Crumpled Heat Shield

NASA Technical Reports Server (NTRS)

2008-01-01

The Phoenix Mars Lander's Surface Stereo Imager took this image of the spacecraft's crumpled heat shield on Sept. 16, 2008, the 111th Martian day of the mission.

The 2-1/2 meter (about 8-1/2 feet) heat shield landed southeast of Phoenix, about halfway between the spacecraft and its backshell/parachute. The backshell/parachute touched ground 300 meters (1,000 ft) to the south of the lander.

The dark area to the right of the heat shield is the 'bounce mark' it made on impact with the Red Planet. This image is the highest-resolution image that will likely be taken by the lander, and is part of the 1,500-image 'Happily Ever After' panorama.

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

Martian Plain in Late Summer

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager on NASA's Mars Phoenix Lander acquired this view of the textured plain near the lander at about 11 a.m. local Mars solar time during the mission's 124th Martian day, or sol (Sept. 29, 2008).

The image was taken through an infrared filter. The brighter patches are dustier than darker areas of the surface.

The last signal from the lander came on Nov. 2, 2008.

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

Payload topography camera of Chang'e-3

NASA Astrophysics Data System (ADS)

Yu, Guo-Bin; Liu, En-Hai; Zhao, Ru-Jin; Zhong, Jie; Zhou, Xiang-Dong; Zhou, Wu-Lin; Wang, Jin; Chen, Yuan-Pei; Hao, Yong-Jie

2015-11-01

Chang'e-3 was China's first soft-landing lunar probe that achieved a successful roving exploration on the Moon. A topography camera functioning as the lander's “eye” was one of the main scientific payloads installed on the lander. It was composed of a camera probe, an electronic component that performed image compression, and a cable assembly. Its exploration mission was to obtain optical images of the lunar topography in the landing zone for investigation and research. It also observed rover movement on the lunar surface and finished taking pictures of the lander and rover. After starting up successfully, the topography camera obtained static images and video of rover movement from different directions, 360° panoramic pictures of the lunar surface around the lander from multiple angles, and numerous pictures of the Earth. All images of the rover, lunar surface, and the Earth were clear, and those of the Chinese national flag were recorded in true color. This paper describes the exploration mission, system design, working principle, quality assessment of image compression, and color correction of the topography camera. Finally, test results from the lunar surface are provided to serve as a reference for scientific data processing and application.

The Viking Orbiter and its Mariner inheritance

NASA Technical Reports Server (NTRS)

Wolfe, A. E.; Norris, H. W.

1975-01-01

The orbiter system of the Viking spacecraft performs the functions of transporting the lander into orbit around Mars, surveying the proposed landing sites, relaying lander data to earth, and conducting independent scientific observations of Mars. The orbiter system is a semiautomatic, solar-powered, triaxially stabilized platform capable of making trajectory corrections and communicating with earth on S-band. Its instruments for visual imaging, detecting water vapor, and thermal mapping are mounted on a separate two-degree-of-freedom scan platform. Radio science is conducted at three frequencies, using the main S-band system, a separate X-band derived from the S-band, and the UHF one-way link with the lander.

TMBM: Tethered Micro-Balloons on Mars

NASA Technical Reports Server (NTRS)

Sims, M. H.; Greeley, R.; Cutts, J. A.; Yavrouian, A. H.; Murbach, M.

2000-01-01

The use of balloons/aerobots on Mars has been under consideration for many years. Concepts include deployment during entry into the atmosphere from a carrier spacecraft, deployment from a lander, use of super-pressurized systems for long duration flights, 'hot-air' systems, etc. Principal advantages include the ability to obtain high-resolution data of the surface because balloons provide a low-altitude platform which moves relatively slowly. Work conducted within the last few years has removed many of the technical difficulties encountered in deployment and operation of balloons/aerobots on Mars. The concept proposed here (a tethered balloon released from a lander) uses a relatively simple approach which would enable aspects of Martian balloons to be tested while providing useful and potentially unique science results. Tethered Micro-Balloons on Mars (TMBM) would be carried to Mars on board a future lander as a stand-alone experiment having a total mass of one to two kilograms. It would consist of a helium balloon of up to 50 cubic meters that is inflated after landing and initially tethered to the lander. Its primary instrumentation would be a camera that would be carried to an altitude of up to tens of meters above the surface. Imaging data would be transmitted to the lander for inclusion in the mission data stream. The tether would be released in stages allowing different resolutions and coverage. In addition during this staged release a lander camera system may observe the motion of the balloon at various heights above he lander. Under some scenarios upon completion of the primary phase of TMBM operations, the tether would be cut, allowing TMBM to drift away from the landing site, during which images would be taken along the ground.

Surface Stereo Imager on Mars, Side View

NASA Technical Reports Server (NTRS)

2008-01-01

This image is a view of NASA's Phoenix Mars Lander's Surface Stereo Imager (SSI) as seen by the lander's Robotic Arm Camera. This image was taken on the afternoon of the 116th Martian day, or sol, of the mission (September 22, 2008). The mast-mounted SSI, which provided the images used in the 360 degree panoramic view of Phoenix's landing site, is about 4 inches tall and 8 inches long.

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

Phoenix Robotic Arm's Workspace After 90 Sols

NASA Technical Reports Server (NTRS)

2008-01-01

During the first 90 Martian days, or sols, after its May 25, 2008, landing on an arctic plain of Mars, NASA's Phoenix Mars Lander dug several trenches in the workspace reachable with the lander's robotic arm.

The lander's Surface Stereo Imager camera recorded this view of the workspace on Sol 90, early afternoon local Mars time (overnight Aug. 25 to Aug. 26, 2008). The shadow of the the camera itself, atop its mast, is just left of the center of the image and roughly a third of a meter (one foot) wide.

The workspace is on the north side of the lander. The trench just to the right of center is called 'Neverland.'

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

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers from the Jet Propulsion Laboratory (JPL) are conducting a systems test of the imager for the Mars Pathfinder. Mounted on the Pathfinder lander, the imager (the white cylindrical element the worker is touching) is a specially designed camera featuring a stereo-imaging system with color capability provided by a set of selectable filters. It is mounted on an extendable mast that will pop up after the lander touches down on the Martian surface. The imager will transmit images of the terrain, allowing engineers back on Earth to survey the landing site before the Pathfinder rover is deployed to explore the area. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2. JPL manages the Pathfinder project for NASA.

Spectral mixture modeling: Further analysis of rock and soil types at the Viking Lander sites

NASA Technical Reports Server (NTRS)

Adams, John B.; Smith, Milton O.

1987-01-01

A new image processing technique was applied to Viking Lander multispectral images. Spectral endmembers were defined that included soil, rock and shade. Mixtures of these endmembers were found to account for nearly all the spectral variance in a Viking Lander image.

The mosaics of Mars: As seen by the Viking Lander cameras

NASA Technical Reports Server (NTRS)

Levinthal, E. C.; Jones, K. L.

1980-01-01

The mosaics and derivative products produced from many individual high resolution images acquired by the Viking Lander Camera Systems are described: A morning and afternoon mosaic for both cameras at the Lander 1 Chryse Planitia site, and a morning, noon, and afternoon camera pair at Utopia Planitia, the Lander 11 site. The derived products include special geometric projections of the mosaic data sets, polar stereographic (donut), stereoscopic, and orthographic. Contour maps and vertical profiles of the topography were overlaid on the mosaics from which they were derived. Sets of stereo pairs were extracted and enlarged from stereoscopic projections of the mosaics.

Passive imaging based multi-cue hazard detection spacecraft safe landing

NASA Technical Reports Server (NTRS)

Huertas, Andres; Cheng, Yang; Madison, Richard

2006-01-01

Accurate assessment of potentially damaging ground hazards during the spacecraft EDL (Entry, Descent and Landing) phase is crucial to insure a high probability of safe landing. A lander that encounters a large rock, falls off a cliff, or tips over on a steep slope can sustain mission ending damage. Guided entry is expected to shrink landing ellipses from 100-300 km to -10 km radius for the second generation landers as early as 2009. Regardless of size and location, however, landing ellipses will almost always contain hazards such as craters, discontinuities, steep slopes, and large rocks. It is estimated that an MSL (Mars Science Laboratory)-sized lander should detect and avoid 16- 150m diameter craters, vertical drops similar to the edges of 16m or 3.75m diameter crater, for high and low altitude HAD (Hazard Detection and Avoidance) respectively. It should also be able to detect slopes 20' or steeper, and rocks 0.75m or taller. In this paper we will present a passive imaging based, multi-cue hazard detection and avoidance (HDA) system suitable for Martian and other lander missions. This is the first passively imaged HDA system that seamlessly integrates multiple algorithm-crater detection, slope estimation, rock detection and texture analysis, and multicues- crater morphology, rock distribution, to detect these hazards in real time.

Sojourner's First Images From Mars

NASA Technical Reports Server (NTRS)

2003-01-01

These images are views of the Mars Pathfinder Lander's forward ramp before (top image) and after (bottom image) deployment. Some data from the before image was lost due to rover-lander communication problems.

Color Image of Phoenix Lander on Mars Surface

NASA Technical Reports Server (NTRS)

2008-01-01

This is an enhanced-color image from Mars Reconnaissance Orbiter's High Resolution Imaging Science Experiment (HiRISE) camera. It shows the Phoenix lander with its solar panels deployed on the Mars surface. The spacecraft appears more blue than it would in reality.

The blue/green and red filters on the HiRISE camera were used to make this picture.

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

Phoenix Carries Soil to Wet Chemistry Lab

NASA Technical Reports Server (NTRS)

2008-01-01

This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Robotic Arm scoop positioned over the Wet Chemistry Lab delivery funnel on Sol 29, the 29th Martian day after landing, or June 24, 2008. The soil will be delivered to the instrument on Sol 30.

This image has been enhanced to brighten the scene.

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

Deepest Trenching at Phoenix Site on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

NASA's Phoenix Mars Lander widened the deepest trench it has excavated, dubbed 'Stone Soup,' (in the lower half of this image) to collect a sample from about 18 centimeters (7 inches) below the surface for analysis by the lander's wet chemistry laboratory.

Phoenix's Surface Stereo Imager took this image on Sol 95 (Aug. 30, 2008), the 95th Martian day since landing. For scale, the rock to the right of the Stone Soup trench is about 15 centimeters (6 inches) across. The lander's robotic arm scooped up a sample from the left half of the trench for delivery the following sol to the wet chemistry laboratory.

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

Dig Hazard Assessment Using a Stereo Pair of Cameras

NASA Technical Reports Server (NTRS)

Rankin, Arturo L.; Trebi-Ollennu, Ashitey

2012-01-01

This software evaluates the terrain within reach of a lander s robotic arm for dig hazards using a stereo pair of cameras that are part of the lander s sensor system. A relative level of risk is calculated for a set of dig sectors. There are two versions of this software; one is designed to run onboard a lander as part of the flight software, and the other runs on a PC under Linux as a ground tool that produces the same results generated on the lander, given stereo images acquired by the lander and downlinked to Earth. Onboard dig hazard assessment is accomplished by executing a workspace panorama command sequence. This sequence acquires a set of stereo pairs of images of the terrain the arm can reach, generates a set of candidate dig sectors, and assesses the dig hazard of each candidate dig sector. The 3D perimeter points of candidate dig sectors are generated using configurable parameters. A 3D reconstruction of the terrain in front of the lander is generated using a set of stereo images acquired from the mast cameras. The 3D reconstruction is used to evaluate the dig goodness of each candidate dig sector based on a set of eight metrics. The eight metrics are: 1. The maximum change in elevation in each sector, 2. The elevation standard deviation in each sector, 3. The forward tilt of each sector with respect to the payload frame, 4. The side tilt of each sector with respect to the payload frame, 5. The maximum size of missing data regions in each sector, 6. The percentage of a sector that has missing data, 7. The roughness of each sector, and 8. Monochrome intensity standard deviation of each sector. Each of the eight metrics forms a goodness image layer where the goodness value of each sector ranges from 0 to 1. Goodness values of 0 and 1 correspond to high and low risk, respectively. For each dig sector, the eight goodness values are merged by selecting the lowest one. Including the merged goodness image layer, there are nine goodness image layers for each stereo pair of mast images.

Lander and rover exploration on the lunar surface: A study for SELENE-B mission

NASA Astrophysics Data System (ADS)

Selene-B Rover Science Group; Sasaki, S.; Sugihara, T.; Saiki, K.; Akiyama, H.; Ohtake, M.; Takeda, H.; Hasebe, N.; Kobayashi, M.; Haruyama, J.; Shirai, K.; Kato, M.; Kubota, T.; Kunii, Y.; Kuroda, Y.

The SELENE-B, a lunar landing mission, has been studied in Japan, where a scientific investigation plan is proposed using a robotic rover and a static lander. The main theme to be investigated is to clarify the lunar origin and evolution, especially for early crustal formation process probably from the ancient magma ocean. The highest priority is placed on a direct in situ geology at a crater central peak, “a window to the interior”, where subcrustal materials are exposed and directly accessed without drilling. As a preliminary study was introduced by Sasaki et al. [Sasaki, S., Kubota, T., Okada, T. et al. Scientific exploration of lunar surface using a rover in Japanse future lunar mission. Adv. Space Res. 30, 1921 1926, 2002.], the rover and lander are jointly used, where detailed analyses of the samples collected by the rover are conducted at the lander. Primary scientific instruments are a multi-band stereo imager, a gamma-ray spectrometer, and a sampling tool on the rover, and a multi-spectral telescopic imager, a sampling system, and a sample analysis package with an X-ray spectrometer/diffractometer, a multi-band microscope as well as a sample cleaning and grinding device on the lander.

The Martian surface as imaged, sampled, and analyzed by the Viking landers

NASA Technical Reports Server (NTRS)

Arvidson, Raymond E.; Gooding, James L.; Moore, Henry J.

1989-01-01

Data collected by two Viking landers are analyzed. Attention is given to the characteristics of the surface inferred from Lander imaging and meteorology data, physical and magnetic properties experiments, and both inorganic and organic analyses of Martian samples. Viking Lander 1 touched down on Chryse Planitia on July 20, 1976 and continued to operate for 2252 sols, until November 20, 1982. Lander 2 touched down about 6500 km away from Lander 1, on Utopia Planitia on September 3, 1976. The chemical compositions of sediments at the two landing sites are similar, suggesting an aeolian origin. The compositions suggest an iron-rich rock an are matched by various clays and salts.

Surface Stereo Imager on Mars, Face-On

NASA Technical Reports Server (NTRS)

2008-01-01

This image is a view of NASA's Phoenix Mars Lander's Surface Stereo Imager (SSI) as seen by the lander's Robotic Arm Camera. This image was taken on the afternoon of the 116th Martian day, or sol, of the mission (September 22, 2008). The mast-mounted SSI, which provided the images used in the 360 degree panoramic view of Phoenix's landing site, is about 4 inches tall and 8 inches long. The two 'eyes' of the SSI seen in this image can take photos to create three-dimensional views of the landing site.

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.

MOSES: a modular sensor electronics system for space science and commercial applications

NASA Astrophysics Data System (ADS)

Michaelis, Harald; Behnke, Thomas; Tschentscher, Matthias; Mottola, Stefano; Neukum, Gerhard

1999-10-01

The camera group of the DLR--Institute of Space Sensor Technology and Planetary Exploration is developing imaging instruments for scientific and space applications. One example is the ROLIS imaging system of the ESA scientific space mission `Rosetta', which consists of a descent/downlooking and a close-up imager. Both are parts of the Rosetta-Lander payload and will operate in the extreme environment of a cometary nucleus. The Rosetta Lander Imaging System (ROLIS) will introduce a new concept for the sensor electronics, which is referred to as MOSES (Modula Sensor Electronics System). MOSES is a 3D miniaturized CCD- sensor-electronics which is based on single modules. Each of the modules has some flexibility and enables a simple adaptation to specific application requirements. MOSES is mainly designed for space applications where high performance and high reliability are required. This concept, however, can also be used in other science or commercial applications. This paper describes the concept of MOSES, its characteristics, performance and applications.

Compositional variability of the Martian surface

NASA Technical Reports Server (NTRS)

Adams, John B.; Smith, Milton O.

1991-01-01

Spectral reflectance data from Viking Landers and Orbiters and from telescopic observations were analyzed with the objective of isolating compositional information about the Martian surface and assessing compositional variability. Two approaches were used to calibrate the data to reflectance to permit direct comparisons with laboratory reference spectra of well characterized materials. In Viking Lander multispectral images (six spectral bands) most of the spectral variation is caused by changes in lighting geometry within individual scenes, from scene to scene, and over time. Lighting variations are both wavelength independent and wavelength dependent. By calibrating lander image radiance values to reflectance using spectral mixture analysis, the possible range of compositions was assessed with reference to a collection of laboratory samples, also resampled to the lander spectral bands. All spectra from the lander images studied plot (in six-space) within a planar triangle having at the apexes the respective spectra of tan basaltic palagonite, gray basalt, and shale. Within this plane all lander spectra fit as mixtures of these three endmembers. Reference spectra that plot outside of the triangle are unable to account for the spectral variation observed in the images.

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 images will be released through the Planetary Data System in accordance with Project policies at a later time.

NASA's Jet Propulsion Laboratory manages the 2001 Mars Odyssey mission for NASA's Office of Space Science, Washington, D.C. The Thermal Emission Imaging System (THEMIS) was developed by Arizona State University, Tempe, in collaboration with Raytheon Santa Barbara Remote Sensing. The THEMIS investigation is led by Dr. Philip Christensen at Arizona State University. Lockheed Martin Astronautics, Denver, is the prime contractor for the Odyssey project, and developed and built the orbiter. Mission operations are conducted jointly from Lockheed Martin and from JPL, a division of the California Institute of Technology in Pasadena.

Phoenix Checks out its Work Area

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

This animation shows a mosaic of images of the workspace reachable by the scoop on the robotic arm of NASA's Phoenix Mars Lander, along with some measurements of rock sizes.

Phoenix was able to determine the size of the rocks based on three-dimensional views from stereoscopic images taken by the lander's 7-foot mast camera, called the Surface Stereo Imager. The stereo pair of images enable depth perception, much the way a pair of human eyes enable people to gauge the distance to nearby objects.

The rock measurements were made by a visualization tool known as Viz, developed at NASA's Ames Research Laboratory. The shadow cast by the camera on the Martian surface appears somewhat disjointed because the camera took the images in the mosaic at different times of day.

Scientists do not yet know the origin or composition of the flat, light-colored rocks on the surface in front 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 NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

Color Image of Phoenix Lander on Mars Surface

NASA Image and Video Library

2008-05-27

This is an enhanced-color image from Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment HiRISE camera. It shows the NASA Mars Phoenix lander with its solar panels deployed on the Mars surface

Processing the Viking lander camera data

NASA Technical Reports Server (NTRS)

Levinthal, E. C.; Tucker, R.; Green, W.; Jones, K. L.

1977-01-01

Over 1000 camera events were returned from the two Viking landers during the Primary Mission. A system was devised for processing camera data as they were received, in real time, from the Deep Space Network. This system provided a flexible choice of parameters for three computer-enhanced versions of the data for display or hard-copy generation. Software systems allowed all but 0.3% of the imagery scan lines received on earth to be placed correctly in the camera data record. A second-order processing system was developed which allowed extensive interactive image processing including computer-assisted photogrammetry, a variety of geometric and photometric transformations, mosaicking, and color balancing using six different filtered images of a common scene. These results have been completely cataloged and documented to produce an Experiment Data Record.

The Martian surface as imaged, sampled, and analyzed by the Viking landers

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

Arvidson, R.E.; Gooding, J.L.; Moore, H.J.

1989-02-01

Data collected by two Viking landers are analyzed. Attention is given to the characteristics of the surface inferred from Lander imaging and meteorology data, physical and magnetic properties experiments, and both inorganic and organic analyses of Martian samples. Viking Lander 1 touched down on Chryse Planitia on July 20, 1976 and continued to operate for 2252 sols, until November 20, 1982. Lander 2 touched down about 6500 km away from Lander 1, on Utopia Planitia on September 3, 1976. The chemical compositions of sediments at the two landing sites are similar, suggesting an aeolian origin. The compositions suggest an iron-richmore » rock an are matched by various clays and salts. 89 refs.« less

Geologic map of the MTM 25047 and 20047 quadrangles, central Chryse Planitia/Viking 1 Lander site, Mars

USGS Publications Warehouse

Crumpler, L.S.; Craddock, R.A.; Aubele, J.C.

2001-01-01

This map uses Viking Orbiter image data and Viking 1 Lander image data to evaluate the geologic history of a part of Chryse Planitia, Mars. The map area lies at the termini of the Maja and Kasei Valles outwash channels and includes the site of the Viking 1 Lander. The photomosaic base for these quadrangles was assembled from 98 Viking Orbiter frames comprising 1204 pixels per line and 1056 lines and ranging in resolution from 20 to 200 m/pixel. These orbital image data were supplemented with images of the surface as seen from the Viking 1 Lander, one of only three sites on the martian surface where planetary geologic mapping is assisted by ground truth.

Phoenix Again Carries Soil to Wet Chemistry Lab

NASA Technical Reports Server (NTRS)

2008-01-01

This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Robotic Arm scoop positioned over the Wet Chemistry Lab Cell 1 delivery funnel on Sol 41, the 42nd Martian day after landing, or July 6, 2008, after a soil sample was delivered to the instrument.

The instrument's Cell 1 is second one from the foreground of the image. The first cell, Cell 0, received a soil sample two weeks earlier.

This image has been enhanced to brighten the scene.

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

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.

Could This Be the Mars Soviet 3 Lander?

NASA Image and Video Library

2013-04-11

This set of images shows what might be hardware from the Soviet Union 1971 Mars 3 lander, seen in a pair of images from the High Resolution Imaging Science Experiment HiRISE camera on NASA Mars Reconnaissance Orbiter.

Solar Panel Buffeted by Wind at Phoenix Site

NASA Technical Reports Server (NTRS)

2008-01-01

Winds were strong enough to cause about a half a centimeter (.19 inch) of motion of a solar panel on NASA's Phoenix Mars lander when the lander's Surface Stereo Imager took this picture on Aug. 31, 2008, during the 96th Martian day since landing.

The lander's telltale wind gauge has been indicating wind speeds of about 4 meters per second (9 miles per hour) during late mornings at the site.

These conditions were anticipated and the wind is not expected to do any harm to the lander.

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

Mars Surface near Viking Lander 1 Footpad

NASA Technical Reports Server (NTRS)

2008-01-01

This image, which has been flipped horizontally, was taken by Viking Lander 1 on August 1, 1976, 12 sols after landing. Much like images that have returned from Phoenix, the soil beneath Viking 1 has been exposed due to exhaust from thruster engines during descent. This is visible to the right of the struts of Viking's surface-sampler arm housing, seen on the left.

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

Imaging experiment: The Viking Mars orbiter

USGS Publications Warehouse

Carr, M.H.; Baum, W.A.; Briggs, G.A.; Masursky, H.; Wise, D.W.; Montgomery, D.R.

1972-01-01

The general objectives of the Imaging Experiment on the Viking Orbiter are to aid the selection of Viking Lander sites, to map and monitor the chosen sites during lander operations, to aid in the selection of future landing sites, and to extend our knowledge of the planet. The imaging system consists of two identical vidicon cameras each attached to a 1026 mm T/8 telescope giving approximately 1?? square field of view. From an altitude of 1500 km the picture elements will be approximately 24m apart. The vidicon is coupled with an image intensifier which provides increased sensitivity and permits electronic shuttering and image motion compensation. A vidicon readout time of 2.24 sec enables pictures to be taken in rapid sequence for contiguous coverage at high resolution. The camera differs from those previously flown to Mars by providing contiguous coverage at high resolution on a single orbital pass, by having sufficient sensitivity to use narrow band color filters at maximum resolution, and by having response in the ultraviolet. These capabilities will be utelized to supplement lander observations and to extend our knowledge particularly of volcanic, erosional, and atmospheric phenomena on Mars. ?? 1972.

Identification of the Beagle 2 lander on Mars.

PubMed

Bridges, J C; Clemmet, J; Croon, M; Sims, M R; Pullan, D; Muller, J-P; Tao, Y; Xiong, S; Putri, A R; Parker, T; Turner, S M R; Pillinger, J M

2017-10-01

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43° E, 11.53° N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the European Space Agency Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis from 174 km to 57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including red and blue-green colours, were obtained over the area of interest and searched, which allowed sub-pixel imaging using super high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, high reflectivity relative to the local terrain, specular reflections, and location close to the centre of the planned landing ellipse led to the identification of the Beagle 2 lander. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels-which may have been caused by damage during landing-would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing.

Identification of the Beagle 2 lander on Mars

PubMed Central

Clemmet, J.; Croon, M.; Sims, M. R.; Pullan, D.; Muller, J.-P.; Tao, Y.; Xiong, S.; Putri, A. R.; Parker, T.; Turner, S. M. R.; Pillinger, J. M.

2017-01-01

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43° E, 11.53° N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the European Space Agency Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis from 174 km to 57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including red and blue-green colours, were obtained over the area of interest and searched, which allowed sub-pixel imaging using super high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, high reflectivity relative to the local terrain, specular reflections, and location close to the centre of the planned landing ellipse led to the identification of the Beagle 2 lander. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels—which may have been caused by damage during landing—would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing. PMID:29134081

Identification of the Beagle 2 lander on Mars

NASA Astrophysics Data System (ADS)

Bridges, J. C.; Clemmet, J.; Croon, M.; Sims, M. R.; Pullan, D.; Muller, J.-P.; Tao, Y.; Xiong, S.; Putri, A. R.; Parker, T.; Turner, S. M. R.; Pillinger, J. M.

