifuge, an experiment refrigerator freezer unit, a SAMS sensor head rotation, an Orbiter shudder, and payload deploy activities are discussed. In the Appendices, all of the data from SAMS Head B (10 Hz) are plotted to provide an overview of the environment during the majority of the STS-60 mission. An evaluation form is included at the end of the report to solicit users' comments about the usefulness of this series of reports.

  1. Conceptual design study for the use of COBE rocket engines on the Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    1992-01-01

    The objective of this conceptual design study is to verify that the Cosmic Background Explorer (COBE) Hydrazine Propulsion Subsystem (HPS) Rocket Engine Assembly (REA) will satisfy the Tropical Rainfall Measuring Mission (TRMM) requirements and to develop a preliminary thruster module design using the existing REAs. The performance of the COBE HPS 5 lbf thrusters meet the TRMM mission requirements. The preliminary design consists of a single 5 lbf REA REM which is isolation mounted to a spacecraft interface angle bracket (5 or 10 deg angle). The REM incorporates a catalyst bed heater and sensor assembly, and propellant thermal control is achieved by thermostatically controlled heaters on the thruster valves. A ROM cost of approx. $950 K has been estimated for the phase 2 program to finalize the design, fabricate, and test the hardware using mechanical thermostats for thermal control. In the event that solid state thermostats are used, the cost is estimated to be $160 K higher. A ROM cost is approx. $145 K is estimated to study the effects of using Japanese manufactured hydrazine for the TRMM mission.

  2. Global Precipitation Measurement. Report 2; Benefits of Partnering with GPM Mission

    NASA Technical Reports Server (NTRS)

    Stocker, Erich F.; Smith, Eric A. (Editor); Adams, W. James (Editor); Starr, David OC. (Technical Monitor)

    2002-01-01

    An important goal of the Global Precipitation Measurement (GPM) mission is to maximize participation by non-NASA partners both domestic and international. A consequence of this objective is the provision for NASA to provide sufficient incentives to achieve partner buy-in and commitment to the program. NASA has identified seven specific areas in which substantive incentives will be offered: (1) partners will be offered participation in governance of GPM mission science affairs including definition of data products; (2) partners will be offered use of NASA's TDRSS capability for uplink and downlink of commands and data in regards to partner provided spacecraft; (3) partners will be offered launch support for placing partner provided spacecraft in orbit conditional upon mutually agreeable co-manifest arrangements; (4) partners will be offered direct data access at the NASA-GPM server level rather than through standard data distribution channels; (5) partners will be offered the opportunity to serve as regional data archive and distribution centers for standard GPM data products; and (6) partners will be offered the option to insert their own specialized filtering and extraction software into the GPM data processing stream or to obtain specialized subsets and products over specific areas of interest (7) partners will be offered GPM developed software tools that can be run on their platforms. Each of these incentives, either individually or in combination, represents a significant advantage to partners who may wish to participate in the GPM mission.

  3. Measurement requirements for a Near-Earth Asteroid impact mitigation demonstration mission

    NASA Astrophysics Data System (ADS)

    Wolters, Stephen D.; Ball, Andrew J.; Wells, Nigel; Saunders, Christopher; McBride, Neil

    2011-10-01

    A concept for an Impact Mitigation Preparation Mission, called Don Quijote, is to send two spacecrafts to a Near-Earth Asteroid (NEA): an Orbiter and an Impactor. The Impactor collides with the asteroid while the Orbiter measures the resulting change in the asteroid's orbit, by means of a Radio Science Experiment (RSE) carried out before and after the impact. Three parallel Phase A studies on Don Quijote were carried out for the European Space Agency: the research presented here reflects the outcomes of the study by QinetiQ. We discuss the mission objectives with regard to the prioritisation of payload instruments, with emphasis on the interpretation of the impact. The Radio Science Experiment is described and it is examined how solar radiation pressure may increase the uncertainty in measuring the orbit of the target asteroid. It is determined that to measure the change in orbit accurately a thermal IR spectrometer is mandatory, to measure the Yarkovsky effect. The advantages of having a laser altimeter are discussed. The advantages of a dedicated wide-angle impact camera are discussed and the field-of-view is initially sized through a simple model of the impact.

  4. The Global Precipitation Measurement (GPM) Mission: Overview and U.S. Status

    NASA Technical Reports Server (NTRS)

    Hou, Arthur Y.; Azarbarzin, Ardeshir A.; Kakar, Ramesh K.; Neeck, Steven

    2011-01-01

    The Global Precipitation Measurement (GPM) Mission is an international satellite mission specifically designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors. Building upon the success of the U.S.-Japan Tropical Rainfall Measuring Mission (TRMM), the National Aeronautics and Space Administration (NASA) of the United States and the Japan Aerospace and Exploration Agency (JAXA) will deploy in 2013 a GPM "Core" satellite carrying a KulKa-band Dual-frequency Precipitation Radar (DPR) and a conical-scanning multi-channel (10-183 GHz) GPM Microwave Imager (GMI) to establish a new reference standard for precipitation measurements from space. The combined active/passive sensor measurements will also be used to provide common database for precipitation retrievals from constellation sensors. For global coverage, GPM relies on existing satellite programs and new mission opportunities from a consortium of partners through bilateral agreements with either NASA or JAXA. Each constellation member may have its unique scientific or operational objectives but contributes microwave observations to GPM for the generation and dissemination of unified global precipitation data products. In addition to the DPR and GMI on the Core Observatory, the baseline GPM constellation consists of the following sensors: (1) Special Sensor Microwave Imager/Sounder (SSMIS) instruments on the U.S. Defense Meteorological Satellite Program (DMSP) satellites, (2) the Advanced Microwave Scanning Radiometer- 2 (AMSR-2) on the GCOM-Wl satellite of JAXA, (3) the Multi-Frequency Microwave Scanning Radiometer (MADRAS) and the multi-channel microwave humidity sounder (SAPHIR) on the French-Indian Megha-Tropiques satellite, (4) the Microwave Humidity Sounder (MHS) on the National Oceanic and Atmospheric Administration (NOAA)-19, (5) MHS instruments on MetOp satellites launched by the European Organisation for the Exploitation of Meteorological

  5. The Global Precipitation Measurement (GPM) Mission: Overview and U.S. Science Status

    NASA Astrophysics Data System (ADS)

    Hou, Arthur Y.; Skofronick-Jackson, Gail; Stocker, Erich F.

    2013-04-01

    The Global Precipitation Measurement (GPM) Mission is a satellite mission specifically designed to unify and advance precipitation measurements from a constellation of research and operational microwave sensors provided by a consortium of international partners. NASA and JAXA will deploy a Core Observatory in 2014 to serve as a reference satellite for precipitation measurements by the constellation sensors. The GPM Core Observatory will carry a Ku/Ka-band Dual-frequency Precipitation Radar (DPR) and a conical-scanning multi-channel (10-183 GHz) GPM Microwave Radiometer (GMI). The DPR, the first dual-frequency radar in space, will provide not only measurements of 3-D precipitation structures but also quantitative information on microphysical properties of precipitating particles. The DPR and GMI measurements will together provide a database that relates vertical hydrometeor profiles to multi-frequency microwave radiances over a variety of environmental conditions across the globe. This combined database will serve as a common transfer standard for improving the accuracy and consistency of precipitation retrievals from all constellation radiometers. In addition to the Core Observatory, the GPM constellation consists of (1) Special Sensor Microwave Imager/Sounder (SSMIS) instruments on the U.S. Defense Meteorological Satellite Program (DMSP) satellites, (2) the Advanced Microwave Scanning Radiometer-2 (AMSR-2) on the GCOM-W1 satellite of JAXA, (3) the Multi-Frequency Microwave Scanning Radiometer (MADRAS) and the multi-channel microwave humidity sounder (SAPHIR) on the French-Indian Megha-Tropiques satellite, (4) the Microwave Humidity Sounder (MHS) on the National Oceanic and Atmospheric Administration (NOAA) Polar Orbiting Environmental Satellites (POES), (5) MHS instruments on MetOp satellites launched by the European Organisation for the Exploitation of Meteorological Satellites (EUMETSAT), (6) the Advanced Technology Microwave Sounder (ATMS) on the National Polar

  6. Pulsed Lidar for Measurement of C02 Concentrations for the ASCENDS Mission - Update

    NASA Technical Reports Server (NTRS)

    Abshire, James; Riris, Haris; Allan, Graham; Sun, Xiaoli; Mao, Jianping; Weaver, Clark; Yu, Anthony; Chen, Jeffrey; Rodriquez, Michael; Kawa, S. Randy

    2011-01-01

    We have been developing a laser-based sounding technique for the remote measurement of the tropospheric CO2 concentrations from orbit for NASA is ASCENDS mission. The mission's goals are to provide measurements of tropospheric CO2 abundance with global-coverage, a few hundred km spatial and monthly temporal resolution. These are needed to better understand CO2 fluxes and the processes that regulate CO2 storage by the land and oceans. For the lIP, we are developing and demonstrating the lidar techniques and key lidar technology that will permit measurements of the CO2 column abundance in the lower troposphere from aircraft. Our final goal is to demonstrate the key capabilities needed for a space lidar and mission approach for the ASCENDS mission. We use a pulsed lidar technique, which is much less sensitive to errors from cloud and atmospheric scattering and to noise from solar background. It allows continuous measurements of CO2 mixing ratio in the lower troposphere during day and night. Our approach uses the 1570nm CO2 band and a two-wavelength laser absorption spectrometer, which continuously measures at nadir from a circular polar orbit. It directs the narrow co-aligned laser beams from the instrument's lasers toward nadir, and measures the energy of the laser echoes reflected from land and water surfaces. It uses a pair of tunable laser transmitters, which allowing measurement of the extinction from a single selected CO2 absorption line in the 1570 nm band and from a line pair in the Oxygen A-band near 765 nm. These regions have temperature insensitive absorption lines are free from interference from other gases. The lasers pulse at 10KHz, use tunable diode seed lasers followed by laser amplifiers, and have MHz spectral widths. During the measurement the lasers are stepped across the selected lines at a kHz rate. The receiver uses a 1-m class telescope and photon sensitive detectors and measures the background light and energies of the laser echoes from the

  7. TRMM ground truth in a monsoon environment - Darwin, Australia. [Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    Keenan, T. D.; Holland, G. J.; Manton, M. J.; Simpson, J.

    1988-01-01

    A ground truth station for the Tropical Rainfall Measuring Mission (TRMM) is described. The station is situated in Darwin, Australia in a monsoon environment typical for Southeast Asia. The climatological features of the site, and the Darwin observational program are examined. The instruments and operations at the station are discussed, including a Doppler radar making full upper tropospheric soundings every 12 hrs and wind soundings every 6 hrs, and a mesoscale raingauge and surface observing network operating continuously through the summer monsoon seasons. The spatial and temporal characteristics of rainfall in the area and an outline of the research objectives of the program are presented.

  8. Oceanographic measurement capabilities of the NASA P-3 aircraft. [ERS-1 mission

    NASA Technical Reports Server (NTRS)

    Mollo-Christensen, Erik; Jackson, F. C.; Walsh, E. J.; Hoge, F.

    1986-01-01

    Instrumentation on NASA P3 aircraft available to provide ground truth for ERS-1 is described. The wave sensors include the 36 GHz Surface Contour Radar (SCR), the Ku-band Radar Ocean Wave Spectrometer (ROWS), and the Airborne Oceanographic Lidar. The other sensors include a C-band scatterometer, video camera, radiation thermometer, and AXRTs. The SCR and ROWS directional spectrum measurements are discussed. When planning for an underflight mission, the limited endurance of the aircraft (6 hr) and flight cost (2.7 K$/hr) must be considered. The advantage of the redundancy afforded by the several wave instruments is another important consideration.

  9. Continuous metabolic and cardiovascular measurements on a monkey subject during a simulated 6-day Spacelab mission

    NASA Technical Reports Server (NTRS)

    Pace, N.; Rahlmann, D. F.; Mains, R. C.; Kodama, A. M.; Mccutcheon, E. P.

    1978-01-01

    An adult male pig-tailed monkey (Macaca nemestrina) with surgically implanted biotelemetry unit was inserted into a fiberglass pod system which was installed in a Spacelab mock-up to simulate a 6-day mission during which extensive physiological measurements were obtained. The purpose of the pod was to make possible the study of respiratory gas exchange. Body temperature and selected cardiovascular parameters were recorded continuously for 2.6 days prior to 'launch', 6.3 days during 'flight', and 1.8 days after 'landing'. The results are surveyed, and it is concluded that it is feasible to perform sound physiological experiments on nonhuman primates in the Spacelab environment

  10. The Landers earthquake; preliminary instrumental results

    USGS Publications Warehouse

    Jones, L.; Mori, J.; Hauksson, E.

    1992-01-01

    Early on the morning of June 28, 1992, millions of people in southern California were awakened by the largest earthquake to occur in the western United States in the past 40 yrs. At 4:58 a.m PDT (local time), faulting associated with the magnitude 7.3 earthquake broke through to earth's surface near the town of Landers, California. the surface rupture then propagated 70km (45 mi) to the north and northwest along a band of faults passing through the middle of the Mojave Desert. Fortunately, the strongest shaking occurred in uninhabited regions of the Mojave Desert. Still one child was killed in Yucca Valley, and about 400 people were injured in the surrounding area. the desert communities of Landers, Yucca Valley, and Joshua Tree in San Bernardino Country suffered considerable damage to buildings and roads. Damage to water and power lines caused problems in many areas. 

  11. Analysis of condensates formed at the Viking 2 lander site - The first winter

    NASA Technical Reports Server (NTRS)

    Wall, S. D.

    1981-01-01

    Relative surface albedo, spectral reflectance estimates and a limited photometric function are reduced from Viking 2 lander data obtained during a 249 Mars day period, in the lander's first year, when a light ground covering appeared on the surface. During the deposition, surface broadband albedo more than doubled and blue reflectance increased by a factor of 4.0. Comparison of lander data with earlier laboratory measurements of CO2 and H2O frosts and snows shows that reflectance estimates do not resemble either of those solids. The condensate reflectance resembles that of the surface after the covering disappeared. The covering may have been colored by dust which fell before it, by dust mixed with it, or by dust on top of it; but the data strongly support a mixture of dust with H2O and CO2 solids. The covering thickness is estimated to be between 0.5 and a few millimeters.

  12. Prospects of passive radio detection of a subsurface ocean on Europa with a lander

    NASA Astrophysics Data System (ADS)

    Romero-Wolf, Andrew; Schroeder, Dustin M.; Ries, Paul; Bills, Bruce G.; Naudet, Charles; Scott, Bryan R.; Treuhaft, Robert; Vance, Steve

    2016-09-01

    We estimate the sensitivity of a lander-based instrument for the passive radio detection of a subsurface ocean beneath the ice shell of Europa, expected to be between 3 km and 30 km thick, using Jupiter's decametric radiation. A passive technique was previously studied for an orbiter. Using passive detection in a lander platform provides a point measurement with significant improvements due to largely reduced losses from surface roughness effects, longer integration times, and diminished dispersion due to ionospheric effects allowing operation at lower frequencies and a wider band. A passive sounder on-board a lander provides a low resource instrument sensitive to subsurface ocean at Europa up to depths of 6.9 km for high loss ice (16 dB/km two-way attenuation rate) and 69 km for pure ice (1.6 dB/km).

  13. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, the fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander is lowered toward the rocket waiting below. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern- most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  14. The fairing for the Delta II rocket carrying the Mars Polar Lander arrives on Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1998-01-01

    On Pad 17B, Cape Canaveral Air Station, the fairing for the upper stages of the Delta II rocket carrying the Mars Polar Lander is prepared for lowering toward the rocket below. The lander, which will be launched on Jan. 3, 1999, is a solar-powered spacecraft designed to touch down on the Martian surface near the northern- most boundary of the south pole in order to study the water cycle there. The lander also will help scientists learn more about climate change and current resources on Mars, studying such things as frost, dust, water vapor and condensates in the Martian atmosphere. It is the second spacecraft to be launched in a pair of Mars '98 missions. The first is the Mars Climate Orbiter, to be launched aboard a Delta II rocket from Launch Complex 17A in December 1998.

  15. From mission to measures: performance measure development for a Teen Pregnancy Prevention Program.

    PubMed

    Farb, Amy Feldman; Burrus, Barri; Wallace, Ina F; Wilson, Ellen K; Peele, John E

    2014-03-01

    The Office of Adolescent Health (OAH) sought to create a comprehensive set of performance measures to capture the performance of the Teen Pregnancy Prevention (TPP) program. This performance measurement system needed to provide measures that could be used internally (by both OAH and the TPP grantees) for management and program improvement as well as externally to communicate the program's progress to other interested stakeholders and Congress. This article describes the selected measures and outlines the considerations behind the TPP measurement development process. Issues faced, challenges encountered, and lessons learned have broad applicability for other federal agencies and, specifically, for TPP programs interested in assessing their own performance and progress.

  16. Project UM-HAUL (UnManned Heavy pAyload Unloader and Lander): The design of a reusable lunar lander with an independent cargo unloader

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Project UM-Haul is the preliminary design of a reusable lunar transportation vehicle that travels between a lunar parking orbit and the lunar surface. This vehicle is an indispensible link in the overall task of establishing a lunar base as defined by the NASA Space Exploration Initiative. The response to this need consists of two independent vehicles: a lander and an unloader. The system can navigate and unload itself with a minimum amount of human intervention. The design addresses structural analysis, propulsion, power, controls, communications, payload handling and orbital operations. The Lander has the capacity to decend from low lunar orbit (LLO) to the lunar surface carrying a 7000 kg payload, plus the unloader, plus propellant for ascent to LLO. The Lander employs the Unloader by way of a motorized ramp. The Unloader is a terrain vehicle capable of carrying cargoes of 8,500 kg mass and employs a lift system to lower payloads to the ground. The system can perform ten missions before requiring major servicing.

  17. Mars Polar Lander Site Compared With Washington, D.C.

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This figure compares five representative views of the Mars Polar Lander primary ellipse near 76oS, 195oW, with a similar-sized view of the U.S. capital for scale. Each box is approximately 1.2 km (0.75 mi) on a side. The brightness variations from one box to another among the Mars images reflects different amounts of frost cover, and possibly the differing compositions of frost (i.e., carbon dioxide vs. water ice). The brightness also depends upon surface texture both above and below the scale of these images (about 5.5 meters--18 feet--per pixel). These pictures show the range of surface texture and morphology that is found within the landing ellipse. Mounds and valleys that range from a few meters to as much as one hundred meters (328 ft) across--with relief of a few meters--dominate the landing site. All of the frost seen here is expected to be gone by the time the Mars Polar Lander arrives in December 1999. The Mars images are illuminated from the lower right. The view of Washington D.C. shows the Capitol Building at the center right and the National Air and Space Museum at center left (immediately below the grassy rectangles of the Mall).

    Malin Space Science Systems and the California Institute of Technology built the MOC using spare hardware from the Mars Observer mission. MSSS operates the camera from its facilities in San Diego, CA. The Jet Propulsion Laboratory's Mars Surveyor Operations Project operates the Mars Global Surveyor spacecraft with its industrial partner, Lockheed Martin Astronautics, from facilities in Pasadena, CA and Denver, CO.

  18. Lunar PanCam: Adapting ExoMars PanCam for the ESA Lunar Lander

    NASA Astrophysics Data System (ADS)

    Coates, A. J.; Griffiths, A. D.; Leff, C. E.; Schmitz, N.; Barnes, D. P.; Josset, J.-L.; Hancock, B. K.; Cousins, C. R.; Jaumann, R.; Crawford, I. A.; Paar, G.; Bauer, A.; the PanCam Team

    2012-12-01

    A scientific camera system would provide valuable geological context from the surface for lunar lander missions. Here, we describe the PanCam instrument from the ESA ExoMars rover and its possible adaptation for the proposed ESA lunar lander. The scientific objectives of the ESA ExoMars rover are designed to answer several key questions in the search for life on Mars. The ExoMars PanCam instrument will set the geological and morphological context for that mission. We describe the PanCam scientific objectives in geology, and atmospheric science, and 3D vision objectives. We also describe the design of PanCam, which includes a stereo pair of Wide Angle Cameras (WACs), each of which has a filter wheel, and a High Resolution Camera for close up investigations. The cameras are housed in an optical bench (OB) and electrical interface is provided via the PanCam Interface Unit (PIU). Additional hardware items include a PanCam Calibration Target (PCT). We also briefly discuss some PanCam testing during field trials. In addition, we examine how such a 'Lunar PanCam' could be adapted for use on the Lunar surface on the proposed ESA lunar lander.