2017-10-01

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43° E, 11.53° N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the European Space Agency Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis from 174 km to 57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including red and blue-green colours, were obtained over the area of interest and searched, which allowed sub-pixel imaging using super high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, high reflectivity relative to the local terrain, specular reflections, and location close to the centre of the planned landing ellipse led to the identification of the Beagle 2 lander. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels-which may have been caused by damage during landing-would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing.

Europa Lander Mission Concept (Artist Rendering)

NASA Image and Video Library

2017-02-08

This artist's rendering illustrates a conceptual design for a potential future mission to land a robotic probe on the surface of Jupiter's moon Europa. The lander is shown with a sampling arm extended, having previously excavated a small area on the surface. The circular dish on top is a dual-purpose high-gain antenna and camera mast, with stereo imaging cameras mounted on the back of the antenna. Three vertical shapes located around the top center of the lander are attachment points for cables that would lower the rover from a sky crane, which is envisioned as the landing system for this mission concept. http://photojournal.jpl.nasa.gov/catalog/PIA21048

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 visible in Viking Orbiter and MGS MOC images, though the actual location of VL-1 lies in a data dropout in the MOC image of the area. Additional information is contained in the original extended abstract.

Valles Marineris

NASA Image and Video Library

1998-06-08

A color image of Valles Marineris, the great canyon of Mars; north toward top. The scene shows the entire canyon system, over 3,000 km long and averaging 8 km deep, extending from Noctis Labyrinthus, the arcuate system of graben to the west, to the chaotic terrain to the east. This image is a composite of Viking medium-resolution images in black and white and low-resolution images in color; Mercator projection. The image extends from latitude 0 degrees to 20 degrees S. and from longitude 45 degrees to 102.5 degrees. The connected chasma or valleys of Valles Marineris may have formed from a combination of erosional collapse and structural activity. Layers of material in the eastern canyons might consist of carbonates deposited in ancient lakes. Huge ancient river channels began from Valles Marineris and from adjacent canyons and ran north. Many of the channels flowed north into Chryse Basin, which contains the site of the Viking 1 Lander and the future site of the Mars Pathfinder Lander. http://photojournal.jpl.nasa.gov/catalog/PIA00422

Opportunity Egress Aid Contacts Soil

NASA Technical Reports Server (NTRS)

2004-01-01

This image from the navigation camera on the Mars Exploration Rover Opportunity shows the rover's egress aid touching the martian soil at Meridiani Planum, Mars. The image was taken after the rear lander petal hyperextended in a manuever to tilt the lander forward. The maneuver pushed the front edge lower, placing the tips of the egress aids in the soil. The rover will drive straight ahead to exit the lander.

Europa Small Lander Design Concepts

NASA Astrophysics Data System (ADS)

Zimmerman, W. F.

2005-12-01

Title: Europa Small Lander Design Concepts Authors: Wayne F. Zimmerman, James Shirley, Robert Carlson, Tom Rivellini, Mike Evans One of the primary goals of NASA's Outer Planets Program is to revisit the Jovian system. A new Europa Geophysical Explorer (EGE) Mission has been proposed and is under evaluation. There is in addition strong community interest in a surface science mission to Europa. A Europa Lander might be delivered to the Jovian system with the EGE orbiter. A Europa Astrobiology Lander (EAL) Mission has also been proposed; this would launch sometime after 2020. The primary science objectives for either of these would most likely include: Surface imaging (both microscopic and near-field), characterization of surface mechanical properties (temperature, hardness), assessment of surface and near-surface organic and inorganic chemistry (volatiles, mineralogy, and compounds), characterization of the radiation environment (total dose and particles), characterization of the planetary seismicity, and the measurement of Europa's magnetic field. The biggest challenges associated with getting to the surface and surviving to perform science investigations revolve around the difficulty of landing on an airless body, the ubiquitous extreme topography, the harsh radiation environment, and the extreme cold. This presentation reviews some the recent design work on drop-off probes, also called "hard landers". Hard lander designs have been developed for a range of science payload delivery systems spanning small impactors to multiple science pods tethered to a central hub. In addition to developing designs for these various payload delivery systems, significant work has been done in weighing the relative merits of standard power systems (i.e., batteries) against radioisotope power systems. A summary of the power option accommodation benefits and issues will be presented. This work was performed at the Jet Propulsion Laboratory, California Institute of Technology, under a contract from NASA,

Robotic Arm Camera on Mars, with Lights Off

NASA Technical Reports Server (NTRS)

2008-01-01

This approximate color image is a view of NASA's Phoenix Mars Lander's Robotic Arm Camera (RAC) as seen by the lander's Surface Stereo Imager (SSI). This image was taken on the afternoon of the 116th Martian day, or sol, of the mission (September 22, 2008). The RAC is about 8 centimeters (3 inches) tall.

The SSI took images of the RAC to test both the light-emitting diodes (LEDs) and cover function. Individual images were taken in three SSI filters that correspond to the red, green, and blue LEDs one at a time. This yields proper coloring when imaging Phoenix's surrounding Martian environment.

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.

Soil on Phoenix Deck

NASA Technical Reports Server (NTRS)

2008-01-01

This image, taken by the Surface Stereo Imager (SSI) of NASA's Phoenix Lander, shows Martian soil piled on top of the spacecraft's deck and some of its instruments. Visible in the upper-left portion of the image are several wet chemistry cells of the lander's Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The instrument on the lower right of the image is the Thermal and Evolved-Gas Analyzer. The excess sample delivered to the MECA's sample stage can be seen on the deck in the lower left portion of the image.

This image was taken on Martian day, or sol, 142, on Saturday, Oct. 19, 2008. Phoenix landed on Mars' northern plains on May 25, 2008.

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

Dark Skies and Clouds Move in at Phoenix site

NASA Technical Reports Server (NTRS)

2008-01-01

Clouds of dust and ice swirl past the Surface Stereo Imager (SSI) camera on NASA's Phoenix Mars Lander in a series of images taken on the 132nd Martian day of the mission (Oct. 7, 2008). The images show the increase in storm activity and potential for snowfall.

The solar powered spacecraft was disabled by decreased light from heavy dust storms in the area a few weeks later. The last communication heard from the lander occurred on Nov. 2, 2008.

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

Composite View from Phoenix Lander

NASA Image and Video Library

2009-07-02

This mosaic of images from the Surface Stereo Imager camera on NASA Phoenix Mars Lander shows several trenches dug by Phoenix, plus a corner of the spacecraft deck and the Martian arctic plain stretching to the horizon.

Physical properties of the martian surface from the viking 1 lander: preliminary results.

PubMed

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

1976-08-27

The purpose of the physical properties experiment is to determine the characteristics of the martian "soil" based on the use of the Viking lander imaging system, the surface sampler, and engineering sensors. Viking 1 lander made physical contact with the surface of Mars at 11:53:07.1 hours on 20 July 1976 G.M.T. Twenty-five seconds later a high-resolution image sequence of the area around a footpad was started which contained the first information about surface conditions on Mars. The next image is a survey of the martian landscape in front of the lander, including a view of the top support of two of the landing legs. Each leg has a stroke gauge which extends from the top of the leg support an amount equal to the crushing experienced by the shock absorbers during touchdown. Subsequent images provided views of all three stroke gauges which, together with the knowledge of the impact velocity, allow determination of "soil" properties. In the images there is evidence of surface erosion from the engines. Several laboratory tests were carried out prior to the mission with a descent engine to determine what surface alterations might occur during a Mars landing. On sol 2 the shroud, which protected the surface sampler collector head from biological contamination, was ejected onto the surface. Later a cylindrical pin which dropped from the boom housing of the surface sampler during the modified unlatching sequence produced a crater (the second Mars penetrometer experiment). These two experiments provided further insight into the physical properties of the martian surface.

Physical properties of the martian surface from the Viking 1 lander: preliminary results

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

Shorthill, R.W.; Hutton, R.E.; Moore, H.J. II

1976-08-27

The purpose of the physical properties experiment is to determine the characteristics of the martian ''soil'' based on the use of the Viking lander imaging system, the surface sampler, and engineering sensors. Viking 1 lander made physical contact with the surface of Mars at 11:53:07.1 hours on 20 July 1976 G.M.T. Twenty-five seconds later a high-resolution image sequence of the area around a footpad was started which contained the first information about surface conditions on Mars. The next image is a survey of the martian landscape in front of the lander, including a view of the top support of twomore » of the landing legs. Each leg has a stroke gauge which extends from the top of the leg support an amount equal to the crushing experienced by the shock absorbers during touchdown. Subsequent images provided views of all three stroke gauges which, together with the knowledge of the impact velocity, allow determination of ''soil'' properties. In the images there is evidence of surface erosion from the engines. Several laboratory tests were carried out prior to the mission with a descent engine to determine what surface alterations might occur during a Mars landing. On sol 2 the shroud, which protected the surface sampler collector head from biological contamination, was ejected onto the surface. Later a cylindrical pin which dropped from the boom housing of the surface sampler during the modified unlatching sequence produced a crater (the second Mars penetrometer experiment). These two experiments provided further insight into the physical properties of the martian surface.« less

Nighttime Clouds in Martian Arctic (Accelerated Movie)

NASA Technical Reports Server (NTRS)

2008-01-01

An angry looking sky is captured in a movie clip consisting of 10 frames taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander.

The clip accelerates the motion. The images were take around 3 a.m. local solar time at the Phoenix site during Sol 95 (Aug. 30), the 95th Martian day since landing.

The swirling clouds may be moving generally in a westward direction over the lander.

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

Determination of the Beagle2 landing site

NASA Astrophysics Data System (ADS)

Trautner, R.; Manaud, N.; Michael, G.; Griffiths, A.; Beauvivre, S.; Koschny, D.; Coates, A.; Josset, J.-L.

2004-02-01

Beagle2 is the UK-led lander element on ESA's Mars Express mission, which will reach Mars in late December 2003. After separation from the Mars Express orbiter 6 days before the atmospheric entry, Beagle2 will descend to the Martian surface by means of ablative heat shields and parachutes. The impact will be cushioned by a set of airbags. The selected landing site at 11.6 deg N/90.75 deg E (IAU 2000 coordinates) is situated in the south-east of the center of Isidis Planitia, a sedimentary basin which is expected to meet the requirements of Beagle's scientific mission, the lander operations, and the entry, descent and landing systems. The exact determination of the Beagle2 landing site is important not only for the Beagle2 and MEX orbiter science investigations, but also for the reconstruction of Beagle's entry and descent trajectory. A precise determination of the Beagle2 position is not possible via the MELACOM radio link. Instead, a novel method based on celestial navigation is employed, which utilizes the Stereo Camera System on the lander for imaging the Martian night sky. The position data is then refined by comparing the landing site panorama images with high resolution orbiter images and laser altimeter data. This combination of celestial navigation with image data analysis for precision position determination will be applicable for many future missions as well.

MARS PATHFINDER CAMERA TEST IN SAEF-2

NASA Technical Reports Server (NTRS)

1996-01-01

In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), workers from the Jet Propulsion Laboratory (JPL) are conducting a systems test of the imager for the Mars Pathfinder. The imager (white and metallic cylindrical element close to hand of worker at left) is a specially designed camera featuring a stereo- imaging system with color capability provided by a set of selectable filters. It is mounted atop an extendable mast on the Pathfinder lander. Visible to the far left is the small rover which will be deployed from the lander to explore the Martian surface. Transmitting back to Earth images of the trail left by the rover will be one of the mission objectives for the imager. To the left of the worker standing near the imager is the mast for the low-gain antenna; the round high-gain antenna is to the right. Visible in the background is the cruise stage that will carry the Pathfinder on a direct trajectory to Mars. The Mars Pathfinder is one of two Mars-bound spacecraft slated for launch aboard Delta II expendable launch vehicles this year.

JPL Testbed Image of Airbag Retraction

NASA Technical Reports Server (NTRS)

2004-01-01

This image shows the deflated airbags retracted underneath the lander petal at the JPL In-Situ Instrument Laboratory. Retracting the airbags helps clear the path for the rover to roll off the lander and onto the martian surface.

Phoenix Lander Amid Disappearing Spring Ice

NASA Image and Video Library

2010-01-11

NASA Phoenix Mars Lander, its backshell and heatshield visible within this enhanced-color image of the Phoenix landing site taken on Jan. 6, 2010 by the High Resolution Imaging Science Experiment HiRISE camera on NASA Mars Reconnaissance Orbiter.

MOC's Highest Resolution View of Mars Pathfinder Landing Site

NASA Technical Reports Server (NTRS)

2000-01-01

[figure removed for brevity, see original site] (A) Mars Pathfinder site, left: April 1998; right: January 2000.

[figure removed for brevity, see original site] (B) top: April 1998; bottom: January 2000.

Can Mars Global Surveyor's 1.5 meter (5 ft) per pixel camera be used to find any evidence as to the fate of the Mars Polar Lander that was lost on December 3, 1999? One way to find out is to look for one of the other Mars landers and determine what, if anything, can be seen. There have been three successful Mars lander missions: Viking 1 (July 1976), Viking 2 (September 1976), and Mars Pathfinder (July 1997). Of these, the location of Mars Pathfinder is known the best because there are several distinct landmarks visible in the lander's images that help in locating the spacecraft. The MGS MOC Operations Team at Malin Space Science Systems has been tasked since mid-December 1999 with looking for the lost Polar Lander. Part of this effort has been to test the capabilities of MOC by taking a picture of the landing site of Mars Pathfinder.

An attempt to photograph the Pathfinder site was made once before, in April 1998, by turning the entire MGS spacecraft so that the camera could point at the known location of the Mars Pathfinder lander. Turning the MGS spacecraft like this is not a normal operation--it takes considerable planning, and disrupts the on-going, normal acquisition of science data. It took 3 attempts to succeed, but on April 22, 1998, MOC acquired the picture seen on the left side of Figure A, above. The three near-by major landmarks that were visible to the Pathfinder's cameras are labeled here (North Peak, Big Crater, Twin Peaks). It was known at the time that this image was not adequate to see the Pathfinder lander because the camera was not in focus and had a resolution of only 3.3 meters (11 ft) per pixel. In this and all other images shown here, north is up. All views of the 1998 MOC image are illuminated from the lower right, all views of the 2000 MOC image are illuminated from the lower left.

As part of the Polar Lander search effort, the Mars Pathfinder site was targeted again in December 1999 and January 2000. Like the 1998 attempt, the spacecraft had to be pointed off of its normal, nadir (straight-down) view. Like history repeating itself, it once again took 3 tries before the Pathfinder landing site was hit. The picture on the right side of Figure A, above, shows the new image that was acquired on January 16, 2000. The white box indicates the location shown in Figure B (above, right). The 1000 m scale bar equals 0.62 miles.

Figure B (above) shows a subsection of both the 1998 image (top, labeled SPO-1-25603) and the 2000 image (bottom, labeled m11-2414) projected at a scale of 3 meters (10 ft) per pixel. At this scale, the differences in camera focus and sunlight illumination angle are apparent, with the January 2000 image being both in focus and having better lighting conditions. In addition, the MGS spacecraft took the 2000 image from a lower altitude than in 1998, thus the image has better spatial resolution overall. The 500 m scale bar is equal to about 547 yards. The white box shows the location of images in Figure C, below.

[figure removed for brevity, see original site] (C) higher-resolution view; left: April 1998; right: January 2000.

[figure removed for brevity, see original site] D) Erroneous, preliminary identification of Mars Pathfinder location in January 2000 image. Subsequent analysis (Figures E & F, below) identified the correct spot.

The third figure (C, above) again shows portions of the April 1998 image (C, left) and January 2000 image (C, right), only this time they have been enlarged to a resolution of 0.75 meters (2.5 ft) per pixel. The intrinsic resolution of the January 2000 image is 1.5 meters (5 ft), so this is a 200% expanded view of the actual M11-02414 image. The circular features in this and the previous images are impact craters in various states of erosion. Some boulders (dark dots) can be seen near the crater in the lower left corner. The texture that runs diagonally across the scene from upper left toward lower right consists of ridges created by the giant floods that washed through the Pathfinder site from Ares and/or Tiu Vallis many hundreds of millions of years ago. These ridges and the troughs between them were also seen by the Pathfinder lander; their crests often covered with boulders and cobbles (which cannot be seen at the resolution of the MOC image). The 100 m scale bar is equal to 109 yards (which can be compared with a 100 yard U.S. football field). The Mars Pathfinder landing site is located near the center of this view.

The fourth picture, Figure D (above), shows a feature that was initially thought to be the Mars Pathfinder lander by MOC investigators. This and the following figures point out just how difficult it is to find a lander on the martian surface using the MGS MOC. Figure D was prepared early in the week following receipt of the new MOC image on January 17, 2000, and for several days it was believed that the lander had been found. As the subsequent two figures will show (E, and F, below), this location appears to be in error. How the features were misidentified is discussed below. Both Figure D and Figure F, showing possible locations of the Pathfinder lander in the MOC image, are enlarged by a factor of three over the intrinsic resolution of that image (that is, to a scale of 0.5 meters or about 1 ft, 7 inch per pixel). The right picture in Figure D shows sight-lines to the large horizon features--Big Crater, Twin Peaks, and North Peak--that were derived by the MOC team by looking at the images taken by the lander in 1997. After placing these lines on the overall image, there appeared to be two features close to the intersection of the sight-lines. Based upon the consistency of the size and shape of the lander as illuminated by sunlight in this image, the northern of the two candidate features (the small 'hump' at the center of both left and right pictures) was considered, at the time, to be the most likely. HOWEVER...

[figure removed for brevity, see original site] (E) Photoclinometry, Topography, and Revised Landing Site Location.

[figure removed for brevity, see original site] (F) Mars Pathfinder Landing Site; lander not resolved by MOC.

Later in the week following acquisition of the January 16, 2000, image (and over the following weekend), there was time for additional analysis to determine whether the rounded hump identified earlier in the week (Figure D, above) was, in fact, the Mars Pathfinder lander. A computer program that estimates relative topography in a MOC image from knowledge of the illumination (called 'shape-from-shading' or photoclinometry) was run to determine which parts of the landing site image are depressions, which are hills, and which are flat surfaces. The picture at the left in Figure E (above) shows the photoclinometry results for the area around the Pathfinder lander. The picture at the center of Figure E shows the same photoclinometry results overlain by an inset of a topographic map of the Pathfinder landing site derived by the U.S. Geological Survey Astrogeology Branch (Flagstaff, Arizona) from photogrammetry (parallax measurements) using images from Pathfinder's own stereo camera. By matching the features seen by MOC with those seen by the Pathfinder (the large arrows are examples of the matching), the location of the lander was refined and is now indicated in the picture on the right side of Figure E. The large, rounded hump previously identified as Pathfinder in Figure D (above), is more likely a large boulder that was seen in Pathfinder's images and named 'Couch' by the Pathfinder science team in 1997.

Figure F is summary of the results of this effort to find Mars Pathfinder: it shows that while the landing site of Mars Pathfinder can be identified, the lander itself cannot be seen. It is too small to be resolved in an image where each pixel acquired by the MOC covers a square of 1.5 meters (5 feet) to a side, given the contrast conditions on Mars and the MOC's ability to discriminate contrast. At this scale, Pathfinder is not much larger than two pixels, and the same is true of the lost Polar Lander.

No evidence has been found in the January 2000 MOC image of the aft portion of Mars Pathfinder's aeroshell or its parachute, either. If the aeroshell is laying on its side, as interpreted from Mars Pathfinder's images, then it would be very difficult to see this from orbit. Because Pathfinder did not image the parachute, it is not known how it may be configured on the surface--it could be wrapped around the aeroshell or a boulder, for example.

This effort to photograph the Mars Pathfinder lander demonstrates that it is extremely difficult to find a lander on the surface of Mars using the Mars Orbiter Camera aboard the MGS spacecraft. This analysis suggests that it is not very likely that the December 1999 Polar Lander will be found by MOC.

Viking lander camera geometry calibration report. Volume 1: Test methods and data reduction techniques

NASA Technical Reports Server (NTRS)

Wolf, M. B.

1981-01-01

The determination and removal of instrument signature from Viking Lander camera geometric data are described. All tests conducted as well as a listing of the final database (calibration constants) used to remove instrument signature from Viking Lander flight images are included. The theory of the geometric aberrations inherent in the Viking Lander camera is explored.

Robotic Arm Camera on Mars with Lights On

NASA Technical Reports Server (NTRS)

2008-01-01

This image is a composite view of NASA's Phoenix Mars Lander's Robotic Arm Camera (RAC) with its lights on, as seen by the lander's Surface Stereo Imager (SSI). This image combines images taken on the afternoon of Phoenix's 116th Martian day, or sol (September 22, 2008). The RAC is about 8 centimeters (3 inches) tall.

The SSI took images of the RAC to test both the light-emitting diodes (LEDs) and cover function. Individual images were taken in three SSI filters that correspond to the red, green, and blue LEDs one at a time. When combined, it appears that all three sets of LEDs are on at the same time. This composite image is not true color. The streaks of color extending from the LEDs are an artifact from saturated exposure.

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.

Microscopic Image of Martian Surface Material on a Silicone Substrate

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for larger version of Figure 1

This image taken by the Optical Microscope on NASA's Phoenix Mars Lander shows soil sprinkled from the lander's Robot Arm scoop onto a silicone substrate. The substrate was then rotated in front of the microscope. This is the first sample collected and delivered for instrumental analysis onboard a planetary lander since NASA's Viking Mars missions of the 1970s. It is also the highest resolution image yet seen of Martian soil.

The image is dominated by fine particles close to the resolution of the microscope. These particles have formed clumps, which may be a smaller scale version of what has been observed by Phoenix during digging of the surface material.

The microscope took this image during Phoenix's Sol 17 (June 11), or the 17th Martian day after landing. The scale bar is 1 millimeter (0.04 inch).

Zooming in on the Martian Soil

In figure 1, three zoomed-in portions are shown with an image of Martian soil particles taken by the Optical Microscope on NASA's Phoenix Mars Lander.

The left zoom box shows a composite particle. The top of the particle has a green tinge, possibly indicating olivine. The bottom of the particle has been reimaged at a different focus position in black and white (middle zoom box), showing that this is a clump of finer particles.

The right zoom box shows a rounded, glassy particle, similar to those which have also been seen in an earlier sample of airfall dust collected on a surface exposed during landing.

The shadows at the bottom of image are of the beams of the Atomic Force Microscope.

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.

Soil Sample Poised at TEGA Door

NASA Technical Reports Server (NTRS)

2008-01-01

This image was taken by NASA's Phoenix Mars Lander's Surface Stereo Imager on Sol 11 (June 5, 2008), the eleventh day after landing. It shows the Robotic Arm scoop containing a soil sample poised over the partially open door of the Thermal and Evolved-Gas Analyzer's number four cell, or oven.

Light-colored clods of material visible toward the scoop's lower edge may be part of the crusted surface material seen previously near the foot of the lander. The material inside the scoop has been slightly brightened in this image.

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.

Image quality prediction - An aid to the Viking lander imaging investigation on Mars

NASA Technical Reports Server (NTRS)

Huck, F. O.; Wall, S. D.

1976-01-01

Image quality criteria and image quality predictions are formulated for the multispectral panoramic cameras carried by the Viking Mars landers. Image quality predictions are based on expected camera performance, Mars surface radiance, and lighting and viewing geometry (fields of view, Mars lander shadows, solar day-night alternation), and are needed in diagnosis of camera performance, in arriving at a preflight imaging strategy, and revision of that strategy should the need arise. Landing considerations, camera control instructions, camera control logic, aspects of the imaging process (spectral response, spatial response, sensitivity), and likely problems are discussed. Major concerns include: degradation of camera response by isotope radiation, uncertainties in lighting and viewing geometry and in landing site local topography, contamination of camera window by dust abrasion, and initial errors in assigning camera dynamic ranges (gains and offsets).

Sampling Strategy

NASA Technical Reports Server (NTRS)

2008-01-01

Three locations to the right of the test dig area are identified for the first samples to be delivered to the Thermal and Evolved Gas Analyzer (TEGA), the Wet Chemistry Lab (WCL), and the Optical Microscope (OM) on NASA's Phoenix Mars Lander. These sampling areas are informally labeled 'Baby Bear', 'Mama Bear', and 'Papa Bear' respectively. This image was taken on the seventh day of the Mars mission, or Sol 7 (June 1, 2008) by the Surface Stereo Imager aboard NASA's Phoenix Mars Lander.

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

ARES I AND ARES V CONCEPT IMAGE

NASA Technical Reports Server (NTRS)

2008-01-01

THIS CONCEPT IMAGE SHOWS NASA'S NEXT GENERATION LAUNCH VEHICLE SYSTEMS STANDING SIDE BY SIDE. ARES I, LEFT, IS THE CREW LAUNCH VEHICLE THAT WILL CARRY THE ORION CREW EXPLORATION VEHICLE TO SPACE. ARES V IS THE CARGO LAUNCH VEHICLE THAT WILL DELIVER LARGE SCALE HARDWARE, INCLUDING THE LUNAR LANDER, TO SPACE.

Opportunity and Its Mother Ship

NASA Technical Reports Server (NTRS)

2004-01-01

This image captured by the Mars Exploration Rover Opportunity's navigation camera shows the rover and the now-empty lander that carried it 283 million miles to Meridiani Planum, Mars. Engineers received confirmation that Opportunity's six wheels rolled off the lander and onto martian soil at 3:02 a.m. PST, January 31, 2004, on the seventh martian day, or sol, of the mission. The rover, seen at the bottom of the image, is approximately 1 meter (3 feet) in front of the lander, facing north.

Network science landers for Mars

NASA Astrophysics Data System (ADS)

Harri, A.-M.; Marsal, O.; Lognonne, P.; Leppelmeier, G. W.; Spohn, T.; Glassmeier, K.-H.; Angrilli, F.; Banerdt, W. B.; Barriot, J. P.; Bertaux, J.-L.; Berthelier, J. J.; Calcutt, S.; Cerisier, J. C.; Crisp, D.; Dehant, V.; Giardini, D.; Jaumann, R.; Langevin, Y.; Menvielle, M.; Musmann, G.; Pommereau, J. P.; di Pippo, S.; Guerrier, D.; Kumpulainen, K.; Larsen, S.; Mocquet, A.; Polkko, J.; Runavot, J.; Schumacher, W.; Siili, T.; Simola, J.; Tillman, J. E.

1999-01-01

The NetLander Mission will deploy four landers to the Martian surface. Each lander includes a network science payload with instrumentation for studying the interior of Mars, the atmosphere and the subsurface, as well as the ionospheric structure and geodesy. The NetLander Mission is the first planetary mission focusing on investigations of the interior of the planet and the large-scale circulation of the atmosphere. A broad consortium of national space agencies and research laboratories will implement the mission. It is managed by CNES (the French Space Agency), with other major players being FMI (the Finnish Meteorological Institute), DLR (the German Space Agency), and other research institutes. According to current plans, the NetLander Mission will be launched in 2005 by means of an Ariane V launch, together with the Mars Sample Return mission. The landers will be separated from the spacecraft and targeted to their locations on the Martian surface several days prior to the spacecraft's arrival at Mars. The landing system employs parachutes and airbags. During the baseline mission of one Martian year, the network payloads will conduct simultaneous seismological, atmospheric, magnetic, ionospheric, geodetic measurements and ground penetrating radar mapping supported by panoramic images. The payloads also include entry phase measurements of the atmospheric vertical structure. The scientific data could be combined with simultaneous observations of the atmosphere and surface of Mars by the Mars Express Orbiter that is expected to be functional during the NetLander Mission's operational phase. Communication between the landers and the Earth would take place via a data relay onboard the Mars Express Orbiter.

Martian Sunrise at Phoenix Landing Site, Sol 101

NASA Technical Reports Server (NTRS)

2008-01-01

This sequence of nine images taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the sun rising on the morning of the lander's 101st Martian day after landing.

The images were taken on Sept. 5, 2008. The local solar times at the landing site for the nine images were between 1:23 a.m. and 1:41 a.m.

The landing site is on far-northern Mars, and the mission started in late northern spring. For nearly the entire first 90 Martian days of the mission, the sun never set below the horizon. As the amount of sunshine each day declined steadily after that, so has the amount of electricity available for the solar-powered spacecraft.

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.

Surface-material maps of Viking landing sites on Mars

NASA Technical Reports Server (NTRS)

Moore, H. J.; Keller, J. M.

1991-01-01

Researchers mapped the surface materials at the Viking landing sites on Mars to gain a better understanding of the materials and rock populations at the sites and to provide information for future exploration. The maps extent to about 9 m in front of each lander and are about 15 m wide - an area comparable to the area of a pixel in high resolution Viking Orbiter images. The maps are divided into the near and far fields. Data for the near fields are from 1/10 scale maps, umpublished maps, and lander images. Data for the far fields are from 1/20 scale contour maps, contoured lander camera mosaics, and lander images. Rocks are located on these maps using stereometric measurements and the contour maps. Frequency size distribution of rocks and the responses of soil-like materials to erosion by engine exhausts during landings are discussed.

How Phoenix Looks Under Itself

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

This is an animation of NASA's Phoenix Mars Lander reaching with its Robotic Arm and taking a picture of the surface underneath the lander. The image at the conclusion of the animation was taken by Phoenix's Robotic Arm Camera (RAC) on the eighth Martian day of the mission, or Sol 8 (June 2, 2008). The light feature in the middle of the image below the leg is informally called 'Holy Cow.' The dust, shown in the dark foreground, has been blown off of 'Holy Cow' by Phoenix's thruster engines.

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.

Conductivity Probe Inserted in Martian Soil, Sol 46

NASA Technical Reports Server (NTRS)

2008-01-01

This image taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the lander's Thermal and Electrical Conductivity Probe (TECP), at the end of the Robotic Arm, on the 46th Martian day, or sol, of the mission (July 11, 2008).

The TECP is inserted at a site called Vestri, which was monitored several times over the course of the mission. The probe's measurements at this site yielded evidence that water was exchanged, daily and seasonally, between the soil and atmosphere.

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

Solar Power Grid Unfurled

NASA Technical Reports Server (NTRS)

2008-01-01

Shown here is one of the first images taken by NASA's Phoenix Mars Lander of one of the octagonal solar panels, which opened like two handheld, collapsible fans on either side of the spacecraft. Beyond this view is a small slice of the north polar terrain of Mars.

The successfully deployed solar panels are critical to the success of the 90-day mission, as they are the spacecraft's only means of replenishing its power. Even before these images reached Earth, power readings from the spacecraft indicated to engineers that the solar panels were already at work recharging the spacecraft's batteries.

Before deploying the Surface Stereo Imager to take these images, the lander waited about 15 minutes for the dust to settle.

This image was taken by the spacecraft's Surface Stereo Imager on Sol, or Martian day, 0 (May 25, 2008).

This image has been geometrically corrected.

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.

Viking Lander 2 Anniversary

NASA Image and Video Library

2002-12-13

This portion of NASA Mars Odyssey image covers NASA 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. http://photojournal.jpl.nasa.gov/catalog/PIA04023

Rock Moved by Mars Lander Arm

NASA Technical Reports Server (NTRS)

2008-01-01

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

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

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

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

This image was taken at about 12:30 p.m., local solar time on Mars. The view is to the north northeast of the lander.

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

PIA05044

NASA Image and Video Library

2004-01-11

This mosaic image taken by the navigation camera on the Mars Exploration Rover Spirit represents an overhead view of the rover as it prepares to roll off the lander and onto the martian surface. The yellow arrow illustrates the direction the rover may take to roll safely off the lander. The rover was originally positioned to roll straight forward off the lander (south side of image). However, an airbag is blocking its path. To take this northeastern route, the rover must back up and perform what is likened to a 3-point turn in a cramped parking lot. http://photojournal.jpl.nasa.gov/catalog/PIA05044

'Bird's Eye' View of Egress

NASA Technical Reports Server (NTRS)

2004-01-01

[figure removed for brevity, see original site]

This mosaic image taken by the navigation camera on the Mars Exploration Rover Spirit represents an overhead view of the rover as it prepares to roll off the lander and onto the martian surface. The yellow arrow illustrates the direction the rover may take to roll safely off the lander. The rover was originally positioned to roll straight forward off the lander (south side of image). However, an airbag is blocking its path. To take this northeastern route, the rover must back up and perform what is likened to a 3-point turn in a cramped parking lot.

Solar Power Grid

NASA Technical Reports Server (NTRS)

2008-01-01

Shown here is one of the first images taken by NASA's Phoenix Mars Lander of one of the octagonal solar panels, which opened like two handheld, collapsible fans on either side of the spacecraft. Beyond this view is a small slice of the north polar terrain of Mars.

The successfully deployed solar panels are critical to the success of the 90-day mission, as they are the spacecraft's only means of replenishing its power. Even before these images reached Earth, power readings from the spacecraft indicated to engineers that the solar panels were already at work recharging the spacecraft's batteries.

Before deploying the Surface Stereo Imager to take these images, the lander waited about 15 minutes for the dust to settle.

This image was taken by the spacecraft's Surface Stereo Imager on Sol, or Martian day, 0 (May 25, 2008).

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

Pathfinder on Mars

NASA Technical Reports Server (NTRS)

1997-01-01

The Sojourner Rover deploys the -proton x-ray spectrometer onto the rock named Moe within the rock garden in this 75- image, color-enhanced mosaic taken by the imager on the lander. (Image of the rover in the rock garden was taken on a different day than the terrain image.) The view is to the southwest, with the Carl Sagan Memorial Station in the foreground and South Twin Peak on the horizon about 1 km from the lander. [Image processed at Jet Propulsion Laboratory, Pasadena, CA]

NOTE: original caption as published in Science Magazine

Digging Movie from Phoenix's Sol 18

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager on NASA's Phoenix Mars Lander recorded the images combined into this movie of the lander's Robotic Arm enlarging and combining the two trenches informally named 'Dodo' (left) and 'Goldilocks.'

The 21 images in this sequence were taken over a period of about 2 hours during Phoenix's Sol 18 (June 13, 2008), or the 18th Martian day since landing.

The main purpose of the Sol 18 dig was to dig deeper for learning the depth of a hard underlying layer. A bright layer, possibly ice, was increasingly exposed as the digging progressed. Further digging and scraping in the combined Dodo-Goldilocks trench was planned for subsequent sols.

The combined trench is about 20 centimeters (about 8 inches) wide. The depth at the end of the Sol 18 digging is 5 to 6 centimeters (about 2 inches).

The Goldilocks trench was the source of soil samples 'Baby Bear' and 'Mama Bear,' which were collected on earlier sols and delivered to instruments on the lander deck. The Dodo trench was originally dug for practice in collecting and depositing soil samples.

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.

Sojourner Rover View of Pathfinder Lander

NASA Technical Reports Server (NTRS)

1997-01-01

Image of Pathfinder Lander on Mars taken from Sojourner Rover left front camera on sol 33. The IMP (on the lattice mast) is looking at the rover. Airbags are prominent, and the meteorology mast is shown to the right. Lowermost rock is Ender, with Hassock behind it and Yogi on the other side of the lander.

NOTE: original caption as published in Science Magazine

A Mars airplane. [for Mars environment surveys

NASA Technical Reports Server (NTRS)

Clarke, V. C.; Kerem, A.; Lewis, R.

1979-01-01

An airplane specifically designed for Mars flight is described, emphasizing its conceivable role as an aerial surveyor for visual imaging, gamma-ray and IR reflectance spectroscopy, studies of atmospheric composition and dynamics, and gravity-field, magnetic-field, and electromagnetic sounding. Possible imaging systems and surveying tasks are considered, along with a plausible mission scenario for a fleet of 12 airplanes, which would be taken to Mars in squadrons of four by three Shuttle/IUS Twin Stage/spacecraft carriers. A basic configuration closely resembling that of a competition glider is examined, and four types of airplane are discussed: hydrazine-powered cruisers and landers and electrically powered cruisers and landers. Attention is given to navigation, guidance, and control avionics, vehicle weight, the use of composite materials for the wing, and flight testing on earth.

Phoenix Test Sample Site

NASA Technical Reports Server (NTRS)

2008-01-01

This image, acquired by NASA's Phoenix Mars Lander's Surface Stereo Imager on Sol 7, the seventh day of the mission (June 1, 2008), shows the so-called 'Knave of Hearts' first-dig test area to the north of the lander. The Robotic Arm's scraping blade left a small horizontal depression above where the sample was taken.

Scientists speculate that white material in the depression left by the dig could represent ice or salts that precipitated into the soil. This material is likely the same white material observed in the sample in the Robotic Arm's scoop.

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

Phoenix Test Sample Site in Color

NASA Technical Reports Server (NTRS)

2008-01-01

This color image, acquired by NASA's Phoenix Mars Lander's Surface Stereo Imager on Sol 7, the seventh day of the mission (June 1, 2008), shows the so-called 'Knave of Hearts' first-dig test area to the north of the lander. The Robotic Arm's scraping blade left a small horizontal depression above where the sample was taken.

Scientists speculate that white material in the depression left by the dig could represent ice or salts that precipitated into the soil. This material is likely the same white material observed in the sample in the Robotic Arm's scoop.

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.

Frost at the Viking Lander 2 Site

NASA Technical Reports Server (NTRS)

1977-01-01

Photo from Viking Lander 2 shows late-winter frost on the ground on Mars around the lander. The view is southeast over the top of Lander 2, and shows patches of frost around dark rocks. The surface is reddish-brown; the dark rocks vary in size from 10 centimeters (four inches) to 76 centimeters (30 inches) in diameter. This picture was obtained Sept. 25, 1977. The frost deposits were detected for the first time 12 Martian days (sols) earlier in a black-and-white image. Color differences between the white frost and the reddish soil confirm that we are observing frost. The Lander Imaging Team is trying to determine if frost deposits routinely form due to cold night temperatures, then disappear during the warmer daytime. Preliminary analysis, however, indicates the frost was on the ground for some time and is disappearing over many days. That suggests to scientists that the frost is not frozen carbon dioxide (dry ice) but is more likely a carbon dioxide clathrate (six parts water to one part carbon dioxide). Detailed studies of the frost formation and disappearance, in conjunction with temperature measurements from the lander's meteorology experiment, should be able to confirm or deny that hypothesis, scientists say.

Low Cost Precision Lander for Lunar Exploration

NASA Astrophysics Data System (ADS)

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

2004-12-01

For 60 years the US Defense Department has invested heavily in producing small, low mass, precision guided vehicles. The technologies matured under these programs include terrain-aided navigation, closed loop terminal guidance algorithms, robust autopilots, high thrust-to-weight propulsion, autonomous mission management software, sensors, and data fusion. These technologies will aid NASA in addressing New Millennium Science and Technology goals as well as the requirements flowing from the Vision articulated in January 2004. Establishing and resupplying a long term lunar presence will require automated landing precision not yet demonstrated. Precision landing will increase safety and assure mission success. In the DOD world, such technologies are used routinely and reliably. Hence, it is timely to generate a point design for a precise planetary lander useful for lunar exploration. In this design science instruments amount to 10 kg, 16% of the lander vehicle mass. This compares favorably with 7% for Mars Pathfinder and less than 15% for Surveyor. The mission design flies the lander in an inert configuration to the moon, relying on a cruise stage for navigation and TCMs. The lander activates about a minute before impact. A solid booster reduces the vehicle speed to 300-450 m/s. The lander is now about 2 minutes from touchdown and has 600 to 700 m/s delta-v capability, allowing for about 10 km of vehicle divert during terminal descent. This concept of operations is chosen because it closely mimics missile operational timelines used for decades: the vehicle remains inert in a challenging environment, then must execute its mission flawlessly on a moment's notice. The vehicle design consists of a re-plumbed propulsion system, using propellant tanks and thrusters from exoatmospheric programs. A redesigned truss provides hard points for landing gear, electronics, power supply, and science instruments. A radar altimeter and a Digital Scene Matching Area Correlator (DSMAC) provide data for the terminal guidance algorithms. DSMAC acquires high-resolution images for real-time correlation with a reference map. This system provides ownship position with a resolution comparable to the map. Since the DSMAC can sample at 1.5 mrad, any imaging acquired below 70 km altitude will surpass the resolution available from previous missions. DSMAC has a mode where image data are compressed and downlinked. This capability could be used to downlink live images during terminal guidance. Approximately 500 kbitps telemetry would be required to provide the first live descent imaging sequence since Ranger. This would provide unique geologic context imaging for the landing site. The development path to produce such a vehicle is that used to develop missiles. First, a pathfinder vehicle is designed and built as a test bed for hardware integration including science instruments. Second, a hover test vehicle would be built. Equipped with mass mockups for the science payload, the vehicle would otherwise be an exact copy of the flight vehicle. The hover vehicle would be flown on earth to demonstrate the proper function and integration of the propulsion system, autopilots, navigation algorithms, and guidance sensors. There is sufficient delta-v in the proposed design to take off from the ground, fly a ballistic arc to over 100 m altitude, then guide to a precision soft landing. Once the vehicle has flown safely on earth, then the validated design would be used to produce the flight vehicle. Since this leverages the billions of dollars DOD has invested in these technologies, it should be possible to land useful science payloads precisely on the lunar surface at relatively low cost.

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 1 made its final transmission to Earth November 11, 1982.

How Phoenix Looks Under Itself

NASA Image and Video Library

2008-06-04

NASA Phoenix Mars Lander reaching with its Robotic Arm and taking a picture of the surface underneath the lander. The light feature in the middle of the image below the leg is informally called Holy Cow.

The Camera of the MASCOT Asteroid Lander on Board Hayabusa 2

NASA Astrophysics Data System (ADS)

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

2017-07-01

The MASCOT Camera (MasCam) is part of the Mobile Asteroid Surface Scout (MASCOT) lander's science payload. MASCOT has been launched to asteroid (162173) Ryugu onboard JAXA's Hayabusa 2 asteroid sample return mission on Dec 3rd, 2014. It is scheduled to arrive at Ryugu in 2018, and return samples to Earth by 2020. MasCam was designed and built by DLR's Institute of Planetary Research, together with Airbus-DS Germany. The scientific goals of the MasCam investigation are to provide ground truth for the orbiter's remote sensing observations, provide context for measurements by the other lander instruments (radiometer, spectrometer and magnetometer), the orbiter sampling experiment, and characterize the geological context, compositional variations and physical properties of the surface (e.g. rock and regolith particle size distributions). During daytime, clear filter images will be acquired. During night, illumination of the dark surface is performed by an LED array, equipped with 4×36 monochromatic light-emitting diodes (LEDs) working in four spectral bands. Color imaging will allow the identification of spectrally distinct surface units. Continued imaging during the surface mission phase and the acquisition of image series at different sun angles over the course of an asteroid day will contribute to the physical characterization of the surface and also allow the investigation of time-dependent processes and to determine the photometric properties of the regolith. The MasCam observations, combined with the MASCOT hyperspectral microscope (MMEGA) and radiometer (MARA) thermal observations, will cover a wide range of observational scales and serve as a strong tie point between Hayabusa 2's remote-sensing scales (103-10^{-3} m) and sample scales (10^{-3}-10^{-6} m). The descent sequence and the close-up images will reveal the surface features over a broad range of scales, allowing an assessment of the surface's diversity and close the gap between the orbital observations and those made by the in-situ measurements. The MasCam is mounted inside the lander slightly tilted, such that the center of its 54.8° square field-of-view is directed towards the surface at an angle of 22° with respect to the surface plane. This is to ensure that both the surface close to the lander and the horizon are observable. The camera optics is designed according to the Scheimpflug principle, thus that the entire scene along the camera's depth of field (150 mm to infinity) is in focus. The camera utilizes a 1024×1024 pixel CMOS sensor sensitive in the 400-1000 nm wavelength range, peaking at 600-700 nm. Together with the f-16 optics, this yields a nominal ground resolution of 150 micron/px at 150 mm distance (diffraction limited). The camera flight model has undergone standard radiometric and geometric calibration both at the component and system (lander) level. MasCam relies on the use of wavelet compression to maximize data return within stringent mission downlink limits. All calibration and flight data products will be generated and archived in the Planetary Data System in PDS image format.

The surface of Mars: the view from the viking 2 lander.

PubMed

Mutch, T A; Grenander, S U; Jones, K L; Patterson, W; Arvidson, R E; Guinness, E A; Avrin, P; Carlston, C E; Binder, A B; Sagan, C; Dunham, E W; Fox, P L; Pieri, D C; Huck, F O; Rowland, C W; Taylor, G R; Wall, S D; Kahn, R; Levinthal, E C; Liebes, S; Tucker, R B; Morris, E C; Pollack, J B; Saunders, R S; Wolf, M R

1976-12-11

Viking 2 lander began imaging the surface of Mars at Utopia Planitia on 3 September 1976. The surface is a boulder-strewn reddish desert cut by troughs that probably form a polygonal network. A plateau can be seen to the east of the spacecraft, which for the most probable lander location is approximately the direction of a tongue of ejecta from the crater Mie. Boulders at the lander 2 site are generally more vesicular than those near lander i. Fines at both lander sites appear to be very fine-grained and to be bound in a duricrust. The pinkish color of the sky, similar to that observed at the lander I site, indicates suspension of surface material. However, the atmospheric optical depth is less than that at the lander I site. After dissipation of a cloud of dust stirred during landing, no changes other than those stemming from sampling activities have been detected in the landscape. No signs of large organisms are apparent at either landing site.

The surface of Mars - The view from the Viking 2 lander

NASA Technical Reports Server (NTRS)

Mutch, T. A.; Grenander, S. U.; Jones, K. L.; Patterson, W.; Arvidson, R. E.; Guinness, E. A.; Avrin, P.; Carlston, C. E.; Binder, A. B.; Sagan, C.

1976-01-01

Viking 2 lander began imaging the surface of Mars at Utopia Planitia on September 3, 1976. The surface is a boulder-strewn reddish desert cut by troughs that probably form a polygonal network. A plateau can be seen to the east of the spacecraft, which for the most probable lander location is approximately the dirction of a tongue of ejecta from the crater Mie. Boulders at the lander 2 site are generally more vesicular than those near lander 1. Fines at both lander sites appear to be very fine-grained and to be bound in a duricrust. The pinkish color of the sky, similar to that observed at the lander 1 site, indicates suspension of surface material. However, the atmospheric optical depth is less than that at the lander 1 site. After dissipation of a cloud of dust stirred during landing, no changes other than those stemming from sampling activities have been detected in the landscape. No signs of large organisms are apparent at either landing site.

Performance Characteristics of Lithium-Ion Prototype Batteries for Mars Surveyor Program 2001 Lander

NASA Technical Reports Server (NTRS)

Smart, M. C.; Ratnakumar, B. V.; Whitcanack, L.; Surampudi, S.; Byers, J.; Marsh, R. A.

2000-01-01

A viewgraph presentation outlines the scientific payload, expected launch date and tasks, and an image of the Mars Surveyor 2001 Lander components. The Lander's battery specifications are given. The program objectives for the Li-ion cells for the Lander are listed, and results performance evaluation and cycle life performance tests are outlined for different temperatures. Cell charge characteristics are described, and test data is presented for charge capacity at varying temperatures. Capacity retention and storage characteristics tests are described and results are shown.

Morning Frost on Martian Surface

NASA Technical Reports Server (NTRS)

2008-01-01

A thin layer of water frost is visible on the ground around NASA's Phoenix Mars Lander in this image taken by the Surface Stereo Imager at 6 a.m. on Sol 79 (August 14, 2008), the 79th Martian day after landing. The frost begins to disappear shortly after 6 a.m. as the sun rises on the Phoenix landing site.

The sun was about 22 degrees above the horizon when the image was taken, enhancing the detail of the polygons, troughs and rocks around the landing site.

This view is looking east southeast with the lander's eastern solar panel visible in the bottom lefthand corner of the image. The rock in the foreground is informally named 'Quadlings' and the rock near center is informally called 'Winkies.'

This false color image has been enhanced to show color variations.

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.

Viking 75 project: Viking lander system primary mission performance report

NASA Technical Reports Server (NTRS)

Cooley, C. G.

1977-01-01

Viking Lander hardware performance during launch, interplanetary cruise, Mars orbit insertion, preseparation, separation through landing, and the primary landed mission, with primary emphasis on Lander engineering and science hardware operations, the as-flown mission are described with respect to Lander system performance and anomalies during the various mission phases. The extended mission and predicted Lander performance is discussed along with a summary of Viking goals, mission plans, and description of the Lander, and its subsystem definitions.

Interannual, seasonal and diurnal Mars surface environmental cycles observed from Viking to Curiosity

NASA Astrophysics Data System (ADS)

Martinez, German; Vicente-Retortillo, Álvaro; Kemppinen, Osku; Fischer, Erik; Fairen, Alberto G.; Guzewich, Scott David; Haberle, Robert; Lemmon, Mark T.; Newman, Claire E.; Renno, Nilton O.; Richardson, Mark I.; Smith, Michael D.; De la Torre, Manuel; Vasavada, Ashwin R.

2016-10-01

We analyze in-situ environmental data from the Viking landers to the Curiosity rover to estimate atmospheric pressure, near-surface air and ground temperature, relative humidity, wind speed and dust opacity with the highest confidence possible. We study the interannual, seasonal and diurnal variability of these quantities at the various landing sites over a span of more than twenty Martian years to characterize the climate on Mars and its variability. Additionally, we characterize the radiative environment at the various landing sites by estimating the daily UV irradiation (also called insolation and defined as the total amount of solar UV energy received on flat surface during one sol) and by analyzing its interannual and seasonal variability.In this study we use measurements conducted by the Viking Meteorology Instrument System (VMIS) and Viking lander camera onboard the Viking landers (VL); the Atmospheric Structure Instrument/Meteorology (ASIMET) package and the Imager for Mars Pathfinder (IMP) onboard the Mars Pathfinder (MPF) lander; the Miniature Thermal Emission Spectrometer (Mini-TES) and Pancam instruments onboard the Mars Exploration Rovers (MER); the Meteorological Station (MET), Thermal Electrical Conductivity Probe (TECP) and Phoenix Surface Stereo Imager (SSI) onboard the Phoenix (PHX) lander; and the Rover Environmental Monitoring Station (REMS) and Mastcam instrument onboard the Mars Science Laboratory (MSL) rover.A thorough analysis of in-situ environmental data from past and present missions is important to aid in the selection of the Mars 2020 landing site. We plan to extend our analysis of Mars surface environmental cycles by using upcoming data from the Temperature and Wind sensors (TWINS) instrument onboard the InSight mission and the Mars Environmental Dynamics Analyzer (MEDA) instrument onboard the Mars 2020 mission.