  19. An Altair Overview: Designing a Lunar Lander for 21st Century Human Space Exploration

    NASA Technical Reports Server (NTRS)

    Brown, Kendall K.; Connolly, John F.

    2012-01-01

    Altair, the lunar lander element of NASA's Constellation program, was conducted in a different design environment than many other NASA projects of similar scope. Because of this relatively unique approach, there are a number of significant success stories that should be considered during the development of any future lunar landers or human spacecraft. This paper is divided into two separate themes; the first is the approach used during the conceptual design studies, including the systematic analysis cycles and the decision making process associated with each: and the second is a summary of the resulting lessons learned that were compiled after looking back at the lifetime of the Project. Altair was terminated before entering Phase B of its design, and was often criticized for being a very heavy and very large vehicle. While there was specific rationale for all of the decisions that led up to that configuration, future design cycles were specifically planned to re-address the mass challenge. Had the project continued, the deliberate, stepwise design process would have converged on an optimized lander design that balanced mass, risk, cost and capabilities. Some of the specific items that will be addressed in this paper include project development strategy, organizational approach and team dynamics, risk-informed design process, mission architecture constraints, mission key driving requirements, model-based systems engineering process, configuration studies, contingency considerations, subsystem overviews and key trade studies. The paper will conclude with a summary of the lessons identified during the Altair project and make suggestions for application to future studies.

  20. 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.

  1. Winter frost at Viking Lander 2 site

    NASA Astrophysics Data System (ADS)

    Svitek, T.; Murray, B.

    1990-02-01

    This paper presents quantitative evidence for cold trapping (frost redeposition) at the Viking Lander 2 site. This evidence consists of the frost surface coverage and color transition, the timing of this transition, and the limited vertical mixing and horizontal water transport. It is argued that cold trapping must be a general property of seasonal frost and, therefore, must be considered in order to understand the evolution of the surface environment of Mars.

  2. Viking lander design and systems integration

    NASA Technical Reports Server (NTRS)

    Goodlette, J.

    1974-01-01

    Malfunction protection requires redundancy planning and mechanization in Viking lander design and systems integration in order to maximize the chance of getting the data back through the Orbiter. Various subsystems are discussed that protect the downlink to man on the ground in the framework of systems integration and insure the basic objectives of Viking: to land on a planet and to acquire data from its surface.

  3. Winter frost at Viking Lander 2 site

    NASA Technical Reports Server (NTRS)

    Svitek, Thomas; Murray, Bruce

    1990-01-01

    This paper presents quantitative evidence for cold trapping (frost redeposition) at the Viking Lander 2 site. This evidence consists of the frost surface coverage and color transition, the timing of this transition, and the limited vertical mixing and horizontal water transport. It is argued that cold trapping must be a general property of seasonal frost and, therefore, must be considered in order to understand the evolution of the surface environment of Mars.

  4. High resolution Microwave Spectrometer Sounder (HIMSS) instrument program. Appendix: TRMM study (an instrument for NASA's tropical rainfall measuring mission)

    NASA Technical Reports Server (NTRS)

    Lobl, E. (Editor)

    1991-01-01

    The TRMM (Tropical Rain Measuring Mission) Study shows the feasibility of a conically scanned, total power radiometer. The heritage of the TRMM radiometer is the Special Sensor Microwave/Imager (SSM/I) flying for the Air Force DMSP.

  5. Japanese Global Precipitation Measurement (GPM) mission status and application of satellite-based global rainfall map

    NASA Astrophysics Data System (ADS)

    Kachi, Misako; Shimizu, Shuji; Kubota, Takuji; Yoshida, Naofumi; Oki, Riko; Kojima, Masahiro; Iguchi, Toshio; Nakamura, Kenji

    2010-05-01

    As accuracy of satellite precipitation estimates improves and observation frequency increases, application of those data to societal benefit areas, such as weather forecasts and flood predictions, is expected, in addition to research of precipitation climatology to analyze precipitation systems. There is, however, limitation on single satellite observation in coverage and frequency. Currently, the Global Precipitation Measurement (GPM) mission is scheduled under international collaboration to fulfill various user requirements that cannot be achieved by the single satellite, like the Tropical Rainfall Measurement Mission (TRMM). The GPM mission is an international mission to achieve high-accurate and high-frequent rainfall observation over a global area. GPM is composed of a TRMM-like non-sun-synchronous orbit satellite (GPM core satellite) and constellation of satellites carrying microwave radiometer instruments. The GPM core satellite carries the Dual-frequency Precipitation Radar (DPR), which is being developed by the Japan Aerospace Exploration Agency (JAXA) and the National Institute of Information and Communications Technology (NICT), and microwave radiometer provided by the National Aeronautics and Space Administration (NASA). Development of DPR instrument is in good progress for scheduled launch in 2013, and DPR Critical Design Review has completed in July - September 2009. Constellation satellites, which carry a microwave imager and/or sounder, are planned to be launched around 2013 by each partner agency for its own purpose, and will contribute to extending coverage and increasing frequency. JAXA's future mission, the Global Change Observation Mission (GCOM) - Water (GCOM-W) satellite will be one of constellation satellites. The first generation of GCOM-W satellite is scheduled to be launched in 2011, and it carries the Advanced Microwave Scanning Radiometer 2 (AMSR2), which is being developed based on the experience of the AMSR-E on EOS Aqua satellite

  6. The Mars Environmental Compatibility Assessment (MECA) Wet Chemistry Experiment on the Mars 2001 Lander

    NASA Technical Reports Server (NTRS)

    Grannan, S. M.; Meloy, T. P.; Hecht, H.; Anderson, M. S.; Buehler, M.; Frant, M.; Kounaves, S. P.; Manatt, K. S.; Pike, W. T.; Schubert, W.

    1999-01-01

    The Mars Environmental Compatibility Assessment (MECA) is an instrument suite that will fly on the Mars Surveyor 2001 Lander Spacecraft. MECA is sponsored by the Human Exploration and Development of Space (HEDS) program and will evaluate potential hazards that the dust and soil of Mars might present to astronauts and their equipment on a future human mission to Mars. Four elements constitute the integrated MECA payload: a microscopy station, patch plates, an electrometer, and the wet chemistry experiment (WCE). The WCE is the first application of electrochemical sensors to study soil chemistry on another planetary body, in addition to being the first measurement of soil/water solution properties on Mars. The chemical composition and properties of the watersoluble materials present in the Martian soil are of considerable interest to the planetary science community because characteristic salts are formed by the water-based weathering of rocks, the action of volcanic gases, and biological activity. Thus the characterization of water-soluble soil materials on Mars can provide information on the geochemical history of the planet surface. Additional information is contained in the original extended abstract.

  7. Lunar Infrared Spectrometer to Characterize the Hydration of Regolith in the Vicinity of a Lander

    NASA Astrophysics Data System (ADS)

    Ivanov, Andrey; Fedorova, Anna; Korablev, Oleg; Mantsevich, Sergey; Stepanov, Alexander; Kalinnikov, Yury

    Lunar Infrared Spectrometer (LIS) is an experiment onboard Luna-Globe (Luna 25) and Luna-Resurce (Luna 27) Russian surface missions. It is a pencil-beam spectrometer to be pointed by a robotic arm of the landing module, and is intended for study of the lunar surface composition in the vicinity of the lander. The instrument’s field of view (FOV) of 1(°) is co-aligned with the FOV (45(°) ) of a stereo TV camera. The spectrometer will provide measurements of selected surface areas in the spectral range of 1.15-3.3 mum. The spectral selection is provided by acousto-optic tunable filter (AOTF), which scans the spectral range sequentially. Electrical command of the AOTF allows selecting the spectral sampling, and permits a random access if needed. The spectral resolution is better than 25 cm (-1) . The instrument’s mass is 1.3 kg. The primary goal of the experiment is to detect the regolith hydration at 3mum, identifying its form from the shape of the spectrum, and to follow its changes during the day/shadow pattern. Also, LIS will allow to study the mineralogical composition from mineral signatures within the spectral range, and will serve for selection of samples to be analyzed by other instruments.

  8. Radiator Study for Stationary Lunar Landers

    NASA Technical Reports Server (NTRS)

    OConnor, Brian; Abel, Elisabeth

    2010-01-01

    This paper provides an overview of a study to identify, select and evaluate potential heat rejection radiators for application to small, low power, stationary lunar landers. While this study supported risk mitigation activities related to the International Lunar Network project, the radiator concepts and performance assessments are applicable to a wide range of lunar lander applications. The radiator concepts identified and evaluated in this study were aimed at providing reliable heat rejection for landers that might be subjected to hot lunar noon conditions at the equator. As a part of the study, a literature search of lunar radiators was performed from which many radiator designs were developed. These designs were compared in a trade study and two of the most promising were used to develop six concepts. These six radiator concepts went through a more detailed thermal analysis using Thermal Desktop. The analysis considered heat rejection capability, and sensitivity to many factors such as dust deposition, latitude, life, and topographical features like landing on a hill, on a rock, or in a hole/crater. From the result of the analysis, two radiator concepts were selected for recommendation: a flat horizontal plate with a dust cover and a stacked vertical radiator with parabolic reflectors and a one degree tilting mechanism.

  9. Advances in Understanding Global Water Cycle with Advent of Global Precipitation Measurement (GPM) Mission

    NASA Technical Reports Server (NTRS)

    Smith, Eric A.; Starr, David (Technical Monitor)

    2002-01-01

    Within this decade the internationally organized Global Precipitation Measurement (GPM) Mission will take an important step in creating a global precipitation observing system from space. One perspective for understanding the nature of GPM is that it will be a hierarchical system of datastreams beginning with very high caliber combined dual frequency radar/passive microwave (PMW) rain-radiometer retrievals, to high caliber PMW rain-radiometer only retrievals, and then on to blends of the former datastreams with additional lower-caliber PMW-based and IR-based rain retrievals. Within the context of the now emerging global water & energy cycle (GWEC) programs of a number of research agencies throughout the world, GPM serves as a centerpiece space mission for improving our understanding of the global water cycle from a global measurement perspective. One of the salient problems within our current understanding of the global water and energy cycle is determining whether a change in the rate of the water cycle is accompanying changes in climate, e.g., climate warming. As there are a number of ways in which to define a rate-change of the global water cycle, it is not entirely clear as to what constitutes such a determination. This paper presents an overview of the GPM Mission and how its observations can be used within the framework of the oceanic and continental water budget equations to determine whether a given perturbation in precipitation is indicative of an actual rate change in the global water cycle, consistent with required responses in water storage and/or water flux transport processes, or whether it is the natural variability of a fixed rate cycle.