Study of application of adaptive systems to the exploration of the solar system. Volume 3: Mars landed systems

NASA Technical Reports Server (NTRS)

1973-01-01

The results of a more detailed study of three missions to the surface of Mars: (1) an advanced lander, (2) a lander with a small tethered rover, and (3) a lander with a medium sized rover that operates independently of the lander for most of its functions but communicates with Earth through the lander are presented. For all three missions it was assumed that the Viking orbiter and lander would be used with modifications as required to improve the science package, to accommodate the rovers, and to handle the increased payloads.

Poro-elastic Rebound Along the Landers 1992 Earthquake Surface Rupture

NASA Technical Reports Server (NTRS)

Peltzer, G.; Rosen, P.; Rogez, F.; Hudnut, K.

1998-01-01

Maps of post-seismic surface displacement after the 1992, Landers, California earthquake, generated by interferometric processing of ERS-1 Synthetic Aperture Radar (SAR) images, reveal effects of various deformation processes near the 1992 surface rupture.

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.

Lander, Airbags, & Martian Terrain

NASA Image and Video Library

1997-07-05

Several objects have been imaged by the Imager for Mars Pathfinder (IMP) during the spacecraft's first day on Mars. Portions of the deflated airbags, part of one the lander's petals, soil, and several rocks are visible. The furrows in the soil were artificially produced by the retraction of the airbags after landing, which occurred at 10:07 a.m. PDT. http://photojournal.jpl.nasa.gov/catalog/PIA00616

Sojourner & Terrain

NASA Image and Video Library

1997-07-06

The undeployed Sojourner rover is seen still latched to a lander petal in this image, taken by the Imager for Mars Pathfinder (IMP) on Sol 1, the lander's first day on Mars. Portions of a petal and deflated airbag are in the foreground. The rectangular rock at right has been dubbed "Flat top," and may be a possible object of study for Sojourner's Alpha Proton X-Ray Spectrometer (APXS) instrument. The mismatched portion of image at left is a misregistered section of data. http://photojournal.jpl.nasa.gov/catalog/PIA00631

Stereo View of Phoenix Test Sample Site

NASA Technical Reports Server (NTRS)

2008-01-01

This anaglyph image, acquired by NASA's Phoenix Lander's Surface Stereo Imager on Sol 7, the seventh day of the mission (June 1, 2008), shows a stereoscopic 3D view of the so-called 'Knave of Hearts' first-dig test area to the north of the lander. The Robotic Arm's scraping blade left a small horizontal depression above where the sample was taken.

Scientists speculate that white material in the depression left by the dig could represent ice or salts that precipitated into the soil. This material is likely the same white material observed in the sample in the Robotic Arm's scoop.

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.

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.

Phoenix Makes an Impression on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

This view from the Surface Stereo Imager on NASA's Phoenix Mars Lander shows the first impression dubbed Yeti and looking like a wide footprint -- made on the Martian soil by the Robotic Arm scoop on Sol 6, the sixth Martian day of the mission, (May 31, 2008).

Touching the ground is the first step toward scooping up soil and ice and delivering the samples to the lander's experiments.

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

Viking lander camera radiometry calibration report, volume 2

NASA Technical Reports Server (NTRS)

Wolf, M. R.; Atwood, D. L.; Morrill, M. E.

1977-01-01

The requirements the performance validation, and interfaces for the RADCAM program, to convert Viking lander camera image data to radiometric units were established. A proposed algorithm is described, and an appendix summarizing the planned reduction of camera test data was included.

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.

Localization, Localization, Localization

NASA Technical Reports Server (NTRS)

Parker, T.; Malin, M.; Golombek, M.; Duxbury, T.; Johnson, A.; Guinn, J.; McElrath, T.; Kirk, R.; Archinal, B.; Soderblom, L.

2004-01-01

Localization of the two Mars Exploration Rovers involved three independent approaches to place the landers with respect to the surface of Mars and to refine the location of those points on the surface with the Mars control net: 1) Track the spacecraft through entry, descent, and landing, then refine the final roll stop position by radio tracking and comparison to images taken during descent; 2) Locate features on the horizon imaged by the two rovers and compare them to the MOC and THEMIS VIS images, and the DIMES images on the two MER landers; and 3) 'Check' and refine locations by acquisition of MOC 1.5 meter and 50 cm/pixel images.

Life Support Systems for a New Lunar Lander

NASA Technical Reports Server (NTRS)

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

2012-01-01

A life support system concept has been developed for a new NASA lunar lander concept. The ground rules and assumptions driving the design of this vehicle are different from the Constellation Altair vehicle, and have led to a different design solution. For example, this concept assumes that the lander vehicle arrives in lunar orbit independently of the crew. It loiters in lunar orbit for months before rendezvousing with the Orion Multi-Purpose Crew Vehicle (MPCV), resulting in the use of solar power for this new lander, rather than fuel cells that provided product water to the life support system in the Altair vehicle. Without the need to perform a single Lunar Orbit Insertion burn for both the lander and the MPCV, the modules do not have to be centered in the same way, so the new lander has a smaller ascent module than Altair and a large habitat rather than a small airlock. This new lander utilizes suitport technology to perform EVAs from the habitat, which leads to significantly different requirements for the pressure control system. This paper describes the major trades and resulting concept design for the life support system of a new lunar lander concept. I

Life Support Systems for a New Lunar Lander

NASA Technical Reports Server (NTRS)

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

2011-01-01

A life support system concept has been developed for a new NASA lunar lander concept. The ground rules and assumptions driving the design of this vehicle are different from the Constellation Altair vehicle, and have led to a different design solution. For example, this concept assumes that the lander vehicle arrives in lunar orbit independently of the crew. It loiters in lunar orbit for months before rendezvousing with the Orion Multi-Purpose Crew Vehicle (MPCV), resulting in the use of solar power for this new lander, rather than fuel cells that provided product water to the life support system in the Altair vehicle. Without the need to perform a single Lunar Orbit Insertion burn for both the lander and the MPCV, the modules do not have to be centered in the same way, so the new lander has a smaller ascent module than Altair and a large habitat rather than a small airlock. This new lander utilizes suitport technology to perform EVAs from the habitat, which leads to significantly different requirements for the pressure control system. This paper describes the major trades and resulting concept design for the life support system of a new lunar lander concept.

Viking High-Resolution Topography and Mars '01 Site Selection: Application to the White Rock Area

NASA Astrophysics Data System (ADS)

Tanaka, K. L.; Kirk, Randolph L.; Mackinnon, D. J.; Howington-Kraus, E.

1999-06-01

Definition of the local topography of the Mars '01 Lander site is crucial for assessment of lander safety and rover trafficability. According to Golombek et al., steep surface slopes may (1) cause retro-rockets to be fired too early or late for a safe landing, (2) the landing site slope needs to be < 1deg to ensure lander stability, and (3) a nearly level site is better for power generation of both the lander and the rover and for rover trafficability. Presently available datasets are largely inadequate to determine surface slope at scales pertinent to landing-site issues. Ideally, a topographic model of the entire landing site at meter-scale resolution would permit the best assessment of the pertinent topographic issues. MOLA data, while providing highly accurate vertical measurements, are inadequate to address slopes along paths of less than several hundred meters, because of along-track data spacings of hundreds of meters and horizontal errors in positioning of 500 to 2000 m. The capability to produce stereotopography from MOC image pairs is not yet in hand, nor can we necessarily expect a suitable number of stereo image pairs to be acquired. However, for a limited number of sites, high-resolution Viking stereo imaging is available at tens of meters horizontal resolution, capable of covering landing-ellipse sized areas. Although we would not necessarily suggest that the chosen Mars '01 Lander site should be located where good Viking stereotopography is available, an assessment of typical surface slopes at these scales for a range of surface types may be quite valuable in landing-site selection. Thus this study has a two-fold application: (1) to support the proposal of White Rock as a candidate Mars '01 Lander site, and (2) to evaluate how Viking high resolution stereotopography may be of value in the overall Mars '01 Lander site selection process.

Cooperative Lander-Surface/Aerial Microflyer Missions for Mars Exploration

NASA Technical Reports Server (NTRS)

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

2004-01-01

Concepts are being investigated for exploratory missions to Mars based on Bioinspired Engineering of Exploration Systems (BEES), which is a guiding principle of this effort to develop biomorphic explorers. The novelty lies in the use of a robust telecom architecture for mission data return, utilizing multiple local relays (including the lander itself as a local relay and the explorers in the dual role of a local relay) to enable ranges 10 to 1,000 km and downlink of color imagery. As illustrated in Figure 1, multiple microflyers that can be both surface or aerially launched are envisioned in shepherding, metamorphic, and imaging roles. These microflyers imbibe key bio-inspired principles in their flight control, navigation, and visual search operations. Honey-bee inspired algorithms utilizing visual cues to perform autonomous navigation operations such as terrain following will be utilized. The instrument suite will consist of a panoramic imager and polarization imager specifically optimized to detect ice and water. For microflyers, particularly at small sizes, bio-inspired solutions appear to offer better alternate solutions than conventional engineered approaches. This investigation addresses a wide range of interrelated issues, including desired scientific data, sizes, rates, and communication ranges that can be accomplished in alternative mission scenarios. The mission illustrated in Figure 1 offers the most robust telecom architecture and the longest range for exploration with two landers being available as main local relays in addition to an ephemeral aerial probe local relay. The shepherding or metamorphic plane are in their dual role as local relays and image data collection/storage nodes. Appropriate placement of the landing site for the scout lander with respect to the main mission lander can allow coverage of extremely large ranges and enable exhaustive survey of the area of interest. In particular, this mission could help with the path planning and risk mitigation in the traverse of the long-distance surface explorer/rover. The basic requirements of design and operation of BEES to implement the scenarios are discussed. Terrestrial applications of such concepts include distributed aerial/surface measurements of meteorological events, i.e., storm watch, seismic monitoring, reconnaissance, biological chemical sensing, search and rescue, surveillance, autonomous security/ protection agents, and/or delivery and lateral distribution of agents (sensors, surface/subsurface crawlers, clean-up agents). Figure 2 illustrates an Earth demonstration that is in development, and its implementation will illustrate the value of these biomorphic mission concepts.

Phoenix's Wet Chemistry Laboratory Units

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows four Wet Chemistry Laboratory units, part of the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA) instrument on board NASA's Phoenix Mars Lander. This image was taken before Phoenix's launch on August 4, 2007.

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.

Maps of the Martian Landing Sites and Rover Traverses: Viking 1 and 2, Mars Pathfinder, and Phoenix Landers, and the Mars Exploration Rovers.

NASA Astrophysics Data System (ADS)

Parker, T. J.; Calef, F. J., III; Deen, R. G.; Gengl, H.

2016-12-01

The traverse maps produced tactically for the MER and MSL rover missions are the first step in placing the observations made by each vehicle into a local and regional geologic context. For the MER, Phoenix and MSL missions, 25cm/pixel HiRISE data is available for accurately localizing the vehicles. Viking and Mars Pathfinder, however, relied on Viking Orbiter images of several tens of m/pixel to triangulate to horizon features visible both from the ground and from orbit. After Pathfinder, MGS MOC images became available for these landing sites, enabling much better correlations to horizon features and localization predictions to be made, that were then corroborated with HiRISE images beginning 9 years ago. By combining topography data from MGS, Mars Express, and stereo processing of MRO CTX and HiRISE images into orthomosaics (ORRs) and digital elevation models (DEMs), it is possible to localize all the landers and rover positions to an accuracy of a few tens of meters with respect to the Mars global control net, and to better than half a meter with respect to other features within a HiRISE orthomosaic. JPL's MIPL produces point clouds of the MER Navcam stereo images that can be processed into 1cm/pixel ORR/DEMs that are then georeferenced to a HiRISE/CTX base map and DEM. This allows compilation of seamless mosaics of the lander and rover camera-based ORR/DEMs with the HiRISE ORR/DEM that can be viewed in 3 dimensions with GIS programs with that capability. We are re-processing the Viking Lander, Mars Pathfinder, and Phoenix lander data to allow similar ORR/DEM products to be made for those missions. For the fixed landers and Spirit, we will compile merged surface/CTX/HiRISE ORR/DEMs, that will enable accurate local and regional mapping of these landing sites, and allow comparisons of the results from these missions to be made with current and future surface missions.

"Shark"

NASA Image and Video Library

1997-10-14

This false color composite image from the Pathfinder lander shows the rock "Shark" at upper right (Shark is about 0.69 m wide, 0.40 m high, and 6.4 m from the lander). The rock looks like a conglomerate in Sojourner rover images, but only the large elements of its surface textures can be seen here. This demonstrates the usefulness of having a robot rover geologist able to examine rocks up close. http://photojournal.jpl.nasa.gov/catalog/PIA00986

Microscopic Materials on a Magnet

NASA Technical Reports Server (NTRS)

2008-01-01

These images show a comparison of the weak magnet OM7 from the Optical Microscope on NASA's Phoenix Mars Lander before (left) and after (right) soil deposition.

The microscope took the left image during Phoenix's Sol 15 (June 10, 2008) and the right image during Sol 21 (Jun 16, 2008).

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

The MVACS Surface Stereo Imager on Mars Polar Lander

NASA Astrophysics Data System (ADS)

Smith, P. H.; Reynolds, R.; Weinberg, J.; Friedman, T.; Lemmon, M. T.; Tanner, R.; Reid, R. J.; Marcialis, R. L.; Bos, B. J.; Oquest, C.; Keller, H. U.; Markiewicz, W. J.; Kramm, R.; Gliem, F.; Rueffer, P.

2001-08-01

The Surface Stereo Imager (SSI), a stereoscopic, multispectral camera on the Mars Polar Lander, is described in terms of its capabilities for studying the Martian polar environment. The camera's two eyes, separated by 15.0 cm, provide the camera with range-finding ability. Each eye illuminates half of a single CCD detector with a field of view of 13.8° high by 14.3° wide and has 12 selectable filters between 440 and 1000 nm. The f18 optics have a large depth of field, and no focusing mechanism is required; a mechanical shutter is avoided by using the frame transfer capability of the 528 × 512 CCD. The resolving power of the camera, 0.975 mrad/pixel, is the same as the Imager for Mars Pathfinder camera, of which it is nearly an exact copy. Specially designed targets are positioned on the Lander; they provide information on the magnetic properties of wind-blown dust, and radiometric standards for calibration. Several experiments beyond the requisite color panorama are described in detail: contour mapping of the local terrain, multispectral imaging of interesting features (possibly with ice or frost in shaded spots) to study local mineralogy, and atmospheric imaging to constrain the properties of the haze and clouds. Eight low-transmission filters are included for imaging the Sun directly at multiple wavelengths to give SSI the ability to measure dust opacity and potentially the water vapor content. This paper is intended to document the functionality and calibration of the SSI as flown on the failed lander.

Spectral mixture modeling - A new analysis of rock and soil types at the Viking Lander 1 site. [on Mars

NASA Technical Reports Server (NTRS)

Adams, J. B.; Smith, M. O.; Johnson, P. E.

1986-01-01

A Viking Lander 1 image was modeled as mixtures of reflectance spectra of palagonite dust, gray andesitelike rock, and a coarse rocklike soil. The rocks are covered to varying degrees by dust but otherwise appear unweathered. Rocklike soil occurs as lag deposits in deflation zones around stones and on top of a drift and as a layer in a trench dug by the lander. This soil probably is derived from the rocks by wind abrasion and/or spallation. Dust is the major component of the soil and covers most of the surface. The dust is unrelated spectrally to the rock but is equivalent to the global-scale dust observed telescopically. A new method was developed to model a multispectral image as mixtures of end-member spectra and to compare image spectra directly with laboratory reference spectra. The method for the first time uses shade and secondary illumination effects as spectral end-members; thus the effects of topography and illumination on all scales can be isolated or removed. The image was calibrated absolutely from the laboratory spectra, in close agreement with direct calibrations. The method has broad applications to interpreting multispectral images, including satellite images.

Highest Resolution Image of Dust and Sand Yet Acquired on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] [figure removed for brevity, see original site] [figure removed for brevity, see original site] Click on image for Figure 1Click on image for Figure 2Click on image for Figure 3

This mosaic of four side-by-side microscope images (one a color composite) was acquired by the Optical Microscope, a part of the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA) instrument suite on NASA's Phoenix Mars Lander. Taken on the ninth Martian day of the mission, or Sol 9 (June 3, 2008), the image shows a 3 millimeter (0.12 inch) diameter silicone target after it has been exposed to dust kicked up by the landing. It is the highest resolution image of dust and sand ever acquired on Mars. The silicone substrate provides a sticky surface for holding the particles to be examined by the microscope.

Martian Particles on Microscope's Silicone Substrate In figure 1, the particles are on a silcone substrate target 3 millimeters (0.12 inch) in diameter, which provides a sticky surface for holding the particles while the microscope images them. Blow-ups of four of the larger particles are shown in the center. These particles range in size from about 30 microns to 150 microns (from about one one-thousandth of an inch to six one-thousandths of an inch).

Possible Nature of Particles Viewed by Mars Lander's Optical Microscope In figure 2, the color composite on the right was acquired to examine dust that had fallen onto an exposed surface. The translucent particle highlighted at bottom center is of comparable size to white particles in a Martian soil sample (upper pictures) seen two sols earlier inside the scoop of Phoenix's Robotic Arm as imaged by the lander's Robotic Arm Camera. The white particles may be examples of the abundant salts that have been found in the Martian soil by previous missions. Further investigations will be needed to determine the white material's composition and whether translucent particles like the one in this microscopic image are found in Martian soil samples.

Scale of Phoenix Optical Microscope Images This set of pictures in figure 3 gives context for the size of individual images from the Optical Microscope on NASA's Mars Phoenix Lander.

The picture in the upper left was taken on Mars by the Surface Stereo Imager on Phoenix. It shows a portion of the microscope's sample stage exposed to accept a sample. In this case, the sample was of dust kicked up by the spacecraft thrusters during landers. Later samples will include soil delivered by the Robotic Arm.

The other pictures were taken on Earth. They show close-ups of circular substrates on which the microscopic samples rest when the microscope images them. Each circular substrate target is 3 millimeters (about one-tenth of an inch) in diameter. Each image taken by the microscope covers and area 2 millimeters by 1 millimeter (0.08 inch by 0.04 inch), the size of a large grain of sand.

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.

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.

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

NASA Image and Video Library

2018-02-20

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

Viking survey paper

NASA Technical Reports Server (NTRS)

Soffen, G.

1976-01-01

The paper reviews Viking injection into Mars orbit, the landing, and the Orbiter. The following Viking investigations are discussed: the search for life (photosynthetic analysis, metabolic analysis, and respiration), molecular analysis, inorganic chemistry, water detection, thermal mapping, radio science, and physical and seismic characteristics. Also considered are the imaging system, the lander camera, entry science, and Mars weather.

Eifel field operation campaign supporting Moon Mars and NEO exploration

NASA Astrophysics Data System (ADS)

Kamps, Oscar; Foing, Bernard H.; Offringa, Marloes

2016-07-01

As follow-up on the 2009 Eifel field campaign new field tests with our ExoGeoLab lander were conducted in November 2015 and February 2016. The two phase campaign was used to test the usability of a mock-up lander as test bench for experiments and its remote control in a Moon, Mars analogue environment. In a real mission such a lander could be used in a robotic or manned mission as scientific tool for scientists on Earth to do preliminary study on in-situ collected rocks. This could be useful for example for a sample return mission where scientists on Earth can determine if sample is interesting enough for a more detailed study. The prototype lander is one of the components of the ExoGeoLab project from ESA and ILEWG. Several student projects have prepared the lander for a geological field campaign in lunar and Martian analogue terrain. The lander can be divided in three sections which are used to store several components of the lander. The lower compartment can be used to store a rover or used as laboratory. The middle compartment is used for the lander computer(s), spectrometers and the associated cables. The top plate is used for a telescope which in our case is used to observe the environment around the lander and to guide astronauts during their EVA. As closest volcanic are there is chosen to do the Eifel area, Germany. Several stages of volcanism from Devon till Quaternary resulted in a variation of rocks which is analogue to volcanic rocks from Moon, Mars and other near Earth objects. Several topics we would like to test were pre-defined. Functional tests and demo were performed at European astronaut centre prior to the campaign. The latest updates with respect to the remote control were tested. The pressurised transport vehicle was equipped as remote base for (scientific) support during the campaign. The new instrument set-up were tested and some spectra were measured on collected rocks. The telescope was used to study the environment around the lander, selecting sites of interest for EVA, and as support for astronauts on both safety as science. From this campaign some lessons were learned and are points of improvement for future campaigns. One of the most important is to make the whole lander more robust. Several times some systems were not working correctly and someone had to repair. To make it more self-contained a stable cable system and power supply is needed. The new set-up of the spectrometer and sample holder seemed to work fine with the sun as illumination source. For future campaigns there should be a good artificial source as alternative or complement for solar illumination. The telescope provided a good image with a lot of details of the volcanic ash stratigraphy, but we have experienced the importance for a wider view to have a better understanding of the context of the telescope view. An alternative for an ad-hoc network is preferred. Four computers and two networks seemed to interfere which made it impossible to use systems on the lander at the same time. With the share screen function there was some delay in controlling the computer. Next campaign we would like to have the remote support separated from the field location so the people which have to support astronauts have no understanding of the area. Acknowledgment: We would like to thank people from ESTEC , EAC, and DLR for their support during the campaign.

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.

Concept study for a Venus Lander Mission to Analyze Atmospheric and Surface Composition

NASA Astrophysics Data System (ADS)

Kumar, K.; Banks, M. E.; Benecchi, S. D.; Bradley, B. K.; Budney, C. J.; Clark, G. B.; Corbin, B. A.; James, P. B.; O'Brien, R. C.; Rivera-Valentin, E. G.; Saltman, A.; Schmerr, N. C.; Seubert, C. R.; Siles, J. V.; Stickle, A. M.; Stockton, A. M.; Taylor, C.; Zanetti, M.; JPL Team X

2011-12-01

We present a concept-level study of a New Frontiers class, Venus lander mission that was developed during Session 1 of NASA's 2011 Planetary Science Summer School, hosted by Team X at JPL. Venus is often termed Earth's sister planet, yet they have evolved in strikingly different ways. Venus' surface and atmosphere dynamics, and their complex interaction are poorly constrained. A lander mission to Venus would enable us to address a multitude of outstanding questions regarding the geological evolution of the Venusian atmosphere and crust. Our proposed mission concept, VenUs Lander for Composition ANalysis (VULCAN), is a two-component mission, consisting of a lander and a carrier spacecraft functioning as relay to transmit data to Earth. The total mission duration is 150 days, with primary science obtained during a 1-hour descent through the atmosphere and a 2-hour residence on the Venusian surface. In the atmosphere, the lander will provide new data on atmospheric evolution by measuring dominant and trace gas abundances, light stable isotopes, and noble gas isotopes with a neutral mass spectrometer. It will make important meteorological observations of mid-lower atmospheric dynamics with pressure and temperature sensors and obtain unprecedented, detailed imagery of surface geomorphology and properties with a descent Near-IR/VIS camera. A nepholometer will provide new constraints on the sizes of suspended particulate matter within the lower atmosphere. On the surface, the lander will quantitatively investigate the chemical and mineralogical evolution of the Venusian crust with a LIBS-Raman spectrometer. Planetary differentiation processes recorded in heavy elements will be evaluated using a gamma-ray spectrometer. The lander will also provide the first stereo images for evaluating the geomorphologic/volcanic evolution of the Venusian surface, as well as panoramic views of the sample site using multiple filters, and detailed images of unconsolidated material and rock textures from a microscopic imager. Our mission proposal will enable the construction of a unique Venus test facility that will attract a new generation of scientists to Venus science. With emphasis on flight heritage, we demonstrate our cost basis and risk mitigation strategies to ensure that the VULCAN mission can be conducted within the requirements and constraints of the New Frontiers Program.

Science Experiments of a Jupiter Trojan asteroid in the Solar Power Sail Mission

NASA Astrophysics Data System (ADS)

Okada, T.; Kebukawa, Y.; Aoki, J.; Kawai, Y.; Ito, M.; Yano, H.; Okamoto, C.; Matsumoto, J.; Bibring, J. P.; Ulamec, S.; Jaumann, R.; Iwata, T.; Mori, O.; Kawaguchi, J.

2017-12-01

A Jupiter Trojan asteroid mission using a large area solar power sail (SPS) is under study in JAXA in collaboration with DLR and CNES. The asteroid will be investigated through remote sensing, followed by in situ in-depth observations on the asteroid with a lander. A sample-return is also studied as an option. LUCY has been selected as the NASA's future Discovery class mission which aims at understanding the diversity of Jupiter Trojans by multiple flybys, complementally to the SPS mission. The SPS is a candidate of the next medium class space science mission in Japan. The 1.4-ton spacecraft will carry a 100-kg class lander and 20-kg mission payloads on it. Its launch is expected in mid 2020s, and will take at least 11 years to visit a Jupiter Trojan asteroid. During the cruise phase, science experiments will be performed such as an infrared astronomy, a very long baseline gamma ray interferometry, and dust and magnetic field measurements. A classical static model of solar system suggests that the Jupiter Trojans were formed around the Jupiter region, while a dynamical model such as Nice model indicates that they formed at the far end of the solar system and then scattered inward due to a dynamical migration of giant planets. The physical, mineralogical, organics and isotopic distribution in the heliocentric distance could solve their origin and evolution of the solar system. A global mapping of the asteroid from the mothership will be conducted such as high-resolved imaging, NIR and TIR imaging spectrometry, and radar soundings. The lander will characterize the asteroid with geological, mineralogical, and geophysical observations using a panoramic camera, an infrared hyperspectral imager, a magnetometer, and a thermal radiometer. These samples will be measured by a high resolved mass spectrometer (HRMS) to investigate isotopic ratios of hydrogen, nitrogen, oxygen, as well as organic species.

Microscopic Comparison of Airfall Dust to Martian Soil

NASA Technical Reports Server (NTRS)

2008-01-01

This pair of images taken by the Optical Microscope on NASA's Phoenix Mars Lander offers a side-by-side comparison of an airfall dust sample collected on a substrate exposed during landing (left) and a soil sample scooped up from the surface of the ground beside the lander. In both cases the sample is collected on a silicone substrate, which provides a sticky surface holding sample particles for observation by the microscope.

Similar fine particles at the resolution limit of the microscope are seen in both samples, indicating that the soil has formed from settling of dust.

The microscope took the image on the left during Phoenix's Sol 9 (June 3, 2008), or the ninth Martian day after landing. It took the image on the right during Sol 17 (June 11, 2008).

The scale bar is 1 millimeter (0.04 inch).

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.

A Fairy-Tale Landscape

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

Fun, fairy-tale nicknames have been assigned to features in this animated view of the workspace reachable by the robotic arm of NASA's Phoenix Mars Lander. For example, 'Sleepy Hollow' denotes a trench and 'Headless' designates a rock.

A 'National Park,' marked by purple text and a purple arrow, has been set aside for protection until scientists and engineers have tested the operation of the robotic scoop. First touches with the scoop will be to the left of the 'National Park' line.

Scientists use such informal names for easy identification of features of interest during the mission.

In this view, rocks are circled in yellow, other areas of interest in green. The images were taken by the lander's 7-foot mast camera, called the Surface Stereo Imager.

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.

Microscope Image of Scavenged Particles

NASA Technical Reports Server (NTRS)

2008-01-01

This image from NASA's Phoenix Mars Lander's Optical Microscope shows a strongly magnetic surface which has scavenged particles from within the microscope enclosure before a sample delivery from the lander's Robotic Arm. The particles correspond to the larger grains seen in fine orange material that makes up most of the soil at the Phoenix site. They vary in color, but are of similar size, about one-tenth of a millimeter.

As the microscope's sample wheel moved during operation, these particles also shifted, clearing a thin layer of the finer orange particles that have also been collected. Together with the previous image, this shows that the larger grains are much more magnetic than the fine orange particles with a much larger volume of the grains being collected by the magnet. The image is 2 milimeters across.

It is speculated that the orange material particles are a weathering product from the larger grains, with the weathering process both causing a color change and a loss of magnetism.

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.

Microscope Image of a Martian Soil Surface Sample

NASA Technical Reports Server (NTRS)

2008-01-01

This is the closest view of the material underneath NASA's Phoenix Mars Lander. This sample was taken from the top centimeter of the Martian soil, and this image from the lander's Optical Microscope demonstrates its overall composition.

The soil is mostly composed of fine orange particles, and also contains larger grains, about a tenth of a millimeter in diameter, and of various colors. The soil is sticky, keeping together as a slab of material on the supporting substrate even though the substrate is tilted to the vertical.

The fine orange grains are at or below the resolution of the Optical Microscope. Mixed into the soil is a small amount&mdashabout 0.5 percent&mdashof white grains, possibly of a salt. The larger grains range from black to almost transparent in appearance. At the bottom of the image, the shadows of the Atomic Force Microscope (AFM) beams are visible. This image is 1 millimeter x 2 millimeters.

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.

Ice Cold Sunrise on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

From the location of NASA's Phoenix Mars Lander, above the Martian arctic circle, the sun does not set during the peak of the Martian summer.

This period of maximum solar energy is past on Sol 86, the 86th Martian day after the Phoenix landing, the sun fully set behind a slight rise to the north for about half an hour.

This red-filter image taken by the lander's Surface Stereo Imager, shows the sun rising on the morning of sol 90, Aug. 25, 2008, the last day of the Phoenix nominal mission.

The image was taken at 51 minutes past midnight local solar time during the slow sunrise that followed a 75 minute 'night.' The skylight in the image is light scattered off atmospheric dust particles and ice crystals.

The setting sun does not mean the end of the mission. In late July, the Phoenix Mission was extended through September, rather than the 90-sol duration originally planned as the prime 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.

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.

Zeroing In on Phoenix's Final Destination

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows the latest estimate, marked by a green crosshair, of the location of NASA's Phoenix Mars Lander. Radio communications between Phoenix and spacecraft flying overhead have allowed engineers to narrow the lander's location to an area about 300 meters (984) long by 100 meters (328 feet) across, or about three football fields long and one football field wide.

During landing, Phoenix traveled across the field of view shown here from the upper left to the lower right. The area outlined in blue represents the area where Phoenix was predicted to land before arriving on Mars. During Phoenix's descent through the Martian atmosphere to the surface of the Red Planet, continuous measurements of the distance the spacecraft traveled enabled engineers to narrow its location further to the circular area outlined in red.

Using radio signals to home in on Phoenix's final location is sort of like trying to find a kitten by listening to the sound of its meows. As NASA's Odyssey spacecraft passes overhead, it receives radio transmissions from the lander. When Odyssey passes overhead again along a slightly different path, it receives new radio signals. With each successive pass, it is able to 'fix' the location of Phoenix a little more precisely.

Meanwhile, NASA's Mars Reconnaissance Orbiter has taken actual images of the spacecraft on the surface, enabling scientists to match the lander's location to geologic features seen from orbit.

The large crater to the right is 'Heimdall crater,' the slopes of which are visible in images of the parachute that lowered Phoenix to the surface, taken by the High Resolution Imaging Science Experiment instrument on the Mars Reconnaissance Orbiter. The map shown here is made up of topography data taken by NASA's Mars Global Surveyor. It shows exaggerated differences in the height of the terrain.

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.

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.

The Mars NetLander panoramic camera

NASA Astrophysics Data System (ADS)

Jaumann, Ralf; Langevin, Yves; Hauber, Ernst; Oberst, Jürgen; Grothues, Hans-Georg; Hoffmann, Harald; Soufflot, Alain; Bertaux, Jean-Loup; Dimarellis, Emmanuel; Mottola, Stefano; Bibring, Jean-Pierre; Neukum, Gerhard; Albertz, Jörg; Masson, Philippe; Pinet, Patrick; Lamy, Philippe; Formisano, Vittorio

2000-10-01

The panoramic camera (PanCam) imaging experiment is designed to obtain high-resolution multispectral stereoscopic panoramic images from each of the four Mars NetLander 2005 sites. The main scientific objectives to be addressed by the PanCam experiment are (1) to locate the landing sites and support the NetLander network sciences, (2) to geologically investigate and map the landing sites, and (3) to study the properties of the atmosphere and of variable phenomena. To place in situ measurements at a landing site into a proper regional context, it is necessary to determine the lander orientation on ground and to exactly locate the position of the landing site with respect to the available cartographic database. This is not possible by tracking alone due to the lack of on-ground orientation and the so-called map-tie problem. Images as provided by the PanCam allow to determine accurate tilt and north directions for each lander and to identify the lander locations based on landmarks, which can also be recognized in appropriate orbiter imagery. With this information, it will be further possible to improve the Mars-wide geodetic control point network and the resulting geometric precision of global map products. The major geoscientific objectives of the PanCam lander images are the recognition of surface features like ripples, ridges and troughs, and the identification and characterization of different rock and surface units based on their morphology, distribution, spectral characteristics, and physical properties. The analysis of the PanCam imagery will finally result in the generation of precise map products for each of the landing sites. So far comparative geologic studies of the Martian surface are restricted to the timely separated Mars Pathfinder and the two Viking Lander Missions. Further lander missions are in preparation (Beagle-2, Mars Surveyor 03). NetLander provides the unique opportunity to nearly double the number of accessible landing site data by providing simultaneous and long-term observations at four different surface locations which becomes especially important for studies of variable surface features as well as properties and phenomena of the atmosphere. Major changes on the surface that can be detected by PanCam are caused by eolian activities and condensation processes, which directly reflect variations in the prevailing near-surface wind regime and the diurnal and seasonal volatile and dust cycles. Atmospheric studies will concentrate on the detection of clouds, measurements of the aerosol contents and the water vapor absorption at 936 nm. In order to meet these objectives, the proposed PanCam instrument is a highly miniaturized, dedicated stereo and multispectral imaging device. The camera consists of two identical camera cubes, which are arranged in a common housing at a fixed stereo base length of 11 cm. Each camera cube is equipped with a CCD frame transfer detector with 1024×1024 active pixels and optics with a focal length of 13 mm yielding a field-of-view of 53°×53° and an instantaneous filed of view of 1.1 mrad. A filter swivel with six positions provides different color band passes in the wavelength range of 400-950 nm. The camera head is mounted on top of a deployable scissors boom and can be rotated by 360° to obtain a full panorama, which is already covered by eight images. The boom raises the camera head to a final altitude of 90 cm above the surface. Most camera activities will take place within the first week and the first month of the mission. During the remainder of the mission, the camera will operate with a reduced data rate to monitor time-dependent variations on a daily basis. PanCam is a joint German/French project with contributions from DLR, Institute of Space Sensor Technology and Planetary Exploration, Berlin, Institut d'Astrophysique Spatiale, CNRS, Orsay, and Service d'Aéronomie, CNRS, Verrières-le-Buisson.

Soil on Phoenix's MECA

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows soil delivery to NASA's Phoenix Mars Lander's Microscopy, Electrochemistry and Conductivity Analyzer (MECA). The image was taken by the lander's Surface Stereo Imager on the 131st Martian day, or sol, of the mission (Oct. 7, 2008).

At the bottom of the image is the chute for delivering samples to MECA's microscopes. It is relatively clean due to the Phoenix team using methods such as sprinkling to minimize cross-contamination of samples. However, the cumulative effect of several sample deliveries can be seen in the soil piles on either side of the chute.

On the right side are the four chemistry cells with soil residue piled up on exposed surfaces. The farthest cell has a large pile of material from an area of the Phoenix workspace called 'Stone Soup.' This area is deep in the trough at a polygon boundary, and its soil was so sticky it wouldn't even go through the funnel.

One of Phoenix's solar panels is shown in the background of this image.

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.

Morning Frost in Trench Dug by Phoenix, Sol 113

NASA Technical Reports Server (NTRS)

2008-01-01

This image from the Surface Stereo Imager on NASA's Phoenix Mars Lander shows morning frost inside the 'Snow White' trench dug by the lander, in addition to subsurface ice exposed by use of a rasp on the floor of the trench.

The camera took this image at about 9 a.m. local solar time during the 113th Martian day of the mission (Sept. 18, 2008). Bright material near and below the four-by-four set of rasp holes in the upper half of the image is water-ice exposed by rasping and scraping in the trench earlier the same morning. Other bright material especially around the edges of the trench, is frost. Earlier in the mission, when the sun stayed above the horizon all night, morning frost was not evident in the trench.

This image is presented in approximately true color.

The trench is 4 to 5 centimeters (about 2 inches) deep, about 23 centimeters (9 inches) wide.

Phoenix landed on a Martian arctic plain on May 25, 2008. The mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is led by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development was by Lockheed Martin Space Systems, Denver.

Morning Frost in Trench Dug by Phoenix, Sol 113 (False Color)

NASA Technical Reports Server (NTRS)

2008-01-01

This image from the Surface Stereo Imager on NASA's Phoenix Mars Lander shows morning frost inside the 'Snow White' trench dug by the lander, in addition to subsurface ice exposed by use of a rasp on the floor of the trench.

The camera took this image at about 9 a.m. local solar time during the 113th Martian day of the mission (Sept. 18, 2008). Bright material near and below the four-by-four set of rasp holes in the upper half of the image is water-ice exposed by rasping and scraping in the trench earlier the same morning. Other bright material especially around the edges of the trench, is frost. Earlier in the mission, when the sun stayed above the horizon all night, morning frost was not evident in the trench.

This image is presented in false color that enhances the visibility of the frost.

The trench is 4 to 5 centimeters (about 2 inches) deep, about 23 centimeters (9 inches) wide.

Phoenix landed on a Martian arctic plain on May 25, 2008. The mission is led by the University of Arizona, Tucson, on behalf of NASA. Project management of the mission is led by NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development was by Lockheed Martin Space Systems, Denver.

Mars Global Surveyor Images

NASA Technical Reports Server (NTRS)

1999-01-01

High resolution images that help scientists fine tune the landing site for NASA's Mars Surveyor lander mission are shown. These images reveal a smooth surface in the southern cratered highlands near the Nepenthes Mensae.

Formulation of image quality prediction criteria for the Viking lander camera

NASA Technical Reports Server (NTRS)

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

1973-01-01

Image quality criteria are defined and mathematically formulated for the prediction computer program which is to be developed for the Viking lander imaging experiment. The general objective of broad-band (black and white) imagery to resolve small spatial details and slopes is formulated as the detectability of a right-circular cone with surface properties of the surrounding terrain. The general objective of narrow-band (color and near-infrared) imagery to observe spectral characteristics if formulated as the minimum detectable albedo variation. The general goal to encompass, but not exceed, the range of the scene radiance distribution within single, commandable, camera dynamic range setting is also considered.

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.

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 Odyssey project, and developed and built the orbiter. Mission operations are conducted jointly from Lockheed Martin and from JPL, a division of the California Institute of Technology in Pasadena.

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.

Measurement methods and accuracy analysis of Chang'E-5 Panoramic Camera installation parameters

NASA Astrophysics Data System (ADS)

Yan, Wei; Ren, Xin; Liu, Jianjun; Tan, Xu; Wang, Wenrui; Chen, Wangli; Zhang, Xiaoxia; Li, Chunlai

2016-04-01

Chang'E-5 (CE-5) is a lunar probe for the third phase of China Lunar Exploration Project (CLEP), whose main scientific objectives are to implement lunar surface sampling and to return the samples back to the Earth. To achieve these goals, investigation of lunar surface topography and geological structure within sampling area seems to be extremely important. The Panoramic Camera (PCAM) is one of the payloads mounted on CE-5 lander. It consists of two optical systems which installed on a camera rotating platform. Optical images of sampling area can be obtained by PCAM in the form of a two-dimensional image and a stereo images pair can be formed by left and right PCAM images. Then lunar terrain can be reconstructed based on photogrammetry. Installation parameters of PCAM with respect to CE-5 lander are critical for the calculation of exterior orientation elements (EO) of PCAM images, which is used for lunar terrain reconstruction. In this paper, types of PCAM installation parameters and coordinate systems involved are defined. Measurement methods combining camera images and optical coordinate observations are studied for this work. Then research contents such as observation program and specific solution methods of installation parameters are introduced. Parametric solution accuracy is analyzed according to observations obtained by PCAM scientifically validated experiment, which is used to test the authenticity of PCAM detection process, ground data processing methods, product quality and so on. Analysis results show that the accuracy of the installation parameters affects the positional accuracy of corresponding image points of PCAM stereo images within 1 pixel. So the measurement methods and parameter accuracy studied in this paper meet the needs of engineering and scientific applications. Keywords: Chang'E-5 Mission; Panoramic Camera; Installation Parameters; Total Station; Coordinate Conversion

Deep 'Stone Soup' Trenching by Phoenix (Stereo)

NASA Technical Reports Server (NTRS)

2008-01-01

Digging by NASA's Phoenix Mars Lander on Aug. 23, 2008, during the 88th sol (Martian day) since landing, reached a depth about three times greater than in any trench Phoenix has excavated. The deep trench, informally called 'Stone Soup' is at the borderline between two of the polygon-shaped hummocks that characterize the arctic plain where Phoenix landed.

Stone Soup is in the center foreground of this stereo view, which appears three dimensional when seen through red-blue glasses. The view combines left-eye and right-eye images taken by the lander's Surface Stereo Imager on Sol 88 after the day's digging. The trench is about 25 centimeters (10 inches) wide and about 18 centimeters (7 inches) deep.

When digging trenches near polygon centers, Phoenix has hit a layer of icy soil, as hard as concrete, about 5 centimeters or 2 inches beneath the ground surface. In the Stone Soup trench at a polygon margin, the digging has not yet hit an icy layer like that.

Stone Soup is toward the left, or west, end of the robotic arm's work area on the north side 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 NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

Design and evaluation of controls for drift, video gain, and color balance in spaceborne facsimile cameras

NASA Technical Reports Server (NTRS)

Katzberg, S. J.; Kelly, W. L., IV; Rowland, C. W.; Burcher, E. E.

1973-01-01

The facsimile camera is an optical-mechanical scanning device which has become an attractive candidate as an imaging system for planetary landers and rovers. This paper presents electronic techniques which permit the acquisition and reconstruction of high quality images with this device, even under varying lighting conditions. These techniques include a control for low frequency noise and drift, an automatic gain control, a pulse-duration light modulation scheme, and a relative spectral gain control. Taken together, these techniques allow the reconstruction of radiometrically accurate and properly balanced color images from facsimile camera video data. These techniques have been incorporated into a facsimile camera and reproduction system, and experimental results are presented for each technique and for the complete system.

COMETARY SCIENCE. 67P/Churyumov-Gerasimenko surface properties as derived from CIVA panoramic images.

PubMed

Bibring, J-P; Langevin, Y; Carter, J; Eng, P; Gondet, B; Jorda, L; Le Mouélic, S; Mottola, S; Pilorget, C; Poulet, F; Vincendon, M

2015-07-31

The structure and composition of cometary constituents, down to their microscopic scale, are critical witnesses of the processes and ingredients that drove the formation and evolution of planetary bodies toward their present diversity. On board Rosetta's lander Philae, the Comet Infrared and Visible Analyser (CIVA) experiment took a series of images to characterize the surface materials surrounding the lander on comet 67P/Churyumov-Gerasimenko. Images were collected twice: just after touchdown, and after Philae finally came to rest, where it acquired a full panorama. These images reveal a fractured surface with complex structure and a variety of grain scales and albedos, possibly constituting pristine cometary material. Copyright © 2015, American Association for the Advancement of Science.

In-Situ Propellant Supplied Lunar Lander Concept

NASA Astrophysics Data System (ADS)

Donahue, Benjamin; Maulsby, Curtis

2008-01-01

Future NASA and commercial Lunar missions will require innovative spacecraft configurations incorporating reliable, sustainable propulsion, propellant storage, power and crew life support technologies that can evolve into long duration, partially autonomous systems that can be used to emplace and sustain the massive supplies required for a permanently occupied lunar base. Ambitious surface science missions will require efficient Lunar transfer systems to provide the consumables, science equipment, energy generation systems, habitation systems and crew provisions necessary for lengthy tours on the surface. Lunar lander descent and ascent stages become significantly more efficient when they can be refueled on the Lunar surface and operated numerous times. Landers enabled by Lunar In-Situ Propellant Production (ISPP) facilities will greatly ease constraints on spacecraft mass and payload delivery capability, and may operate much more affordably (in the long term) then landers that are dependant on Earth supplied propellants. In this paper, a Lander concept that leverages ISPP is described and its performance is quantified. Landers, operating as sortie vehicles from Low Lunar Orbit, with efficiencies facilitated by ISPP will enable economical utilization and enhancements that will provide increasingly valuable science yields from Lunar Bases.

COMPASS Final Report: Low Cost Robotic Lunar Lander

NASA Technical Reports Server (NTRS)

McGuire, Melissa L.; Oleson, Steven R.

2010-01-01

The COllaborative Modeling for the Parametric Assessment of Space Systems (COMPASS) team designed a robotic lunar Lander to deliver an unspecified payload (greater than zero) to the lunar surface for the lowest cost in this 2006 design study. The purpose of the low cost lunar lander design was to investigate how much payload can an inexpensive chemical or Electric Propulsion (EP) system deliver to the Moon s surface. The spacecraft designed as the baseline out of this study was a solar powered robotic lander, launched on a Minotaur V launch vehicle on a direct injection trajectory to the lunar surface. A Star 27 solid rocket motor does lunar capture and performs 88 percent of the descent burn. The Robotic Lunar Lander soft-lands using a hydrazine propulsion system to perform the last 10% of the landing maneuver, leaving the descent at a near zero, but not exactly zero, terminal velocity. This low-cost robotic lander delivers 10 kg of science payload instruments to the lunar surface.

Using virtual reality for science mission planning: A Mars Pathfinder case

NASA Technical Reports Server (NTRS)

Kim, Jacqueline H.; Weidner, Richard J.; Sacks, Allan L.

1994-01-01

NASA's Mars Pathfinder Project requires a Ground Data System (GDS) that supports both engineering and scientific payloads with reduced mission operations staffing, and short planning schedules. Also, successful surface operation of the lander camera requires efficient mission planning and accurate pointing of the camera. To meet these challenges, a new software strategy that integrates virtual reality technology with existing navigational ancillary information and image processing capabilities. The result is an interactive workstation based applications software that provides a high resolution, 3-dimensial, stereo display of Mars as if it were viewed through the lander camera. The design, implementation strategy and parametric specification phases for the development of this software were completed, and the prototype tested. When completed, the software will allow scientists and mission planners to access simulated and actual scenes of Mars' surface. The perspective from the lander camera will enable scientists to plan activities more accurately and completely. The application will also support the sequence and command generation process and will allow testing and verification of camera pointing commands via simulation.

Martian Soil Ready for Robotic Laboratory Analysis

NASA Technical Reports Server (NTRS)

2008-01-01

NASA's Phoenix Mars Lander scooped up this Martian soil on the mission's 11th Martian day, or sol, after landing (June 5, 2008) as the first soil sample for delivery to the laboratory on the lander deck.

The material includes a light-toned clod possibly from crusted surface of the ground, similar in appearance to clods observed near a foot of the lander.

This approximately true-color view of the contents of the scoop on the Robotic Arm comes from combining separate images taken by the Robotic Arm Camera on Sol 11, using illumination by red, green and blue light-emitting diodes on the camera.

The scoop loaded with this sample was poised over an open sample-delivery door of Thermal and Evolved-Gas Analyzer at the end of Sol 11, ready to be dumped into the instrument on the next sol.

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

Dust Devil Tracks and Wind Streaks in the North Polar Region of Mars: A Study of the 2007 Phoenix Mars Lander Sites

NASA Technical Reports Server (NTRS)

Drake, Nathan B.; Tamppari, Leslie K.; Baker, R. David; Cantor, Bruce A.; Hale, Amy S.

2006-01-01

The 65-72 latitude band of the North Polar Region of Mars, where the 2007 Phoenix Mars Lander will land, was studied using satellite images from the Mars Global Surveyor (MGS) Mars Orbiter Camera Narrow-Angle (MOC-NA) camera. Dust devil tracks (DDT) and wind streaks (WS) were observed and recorded as surface evidence for winds. No active dust devils (DDs) were observed. 162 MOC-NA images, 10.3% of total images, contained DDT/WS. Phoenix landing Region C (295-315W) had the highest concentration of images containing DDT/WS per number of available images (20.9%); Region D (130-150W) had the lowest (3.5%). DDT and WS direction were recorded for Phoenix landing regions A (110-130W), B (240-260W), and C to infer local wind direction. Region A showed dominant northwest-southeast DDT/WS, Region B showed dominant north-south, east-west and northeast-southwest DDT/WS, and region C showed dominant west/northwest - east/southeast DDT/ WS. Results indicate the 2007 Phoenix Lander has the highest probability of landing near DDT/WS in landing Region C. Based on DDT/WS linearity, we infer Phoenix would likely encounter directionally consistent background wind in any of the three regions.

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.

Home and Back Again

NASA Technical Reports Server (NTRS)

2004-01-01

The Mars Exploration Rover Opportunity finished observations of the prominent rock outcrop it has been studying during its 51 martian days, or sols, on Mars, and is currently on the hunt for new discoveries. This image from the rover's navigation camera atop its mast features Opportunity's lander--its temporary home for the six-month cruise to Mars. The rover's soil survey traverse plan involves arcing around its landing site, called the Challenger Memorial Station, and over the trench it made on sol 23. In this image, Opportunity is situated about 6.2 meters (about 20.3 feet) from the lander. Rover tracks zig-zag along the surface. Bounce marks and airbag retraction marks are visible around the lander. The calibration target or sundial, which both rover panoramic cameras use to verify the true colors and brightness of the red planet, is visible on the back end of the rover.

Mars Pathfinder Landing Site and Surroundings

NASA Technical Reports Server (NTRS)

2007-01-01

NASA's Mars Pathfinder landed on Mars on July 4, 1997, and continued operating until Sept. 27 of that year. The landing site is on an ancient flood plain of the Ares and Tiu outflow channels. The High Resolution Imaging Science Experiment (HiRISE) camera on NASA's Mars Reconnaissance Orbiter took an image on Dec. 21, 2006, that provides unprecedented detail of the geology of the region and hardware on the surface.

[figure removed for brevity, see original site] HiRISE Image This is the entire image. The crater at center bottom was unofficially named 'Big Crater' by the Pathfinder team. Its wall was visible from Pathfinder, located 3 kilometers (2 miles) to the north. The two bright features to the upper left of Big Crater are the 'Twin Peaks,' also observed by Pathfinder. The bright mound to the upper right of the Twin Peaks is 'North Knob,' seen in Pathfinder images as peaking over the horizon.