  10. Validation for the Tropical Rainfall Measuring Mission: Lessons Learned and Future Plans

    NASA Astrophysics Data System (ADS)

    Wolff, D. B.; Amitai, E.; Marks, D. A.; Silberstein, D.; Lawrence, R. A.

    2005-05-01

    The Tropical Rainfall Measuring Mission (TRMM) was launched in November 1997 and was a highly regarded and successful mission. A major component of the TRMM program was its Ground Validation (GV) program. Through dedicated research and hard work by many groups, both the GV and satellite-retrieved rain estimates have shown a convergence at key GV sites, lending credibility to the global TRMM estimates. To be sure, there are some regional differences between the various satellite estimates themselves which still need to be addressed; however, it can be said with some certainty that TRMM has provided a high-quality, long-term climatological data set for researchers that provides errors on the order of 10-20%, rather than pre-TRMM-era error estimates on the order of 50-10%. The TRMM GV program's main operational task was to provide rainfall products for four sites: Darwin, Australia; Houston, Texas; Kwajalein, Republic of the Marshall Islands; and, Melbourne, Florida. A comparison between TRMM GV (Version 5) and satellite (Version 6) rain intensity estimates is presented. The gridded satellite product (3G-68) will be compared to GV Level II rain-intensity and -type maps. The 3G-68 product represents a 0.5 deg x 0.5 deg data grid providing estimates of rain intensities from the TRMM Precipitation Radar, Microwave Imager and Combined algorithms. The comparisons will be classified according to geographical type (land, coast or ocean). The convergence of the GV and satellite estimates bodes well for expectations for the proposed Global Precipitation Measurement (GPM) program, but it is now well understood that providing uncertainties of the estimates is perhaps more important than convergence on its own. Further, while TRMM originally focused on monthly and climatological validation, future precipitation missions should concentrate on instantaneous validation in order to avoid inevitable and large sampling errors.

  11. Trajectory Design for MoonRise: A Proposed Lunar South Pole-Aitken Basin Sample Return Mission

    NASA Technical Reports Server (NTRS)

    Parker, Jeffrey S.; McElrath, Timothy P.; Anderson, Rodney L.; Sweetser, Theodore H.

    2013-01-01

    This paper presents the mission design for the proposed MoonRise New Frontiers mission: a lunar far side lander and return vehicle, with an accompanying communication satellite. Both vehicles are launched together, but fly separate low-energy transfers to the Moon. The communication satellite enters lunar orbit immediately upon arrival at the Moon, whereas the lander enters a staging orbit about the lunar Lagrange points. The lander descends and touches down on the surface 17 days after the communication satellite enters orbit. The lander remains on the surface for nearly two weeks before lifting off and returning to Earth via a low-energy return.

  12. The Boeing Delta II rocket with Mars Polar Lander aboard lifts off at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Looking like a Roman candle, the exhaust from the Boeing Delta II rocket with the Mars Polar Lander aboard lights up the clouds as it hurtles skyward. The rocket was launched at 3:21:10 p.m. EST from Launch Complex 17B, Cape Canaveral Air Station. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south polar cap, which consists of carbon dioxide ice. The lander will study the polar water cycle, frosts, water vapor, condensates and dust in the Martian atmosphere. It is equipped with a robotic arm to dig beneath the layered terrain. In addition, Deep Space 2 microprobes, developed by NASA's New Millennium Program, are installed on the lander's cruise stage. After crashing into the planet's surface, they will conduct two days of soil and water experiments up to 1 meter (3 feet) below the Martian surface, testing new technologies for future planetary descent probes. The lander is the second spacecraft to be launched in a pair of Mars Surveyor '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  13. The Boeing Delta II rocket with Mars Polar Lander aboard lifts off at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Silhouetted against the gray sky, a Boeing Delta II expendable launch vehicle with NASA's Mars Polar Lander lifts off from Launch Complex 17B, Cape Canaveral Air Station, at 3:21:10 p.m. EST. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south polar cap, which consists of carbon dioxide ice. The lander will study the polar water cycle, frosts, water vapor, condensates and dust in the Martian atmosphere. It is equipped with a robotic arm to dig beneath the layered terrain at the polar cap. In addition, Deep Space 2 microprobes, developed by NASA's New Millennium Program, are installed on the lander's cruise stage. After crashing into the planet's surface, they will conduct two days of soil and water experiments up to 1 meter (3 feet) below the Martian surface, testing new technologies for future planetary descent probes. The lander is the second spacecraft to be launched in a pair of Mars Surveyor '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  14. The Boeing Delta II rocket with Mars Polar Lander aboard lifts off at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Amid clouds of exhaust, a Boeing Delta II expendable launch vehicle with NASA's Mars Polar Lander clears Launch Complex 17B, Cape Canaveral Air Station, after launch at 3:21:10 p.m. EST. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south polar cap, which consists of carbon dioxide ice. The lander will study the polar water cycle, frosts, water vapor, condensates and dust in the Martian atmosphere. It is equipped with a robotic arm to dig beneath the layered terrain at the polar cap. In addition, Deep Space 2 microprobes, developed by NASA's New Millennium Program, are installed on the lander's cruise stage. After crashing into the planet's surface, they will conduct two days of soil and water experiments up to 1 meter (3 feet) below the Martian surface, testing new technologies for future planetary descent probes. The lander is the second spacecraft to be launched in a pair of Mars Surveyor '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  15. The Boeing Delta II rocket with Mars Polar Lander aboard lifts off at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Amid clouds of exhaust and into a gray-clouded sky , a Boeing Delta II expendable launch vehicle lifts off with NASA's Mars Polar Lander at 3:21:10 p.m. EST from Launch Complex 17B, Cape Canaveral Air Station. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern- most boundary of the south polar cap, which consists of carbon dioxide ice. The lander will study the polar water cycle, frosts, water vapor, condensates and dust in the Martian atmosphere. It is equipped with a robotic arm to dig beneath the layered terrain at the polar cap. In addition, Deep Space 2 microprobes, developed by NASA's New Millennium Program, are installed on the lander's cruise stage. After crashing into the planet's surface, they will conduct two days of soil and water experiments up to 1 meter (3 feet) below the Martian surface, testing new technologies for future planetary descent probes. The lander is the second spacecraft to be launched in a pair of Mars Surveyor '98 missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  16. The Boeing Delta II rocket with Mars Polar Lander aboard lifts off at Pad 17B, CCAS

    NASA Technical Reports Server (NTRS)

    1999-01-01

    A Boeing Delta II expendable launch vehicle lifts off with NASA's Mars Polar Lander into a cloud-covered sky at 3:21:10 p.m. EST from Launch Complex 17B, Cape Canaveral Air Station. The lander is a solar-powered spacecraft designed to touch down on the Martian surface near the northern-most boundary of the south polar cap, which consists of carbon dioxide ice. The lander will study the polar water cycle, frosts, water vapor, condensates and dust in the Martian atmosphere. It is equipped with a robotic arm to dig beneath the layered terrain at the polar cap. In addition, Deep Space 2 microprobes, developed by NASA's New Millennium Program, are installed on the lander's cruise stage. After crashing into the planet's surface, they will conduct two days of soil and water experiments up to 1 meter (3 feet) below the Martian surface, testing new technologies for future planetary descent probes. The lander is the second spacecraft to be launched in a pair of Mars Surveyor '98missions. The first is the Mars Climate Orbiter, which was launched aboard a Delta II rocket from Launch Complex 17A on Dec. 11, 1998.

  17. Atmospheric Airborne Pressure Measurements Using the Oxygen A Band for the ASCENDS Mission

    NASA Astrophysics Data System (ADS)

    Rodriguez, M.; Riris, H.; Abshire, J. B.; Allan, G. R.; Stephen, M.; Hasselbrack, W.; Mao, J.

    2012-12-01

    We report on airborne atmospheric pressure measurements using fiber-based laser technology and the oxygen A-band at 765 nm. Remote atmospheric temperature and pressure measurements are needed for NASA's Active Sensing of CO2 Emissions Over Nights, Days, and Seasons (ASCENDS) mission. ASCENDS will measure atmospheric CO2 dry mixing ratios on a global scale. Remote atmospheric pressure measurements are necessary to normalize ASCENDS CO2 measurements. Our work, funded by the ESTO IIP program, uses erbium doped fiber optic amplifiers and non-linear optics technology to tune laser radiation over the Oxygen A-band between 764.5 nm and 765 nm. Surface reflections are fiber-coupled from a receiver telescope to photon counting detectors. Our pulsed, time gated approach resolves ground reflections from cloud returns. This system successfully recorded O2 absorption spectra during two airborne campaigns aboard a NASA DC-8. Airborne data has been analyzed and fitted to HITRAN reference spectra based upon aircraft meteorological data. Our algorithm linearly scales the HITRAN reference until measurement errors are minimized. Atmospheric pressure changes are estimated by comparing the differential optical depth of the optimum scaled HITRAN spectra to the differential optical depth of the nominal HITRAN spectra. On flights over gradually sloping terrain, these results compare favorably with ground-based observations and predictions from computer models. Measurement uncertainty is commensurate with photon counting noise. We plan to reduce measurement uncertainty in future campaigns by improving transmitter pulse energy and increasing wavelength sweep frequency.

  18. NEEMO 14: Evaluation of Human Performance for Rover, Cargo Lander, Crew Lander, and Exploration Tasks in Simulated Partial Gravity

    NASA Technical Reports Server (NTRS)

    Chappell, Steven P.; Abercromby, Andrew F.; Gernhardt, Michael L.