At this scale there is no obvious geologic evidence of an ancient flood. Rather, impact craters dominate the scene, attesting to an old surface. The age is probably on the order of 1.8 billion to 3.5 billion years, when the Ares and Tiu floods are estimated to have occurred. Wind-formed linear ripples and dunes are seen throughout and are concentrated within craters. Sets of polygonal ridges of enigmatic origin are seen east of the Pathfinder lander. Rocks are visible over the entire image, with heavy concentrations near fresh-looking craters. Most of them are probably blocks tossed outward by crater-forming impacts.

The complete image is centered at 19.1 degrees north latitude, 326.8 degrees east longitude. The range to the target site was 284.7 kilometers (177.9 miles). At this distance the image scale is 28.5 centimeters (11 inches) per pixel, so objects about 85 centimeters (33 inches) across are resolved. The image shown here has been map-projected to 25 centimeters (10 inches) per pixel. North is up. The image was taken at a local Mars time of 3:35 p.m., and the scene is illuminated from the west with a solar incidence angle of 52 degrees, thus the sun was about 38 degrees above the horizon. At a solar longitude of 154.0 degrees, the season on Mars is northern summer.

[figure removed for brevity, see original site] Landing Site Region This is a close-up of the area in the vicinity of the Pathfinder landing site. Major features are named. The white box outlines the area of the image, discussed next, where hardware is seen.

[figure removed for brevity, see original site] Hardware on the Surface This image shows the Pathfinder lander on the surface. Zooming in, one can discern the ramps, science deck, and portions of the airbags on the Pathfinder lander. (See next image for closer view.) The back shell and parachute are to the south, and four features that may be portions of the heat shield are identified. Two of these were visible from Pathfinder. At the time of that mission, the nearest object was provisionally identified as the back shell. However, analysis of the HiRISE image and reinterpretation of Pathfinder images, plus an improved understanding of how hardware looks on the Martian surface based on ground-level and orbital images of the Mars Exploration Rover landing sites, indicate that the glint is bright enough that it may be insulating material from inside the heat shield. The back shell and parachute were out of sight behind a ridge from Pathfinder's ground view. One of the three bright features, identified as heat shield debris, was also identified during the Pathfinder mission.

[figure removed for brevity, see original site] [figure removed for brevity, see original site] Annotated Version Unannotated Version Topographic Map of Landing Site Region Portions of the HiRISE image are overlaid onto color-coded topographic maps constructed by the U.S. Geological Survey from stereo images acquired by the Imager for Mars Pathfinder on the lander. The white feature at the center is Pathfinder lander. The scales on the x and y axes are in meters, with the lander as the zero point. The color code for elevation relative to the lander is different in the left and right images, and shown in meters underneath each image. The correspondence between the overhead view revealed by HiRISE and the positions of topographic features inferred almost a decade ago from Pathfinder's horizontal view of the landscape is striking. The close-up on the right complements panoramas taken by the lander's camera, including the accompanying composite version showing the Sojourner rover at various locations it reached during the mission.

[figure removed for brevity, see original site] Mars Pathfinder Gallery Panorama This version of the Gallery Panorama taken with the lander's Imager for Mars Pathfinder camera shows many of the locations where the mission's Sojourner rover ended a Martian day during the 12-week mission. (There was only one Sojourner. The image is a composite.) One annotation indicates the last known position of Sojourner, near the rock 'Chimp,' at the time of the final data transmission from the lander. The location labeled 'Sojourner?' has been tentatively identified as the current position of the rover based on comparison of the ground-level view with the Dec. 21, 2006, image from NASA's Mars Reconnaissance Orbiter. At the proposed current location of the rover, a feature can be discerned in the 2006 orbital image that is about the right size for Sojourner and wasn't present when the Gallery Panorama was taken. Some rocks and other features that can be identified in the orbiter's high-resolution view are labeled in this ground-level view.

[figure removed for brevity, see original site] Topographic Perspective of Landing Site Region) This is a perspective view based on the topographic map and artificial color derived from Pathfinder and other data. The vertical scale is exaggerated by a factor of three, compared with horizontal dimensions. The white feature at center is the Pathfinder lander. It appears flat because the topographic map derived from the Imager for Mars Pathfinder data did not include the spacecraft itself.

The Mars climate for a photovoltaic system operation

NASA Technical Reports Server (NTRS)

Appelbaum, Joseph; Flood, Dennis J.

1989-01-01

Detailed information on the climatic conditions on Mars are very desirable for the design of photovoltaic systems for establishing outposts on the Martian surface. The distribution of solar insolation (global, direct and diffuse) and ambient temperature is addressed. This data are given at the Viking lander's locations and can also be used, to a first approximation, for other latitudes. The insolation data is based on measured optical depth of the Martian atmosphere derived from images taken of the sun with a special diode on the Viking cameras; and computation based on multiple wavelength and multiple scattering of the solar radiation. The ambient temperature (diurnal and yearly distribution) is based on direct measurements with a thermocouple at 1.6 m above the ground at the Viking lander locations. The insolation and ambient temperature information are short term data. New information about Mars may be forthcoming in the future from new analysis of previously collected data or from future flight missions. The Mars climate data for photovoltaic system operation will thus be updated accordingly.

Soil and surface temperatures at the Viking landing sites

NASA Technical Reports Server (NTRS)

Kieffer, H. H.

1976-01-01

The annual temperature range for the Martian surface at the Viking lander sites is computed on the basis of thermal parameters derived from observations made with the infrared thermal mappers. The Viking lander 1 (VL1) site has small annual variations in temperature, whereas the Viking lander 2 (VL2) site has large annual changes. With the Viking lander images used to estimate the rock component of the thermal emission, the daily temperature behavior of the soil alone is computed over the range of depths accessible to the lander; when the VL1 and VL2 sites were sampled, the daily temperature ranges at the top of the soil were 183 to 263 K and 183 to 268 K, respectively. The diurnal variation decreases with depth with an exponential scale of about 5 centimeters. The maximum temperature of the soil sampled from beneath rocks at the VL2 site is calculated to be 230 K. These temperature calculations should provide a reference for study of the active chemistry reported for the Martian soil.

Soil and surface temperatures at the viking landing sites.

PubMed

Kieffer, H H

1976-12-11

The annual temperature range for the martian surface at the Viking lander sites is computed on the basis of thermal parameters derived from observations made with the infrared thermal mappers. The Viking lander 1 (VL1) site has small annual variations in temperature, whereas the Viking lander 2 (VL2) site has large annual changes. With the Viking lander images used to estimate the rock component of the thermal emission, the daily temperature behavior of the soil alone is computed over the range of depths accessible to the lander; when the VL1 and VL2 sites were sampled, the daily temperature ranges at the top of the soil were 183 to 263 K and 183 to 268 K, respectively. The diurnal variation decreases with depth with an exponential scale of about 5 centimeters. The maximum temperature of the soil sampled from beneath rocks at the VL2 site is calculated to be 230 K. These temperature calculations should provide a reference for study of the active chemistry reported for the martian soil.

Viking

NASA Technical Reports Server (NTRS)

1975-01-01

The Viking program, its characteristics, goals, and investigations are described. The program consists of launching two spacecraft to Mars in 1975 to soft-land on the surface and test for signs of life. Topics discussed include the launch, the journey through space, tracking, Mars orbit and landing, experiments on the search for life, imaging systems, lander camera, water detection experiments, thermal mapping, and a possible weather station on Mars.

Animation of Panorama of Phoenix Landing Area Looking Southeast

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

This is an animation of panoramic images taken by NASA's Phoenix Mars Lander's Surface Stereo Imager on Sol 15 (June 9, 2008), the 15th Martian day after landing. The panorama looks to the southeast and shows rocks casting shadows, polygons on the surface and as the image looks to the horizon, Phoenix's backshell gleams in the distance.

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

Mars Pathfinder mission operations concepts

NASA Technical Reports Server (NTRS)

Sturms, Francis M., Jr.; Dias, William C.; Nakata, Albert Y.; Tai, Wallace S.

1994-01-01

The Mars Pathfinder Project plans a December 1996 launch of a single spacecraft. After jettisoning a cruise stage, an entry body containing a lander and microrover will directly enter the Mars atmosphere and parachute to a hard landing near the sub-solar latitude of 15 degrees North in July 1997. Primary surface operations last for 30 days. Cost estimates for Pathfinder ground systems development and operations are not only lower in absolute dollars, but also are a lower percentage of total project costs than in past planetary missions. Operations teams will be smaller and fewer than typical flight projects. Operations scenarios have been developed early in the project and are being used to guide operations implementation and flight system design. Recovery of key engineering data from entry, descent, and landing is a top mission priority. These data will be recorded for playback after landing. Real-time tracking of a modified carrier signal through this phase can provide important insight into the spacecraft performance during entry, descent, and landing in the event recorded data is never recovered. Surface scenarios are dominated by microrover activity and lander imaging during 7 hours of the Mars day from 0700 to 1400 local solar time. Efficient uplink and downlink processes have been designed to command the lander and microrover each Mars day.

Preparing the Phoenix Lander for Mars

NASA Image and Video Library

2005-06-01

The Phoenix lander, housed in a 100,000-class clean room at Lockheed Martin Space Systems facilities near Denver, Colo. Shown here, the lander is contained inside the backshell portion of the aeroshell with the heat shield removed.

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.;

Lander Technologies

NASA Technical Reports Server (NTRS)

Chavers, Greg

2015-01-01

Since 2006 NASA has been formulating robotic missions to the lunar surface through programs and projects like the Robotic Lunar Exploration Program, Lunar Precursor Robotic Program, and International Lunar Network. All of these were led by NASA Marshall Space Flight Center (MSFC). Due to funding shortfalls, the lunar missions associated with these efforts, the designs, were not completed. From 2010 to 2013, the Robotic Lunar Lander Development Activity was funded by the Science Mission Directorate (SMD) to develop technologies that would enable and enhance robotic lunar surface missions at lower costs. In 2013, a requirements-driven, low-cost robotic lunar lander concept was developed for the Resource Prospector Mission. Beginning in 2014, The Advanced Exploration Systems funded the lander team and established the MSFC, Johnson Space Center, Applied Physics Laboratory, and the Jet Propulsion Laboratory team with MSFC leading the project. The lander concept to place a 300-kg rover on the lunar surface has been described in the New Technology Report Case Number MFS-33238-1. A low-cost lander concept for placing a robotic payload on the lunar surface is shown in figures 1 and 2. The NASA lander team has developed several lander concepts using common hardware and software to allow the lander to be configured for a specific mission need. In addition, the team began to transition lander expertise to United States (U.S.) industry to encourage the commercialization of space, specifically the lunar surface. The Lunar Cargo Transportation and Landing by Soft Touchdown (CATALYST) initiative was started and the NASA lander team listed above is partnering with three competitively selected U.S. companies (Astrobotic, Masten Space Systems, and Moon Express) to develop, test, and operate their lunar landers.

Surface Changes in Chryse Planitia

NASA Technical Reports Server (NTRS)

1979-01-01

At the conclusion of the Viking Continuation Mission (May to November, 1978), all four cameras on the Viking Landers - two on each spacecraft - continued to function normally. During the two and one-half years since the landers touched down on Mars, images totaled 2,255 for Viking Lander 1 and 2,016 for Viking Lander 2. The surface around the landers was completely photographed by the end of 1976; subsequent images acquired during 1977-1978 have concentrated on searching for changes in the scene - changes which can be used to infer both the types of erosive processes which modify the landscape around the landers and the rates at which these processes may occur. The major surface changes have included the water-ice snow seen by Lander 2 during the winter at Utopia Planitia, and a thin dust layer deposited at both sites during the dust storms of 1977. The most recently identified change occurred at Chryse Planitia between VL-1 sols 767 (Sept. 16, 1978) and 771 (Sept. 20, 1978) as seen in the lower photo. Picture at top, selected to show similar lighting conditions, was taken during sol 25 (August 15, 1976). The change (A) appears as a small circle-like formation on the side of a drift in the lee, or downwind, side of Whale Rock. This is believed to have been a small-scale landslide of an unstable dust layer which had accumulated behind the rock. Interpretation of this feature would be difficult without an earlier change (B) near Big Joe, a slump which occurred between sols 74 and 183. The new slump is approximately 25- 35 meters from the lander, and just under a meter across. The slumping probably was initiated by the daily heating and cooling of the surface by solar radiation. More importantly, it is now believed that, based on the repeated occurrence of such slumping features, a dust layer which overlies the surface may in fact be redistributed fairly regularly during periods of high wind activity. There are no obvious indications of fossil slump features, therefore similar features must be destroyed on a regular basis. After the end of February, when Viking operations essentially terminate, Lander 1 will continue preselected observations over a period of possibly up to 10 years, following the instructions stored in its computer memory. Earth commands will be required only to initiate data transmission to Earth. During this time, it is now anticipated that one of the yearly planetwide global dust storms may reach an intensity necessary to shift the dust cover around the lander significantly.

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.

Design and Sizing of the Air Revitalization System for Altair Lunar Lander

NASA Technical Reports Server (NTRS)

Allada, Rama Kumar

2009-01-01

Designing closed-loop Air Revitalization Systems (ARS) for human spaceflight applications requires a delicate balance between designing for system robustness while minimizing system power and mass requirements. This presentation will discuss the design of the ARS for the Altair Lunar Lander. The presentation will illustrate how dynamic simulations, using Aspen Custom Modeler, were used to develop a system configuration with the ability to control atmospheric conditions under a wide variety of circumstances while minimizing system mass/volume and the impact on overall power requirements for the Lander architecture.

Structural analyses of the JPL Mars Pathfinder impact

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

Gwinn, K.W.

1994-12-31

The purpose of this paper is to demonstrate that finite element analysis can be used in the design process for high performance fabric structures. These structures exhibit extreme geometric nonlinearity; specifically, the contact and interaction of fabric surfaces with the large deformation which necessarily results from membrane structures introduces great complexity to analyses of this type. All of these features are demonstrated here in the analysis of the Jet Propulsion Laboratory (JPL) Mars Pathfinder impact onto Mars. This lander system uses airbags to envelope the lander experiment package, protecting it with large deformation upon contact. Results from the analysis showmore » the stress in the fabric airbags, forces in the internal tendon support system, forces in the latches and hinges which allow the lander to deploy after impact, and deceleration of the lander components. All of these results provide the JPL engineers with design guidance for the success of this novel lander system.« less

Structural analyses of the JPL Mars Pathfinder impact

NASA Astrophysics Data System (ADS)

Gwinn, Kenneth W.

The purpose of this paper is to demonstrate that finite element analysis can be used in the design process for high performance fabric structures. These structures exhibit extreme geometric nonlinearity; specifically, the contact and interaction of fabric surfaces with the large deformation which necessarily results from membrane structures introduces great complexity to analyses of this type. All of these features are demonstrated here in the analysis of the Jet Propulsion Laboratory (JPL) Mars Pathfinder impact onto Mars. This lander system uses airbags to envelope the lander experiment package, protecting it with large deformation upon contact. Results from the analysis show the stress in the fabric airbags, forces in the internal tendon support system, forces in the latches and hinges which allow the lander to deploy after impact, and deceleration of the lander components. All of these results provide the JPL engineers with design guidance for the success of this novel lander system.

Understanding the Lunar System Architecture Design Space

NASA Technical Reports Server (NTRS)

Arney, Dale C.; Wilhite, Alan W.; Reeves, David M.

2013-01-01

Based on the flexible path strategy and the desire of the international community, the lunar surface remains a destination for future human exploration. This paper explores options within the lunar system architecture design space, identifying performance requirements placed on the propulsive system that performs Earth departure within that architecture based on existing and/or near-term capabilities. The lander crew module and ascent stage propellant mass fraction are primary drivers for feasibility in multiple lander configurations. As the aggregation location moves further out of the lunar gravity well, the lunar lander is required to perform larger burns, increasing the sensitivity to these two factors. Adding an orbit transfer stage to a two-stage lunar lander and using a large storable stage for braking with a one-stage lunar lander enable higher aggregation locations than Low Lunar Orbit. Finally, while using larger vehicles enables a larger feasible design space, there are still feasible scenarios that use three launches of smaller vehicles.

Mars Pathfinder flight system integration and test.

NASA Astrophysics Data System (ADS)

Muirhead, B. K.

This paper describes the system integration and test experiences, problems and lessons learned during the assembly, test and launch operations (ATLO) phase of the Mars Pathfinder flight system scheduled to land on the surface of Mars on July 4, 1997. The Mars Pathfinder spacecraft consists of three spacecraft systems: cruise stage, entry vehicle and lander. The cruise stage carries the entry and lander vehicles to Mars and is jettisoned prior to entry. The entry vehicle, including aeroshell, parachute and deceleration rockets, protects the lander during the direct entry and reduces its velocity from 7.6 to 0 km/s in stages during the 5 min entry sequence. The lander's touchdown is softened by airbags which are retracted once stopped on the surface. The lander then uprights itself, opens up fully and begins surface operations including deploying its camera and rover. This paper overviews the system design and the results of the system integration and test activities, including the entry, descent and landing subsystem elements. System test experiences including science instruments, the microrover, Sojourner, and software are discussed. The final qualification of the entry, descent and landing subsystems during this period is also discussed.

Stunning Image of Rosetta above Mars taken by the Philae Lander Camera

NASA Image and Video Library

2007-02-05

Stunning image taken by the CIVA imaging instrument on Rosetta Philae lander just 4 minutes before closest approach at a distance of some 1000 km from Mars on Feb. 25, 2007. A portion of the spacecraft and one of its solar arrays are visible in nice detail. Beneath, the Mawrth Vallis region is visible on the planet's disk. Mawrth Vallis is particularly relevant as it is one of the areas on the Martian surface where the OMEGA instrument on board ESA's Mars Express detected the presence of hydrated clay minerals -- a sign that water may have flown abundantly on that region in the very early history of Mars. Id 217487 http://photojournal.jpl.nasa.gov/catalog/PIA18154

The Mars Pathfinder Mission and Science Results

NASA Technical Reports Server (NTRS)

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 geology and geomorphology of the surface, mineralogy and geochemistry of rocks and soils, physical properties of surface materials, magnetic properties of airborne dust, atmospheric science including aerosols, and rotational and orbital dynamics of Mars. Scientists were assembled into 7 Science Operations Groups that were responsible for requesting measurements by the 3 instruments, rover and engineering subsystems for carrying out their scientific investigations and for analyzing the data and reporting on their findings. The spacecraft was launched on December 4, 1996 and had a 7 month cruise to Mars, with four trajectory correction maneuvers. The vehicle entered the atmosphere directly following cruise stage separation. Parachute deployment, heatshield and lander separation, radar ground acquisition, airbag inflation and rocket ignition all occurred before landing at 2:58 AM true local solar time (9:56:55 AM PDT). The lander bounced at least 15 times up to 12 in high without airbag rupture, demonstrating the robustness of this landing system. Reconstruction of the final landing sequence indicates that the parachute/backshel1/1ander was tilted due to a northwest directed wind and wind shear, which resulted in the lander bouncing about I km to the northwest and initially downhill about 20 m from where the solid rockets fired. Two anomalously bright spots located in the lander scene are likely the heatshield, which continued in a ballistic trajectory about 2 km downrange (west southwest), and the backshell/parachute, which stayed nearer to where the rockets fired. Unconnected disturbed soil patches in the scene indicate that the final few bounces of the lander were from the east-southeast and were followed by a gentle roll to the west before coming to rest on the base petal. The location of the lander away from where the solid rockets fired and considerations of the exhaust products used to inflate the airbags and their fate, indicate that the Pathfinder landing system is one of the cleanest designed leaving the local area essentially contaminant free. The radio signal from the low-=gain antenna was received at 11:34 AM PDT indicating a successful landing.

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 necessary, the active suspension significantly contributes to the lightweight MPE design. The thermal control system enables the MPE to operate in shaded areas for about 2 h and hibernate darkness periods of about 14 h. Increasing the hibernation capability requires additional battery capacity and thus increases the MPE mass. As operational modes teleoperations from earth and autonomous navigation are foreseen. The MPE payload includes navigation cameras, a close-up imager and a mole as sampling device. The MPE phase 0/A study finished in early 2012. This article describes the resulting MPE rover concept with focus on its scientific benefit for the Lunar Lander Mission.

Phoenix Wet Chemistry Laboratory Units

NASA Image and Video Library

2008-06-26

This image shows four Wet Chemistry Laboratory units, part of the Microscopy, Electrochemistry, and Conductivity Analyzer MECA instrument on board NASA Phoenix Mars Lander. This image was taken before Phoenix launch on August 4, 2007.

Robotic Lunar Landers for Science and Exploration

NASA Technical Reports Server (NTRS)

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

2010-01-01

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

Performance evaluation of a quasi-microscope for planetary landers

NASA Technical Reports Server (NTRS)

Burcher, E. E.; Huck, F. O.; Wall, S. D.; Woehrle, S. B.

1977-01-01

Spatial resolutions achieved with cameras on lunar and planetary landers have been limited to about 1 mm, whereas microscopes of the type proposed for such landers could have obtained resolutions of about 1 um but were never accepted because of their complexity and weight. The quasi-microscope evaluated in this paper could provide intermediate resolutions of about 10 um with relatively simple optics that would augment a camera, such as the Viking lander camera, without imposing special design requirements on the camera of limiting its field of view of the terrain. Images of natural particulate samples taken in black and white and in color show that grain size, shape, and texture are made visible for unconsolidated materials in a 50- to 500-um size range. Such information may provide broad outlines of planetary surface mineralogy and allow inferences to be made of grain origin and evolution. The mineralogical descriptions of single grains would be aided by the reflectance spectra that could, for example, be estimated from the six-channel multispectral data of the Viking lander camera.

Power System Trade Studies for the Lunar Surface Access Module

NASA Technical Reports Server (NTRS)

Kohout, Lisa, L.

2008-01-01

A Lunar Lander Preparatory Study (LLPS) was undertaken for NASA's Lunar Lander Pre-Project in 2006 to explore a wide breadth of conceptual lunar lander designs. Civil servant teams from nearly every NASA center responded with dozens of innovative designs that addressed one or more specific lander technical challenges. Although none of the conceptual lander designs sought to solve every technical design issue, each added significantly to the technical database available to the Lunar Lander Project Office as it began operations in 2007. As part of the LLPS, a first order analysis was performed to identify candidate power systems for the ascent and descent stages of the Lunar Surface Access Module (LSAM). A power profile by mission phase was established based on LSAM subsystem power requirements. Using this power profile, battery and fuel cell systems were modeled to determine overall mass and volume. Fuel cell systems were chosen for both the descent and ascent stages due to their low mass. While fuel cells looked promising based on these initial results, several areas have been identified for further investigation in subsequent studies, including the identification and incorporation of peak power requirements into the analysis, refinement of the fuel cell models to improve fidelity and incorporate ongoing technology developments, and broadening the study to include solar power.

Inference of dust opacities for the 1977 Martian great dust storms from Viking Lander 1 pressure data

NASA Technical Reports Server (NTRS)

Zurek, R. W.

1981-01-01

The tidal heating components for the dusty Martian atmosphere are computed based on dust optical parameters estimated from Viking Lander imaging data, and used to compute the variation of the tidal surface pressure components at the Viking Lander sites as a function of season and the total vertical extinction optical depth of the atmosphere. An atmospheric tidal model is used which is based on the inviscid, hydrostatic primitive equations linearized about a motionless basic state the temperature of which varies only with height, and the profiles of the tidal forcing components are computed using a delta-Eddington approximation to the radiative transfer equations. Comparison of the model results with the observed variations of surface pressure and overhead dust opacity at the Viking Lander 1 site reveal that the dust opacities and optical parameters derived from imaging data are roughly representative of the global dust haze necessary to reproduce the observed surface pressure amplitudes, with the exception of the model-inferred asymmetry parameter, which is smaller during the onset of a great storm. The observed preferential enhancement of the semidiurnal tide with respect to the diurnal tide during dust storm onset is shown to be due primarily to the elevation of the tidal heating source in a very dusty atmosphere.

Integration Of Launch Vehicle Simulation/Analysis Tools And Lunar Cargo Lander Design. Part 2/2

NASA Technical Reports Server (NTRS)

DeJean, George Brian; Shiue, Yeu-Sheng Paul; King, Jeffrey

2005-01-01

Part 2, which will be discussed in this report, will discuss the development of a Lunar Cargo Lander (unmanned launch vehicle) that will transport usable payload from Trans- Lunar Injection to the moon. The Delta IV-Heavy was originally used to transport the Lunar Cargo Lander to TLI, but other launch vehicles have been studied. In order to uncover how much payload is possible to land on the moon, research was needed in order to design the sub-systems of the spacecraft. The report will discuss and compare the use of a hypergolic and cryogenic system for its main propulsion system. The guidance, navigation, control, telecommunications, thermal, propulsion, structure, mechanisms, landing gear, command, data handling, and electrical power sub-systems were designed by scaling off other flown orbiters and moon landers. Once all data was collected, an excel spreadsheet was created to accurately calculate the usable payload that will land on the moon along with detailed mass and volume estimating relations. As designed, The Lunar Cargo Lander can plant 5,400 lbm of usable payload on the moon using a hypergolic system and 7,400 lbm of usable payload on the moon using a cryogenic system.

Digital image transformation and rectification of spacecraft and radar images

USGS Publications Warehouse

Wu, S.S.C.