    2011-01-01

    The ultimate success of future human space exploration missions is dependent on the ability to perform extravehicular activity (EVA) tasks effectively, efficiently, and safely, whether those tasks represent a nominal mode of operation or a contingency capability. To optimize EVA systems for the best human performance, it is critical to study the effects of varying key factors such as suit center of gravity (CG), suit mass, and gravity level. During the 2-week NASA Extreme Environment Mission Operations (NEEMO) 14 mission, four crewmembers performed a series of EVA tasks under different simulated EVA suit configurations and used full-scale mockups of a Space Exploration Vehicle (SEV) rover and lander. NEEMO is an underwater spaceflight analog that allows a true mission-like operational environment and uses buoyancy effects and added weight to simulate different gravity levels. Quantitative and qualitative data collected during NEEMO 14, as well as from spacesuit tests in parabolic flight and with overhead suspension, are being used to directly inform ongoing hardware and operations concept development of the SEV, exploration EVA systems, and future EVA suits. OBJECTIVE: To compare human performance across different weight and CG configurations. METHODS: Four subjects were weighed out to simulate reduced gravity and wore either a specially designed rig to allow adjustment of CG or a PLSS mockup. Subjects completed tasks including level ambulation, incline/decline ambulation, standing from the kneeling and prone position, picking up objects, shoveling, ladder climbing, incapacitated crewmember handling, and small and large payload transfer. Subjective compensation, exertion, task acceptability, and duration data as well as photo and video were collected. RESULTS: There appear to be interactions between CG, weight, and task. CGs nearest the subject s natural CG are the most predictable in terms of acceptable performance across tasks. Future research should focus on

  19. The RAVAN CubeSat mission: Progress toward a new measurement of Earth outgoing radiation

    NASA Astrophysics Data System (ADS)

    Swartz, B. H.; Dyrud, L. P.; Lorentz, S. R.; Wu, D. L.; Wiscombe, W. J.; Papadakis, S.; Huang, P. M.; Smith, A.; Deglau, D.

    2014-12-01

    The Earth radiation imbalance (ERI) is the single most important quantity for predicting the course of climate change over the next century. The Radiometer Assessment using Vertically Aligned Nanotubes (RAVAN) CubeSat mission, funded by NASA's Earth Science Technology Office, will demonstrate an affordable, accurate radiometer that directly measures Earth-leaving fluxes of total and solar-reflected radiation. The objective of RAVAN is to demonstrate that a compact spaceborne radiometer that is absolutely accurate to NIST-traceable standards can be built for low cost. The key technologies that enable a radiometer with all these attributes are: a vertically aligned carbon nanotube (VACNT) absorber and a gallium fixed-point blackbody as a built-in calibration source. VACNTs are exceedingly black and spectrally flat, making them ideal radiometer absorbers. We present results from the fabrication and calibration of the RAVAN radiometer and plans for CubeSat hosting and launch. RAVAN will help enable the development of a constellation Earth radiation budget mission that can provide the measurements needed for superior predictions of future climate change.

  20. Conceptual definition of a 50-100 kWe NEP system for planetary science missions

    NASA Technical Reports Server (NTRS)

    Friedlander, Alan

    1993-01-01

    The Phase 1 objective of this project is to assess the applicability of a common Nuclear Electric Propulsion (NEP) flight system of the 50-100 kWe power class to meet the advanced transportation requirements of a suite of planetary science (robotic) missions, accounting for differences in mission-specific payloads and delivery requirements. The candidate missions are as follows: (1) Comet Nucleus Sample Return; (2) Multiple Mainbelt Asteroid Rendezvous; (3) Jupiter Grand Tour (Galilean satellites and magnetosphere); (4) Uranus Orbiter/Probe (atmospheric entry and landers); (5) Neptune Orbiter/Probe (atmospheric entry and landers); and (6) Pluto-Charon Orbiter/Lander. The discussion is presented in vugraph form.

  1. Mars Polar Lander: The Search Continues

    NASA Technical Reports Server (NTRS)

    2000-01-01

    [figure removed for brevity, see original site] (A) Polar Lander landing site ellipses.

    [figure removed for brevity, see original site] (B) MOC coverage (orange) to 17 Jan. 2000.

    [figure removed for brevity, see original site] (C) MOC image mosaic to 17 Jan. 2000.

    [figure removed for brevity, see original site] (D) Sample high resolution views from MOC mosaic.

    Since mid-December 1999, the Mars Orbiter Camera (MOC) onboard the Mars Global Surveyor (MGS) spacecraft has been taking pictures of Mars Polar Lander's landing zone near 76oS, 195oW, in hopes of finding some evidence as to the fate of the spacecraft that went missing during its December 3, 1999, landing attempt. To take these pictures, the MGS spacecraft is pointed a few degrees off its normal, nadir-looking (straight down) path. The first phase of imaging was completed December 24, 1999, but nothing was found. A second, expanded search was requested by the Mars Surveyor Operations Project and was begun in early January 2000.

    The MOC operations team at Malin Space Science Systems has been busy with the Mars Polar Lander search since December 3rd--initial efforts focused on the use of MOC as a buffer or 'storage space' for data relayed through the MGS Mars Relay (MR) system. It had been hoped that the Polar Lander would try to communicate to Earth using its UHF antenna to relay data through the MGS relay system. Data from the relay come through the MOC and are received at Malin Space Science Systems much in the same way that pictures from MOC are obtained. The relay effort was concluded on January 17, 2000, with no word from the Polar Lander. Meanwhile, the MOC operations team began to plan, command, retrieve, and analyze images designed to look for the Polar Lander. These pictures are taken at the highest spatial resolution possible for MOC, 1.5 meters (5 ft.) per pixel. At this resolution, the fuselage and wings of a jumbo jet can be distinguished, but a Polar Lander would only be a few

  2. The PICARD Mission: an investigation based on measurements dedicated to solar and climate modeling

    NASA Astrophysics Data System (ADS)

    Thuillier, Gerard; Schmutz, Werner; Dewitte, Steven

    PICARD mission is dedicated to the study of the solar activity origin using several key solar measurements. The project also includes development of the solar convective zone and climate models to evaluate the consequences for the Earth'climate of the solar activity. The measure-ments are the total and spectral solar irradiance, solar diameter, limb shape, solar asphericity, and helioseismic waves, which are key inputs for solar physics modeling. The measurements will be carried out by two absolute radiometers, sunphotometers, and a metrological imag-ing telescope onboard a microsatellite built by the French Space Agency CNES, with launch scheduled for March 2010. The radiometers are similar to the ones flown on board SOHO. The imaging telescope contains an angular reference allowing a permanent control of the instrument geometric scale, which is referred to angular stars distances. Optical distortion and flatfield of the imaging telescope are foreseen to be regularly measured. The measurements in space will have correlative measurements from ground using an identical imaging telescope, associated to the measurement of the local turbulence and aerosols localization and concentration. The op-portunity of diameter measurements by solar eclipse method will be used and finally the Solar Disk Sextant instrument will be regularly flown as an external measurement validation. An after launch activities is scheduled for three months, which consists in several instrument checks and recording of some scientific data. Given the launch date, these preliminary measurements will be shown. Images in UV, CaII line and solar photospheric continuum will be presented with some analysis of their contains. Furthermore, preliminary information concerning the radiometric and spectrometric measurements will be given.

  3. Tropical Rainfall Measuring Mission (TRMM) Satellite: Assessment and Lessons Learned After Three Flight Years

    NASA Technical Reports Server (NTRS)

    Simpson, Joanne; Einaudi, Franco (Technical Monitor)

    2000-01-01

    Tropical Rain Measuring Mission (TRMM) is an experiment in measuring rainfall and the associated latent heat release from space. A primary goal is to help in initializing the large-scale weather and climate models for crucial improvement in location and profile of atmospheric heat release. For this, precipitation and latent heating profiles are needed. This goal requires cloud-resolving models. The basic approach was to use passive microwave and rain radar in combination to issue a limited number of products, improving the retrieval algorithms by testing during flight, so the products are updated annually. Despite a tight budget, the TRMM observatory and data system worked excellently from launch for the past three years. A basic philosophy has been to do physical validation as much as possible, in preference to empirical adjustments for algorithm improvement. Additional information is contained in the original extended abstract.

  4. The Rosetta mission

    NASA Astrophysics Data System (ADS)

    Taylor, Matt; Altobelli, Nicolas; Martin, Patrick; Buratti, Bonnie J.; Choukroun, Mathieu

    2016-10-01

    The Rosetta Mission is the third cornerstone mission the ESA programme Horizon 2000. The aim of the mission is to map the comet 67-P/Churyumov-Gerasimenko by remote sensing, to examine its environment insitu and its evolution in the inner solar system. The lander Philae is the first device to land on a comet and perform in-situ science on the surface. Following its launch in March 2004, Rosetta underwent 3 Earth and 1 Mars flybys to achieve the correct trajectory to capture the comet, including flybys of asteroid on 2867 Steins and 21 Lutetia. For June 2011- January 2014 the spacecraft passed through a period of hibernation, due to lack of available power for full payload operation and following successful instrument commissioning, successfully rendezvoused with the comet in August 2014. Following an intense period of mapping and characterisation, a landing site for Philae was selected and on 12 November 2014, Philae was successfully deployed. Rosetta then embarked on the main phase of the mission, observing the comet on its way into and away from perihelion in August 2015. At the time of writing the mission is planned to terminate with the Rosetta orbiter impacting the comet surface on 30 September 2016. This presentation will provide a brief overview of the mission and its science. The first author is honoured to give this talk on behalf of all Rosetta mission science, instrument and operations teams, for it is they who have worked tirelessly to make this mission the success it is.

  5. Summary Report of Mission Acceleration Measurements for STS-73, Launched October 20, 1995

    NASA Technical Reports Server (NTRS)

    Rogers, Melissa J. B.; DeLombard, Richard

    1996-01-01

    The microgravity environment of the Space Shuttle Columbia was measured during the STS-73 mission using accelerometers from five different instruments: the Orbital Acceleration Research Experiment, the Space Acceleration Measurement System, the Three-dimensional Microgravity Accelerometer, the Microgravity Measuring Device, and Suppression of Transient Accelerations by Levitation Evaluation System. The Microgravity Analysis Workstation quasi-steady environment calculation and comparison of this calculation with Orbital Acceleration Research Experiment data was used to assess how appropriate a planned attitude was expected to be for one Crystal Growth Facility experiment sample. The microgravity environment related to several different Orbiter, crew, and experiment operations is presented and interpreted in this report. Data are examined to show the effects of vernier reaction control system jet firings for Orbiter attitude control. This is compared to examples of data when no thrusters were firing, when the primary reaction control system jets were used for attitude control, and when single vernier jets were fired for test purposes. In general, vernier jets, when used for attitude control, cause accelerations in the 3 x 10(exp -4) g to 7 x 10(exp -4) g range. Primary jets used in this manner cause accelerations in the 0.01 to 0.025 g range. Other significant disturbance sources characterized are water dump operations, with Y(sub b) axis acceleration deviations of about 1 x 10(exp -6) g; payload bay door opening motion, with Y(sub o) and Z(sub o) axis accelerations of frequency 0.4 Hz; and probable Glovebox fan operations with notable frequency components at 20, 38, 43, 48, and 53 Hz. The STS-73 microgravity environment is comparable to the environments measured on earlier microgravity science missions.

  6. Polarized Imaging Nephelometer Scattering Measurements from the Winter of 2013 Discover-AQ Field Mission

    NASA Astrophysics Data System (ADS)

    Espinosa, R.; Martins, J.; Dolgos, G.; Dubovik, O.; Ziemba, L. D.; Beyersdorf, A. J.

    2013-12-01

    the Deriving Information on Surface Conditions from Column and Vertically Resolved Observations Relevant to Air Quality (Discover-AQ) mission. This presentation will focus on the results of the PI-Neph's twelve successful science flights during this past winter's Discover-AQ mission. These flights focused primarily on vehicle traffic, agriculture and biomass burning emissions over the San Joaquin Valley in central California. PI-Neph scattering data from this mission will be analyzed with an emphasis on evaluating horizontal, vertical and temporal variation in the sampled aerosol to asses the reliability of column measurements made by remote sensing platforms in determining air quality. Measured PI-Neph phase functions during spirals over AERONET (AErosol RObotic NETwork) stations will also be compared with retrieved phase functions from AERONET. In an effort to further validate AERONET retrievals an inversion method (Dubovik et al., J. Geophys. Res., 111, D11208, doi:10.1029/2005JD006619d, 2006) similar to the AERONET inversion will be applied to PI-NEPH data to obtain size distribution estimates. These results will be compared to measurements of the same sample made by particle counters on board the aircraft.

  7. CHASER: An Innovative Satellite Mission Concept to Measure the Effects of Aerosols on Clouds and Climate

    NASA Astrophysics Data System (ADS)

    Renno, N.; Williams, E.; Rosenfeld, D.; Fischer, D.; Fischer, J.; Kremic, T.; Agrawal, A.; Andreae, M.; Bierbaum, R.; Blakeslee, R.; Boerner, A.; Bowles, N.; Christian, H.; Dunion, J.; Horvath, A.; Huang, X.; Khain, A.; Kinne, S.; Lemos, M.-C.; Penner, J.

    2012-04-01

    The formation of cloud droplets on aerosol particles, technically known as the activation of cloud condensation nuclei (CCN), is the fundamental process driving the interactions of aerosols with clouds and precipitation. Knowledge of these interactions is foundational to our understanding of weather and climate. The Intergovernmental Panel on Climate Change (IPCC) and the Decadal Survey (NRC 2007) indicate that the uncertainty in how clouds adjust to aerosol perturbations dominates the uncertainty in the overall quantification of the radiative forcing attributable to human activities. The Clouds, Hazards, and Aerosols Survey for Earth Researchers (CHASER) mission concept responds to the IPCC and Decadal Survey concerns by studying the activation of CCN and their interactions with clouds and storms. CHASER proposes to revolutionize our understanding of the interactions of aerosols with clouds by making the first global measurements of the fundamental physical entity linking them: activated cloud condensation nuclei. The CHASER mission was conceptualized to measure all quantities necessary for determining the interactions of aerosols with clouds and storms. Measurements by current satellites allow the determination of crude profiles of cloud particle size but not of the activated CCN that seed them. CHASER uses a new technique (Freud et al. 2011; Rosenfeld et al. 2012) and high-heritage instruments to produce the first global maps of activated CCN and the properties of the clouds associated with them. CHASER measures the CCN concentration and cloud thermodynamic forcing simultaneously, allowing their effects to be distinguished. Changes in the behavior of a group of weather systems in which only one of the quantities varies (a partial derivative of the intensity with the desirable quantity) allow the determination of each effect statistically. The high uncertainties of current climate predictions limit their much-needed use in decision-making. CHASER mitigates this

  8. Tropical Rainfall Measuring Mission: Monitoring the Global Tropics for 3 Years and Beyond. 1.1

    NASA Technical Reports Server (NTRS)

    Shepherd, Marshall; Starr, David OC. (Technical Monitor)

    2001-01-01

    The Tropical Rainfall Measuring Mission (TRMM) was launched in November 1997 as a joint U.S.-Japanese mission to advance understanding of the global energy and water cycle by providing distributions of rainfall and latent heating over the global tropics. As a part of NASA's Earth System Enterprise, TRMM seeks to understand the mechanisms through which changes in tropical rainfall influence global circulation. Additionally, a goal is to improve the ability to model these processes in order to predict global circulations and rainfall variability at monthly and longer time scales. Such understanding has implications for assessing climate processes related to El Nino/La Nina and Global Warming. TRMM has also provided unexpected and exciting new knowledge and applications in areas related to hurricane monitoring, lightning, pollution, hydrology, and other areas. This CD-ROM includes a self-contained PowerPoint presentation that provides an overview of TRMM and significant science results; a set of data movies or animation; and listings of current TRMM-related publications in the literature.

  9. Acquisition and Analysis of NASA Ames Sunphotometer Measurements during SAGE III Validation Campaigns and other Tropospheric and Stratospheric Research Missions

    NASA Technical Reports Server (NTRS)

    Livingston, John M.

    2004-01-01

    NASA Cooperative Agreement NCC2-1251 provided funding from April 2001 through December 2003 for Mr. John Livingston of SRI International to collaborate with NASA Ames Research Center scientists and engineers in the acquisition and analysis of airborne sunphotometer measurements during various atmospheric field studies. Mr. Livingston participated in instrument calibrations at Mauna Loa Observatory, pre-mission hardware and software preparations, acquisition and analysis of sunphotometer measurements during the missions, and post-mission analysis of data and reporting of scientific findings. The atmospheric field missions included the spring 2001 Intensive of the Asian Pacific Regional Aerosol Characterization Experiment (ACE-Asia), the Asian Dust Above Monterey-2003 (ADAM-2003) experiment, and the winter 2003 Second SAGE III Ozone Loss and Validation Experiment (SOLVE II).

  10. Overview and early results of the Global Lightning and Sprite Measurements mission

    NASA Astrophysics Data System (ADS)

    Sato, M.; Ushio, T.; Morimoto, T.; Kikuchi, M.; Kikuchi, H.; Adachi, T.; Suzuki, M.; Yamazaki, A.; Takahashi, Y.; Inan, U.; Linscott, I.; Ishida, R.; Sakamoto, Y.; Yoshida, K.; Hobara, Y.; Sano, T.; Abe, T.; Nakamura, M.; Oda, H.; Kawasaki, Z.-I.

    2015-05-01

    Global Lightning and Sprite Measurements on Japanese Experiment Module (JEM-GLIMS) is a space mission to conduct the nadir observations of lightning discharges and transient luminous events (TLEs). The main objectives of this mission are to identify the horizontal distribution of TLEs and to solve the occurrence conditions determining the spatial distribution. JEM-GLIMS was successfully launched and started continuous nadir observations in 2012. The global distribution of the detected lightning events shows that most of the events occurred over continental regions in the local summer hemisphere. In some events, strong far-ultraviolet emissions have been simultaneously detected with N2 1P and 2P emissions by the spectrophotometers, which strongly suggest the occurrence of TLEs. Especially, in some of these events, no significant optical emission was measured by the narrowband filter camera, which suggests the occurrence of elves, not sprites. The VLF receiver also succeeded in detecting lightning whistlers, which show clear falling-tone frequency dispersion. Based on the optical data, the time delay from the detected lightning emission to the whistlers was identified as ˜10 ms, which can be reasonably explained by the wave propagation with the group velocity of whistlers. The VHF interferometer conducted the spaceborne interferometric observations and succeeded in detecting VHF pulses. We observed that the VHF pulses are likely to be excited by the lightning discharge possibly related with in-cloud discharges and measured with the JEM-GLIMS optical instruments. Thus, JEM-GLIMS provides the first full set of optical and electromagnetic data of lightning and TLEs obtained by nadir observations from space.

  11. ExoGeoLab Test Bench for Landers, Rovers and Instruments

    NASA Astrophysics Data System (ADS)

    Foing, B. H.

    2009-04-01

    In the frame of ESTEC technology and research pilot project, we have started a small pilot facility with a ExoGeoLab and a mini-Habitat, supported by two design and control offices in the European Space Incubator (ESI), as well as infrastructure support and manpower. We have in addition to contribution on external instruments and manpower from partner institutes. From this test bench and kit of ExoGeoLab instruments, we plan to operate comprehensive instruments packages that could help in the technical research and science preparation of lander/rover missions studied in the frame of Cosmic Vision or the Exploration programme. The ExoGeoLab research incubator project includes a sequence of activities: - Data analysis and interpretation of remote sensing data (MEX, SMART-1, VEX, Cassini-Huygens) and in-situ (Huygens, MER) , and merging of multi-scale data sets - Procurement and integration of geophysical, geochemical and astrobiological breadboard instruments in an surface station and rover (ExoGeoLab) - Research operations and exploitation of ExoGeoLab test bench for various conceptual configurations (Moon, Mars, NEO, Titan) - Contribution to the exploitation of surface lander results (MER, Phenix, MSL, preparation Exomars) - Scientific simulation of planetary surfaces using laboratory and modelling tools - Support research for definition and design of science surface packages on the Moon, Mars, NEO, Titan - Research support to community preparation of payload for surface lander opportunities Specific goals and methods of ESTEC ExoGeoLab: we have started to integrate instruments in an ExoGeoLab crossing various techniques. The methodic steps for this hands-on research are: 1) We have procured and adapted instruments to equip a mid-size ExoGeoRover (made available in collaboration with ESTEC robotics section), and a small surface station. 2) This terrestrial payload (instruments, sensors, data handling) will be deployed, operated and used as collaborative research

  12. Advanced Soil Moisture Network Technologies; Developments in Collecting in situ Measurements for Remote Sensing Missions

    NASA Astrophysics Data System (ADS)

    Moghaddam, M.; Silva, A. R. D.; Akbar, R.; Clewley, D.