1985-01-01

Digital image transformation and rectification can be described in three categories: (1) digital rectification of spacecraft pictures on workable stereoplotters; (2) digital correction of radar image geometry; and (3) digital reconstruction of shaded relief maps and perspective views including stereograms. Digital rectification can make high-oblique pictures workable on stereoplotters that would otherwise not accommodate such extreme tilt angles. It also enables panoramic line-scan geometry to be used to compile contour maps with photogrammetric plotters. Rectifications were digitally processed on both Viking Orbiter and Lander pictures of Mars as well as radar images taken by various radar systems. By merging digital terrain data with image data, perspective and three-dimensional views of Olympus Mons and Tithonium Chasma, also of Mars, are reconstructed through digital image processing. ?? 1985.

Martian Surface Beneath Phoenix

NASA Technical Reports Server (NTRS)

2008-01-01

This is an image of the Martian surface beneath NASA's Phoenix Mars Lander. The image was taken by Phoenix's Robotic Arm Camera (RAC) on the eighth Martian day of the mission, or Sol 8 (June 2, 2008). The light feature in the middle of the image below the leg is informally called 'Holy Cow.' The dust, shown in the dark foreground, has been blown off of 'Holy Cow' by Phoenix's thruster engines.

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.

Work on Phoenix Science Deck

NASA Technical Reports Server (NTRS)

2007-01-01

Lockheed Martin Space Systems technicians Jim Young (left) and Jack Farmerie (right) work on the science deck of NASA's Phoenix Mars Lander.

The spacecraft was built in a 100,000-class clean room near Denver under NASA's planetary protection practices to keep organics from being taken to Mars. The lander's robotic arm, built by the Jet Propulsion Laboratory, Pasadena, is seen at the top of the picture. The color and grey dots will be used to calibrate the spacecraft's Surface Stereoscopic Imager camera once the spacecraft has landed on the red planet.

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.

In Brief: NASA's Phoenix spacecraft lands on Mars

NASA Astrophysics Data System (ADS)

Showstack, Randy; Kumar, Mohi

2008-06-01

After a 9.5-month, 679-million-kilometer flight from Florida, NASA's Phoenix spacecraft made a soft landing in Vastitas Borealis in Mars's northern polar region on 25 May. The lander, whose camera already has returned some spectacular images, is on a 3-month mission to examine the area and dig into the soil of this site-chosen for its likelihood of having frozen water near the surface-and analyze samples. In addition to a robotic arm and robotic arm camera, the lander's instruments include a surface stereo imager; thermal and evolved-gas analyzer; microscopy, electrochemistry, and conductivity analyzer; and a meteorological station that is tracking daily weather and seasonal changes.

Deep 'Stone Soup' Trenching by Phoenix

NASA Technical Reports Server (NTRS)

2008-01-01

Digging by NASA's Phoenix Mars Lander on Aug. 23, 2008, during the 88th sol (Martian day) since landing, reached a depth about three times greater than in any trench Phoenix has excavated. The deep trench, informally called 'Stone Soup' is at the borderline between two of the polygon-shaped hummocks that characterize the arctic plain where Phoenix landed.

The lander's Surface Stereo Imager took this picture of Stone Soup trench on Sol 88 after the day's digging. The trench is about 25 centimeters (10 inches) wide and about 18 centimeters (7 inches) deep.

When digging trenches near polygon centers, Phoenix has hit a layer of icy soil, as hard as concrete, about 5 centimeters or 2 inches beneath the ground surface. In the Stone Soup trench at a polygon margin, the digging has not yet hit an icy layer like that.

Stone Soup is toward the left, or west, end of the robotic arm's work area on the north side 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 NASA's Jet Propulsion Laboratory, Pasadena, Calif. Spacecraft development is by Lockheed Martin Space Systems, Denver.

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.

Mission Plan for the Mars Surveyor 2001 Orbiter and Lander

NASA Technical Reports Server (NTRS)

Plaut, J. J.; Spencer, D. A.

1999-01-01

The Mars Surveyor 2001 Project consists of two missions to Mars, an Orbiter and a Lander, both to be launched in the spring of 2001 for October 2001 (Orbiter) and January 2002 (Lander) arrival at Mars. The Orbiter will support the Lander mission primarily as a communications relay system; the Lander will not have direct-to-Earth communications capability. Science data collected from the Orbiter will also be used to aid in the geologic interpretation of the landing site, along with data from past missions. Combining the Orbiter and Lander missions into a single Project has enabled the streamlining of many activities and an efficient use of personnel and other resources at the Jet Propulsion Laboratory and at the spacecraft contractor, Lockheed Martin Astronautics.

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-V. It will generate 15,000-lbf of thrust with a single burn of 80's seconds. The lander stage is a bi-propellant, pressure-regulated, pulsing liquid propulsion system to perform all other functions.

Telecommunications and data acquisition systems support for the Viking 1975 mission to Mars

NASA Technical Reports Server (NTRS)

Mudgway, D. J.

1983-01-01

The background for the Viking Lander Monitor Mission (VLMM) is given, and the technical and operational aspects of the tracking and data acquisition support that the Network was called upon to provide are described. An overview of the science results obtained from the imaging, meteorological, and radio science data is also given. The intensive efforts that were made to recover the mission are described.

Flyover Video of Phoenix Work Area

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

This video shows an overhead view of NASA's Phoenix Mars Lander and the work area of the Robotic Arm.

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.

New perspective of undeployed rover

NASA Technical Reports Server (NTRS)

1997-01-01

This image features a different perspective of one of the first pictures taken by the Imager for Mars Pathfinder (IMP) lander shortly after its touchdown at 10:07 AM Pacific Daylight Time on July 4. The image has been transformed to a perspective that would match that of an observer standing at the point the image was taken. Sojourner is seen in the foreground in its stowed position on a solar panel of the lander. Both ramps, the rear of which Sojourner would use on July 5 to safely descend to the Martian surface, were still undeployed when this image was taken. The double hills called 'Twin Peaks' are clearly visible in the background.

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 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.

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.

Test of Lander Vision System for Mars 2020

NASA Image and Video Library

2016-10-04

A prototype of the Lander Vision System for NASA Mars 2020 mission was tested in this Dec. 9, 2014, flight of a Masten Space Systems Xombie vehicle at Mojave Air and Space Port in California. http://photojournal.jpl.nasa.gov/catalog/PIA20848

Happy Mars Solstice!

NASA Image and Video Library

2008-06-27

This image was acquired by NASA Phoenix Mars Lander Surface Stereo Imager SSI in the late afternoon of the 30th Martian day of the mission, or Sol 30 June 25, 2008. This is hours after the beginning of Martian northern summer.

Zooming in on Landing Site

NASA Image and Video Library

2008-05-24

This animation zooms in on the area on Mars where NASA Phoenix Mars Lander will touchdown on May 25, 2008. The image was taken by the High Resolution Imaging Science Experiment HiRISE camera on NASA Mars Reconnaissance Orbiter.

Martian Arctic Dust Devil, Phoenix Sol 104

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager on NASA's Phoenix Mars Lander caught this dust devil in action west-southwest of the lander at 11:16 a.m. local Mars time on Sol 104, or the 104th Martian day of the mission, Sept. 9, 2008.

Dust devils have not been detected in any Phoenix images from earlier in the mission, but at least six were observed in a dozen images taken on Sol 104.

Dust devils are whirlwinds that often occur when the Sun heats the surface of Mars, or some areas on Earth. The warmed surface heats the layer of atmosphere closest to it, and the warm air rises in a whirling motion, stirring dust up from the surface like a miniature tornado.

The dust devil visible in the center of this image just below the horizon is estimated to be about 400 meters (about 1,300 feet) from Phoenix, and 4 meters (13 feet) in diameter. It is much smaller than dust devils that have been observed by NASA's Mars Exploration Rover Spirit much closer to the equator. It is closer in size to dust devils seen from orbit in the Phoenix landing region, though still smaller than those.

The image has been enhanced to make the dust devil easier to see.

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.

Venus - Venera 8 Landing Site in Navka Region

NASA Image and Video Library

1996-09-26

This image is a mosaic of 24 orbits of the Navka region of Venus. The image is centered at about 10 degrees south latitude and 335 degrees east longitude. The image is about 400 km (240 miles) across. 'Behepa 8' marks the approximate landing site of the Soviet Venera 8 lander, which took measurements at the surface of Venus in 1972. The Venera 8 lander measured granitic or continental-like materials at the landing site. Magellan data reveals the landing site to lie in a region of plains cut by tectonic ridges and troughs. Volcanic domes and flows are seen throughout the region. Studying the regional setting of the Venera landing sites is important in linking information about surface composition to surface morphology seen in radar images. Resolution of the Magellan data is about 120 meters (400 feet). http://photojournal.jpl.nasa.gov/catalog/PIA00460

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

Propulsion and Cryogenics Advanced Development (PCAD) Project Propulsion Technologies for the Lunar Lander

NASA Technical Reports Server (NTRS)

Klem, Mark D.; Smith, Timothy D.

2008-01-01

The Propulsion and Cryogenics Advanced Development (PCAD) Project in the Exploration Technology Development Program is developing technologies as risk mitigation for Orion and the Lunar Lander. An integrated main and reaction control propulsion system has been identified as a candidate for the Lunar Lander Ascent Module. The propellants used in this integrated system are Liquid Oxygen (LOX)/Liquid Methane (LCH4) propellants. A deep throttle pump fed Liquid Oxygen (LOX)/Liquid Hydrogen (LH2) engine system has been identified for the Lunar Lander Descent Vehicle. The propellant combination and architecture of these propulsion systems are novel and would require risk reduction prior to detailed design and development. The PCAD Project addresses the technology requirements to obtain relevant and necessary test data to further the technology maturity of propulsion hardware utilizing these propellants. This plan and achievements to date will be presented.

False Color Terrain Model of Phoenix Workspace

NASA Technical Reports Server (NTRS)

2008-01-01

This is a terrain model of Phoenix's Robotic Arm workspace. It has been color coded by depth with a lander model for context. The model has been derived using images from the depth perception feature from Phoenix's Surface Stereo Imager (SSI). Red indicates low-lying areas that appear to be troughs. Blue indicates higher areas that appear to be polygons.

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.

Wedge filter imaging spectrometer

NASA Astrophysics Data System (ADS)

Sémery, Alain; Réess, Jean-Michel; Lemarquis, Frédéric; Drossart, Pierre; Laubier, David; Bernardi, Pernelle

2017-11-01

The development of the planetary exploration for landers makes it more and more necessary to have at our disposal small and light instruments. This is why we are developing in our laboratory a light imaging spectrometer with a wedge filter making the spectral splitting. This design already developed in other laboratories has the great advantage to need a limited number of optical components. However its drawback is that at a given instant the different spectral pixels don't see the same spot in the field. We propose a new design to remedy this drawback by the adjunction of a dispersive system in the fore-optics.

InSight Lander in Mars-Surface Configuration

NASA Image and Video Library

2015-05-27

The solar arrays on NASA's InSight lander are deployed in this test inside a clean room at Lockheed Martin Space Systems, Denver. This configuration is how the spacecraft will look on the surface of Mars. The image was taken on April 30, 2015. InSight, for Interior Exploration Using Seismic Investigations, Geodesy and Heat Transport, is scheduled for launch in March 2016 and landing in September 2016. It will study the deep interior of Mars to advance understanding of the early history of all rocky planets, including Earth. Note: After thorough examination, NASA managers have decided to suspend the planned March 2016 launch of the Interior Exploration using Seismic Investigations Geodesy and Heat Transport (InSight) mission. The decision follows unsuccessful attempts to repair a leak in a section of the prime instrument in the science payload. http://photojournal.jpl.nasa.gov/catalog/PIA19664

Design of an unmanned Martian polar exploration system

NASA Technical Reports Server (NTRS)

Baldwin, Curt; Chitwood, Denny; Demann, Brian; Ducheny, Jordan; Hampton, Richard; Kuhns, Jesse; Mercer, Amy; Newman, Shawn; Patrick, Chris; Polakowski, Tony

1994-01-01

The design of an unmanned Martian polar exploration system is presented. The system elements include subsystems for transportation of material from earth to Mars, study of the Martian north pole, power generation, and communications. Early next century, three Atlas 2AS launch vehicles will be used to insert three Earth-Mars transfer vehicles, or buses, into a low-energy transfer orbit. Capture at Mars will be accomplished by aerobraking into a circular orbit. Each bus contains four landers and a communications satellite. Six of the twelve total landers will be deployed at 60 deg intervals along 80 deg N, and the remaining six landers at 5 deg intervals along 30 deg E from 65 deg N to 90 deg N by a combination of retrorockets and parachutes. The three communications satellites will be deployed at altitudes of 500 km in circular polar orbits that are 120 deg out of phase. These placements maximize the polar coverage of the science and communications subsystems. Each lander contains scientific equipment, two microrovers, power supplies, communications equipment, and a science computer. The lander scientific equipment includes a microweather station, seismometer, thermal probe, x-ray spectrometer, camera, and sounding rockets. One rover, designed for short-range (less than 2 km) excursions from the lander, includes a mass spectrometer for mineral analysis, an auger/borescope system for depth profiling, a deployable thermal probe, and charge coupled device cameras for terrain visualization/navigation. The second rover, designed for longer-range (2-5 km) excursions from the lander, includes radar sounding/mapping equipment, a seismometer, and laser ranging devices. Power for all subsystems is supplied by a combination of solar cells, Ni-H batteries, and radioisotope thermoelectric generators. Communications are sequenced from rovers, sounding rockets, and remote sensors to the lander, then to the satellites, through the Deep Space Network to and from earth.

Phoenix Telltale Movement

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

This is an animation of a camera pushing through NASA's Phoenix Mars Lander's Stereo Surface Imager (SSI). At the conclusion of the animation is a set of SSI images of the telltale taken on the first, second, and third days of the mission, or sols 1, 2, and 3 (May 26, 27, and 28, 2008). The last set of images were taken one minute apart and shows the telltale moving in the wind.

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

Phoenix Laser Beam in Action on Mars

NASA Image and Video Library

2008-09-30

The Surface Stereo Imager camera aboard NASA Phoenix Mars Lander acquired a series of images of the laser beam in the Martian night sky. Bright spots in the beam are reflections from ice crystals in the low level ice-fog.

Roll-Off Test at JPL

NASA Image and Video Library

2004-01-11

This still image illustrates what the Mars Exploration Rover Spirit will look like as it rolls off the northeastern side of the lander on Mars. The image was taken from footage of rover testing at JPL In-Situ Instruments Laboratory, or Testbed.

Viking Lander 1's U.S. Flag on Mars Surface

NASA Technical Reports Server (NTRS)

1976-01-01

The flag of the United States with the rocky Martian surface in the background is seen in this color picture taken on the sixth day of Viking Lander 1 on Mars (July 26). The flag is on the RTG (Radioisotope Thermoelectric Generator) wind screen. Below the flag is the bicentennial logo and the Viking symbol which shows an ancient Viking ship. This Viking symbol was designed by Peter Purol of Baltimore, winner of the Viking logo contest open to high school science students. To the right is the Reference Test Chart used for color balancing of the color images. At the bottom is the GCMS Processor Distribution Assembly with the wind screens unfurled demonstrating that the GCMS cover was deployed properly. The scene in the background is looking almost due west on Mars. The lighter zone at the far horizon is about 3 km (nearly 2 miles) from the Lander. The darker line below this is a hill crest much closer to the Lander (about 200 m or about 650 feet). The picture was taken at local Mars Time of 7:18 A.M., hence the relatively dark sky and the far horizon illuminated by the sun just rising behind the Lander.

Stereo View of Phoenix Test Sample Site

NASA Image and Video Library

2008-06-02

This anaglyph image, acquired by NASA’s Phoenix Lander’s Surface Stereo Imager on June 1, 2008, shows a stereoscopic 3D view of the so-called Knave of Hearts first-dig test area to the north of the lander. 3D glasses are necessary to view this image.

MARS PATHFINDER PYRO SYSTEMS SWITCHING ACTIVITY

NASA Technical Reports Server (NTRS)

1996-01-01

The Mars Pathfinder lander is subjected to a electrical and functional tests of its pyrotechic petal deployer system by Jet Propulsion Laboratory (JPL) engineers and technicians in KSC's Spacecraft Assembly and Encapsulation Facility (SAEF-2). In the background is the Pathfinder cruise stage, which the lander will be mated to once its functional tests are complete. The lander will remain attached to this stage during its six-to-seven-month journey to Mars. When the lander touches down on the surface of Mars next year, the pyrotechnic system will deploy its three petals open like a flower and allow the Sojourner autonomous rover to explore the Martian surface. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2, the beginning of a 24-day launch period. JPL is managing the Mars Pathfinder project for NASA.

COMPASS Final Report: Advanced Long-Life Lander Investigating the Venus Environment (ALIVE)

NASA Technical Reports Server (NTRS)

Oleson, Steven R.; Paul, Michael

2016-01-01

The COncurrent Multi-disciplinary Preliminary Assessment of Space Systems (COMPASS) Team partnered with the Applied Research Laboratory to perform a NASA Innovative Advanced Concepts (NIAC) Program study to evaluate chemical based power systems for keeping a Venus lander alive(power and cooling) and functional for a period of days. The mission class targeted was either a Discovery ($500M) or New Frontiers ($750M to $780M) class mission. Historic Soviet Venus landers have only lasted on the order of 2 hours in the extreme Venus environment: temperatures of 460 C and pressures of 93 bar. Longer duration missions have been studied using plutonium powered systems to operate and cool landers for up to a year. However, the plutonium load is very large. This NIAC study sought to still provide power and cooling but without the plutonium.

Enabling technologies for Chinese Mars lander guidance system

NASA Astrophysics Data System (ADS)

Jiang, Xiuqiang; Li, Shuang

2017-04-01

Chinese first Mars exploration activity, orbiting landing and roaming collaborative mission, has been programmed and started. As a key technology, Mars lander guidance system is intended to serve atmospheric entry, descent and landing (EDL) phases. This paper is to report the formation process of enabling technology road map for Chinese Mars lander guidance system. First, two scenarios of the first-stage of the Chinese Mars exploration project are disclosed in detail. Second, mission challenges and engineering needs of EDL guidance, navigation, and control (GNC) are presented systematically for Chinese Mars exploration program. Third, some useful related technologies developed in China's current aerospace projects are pertinently summarized, especially on entry guidance, parachute descent, autonomous hazard avoidance and safe landing. Finally, an enabling technology road map of Chinese Mars lander guidance is given through technological inheriting and improving.

Hazard detection and avoidance sensor for NASA's planetary landers

NASA Technical Reports Server (NTRS)

Lau, Brian; Chao, Tien-Hsin

1992-01-01

An optical terrain analysis based sensor system specifically designed for landing hazard detection as required for NASA's autonomous planetary landers is introduced. This optical hazard detection and avoidance (HDA) sensor utilizes an optoelectronic wedge-and-ting (WRD) filter for Fourier transformed feature extraction and an electronic neural network processor for pattern classification. A fully implemented optical HDA sensor would assure safe landing of the planetary landers. Computer simulation results of a successful feasibility study is reported. Future research for hardware system implementation is also provided.

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

NASA Technical Reports Server (NTRS)

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

2017-01-01

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

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.

SeeStar: an open-source, low-cost imaging system for subsea observations

NASA Astrophysics Data System (ADS)

Cazenave, F.; Kecy, C. D.; Haddock, S.

2016-02-01

Scientists and engineers at the Monterey Bay Aquarium Research Institute (MBARI) have collaborated to develop SeeStar, a modular, light weight, self-contained, low-cost subsea imaging system for short- to long-term monitoring of marine ecosystems. SeeStar is composed of separate camera, battery, and LED lighting modules. Two versions of the system exist: one rated to 300 meters depth, the other rated to 1500 meters. Users can download plans and instructions from an online repository and build the system using low-cost off-the-shelf components. The system utilizes an easily programmable Arduino based controller, and the widely distributed GoPro camera. The system can be deployed in a variety of scenarios taking still images and video and can be operated either autonomously or tethered on a range of platforms, including ROVs, AUVs, landers, piers, and moorings. Several Seestar systems have been built and used for scientific studies and engineering tests. The long-term goal of this project is to have a widely distributed marine imaging network across thousands of locations, to develop baselines of biological information.

Selecting A Landing Site Of Astrobiological Interest For Mars Landers And Sample Return Missions

NASA Astrophysics Data System (ADS)

Wills, Danielle; Monaghan, E.; Foing, B.

2008-09-01

The landscape of Mars, despite its apparent hostility to life, is riddled with geological and mineralogical signs of past or present hydrological activity. As such, it is a key target for astrobiological exploration. The aim of this work is to combine data and studies to select top priority landing locations for in-situ landers and sample return missions to Mars. We report in particular on science and technical criteria and our data analysis for sites of astrobiological interest. 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 evidence for volatiles, organics and habitability conditions). We discuss key mission objectives, and consider the accessibility of chosen locations. We describe what additional measurements are needed, and outline the technical and scientific operations requirements of in-situ landers and sample return missions to Mars.

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.

First Dodo Trench with White Layer Visible in Dig Area

NASA Technical Reports Server (NTRS)

2008-01-01

These color images were taken by NASA's Phoenix Mars Lander's Stereo Surface Imager on the ninth Martian day of the mission, or Sol 9 (June 3, 2008). The images of the trench shows a white layer that has been uncovered by the Robotic Arm (RA) scoop and is now visible in the wall of the trench. This trench was the first one dug by the RA to understand the Martian soil and plan the digging strategy.

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.

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.

Integration Testing of Space Flight Systems

NASA Technical Reports Server (NTRS)

Honeycutt, Timothy; Sowards, Stephanie

2008-01-01

Based on the previous success' of Multi-Element Integration Testing (MEITs) for the International Space Station Program, these type of integrated tests have also been planned for the Constellation Program: MEIT (1) CEV to ISS (emulated) (2) CEV to Lunar Lander/EDS (emulated) (3) Future: Lunar Surface Systems and Mars Missions Finite Element Integration Test (FEIT) (1) CEV/CLV (2) Lunar Lander/EDS/CaL V Integrated Verification Tests (IVT) (1) Performed as a subset of the FEITs during the flight tests and then performed for every flight after Full Operational Capability (FOC) has been obtained with the flight and ground Systems.

A Long Way From Home

NASA Technical Reports Server (NTRS)

2004-01-01

This pair of pieced-together images was taken by the Mars Exploration Rover Spirit's left navigation camera looking aft on March 6, 2004. It reveals the long and rocky path of nearly 240 meters (787 feet) that Spirit had traveled since safely arriving at Gusev Crater on Jan. 3, 2004.

The lander can still be seen in the distance, but will never be 'home' again for the journeying rover. This image is also a tribute to the effectiveness of the autonomous navigation system that the rovers use during parts of their martian drives. Instead of driving directly through the 'hollow' seen in the middle right of the image, the autonomous navigation system guided Spirit around the high ridge bordering the hollow.

In the two days after these images were taken, Spirit has traveled roughly 60 meters (197 feet) farther toward its destination at the crater nicknamed 'Bonneville'.

Planetary entry, descent, and landing technologies

NASA Astrophysics Data System (ADS)

Pichkhadze, K.; Vorontsov, V.; Polyakov, A.; Ivankov, A.; Taalas, P.; Pellinen, R.; Harri, A.-M.; Linkin, V.

2003-04-01

Martian meteorological lander (MML) is intended for landing on the Martian surface in order to monitor the atmosphere at landing point for one Martian year. MMLs shall become the basic elements of a global network of meteorological mini-landers, observing the dynamics of changes of the atmospheric parameters on the Red Planet. The MML main scientific tasks are as follows: (1) Study of vertical structure of the Martian atmosphere throughout the MML descent; (2) On-surface meteorological observations for one Martian year. One of the essential factors influencing the lander's design is its entry, descent, and landing (EDL) sequence. During Phase A of the MML development, five different options for the lander's design were carefully analyzed. All of these options ensure the accomplishment of the above-mentioned scientific tasks with high effectiveness. CONCEPT A (conventional approach): Two lander options (with a parachute system + airbag and an inflatable airbrake + airbag) were analyzed. They are similar in terms of fulfilling braking phases and completely analogous in landing by means of airbags. CONCEPT B (innovative approach): Three lander options were analyzed. The distinguishing feature is the presence of inflatable braking units (IBU) in their configurations. SELECTED OPTION (innovative approach): Incorporating a unique design approach and modern technologies, the selected option of the lander represents a combination of the options analyzed in the framework of Concept B study. Currently, the selected lander option undergoes systems testing (Phase D1). Several MMLs can be delivered to Mars in frameworks of various missions as primary or piggybacking payload: (1) USA-led "Mars Scout" (2007); (2) France-led "NetLander" (2007/2009); (3) Russia-led "Mars-Deimos-Phobos sample return" (2007); (4) Independent mission (currently under preliminary study); etc.

False Color Terrain Model of Phoenix Workspace

NASA Image and Video Library

2008-05-28

This is a terrain model of Phoenix Robotic Arm workspace. It has been color coded by depth with a lander model for context. The model has been derived using images from the depth perception feature from Phoenix Surface Stereo Imager SSI.

Rest In Peace Mars Polar Lander

NASA Image and Video Library

2002-12-04

On 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. http://photojournal.jpl.nasa.gov/catalog/PIA04016

Spirit rover localization and topographic mapping at the landing site of Gusev crater, Mars

USGS Publications Warehouse

Li, R.; Archinal, B.A.; Arvidson, R. E.; Bell, J.; Christensen, P.; Crumpler, L.; Des Marais, D.J.; Di, K.; Duxbury, T.; Golombek, M.P.; Grant, J. A.; Greeley, R.; Guinn, J.; Johnson, Aaron H.; Kirk, R.L.; Maimone, M.; Matthies, L.H.; Malin, M.; Parker, T.; Sims, M.; Thompson, S.; Squyres, S. W.; Soderblom, L.A.