    2015-12-01

    The Soil moisture Sensing Controller And oPtimal Estimator (SoilSCAPE) wireless sensor network has been developed to support Calibration and Validation activities (Cal/Val) for large scale soil moisture remote sensing missions (SMAP and AirMOSS). The technology developed here also readily supports small scale hydrological studies by providing sub-kilometer widespread soil moisture observations. An extensive collection of semi-sparse sensor clusters deployed throughout north-central California and southern Arizona provide near real time soil moisture measurements. Such a wireless network architecture, compared to conventional single points measurement profiles, allows for significant and expanded soil moisture sampling. The work presented here aims at discussing and highlighting novel and new technology developments which increase in situ soil moisture measurements' accuracy, reliability, and robustness with reduced data delivery latency. High efficiency and low maintenance custom hardware have been developed and in-field performance has been demonstrated for a period of three years. The SoilSCAPE technology incorporates (a) intelligent sensing to prevent erroneous measurement reporting, (b) on-board short term memory for data redundancy, (c) adaptive scheduling and sampling capabilities to enhance energy efficiency. A rapid streamlined data delivery architecture openly provides distribution of in situ measurements to SMAP and AirMOSS cal/val activities and other interested parties.

  13. The HYSPIRI Decadal Survey Mission: Update on the Mission Concept and Science Objectives for Global Imaging Spectroscopy and Multi-Spectral Thermal Measurements

    NASA Technical Reports Server (NTRS)

    Green, Robert O.; Hook, Simon J.; Middleton, Elizabeth; Turner, Woody; Ungar, Stephen; Knox, Robert

    2012-01-01

    The NASA HyspIRI mission is planned to provide global solar reflected energy spectroscopic measurement of the terrestrial and shallow water regions of the Earth every 19 days will all measurements downlinked. In addition, HyspIRI will provide multi-spectral thermal measurements with a single band in the 4 micron region and seven bands in the 8 to 12 micron region with 5 day day/night coverage. A direct broadcast capability for measurement subsets is also planned. This HyspIRI mission is one of those designated in the 2007 National Research Council (NRC) Decadal Survey: Earth Science and Applications from Space. In the Decadal Survey, HyspIRI was recognized as relevant to a range of Earth science and science applications, including climate: "A hyperspectral sensor (e.g., FLORA) combined with a multispectral thermal sensor (e.g., SAVII) in low Earth orbit (LEO) is part of an integrated mission concept [described in Parts I and II] that is relevant to several panels, especially the climate variability panel." The HyspIRI science study group was formed in 2008 to evaluate and refine the mission concept. This group has developed a series of HyspIRI science objectives: (1) Climate: Ecosystem biochemistry, condition & feedback; spectral albedo; carbon/dust on snow/ice; biomass burning; evapotranspiration (2) Ecosystems: Global plant functional types, physiological condition, and biochemistry including agricultural lands (3) Fires: Fuel status, fire frequency, severity, emissions, and patterns of recovery globally (4) Coral reef and coastal habitats: Global composition and status (5) Volcanoes: Eruptions, emissions, regional and global impact (6) Geology and resources: Global distributions of surface mineral resources and improved understanding of geology and related hazards These objectives are achieved with the following measurement capabilities. The HyspIRI imaging spectrometer provides: full spectral coverage from 380 to 2500 at 10 nm sampling; 60 m spatial sampling

  14. Mars Environmental Survey (MESUR): Science objectives and mission description

    NASA Technical Reports Server (NTRS)

    Hubbard, G. Scott; Wercinski, Paul F.; Sarver, George L.; Hanel, Robert P.; Ramos, Ruben

    1992-01-01

    In-situ observations and measurements of Mars are objectives of a feasibility study beginning at the Ames Research Center for a mission called the Mars Environmental SURvey (MESUR). The purpose of the MESUR mission is to emplace a pole-to-pole global distribution of landers on the Martian surface to make both short- and long-term observations of the atmosphere and surface. The basic concept is to deploy probes which would directly enter the Mars atmosphere, provide measurements of the upper atmospheric structure, image the local terrain before landing, and survive landing to perform meteorology, seismology, surface imaging, and soil chemistry measurements. MESUR is intended to be a relatively low-cost mission to advance both Mars science and human presence objectives. Mission philosophy is to: (1) 'grow' a network over a period of years using a series of launch opportunities, thereby minimizing the peak annual costs; (2) develop a level-of-effort which is flexible and responsive to a broad set of objectives; (3) focus on science while providing a solid basis for human exploration; and (4) minimize project cost and complexity wherever possible. In order to meet the diverse scientific objectives, each MESUR lander will carry the following strawman instrument payload consisting of: (1) Atmospheric structure experiment, (2) Descent and surface imagers, (3) Meteorology package, (4) Elemental composition instrument, (5) 3-axis seismometer, and (6) Thermal analyzer/evolved gas analyzer. The feasibility study is primarily to show a practical way to design an early capability for characterizing Mars' surface and atmospheric environment on a global scale. The goals are to answer some of the most urgent questions to advance significantly our scientific knowledge about Mars, and for planning eventual exploration of the planet by robots and humans.

  15. Observation of Lunar Rotation by Future Landing Missions

    NASA Astrophysics Data System (ADS)

    Hanada, H.; Sasaki, S.; Kikuchi, F.; Noda, H.; Kawano, N.; Funazaki, K.; Iwata, T.; Kunimori, H.; Rise Project Team

    2009-04-01

    Following the successful KAGUYA (SELENE), Japan will launch a lunar landing mission (SELENE-2) in 2013 or 2014 on the nearside of the moon. This mission shall be followed by other lunar exploration missions. We are proposing instruments measuring lunar rotation on board SELENE-2 (and further missions): ILOM (In-situ Lunar Orientation Measurement), Inverse VLBI, and LLR (Lunar Laser Ranging). Long-term observation of lunar rotation variability will determine various components of physical librations and possibly of free librations. Those components can provide information of the state of lunar mantle and core, i.e., whether the lunar core is molten or not. Together with seismic and gravity data, these data can be used to investigate the interior of the moon, and thus the origin of the moon. So far, observations of physical librations and free librations have been done by Lunar Laser Ranging (LLR) for more than 25 years. There were produced data on the state of the core. SELENE-2 will bring CCRs (Comer Cube Reflectors) for LLR measurements. We are also studying active LLR where laser pulses will be shot from the lunar surface by the triggering laser signals from the Earth. The active LLR can enhance the accuracy of the lunar rotation measurements. The ILOM (In-situ Lunar Orientation Measurement) is an optical telescope which can track trajectories of stars and then provide information of variability of lunar rotation. Since the ILOM observation is done on the lunar surface, orbital motion is separated from the rotational motion. We expect direct observations of the lunar physical and free librations with an accuracy of 1 millisecond of arc. As for ILOM, we applied a photographic zenith tube (PZT) telescope, which is similar to ones used for the international latitude observations of the Earth. The ILOM optical telescope is small in size (20 cm in diameter) but it can be considered as a precursor for the future larger telescopes. The I-VLBI (Inverse VLBI) can measure

  16. Performance of the Falling Snow Retrieval Algorithms for the Global Precipitation Measurement (GPM) Mission

    NASA Technical Reports Server (NTRS)

    Skofronick-Jackson, Gail; Munchak, Stephen J.; Ringerud, Sarah

    2016-01-01

    Retrievals of falling snow from space represent an important data set for understanding the Earth's atmospheric, hydrological, and energy cycles, especially during climate change. Estimates of falling snow must be captured to obtain the true global precipitation water cycle, snowfall accumulations are required for hydrological studies, and without knowledge of the frozen particles in clouds one cannot adequately understand the energy and radiation budgets. While satellite-based remote sensing provides global coverage of falling snow events, the science is relatively new and retrievals are still undergoing development with challenges remaining). This work reports on the development and testing of retrieval algorithms for the Global Precipitation Measurement (GPM) mission Core Satellite, launched February 2014.

  17. Long Duration Exposure Facility post-flight data as it influences the Tropical Rainfall Measuring Mission

    NASA Technical Reports Server (NTRS)

    Straka, Sharon A.

    1995-01-01

    The Tropical Rainfall Measuring Mission (TRMM) is an earth observing satellite that will be in a low earth orbit (350 kilometers) during the next period of maximum solar activity. The TRMM observatory is expected to experience an atomic oxygen fluence of 8.9 x 10(exp 22) atoms per square centimeter. This fluence is ten times higher than the atomic oxygen impingement incident to the Long Duration Exposure Facility (LDEF). Other environmental concerns on TRMM include: spacecraft glow, silicon oxide contaminant build-up, severe spacecraft material degradation, and contamination deposition resulting from molecular interactions with the dense ambient atmosphere. Because of TRMM's predicted harsh environment, TRMM faces many unique material concerns and subsystem design issues. The LDEF data has influenced the design of TRMM and the TRMM material selection process.

  18. Measurements of heavy solar wind and higher energy solar particles during the Apollo 17 mission

    NASA Technical Reports Server (NTRS)

    Walker, R. M.; Zinner, E.; Maurette, M.

    1973-01-01

    The lunar surface cosmic ray experiment, consisting of sets of mica, glass, plastic, and metal foil detectors, was successfully deployed on the Apollo 17 mission. One set of detectors was exposed directly to sunlight and another set was placed in shade. Preliminary scanning of the mica detectors shows the expected registration of heavy solar wind ions in the sample exposed directly to the sun. The initial results indicate a depletion of very-heavy solar wind ions. The effect is probably not real but is caused by scanning inefficiencies. Despite the lack of any pronounced solar activity, energetic heavy particles with energies extending to 1 MeV/nucleon were observed. Equal track densities of approximately 6000 tracks/cm sq 0.5 microns in length were measured in mica samples exposed in both sunlight and shade.

  19. Photogrammetry of the Viking-Lander imagery.

    USGS Publications Warehouse

    Wu, S.S.C.; Schafer, F.J.

    1982-01-01

    We have solved the problem of photogrammetric mapping from the Viking Lander photography in two ways: 1) by converting the azimuth and elevation scanning imagery to the equivalent of a frame picture by means of computerized rectification; and 2) by interfacing a high-speed, general-purpose computer to the AS-11A analytical plotter so that all computations of corrections can be performed in real time during the process of model orientation and map compilation. Examples are presented of photographs and maps of Earth and Mars. -from Authors

  20. Microscopes for NASA's Phoenix Mars Lander

    NASA Technical Reports Server (NTRS)

    2007-01-01

    One part of the Microscopy, Electrochemistry, and Conductivity Analyzer instrument for NASA's Phoenix Mars Lander is a pair of telescopes with a special wheel (on the right in this photograph) for presenting samples to be inspected with the microscopes. A horizontally mounted optical microscope (on the left in this photograph) and an atomic force microscope will examine soil particles and possibly ice particles.

    The shapes and the size distributions of soil particles may tell scientists about environmental conditions the material has experienced. Tumbling rounds the edges. Repeated wetting and freezing causes cracking. Clay minerals formed during long exposure to water have distinctive, platy particles shapes.

  1. EGPM - The proposed European contribution to the Global Precipitation Measurement (GPM) mission

    NASA Astrophysics Data System (ADS)

    Mugnai, A.; Egpm Mission Advisory Group

    2003-04-01

    At the beginning of January 2002, an international scientific consortium (the EGPM Science Team) constituted by numerous scientists involved in several disciplines related to precipitation, submitted to the European Space Agency (ESA) a proposal titled "EGPM: European contribution to the Global Precipitation Mission" in response to ESA's second call for proposals for Earth Explorer Opportunity Missions (EEOMs). The principle objective of the EGPM proposal was to encourage ESA to directly engage in the international organization for the Global Precipitation Measurement (GPM) mission formulated by NASA and NASDA, by providing one member of the GPM constellation of satellites aimed at providing frequent global rainfall observations for an extended operations period starting in the time frame of 2007. Noteworthy, a large part of the European scientific and operational community is strongly interested in GPM. Especially, the operational community related to NWP, nowcasting and hydrological hazards would take advantage of Europe being part of the constellation, because this would guarantee direct access to real-time data. The proposed EGPM satellite should satisfy, in association with the overall GPM constellation, the following "regional" requirements: - Improve the rainfall estimation accuracy with respect to SSM/I; - Enhance the detectability of light rain and snowfall, specifically over land, as appropriate for Northern Europe and Canada and in mid-latitude oceanic perturbations; - Provide a significant contribution to the monitoring and the understanding of hazardous and flash-flood producing storms along the Mediterranean coasts; - Improve the forecast skill of global and regional NWP models through data assimilation of precipitation measurements; - Provide direct-read-out data for real-time applications, as well as global data acquisition. To this end, the scientific payload of the EGPM satellite would consist of an advanced conically scanning microwave radiometer

  2. Open Imaging Nephelometer Scattering Measurements from the 2014 Discover-AQ Field Mission

    NASA Astrophysics Data System (ADS)

    Espinosa, R.; Orozco, D.; Dolgos, G.; Martins, J. V.

    2014-12-01

    After greenhouse gases, aerosols are thought to have the largest contribution to total atmospheric radiative forcing, but they are frequently cited as the single largest source of uncertainty among all anthropogenic radiative forcing components. Remote sensing allows for global measurements of aerosol properties, however validation of these measurements and the climatological assumptions used in their retrieval algorithms require high quality in situ sampling. The Laboratory for Aerosols, Clouds and Optics (LACO) at the University of Maryland Baltimore County (UMBC) has developed the Imaging Nephelometer, a novel and highly accurate instrument concept designed to significantly aid in situ optical scattering measurements. Imaging Nephelometers allow for measurements of scattering coefficient, phase function and polarized phase function over a wide angular range of 2 to 178 degrees with an angular resolution of less than half of a degree. The simple layout of these devices also permits the construction of an instrument that is compact enough to be deployed on a variety of airborne platforms. Additionally, a version of this instrument that is capable of in situ sampling in open-air, free from sample biases potentially introduced by an inlet or containment apparatus, has recently been constructed. This instrument, known as the Open Imaging NEPHelometer (OI-NEPH), was flown on the P3 aircraft in the summer of 2014 during the Colorado portion of the Discover-AQ field mission (Deriving Information on Surface Conditions from Column and Vertically Resolved Observations Relevant to Air Quality). This presentation will focus on the results of the OI-NEPH's successful science flights during this field experiment. The P3's flights during this mission focused primarily on vehicle, agriculture, biomass burning and industrial processing emissions over the Colorado Front Range. Emphasis will be placed on any observed differences in scattering properties between the measurements

  3. Validation for the Tropical Rainfall Measuring Mission: Lessons Learned and Future Plans

    NASA Technical Reports Server (NTRS)

    Wolff, David B.; Amitai, E.; Marks, D. A.; Silberstein, D.; Lawrence, R. J.

    2005-01-01

    The Tropical Rainfall Measuring Mission (TRMM) was launched in November 1997 and is a highly regarded and successful mission. A major component of the TRMM program was its Ground Validation (GV) program. Through dedicated research and hard work by many groups, both the GV and satellite-retrieved rain estimates have shown a convergence at key GV sites, lending credibility to the global TRMM estimates. To be sure, there are some regional differences between the various satellite estimates themselves, which still need to be addressed; however, it can be said with some certainty that TRMM has provided a high-quality, long-term climatological data set for researchers that provides errors on the order of 10-20%, rather than pre-TRMM era error estimates on the order of 50-100%. The TRMM GV program's main operational task is to provide rainfall products for four sites: Darwin, Australia (DARW); Houston, Texas (HSTN); Kwajalein, Republic of the Marshall Islands (KWAJ); and, Melbourne, Florida (MELB). A comparison between TRMM Ground Validation (Version 5) and Satellite (Version 6) rain intensity estimates is presented. The gridded satellite product (3668) will be compared to GV Level II rain-intensity and -type maps (2A53 and 2A54, respectively). The 3G68 product represents a 0.5 deg x 0.5 deg data grid providing estimates of rain intensities from the TRMM Precipitation Radar (PR), Microwave Imager (TMI) and Combined (COM) algorithms. The comparisons will be sub-setted according to geographical type (land, coast and ocean). The convergence of the GV and satellite estimates bodes well for expectations for the proposed Global Precipitation Measurement (GPM) program and this study and others are being leveraged towards planning GV goals for GPM. A discussion of lessons learned and future plans for TRMM GV in planning for GPM will also be provided.

  4. On pressure measurement and seasonal pressure variations during the Phoenix mission

    NASA Astrophysics Data System (ADS)

    Taylor, Peter A.; Kahanpää, Henrik; Weng, Wensong; Akingunola, Ayodeji; Cook, Clive; Daly, Mike; Dickinson, Cameron; Harri, Ari-Matti; Hill, Darren; Hipkin, Victoria; Polkko, Jouni; Whiteway, Jim

    2010-03-01

    In situ surface pressures measured at 2 s intervals during the 150 sol Phoenix mission are presented and seasonal variations discussed. The lightweight Barocap®/Thermocap® pressure sensor system performed moderately well. However, the original data processing routine had problems because the thermal environment of the sensor was subject to more rapid variations than had been expected. Hence, the data processing routine was updated after Phoenix landed. Further evaluation and the development of a correction are needed since the temperature dependences of the Barocap sensor heads have drifted after the calibration of the sensor. The inaccuracy caused by this appears when the temperature of the unit rises above 0°C. This frequently affects data in the afternoons and precludes a full study of diurnal pressure variations at this time. Short-term fluctuations, on time scales of order 20 s are unaffected and are reported in a separate paper in this issue. Seasonal variations are not significantly affected by this problem and show general agreement with previous measurements from Mars. During the 151 sol mission the surface pressure dropped from around 860 Pa to a minimum (daily average) of 724 Pa on sol 140 (Ls 143). This local minimum occurred several sols earlier than expected based on GCM studies and Viking data. Since battery power was lost on sol 151 we are not sure if the timing of the minimum that we saw could have been advanced by a low-pressure meteorological event. On sol 95 (Ls 122), we also saw a relatively low-pressure feature. This was accompanied by a large number of vertical vortex events, characterized by short, localized (in time), low-pressure perturbations.

  5. Measurement of the PPN-beta parameter in the GAME mission.

    NASA Astrophysics Data System (ADS)

    Vecchiato, Alberto; Bernardi, Gabriella; Gai, Mario

    GAME (Gamma Astrometric Measurement Experiment) is a proposal for a space mission whose main scientific goal is the estimation of the γ parameter of the Parametrized Post-Newtonian (PPN) formalism. A possible configuration as a small mission, and its possible performances for the main scientific case, has already been described in some recent papers (Gai et al. 2009, Vecchiato et al. 2009). However, simple considerations on the applicable observation strategy suggest that GAME can also provide outstanding results on other topics. We address the possible application to another classical test of General Relativity, i.e. the determination of the β parameter of the PPN formalism, or more precisely of the (2γ - β - 1) combination, by means of the reconstruction of the orbit of Mercury. The present accepted limit for this combination is |2γ - β - 1| < 10-3 (Will, 2006), while the proposed ESA Bepi-Colombo Mercury orbiter is expected to improve this limit to 3 × 10-4 after 2020. Preliminary estimations, based on the astrometric accuracy of the satellite measurements, suggest that GAME, in the baseline configuration, could reach the 10-4 -level of accuracy or better, hence calling for a more accurate evaluation which takes into account a relativistic model of the observable. The astrometric position of the planet, in fact, is influenced by the well-known light deflection effect whose lower limit, in the case of Mercury, is of the order of 10-2 arcsec, i.e. well above the expected sub-mas astrometric accuracy of GAME for bright objects. We describe the results of some simulations based on this relativistic model applied to the case of Mercury. Further work will assess in more detail the GAME performance by optimization of the observation strategy and the possible inclusion of other observational targets (high ellipticity orbit asteroids) which could improve on the overall accuracy of the estimate of the β parameter.

  6. The Measurements of The Phobos Magnetic Field During The Phobos-2 Mission

    NASA Astrophysics Data System (ADS)

    Mordovskaya, V. G.; Oraevsky, V. N.

    The measurements obtained by the magnetometers during the Phobos-2 mission from March 22 to March 26, 1989, are discussed. In particular it is suggested that the solar wind interaction with Phobos and the rotating direction of the magnetic field in the circular orbits around Mars are the evidence for the existence of an intrinsic plane- tary field of Phobos with a dipole moment of the order of 10^18 Gauss cm^3 . The discovery of the Phobos magnetic field was studied in [1,2]. The magnetization of the Phobos substance is 0.15 CGS. It should be noted that there are some meteorites with a magnetization of 3 CGS [3]. Phobos is the magnetized body, rotating around Mars so; it always presents the same face to a hypothetical observer on Mars. The peculiarity of the rotation of the magnetized Phobos supplies the magnetic field signatures, which, specifically the direction, are phase locked with Phobos rotation rate. To resolve this issue completely, in situ measurements from Phobos vicinity are required. The Pho- bos space project had had a very complicated scheme of flight relative to Phobos and the organization of a unique experiment named "Celestial Mechanics". The spacecraft was inserted into such an orbit around Mars on 22 March 1989 that it remained perma- nently within the vicinity of Phobos until 27 March. The direct experimental evidence of the Phobos magnetic field was o