2006-01-01

By sol 440, the Spirit rover has traversed a distance of 3.76 km (actual distance traveled instead of odometry). Localization of the lander and the rover along the traverse has been successfully performed at the Gusev crater landing site. We localized the lander in the Gusev crater using two-way Doppler radio positioning and cartographic triangulations through landmarks visible in both orbital and ground images. Additional high-resolution orbital images were used to verify the determined lander position. Visual odometry and bundle adjustment technologies were applied to compensate for wheel slippage, azimuthal angle drift, and other navigation errors (which were as large as 10.5% in the Husband Hill area). We generated topographic products, including 72 ortho maps and three-dimensional (3-D) digital terrain models, 11 horizontal and vertical traverse profiles, and one 3-D crater model (up to sol 440). Also discussed in this paper are uses of the data for science operations planning, geological traverse surveys, surveys of wind-related features, and other science applications. Copyright 2006 by the American Geophysical Union.

Solar radiation for Mars power systems

NASA Technical Reports Server (NTRS)

Appelbaum, Joseph; Landis, Geoffrey A.

1991-01-01

Detailed information about the solar radiation characteristics on Mars are necessary for effective design of future planned solar energy systems operating on the surface of Mars. A procedure and solar radiation related data from which the diurnally and daily variation of the global, direct (or beam), and diffuse insolation on Mars are calculated, are presented. The radiation data are based on measured optical depth of the Martian atmosphere derived from images taken of the Sun with a special diode on the Viking Lander cameras; and computation based on multiple wavelength and multiple scattering of the solar radiation.

Mars Descent Imager (MARDI) on the Mars Polar Lander

USGS Publications Warehouse

Malin, M.C.; Caplinger, M.A.; Carr, M.H.; Squyres, S.; Thomas, P.; Veverka, J.

2001-01-01

The Mars Descent Imager, or MARDI, experiment on the Mars Polar Lander (MPL) consists of a camera characterized by small physical size and mass (???6 ?? 6 ?? 12 cm, including baffle; <500 gm), low power requirements (<2.5 W, including power supply losses), and high science performance (1000 x 1000 pixel, low noise). The intent of the investigation is to acquire nested images over a range of resolutions, from 8 m/pixel to better than 1 cm/pixel, during the roughly 2 min it takes the MPL to descend from 8 km to the surface under parachute and rocket-powered deceleration. Observational goals will include studies of (1) surface morphology (e.g., nature and distribution of landforms indicating past and present environmental processes); (2) local and regional geography (e.g., context for other lander instruments: precise location, detailed local relief); and (3) relationships to features seen in orbiter data. To accomplish these goals, MARDI will collect three types of images. Four small images (256 x 256 pixels) will be acquired on 0.5 s centers beginning 0.3 s before MPL's heatshield is jettisoned. Sixteen full-frame images (1024 X 1024, circularly edited) will be acquired on 5.3 s centers thereafter. Just after backshell jettison but prior to the start of powered descent, a "best final nonpowered descent image" will be acquired. Five seconds after the start of powered descent, the camera will begin acquiring images on 4 s centers. Storage for as many as ten 800 x 800 pixel images is available during terminal descent. A number of spacecraft factors are likely to impact the quality of MARDI images, including substantial motion blur resulting from large rates of attitude variation during parachute descent and substantial rocket-engine-induced vibration during powered descent. In addition, the mounting location of the camera places the exhaust plume of the hydrazine engines prominently in the field of view. Copyright 2001 by the American Geophysical Union.

Transient stress-coupling between the 1992 Landers and 1999 Hector Mine, California, earthquakes

USGS Publications Warehouse

Masterlark, Timothy; Wang, H.F.

2002-01-01

A three-dimensional finite-element model (FEM) of the Mojave block region in southern California is constructed to investigate transient stress-coupling between the 1992 Landers and 1999 Hector Mine earthquakes. The FEM simulates a poroelastic upper-crust layer coupled to a viscoelastic lower-crust layer, which is decoupled from the upper mantle. FEM predictions of the transient mechanical behavior of the crust are constrained by global positioning system (GPS) data, interferometric synthetic aperture radar (InSAR) images, fluid-pressure data from water wells, and the dislocation source of the 1999 Hector Mine earthquake. Two time-dependent parameters, hydraulic diffusivity of the upper crust and viscosity of the lower crust, are calibrated to 10–2 m2·sec–1 and 5 × 1018 Pa·sec respectively. The hydraulic diffusivity is relatively insensitive to heterogeneous fault-zone permeability specifications and fluid-flow boundary conditions along the elastic free-surface at the top of the problem domain. The calibrated FEM is used to predict the evolution of Coulomb stress during the interval separating the 1992 Landers and 1999 Hector Mine earthquakes. The predicted change in Coulomb stress near the hypocenter of the Hector Mine earthquake increases from 0.02 to 0.05 MPa during the 7-yr interval separating the two events. This increase is primarily attributed to the recovery of decreased excess fluid pressure from the 1992 Landers coseismic (undrained) strain field. Coulomb stress predictions are insensitive to small variations of fault-plane dip and hypocentral depth estimations of the Hector Mine rupture.

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

NASA Technical Reports Server (NTRS)

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

2017-01-01

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

After Rasping by Phoenix in 'Snow White' Trench, Sol 60

NASA Technical Reports Server (NTRS)

2008-01-01

NASA's Phoenix Mars Lander used the motorized rasp on the back of its robotic arm scoop during the mission's 60th Martian day, or sol, (July 26, 2008) to penetrate a hard layer at the bottom of a trench informally called 'Snow White.' This view, taken by the lander's Surface Stereo Imager and presented in approximately true color, shows the trench later the same sol.

Most of the 16 holes left by a four-by-four array of rasp placements are visible in the central area of the image.

A total 3 cubic centimeters, or about half a teaspoon, of material was collected in the scoop. Material in the scoop was collected both by the turning rasp, which threw material into the scoop through an opening at the back of the scoop, and by the scoop's front blade, which was run over the rasped area to pick up more shavings.

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

The Viking biology results

NASA Technical Reports Server (NTRS)

Klein, Harold P.

1989-01-01

A brief review of the purposes and the results from the Viking Biology experiments is presented, in the expectation that the lessons learned from this mission will be useful in planning future approaches to the biological exploration of Mars. Since so little was then known about potential micro-environments on Mars, three different experiments were included in the Viking mission, each one based on different assumptions about what Martian organisms might be like. In addition to the Viking Biology Instrument (VBI), important corollary information was obtained from the Viking lander imaging system and from the molecular analysis experiments that were conducted using the gas chromatograph-mass spectrometer (GCMS) instrument. No biological objects were noted by the lander imaging instrument. The GCMS did not detect any organic compounds. A description of the tests conducted by the Gas Exchange Experiment, the Labeled Release experiment, and the Pyrolytic Release experiment is given. Results are discussed. Taken as a whole, the Viking data yielded no unequivocal evidence for a Martian biota at either landing site. The results also revealed the presence of one or more reactive oxidants in the surface material and these need to be further characterized, as does the range of micro-environments, before embarking upon future searches for extant life on Mars.

Characterization of rock populations on planetary surfaces - Techniques and a preliminary analysis of Mars and Venus

NASA Technical Reports Server (NTRS)

Garvin, J. B.; Mouginis-Mark, P. J.; Head, J. W.

1981-01-01

A data collection and analysis scheme developed for the interpretation of rock morphology from lander images is reviewed with emphasis on rock population characterization techniques. Data analysis techniques are also discussed in the context of identifying key characteristics of a rock that place it in a single category with similar rocks. Actual rock characteristics observed from Viking and Venera lander imagery are summarized. Finally, some speculations regarding the block fields on Mars and Venus are presented.

Automatic control of a mobile Viking lander on the surface of Mars

NASA Technical Reports Server (NTRS)

Moore, J.; Scofield, W.; Tobey, W.

1976-01-01

A mobile lander system is being considered for use in a possible follow-on mission to the Viking '75 landings on Mars. A mobile Viking lander, which could be launched as early as the 1979 opportunity, would be capable of traversing 100 m to 1 km per day on a commanded heading while sensing hazards and performing avoidance maneuvers. The degree of autonomous control, and consequently the daily traverse range, is still under study. The mobility concept requires the addition of: (1) track-laying or wheel units in place of the Viking Lander footpads, (2) a set of hazard and navigation sensors, and (3) a mobility control computer capability. The technology required to develop these three subsystems is available today. The principal objective of current design studies, as described in this paper, is to define a mobile lander system that will demonstrate high reliability and fail-safe hazard avoidance while achieving range- and terrain-handling capabilities which satisfy the Mars exploration science requirements.

Experiences with operations and autonomy of the Mars Pathfinder Microrover.

NASA Astrophysics Data System (ADS)

Mishkin, A. H.; Morrison, J. C.; Nguyen, T. T.; Stone, H. W.; Cooper, B. K.; Wilcox, B. H.

The Microrover Flight Experiment (MFEX) is a NASA OACT (Office of Advanced Concepts and Technology) flight experiment which, integrated with the Mars Pathfinder (MPF) lander and spacecraft system, landed on Mars on July 4, 1997. In the succeeding 30 sols (1 sol = 1 Martian day), the Sojourner microrover accomplished all of its primary and extended mission objectives. After completion of the originally planned extended mission, MFEX continued to conduct a series of technology experiments, deploy its alpha proton X-ray spectrometer (APXS) on rocks and soil, and image both terrain features and the lander. This mission was conducted under the constraints of a once-per-sol opportunity for command and telemetry transmissions between the lander and Earth operators. As such, the MFEX rover was required to carry out its mission, including terrain navigation and contingency response, under supervised autonomous control. For example, goal locations were specified daily by human operators; the rover then safely traversed to these locations. During traverses, the rover autonomously detected and avoided rock, slope, and drop-off hazards, changing its path as needed before turning back towards its goal. This capability to operate in an unmodeled environment, choosing actions in response to sensor input to accomplish requested objectives, is unique among robotic space missions to date.

Location of Spirit's Home

NASA Technical Reports Server (NTRS)

2004-01-01

This image shows where Earth would set on the martian horizon from the perspective of the Mars Exploration Rover Spirit if it were facing northwest atop its lander at Gusev Crater. Earth cannot be seen in this image, but engineers have mapped its location. This image mosaic was taken by the hazard-identification camera onboard Spirit.

SNAP 19 Viking Program. Bimonthly technical progress report, April-May 1980

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

Not Available

1980-01-01

Monitoring and evaluation of Viking Lander 1 power system data continued. The RTG series power range as measured at the PCDA was 65 to 67 watts at finroot temperatures between 280/sup 0/F and 310/sup 0/F. The Mars Lander performance history of Viking 1 include both the minimum and maximum data for each of the SOL days. Final available power system data for Viking Lander 2 are shown. Typical SOL day cycles for mission day 1193 are presented. The RTG series power ranged from 69 to 70 watts at finroot temperatures between 270/sup 0/F and 300/sup 0/F. The Mars Lander performancemore » history for Viking 2 is shown. Power system performance data for Pioneer 10 and Pioneer Saturn (initially designated Pioneer 11) were monitored through the reporting period. After adjusting for the telemetry characteristics, the estimated RTG system net power was 114 watts for both Pioneer 10 and Pioneer Saturn.« less

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 5 DoF robotic arm and can travel with an average speed of about 1 cm/s. The Rover is generally tele-operated but has the capability to execute autonomously pre-selected operation tasks, is aware of its current status and analyses potential hazards to avoid loss of its mission by operator failure. It is equipped with a model payload consisting of a camera system for multi-spectra including infra-red, a Raman-LIBS and a CLUPI. In addition its task is to position seismometers at a distance of about 1 km away from the lander. The baseline scenario includes a launch in the 2018 timeframe and one year of surface operations at the Shakleton crater rim. This presentation will focus on the following points: • Mission architecture and spacecraft layout as elaborated during the past study activities • Surface operations of lander and rover • Current mission capability to support scientific investigations at the lunar South Pole

Zenith Movie showing Phoenix's Lidar Beam (Animation)

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

A laser beam from the Canadian-built lidar instrument on NASA's Phoenix Mars Lander can be seen in this contrast-enhanced sequence of 10 images taken by Phoenix's Surface Stereo Imager on July 26, 2008, during early Martian morning hours of the mission's 61st Martian day after landing.

The view is almost straight up and includes about 1.5 kilometer (about 1 mile) of the length of the beam. The camera, from its position close to the lidar on the lander deck, took the images through a green filter centered on light with wavelength 532 nanometers, the same wavelength of the laser beam. The movie has been artificially colored to to approximately match the color that would be seen looking through this filter on Mars. Contrast is enhanced to make the beam more visible.

The lidar beam can be seen extending from the lower right to the upper right, near the zenith, as it reflects off particles suspended in the atmosphere. Particles that scatter the beam directly into the camera can be seen to produce brief sparkles of light. In the background, dust can be seen drifting across the sky pushed by winds aloft.

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.

Sublimation of Exposed Snow Queen Surface Water Ice as Observed by the Phoenix Mars Lander

NASA Astrophysics Data System (ADS)

Markiewicz, W. J.; Keller, H. U.; Kossacki, K. J.; Mellon, M. T.; Stubbe, H. F.; Bos, B. J.; Woida, R.; Drube, L.; Leer, K.; Madsen, M. B.; Goetz, W.; El Maarry, M. R.; Smith, P.

2008-12-01

One of the first images obtained by the Robotic Arm Camera on the Mars Phoenix Lander was that of the surface beneath the spacecraft. This image, taken on sol 4 (Martian day) of the mission, was intended to check the stability of the footpads of the lander and to document the effect the retro-rockets had on the Martian surface. Not completely unexpected the image revealed an oval shaped, relatively bright and apparently smooth object, later named Snow Queen, surrounded by the regolith similar to that already seen throughout the landscape of the landing site. The object was suspected to be the surface of the ice table uncovered by the blast of the retro-rockets during touchdown. High resolution HiRISE images of the landing site from orbit, show a roughly circular dark region of about 40 m diameter with the lander in the center. A plausible explanation for this region being darker than the rest of the visible Martian Northern Planes (here polygonal patterns) is that a thin layer of the material ejected by the retro-rockets covered the original surface. Alternatively the thrusters may have removed the fine surface dust during the last stages of the descent. A simple estimate requires that about 10 cm of the surface material underneath the lander is needed to be ejected and redistributed to create the observed dark circular region. 10 cm is comparable to 4-5 cm predicted depth at which the ice table was expected to be found at the latitude of the Phoenix landing site. The models also predicted that exposed water ice should sublimate at a rate not faster but probably close to 1 mm per sol. Snow Queen was further documented on sols 5, 6 and 21 with no obvious changes detected. The following time it was imaged was on sol 45, 24 sols after the previous observation. This time some clear changes were obvious. Several small cracks, most likely due to thermal cycling and sublimation of water ice appeared. Nevertheless, the bulk of Snow Queen surface remained smooth. The next image of Snow Queen was taken on sol 73. This time its appearance was dramatically different. The surface had become much rougher and many cracks of at least 1 mm depth and decimeter scale length had appeared. The surface colour of Snow Queen was now no longer different from that of the surrounding regolith. This observation is compatible with the ice table sublimating away, leaving behind a lag deposit of thickness of the order of 1 mm. We will present these data as well as thermal models, including the diurnal cycle of the interaction with the atmosphere, which may explain the observed evolution of Snow Queen.

Hydrolytic Network Structure Degradation in Multi-Component Polycyanurate Networks

DTIC Science & Technology

2016-07-28

Approved for Public Release; Distribution Unlimited. PA# 16335 UNCLASSIFIED Cyanate Esters Around the Solar System Images:  courtesy  NASA  (public...release) • The science decks on the Mars Phoenix lander are made from M55J/cyanate ester composites • The solar panel supports on the MESSENGER space...designed by NASA for use as instrument holding structures aboard the James Webb Space Telescope Photo courtesy of  NASA 5Distribution A: Approved for

Cold Helium Pressurization for Liquid Oxygen / Liquid Methane Propulsion Systems: Fully-Integrated Initial Hot-Fire Test Results

NASA Technical Reports Server (NTRS)

Morehead, R. L.; Atwell, M. J.; Melcher, J. C.; Hurlbert, E. A.

2016-01-01

A prototype cold helium active pressurization system was incorporated into an existing liquid oxygen (LOX) / liquid methane (LCH4) prototype planetary lander and hot-fire tested to collect vehicle-level performance data. Results from this hot-fire test series were used to validate integrated models of the vehicle helium and propulsion systems and demonstrate system effectiveness for a throttling lander. Pressurization systems vary greatly in complexity and efficiency between vehicles, so a pressurization performance metric was also developed as a means to compare different active pressurization schemes. This implementation of an active repress system is an initial sizing draft. Refined implementations will be tested in the future, improving the general knowledge base for a cryogenic lander-based cold helium system.

KSC-2012-3948

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the launch platform for the Project Morpheus lander at the midfield point of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida. At the north end of the runway is a rock and crater-filled planetary scape built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3949

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the launch platform for the Project Morpheus lander at the midfield point of the Shuttle Landing Facility, or SLF, at NASA’s Kennedy Space Center in Florida. At the north end of the runway is a rock and crater-filled planetary scape built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

Particle Ejection and Levitation Technology (PELT)

NASA Technical Reports Server (NTRS)

2008-01-01

Each of the six Apollo landers touched down at unique sites on the lunar surface. Aside from the Apollo 12 landing site located 180 meters from the Surveyor III lander, plume impingement effects on ground hardware during the landings were not a problem. The planned return to the Moon requires numerous landings at the same site. Since the top few centimeters of lunar soil are loosely packed regolith, plume impingement from the lander will eject the granular material at high velocities. A picture shows what the astronauts viewed from the window of the Apollo 14 lander. There was tremendous dust excavation beneath the vehicle. With high-vacuum conditions on the Moon (10 (exp -14) to 10 (exp -12) torr), motion of all particles is completely ballistic. Estimates derived from damage to Surveyor III caused by the Apollo 12 lander show that the speed of the ejected regolith particles varies from 100 m/s to 2,000 m/s. It is imperative to understand the physics of plume impingement to safely design landing sites for future Moon missions. Aerospace scientists and engineers have examined and analyzed images from Apollo video extensively in an effort to determine the theoretical effects of rocket exhaust impingement. KSC has joined the University of Central Florida (UCF) to develop an instrument that will measure the 3-D vector of dust flow caused by plume impingement during descent of landers. The data collected from the instrument will augment the theoretical studies and analysis of the Apollo videos.

Shark

NASA Technical Reports Server (NTRS)

1997-01-01

This false color composite image from the Pathfinder lander shows the rock 'Shark' at upper right (Shark is about 0.69 m wide, 0.40 m high, and 6.4 m from the lander). The rock looks like a conglomerate in Sojourner rover images, but only the large elements of its surface textures can be seen here. This demonstrates the usefulness of having a robot rover geologist able to examine rocks up close.

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 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.

Are the Viking Lander sites representative of the surface of Mars?

NASA Technical Reports Server (NTRS)

Jakosky, B. M.; Christensen, P. R.

1986-01-01

Global remote sensing data of the Martian surface, collected by earth- and satellite-based instruments, are compared with data from the two Viking Landers to determine if the Lander data are representative of the Martian surface. The landing sites are boulder-strewn and feature abundant fine material and evidence of strong eolian forces. One site (VL-1) is in a plains-covered basin which is associated with volcanic activity; the VL-2 site is in the northern plains. Thermal IR, broadband albedo, color imaging and radar remote sensing has been carried out of the global Martian surface. The VL-1 data do not fit a general correlation observed between increases in 70-cm radar cross-sections and thermal inertia. A better fit is found with 12.5-cm cross sections, implying the presence of a thinner or discontinuous duricrust at the VL-1 site, compared to other higher-inertia regions. A thin dust layer is also present at the VL-2 site, based on the Lander reflectance data. The Lander sites are concluded to be among the three observed regions of anomalous reflectivity, which can be expected in low regions selected for the landings. Recommendations are furnished for landing sites of future surface probes in order to choose sites more typical of the global Martian surface.

Martian Dust Devil Movie, Phoenix Sol 104

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager on NASA's Phoenix Mars Lander caught this dust devil in action west of the lander in four frames shot about 50 seconds apart from each other between 11:53 a.m. and 11:56 a.m. local Mars time on Sol 104, or the 104th Martian day of the mission, Sept. 9, 2008.

Dust devils have not been detected in any Phoenix images from earlier in the mission, but at least six were observed in a dozen images taken on Sol 104.

Dust devils are whirlwinds that often occur when the Sun heats the surface of Mars, or some areas on Earth. The warmed surface heats the layer of atmosphere closest to it, and the warm air rises in a whirling motion, stirring dust up from the surface like a miniature tornado.

The dust devil visible in this sequence was about 1,000 meters (about 3,300 feet) from the lander when the first frame was taken, and had moved to about 1,700 meters (about 5,600 feet) away by the time the last frame was taken about two and a half minutes later. The dust devil was moving westward at an estimated speed of 5 meters per second (11 miles per hour), which is similar to typical late-morning wind speed and direction indicated by the telltale wind gauge on Phoenix.

This dust devil is about 5 meters (16 feet) in diameter. This is much smaller than dust devils that have been observed by NASA's Mars Exploration Rover Spirit much closer to the equator. It is closer in size to dust devils seen from orbit in the Phoenix landing region, though still smaller than those..

The image has been enhanced to make the dust devil easier to see. Some of the frame-to-frame differences in the appearance of foreground rocks is because each frame was taken through a different color filter.

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

Mars Lander/Rover vehicle development: An advanced space design project for USRA and NASA/OAST

NASA Technical Reports Server (NTRS)

1987-01-01

The accomplishments of the Utah State University (USU) Mars Lander/Rover (MLR) design class during the Winter Quarter are delineated and explained. Environment and trajectory, ground systems, balloon system, and payload system are described. Results from this effort will provide a valid and useful basis for further studies of Mars exploratory vehicles.

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.

Insights into the relationship between surface and subsurface activity from mechanical modeling of the 1992 Landers M7.3 earthquake

NASA Astrophysics Data System (ADS)

Madden, E. H.; Pollard, D. D.

2009-12-01

Multi-fault, strike-slip earthquakes have proved difficult to incorporate into seismic hazard analyses due to the difficulty of determining the probability of these ruptures, despite collection of extensive data associated with such events. Modeling the mechanical behavior of these complex ruptures contributes to a better understanding of their occurrence by elucidating the relationship between surface and subsurface earthquake activity along transform faults. This insight is especially important for hazard mitigation, as multi-fault systems can produce earthquakes larger than those associated with any one fault involved. We present a linear elastic, quasi-static model of the southern portion of the 28 June 1992 Landers earthquake built in the boundary element software program Poly3D. This event did not rupture the extent of any one previously mapped fault, but trended 80km N and NW across segments of five sub-parallel, N-S and NW-SE striking faults. At M7.3, the earthquake was larger than the potential earthquakes associated with the individual faults that ruptured. The model extends from the Johnson Valley Fault, across the Landers-Kickapoo Fault, to the Homestead Valley Fault, using data associated with a six-week time period following the mainshock. It honors the complex surface deformation associated with this earthquake, which was well exposed in the desert environment and mapped extensively in the field and from aerial photos in the days immediately following the earthquake. Thus, the model incorporates the non-linearity and segmentation of the main rupture traces, the irregularity of fault slip distributions, and the associated secondary structures such as strike-slip splays and thrust faults. Interferometric Synthetic Aperture Radar (InSAR) images of the Landers event provided the first satellite images of ground deformation caused by a single seismic event and provide constraints on off-fault surface displacement in this six-week period. Insight is gained by comparing the density, magnitudes and focal plane orientations of relocated aftershocks for this time frame with the magnitude and orientation of planes of maximum Coulomb shear stress around the fault planes at depth.

Development of an Audio Microphone for the Mars Surveyor 98 Lander

NASA Astrophysics Data System (ADS)

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

1998-01-01

In December 1999, the next Mars Surveyor Lander will bring the first microphone to the surface of Mars. The Mars Microphone represents a joint effort between the Planetary Society and the University of California at Berkeley Space Sciences Laboratory and is riding on the lander as part of the LIDAR instrument package provided by the Russian Academy of Sciences in Moscow. The inclusion of a microphone on the Mars Surveyor Lander represents a unique opportunity to sample for the first time the acoustic environment on the surface, including both natural and lander-generated sounds. Sounds produced by martian meteorology are among the signals to be recorded, including wind and impacts of sand particles on the instrument. Photographs from the Viking orbiters as well as Pathfinder images show evidence of small tornado-like vortices that may be acoustically detected, along with noise generated by static discharges possible during sandstorms. Lander-generated sounds that will be measured include the motion and digging of the lander arm as it gathers soil samples for analysis. Along with these scientific objectives, the Mars Microphone represents a powerful tool for public outreach by providing sound samples on the Internet recorded during the mission. The addition of audio capability to the lander brings us one step closer to a true virtual presence on the Mars surface by complementing the visual capabilities of the Mars Surveyor cameras. The Mars Microphone is contained in a 5 x 5 x 1 cm box, weighs less than 50 g, and uses 0.1 W of power during its most active times. The microphone used is a standard hearing-aid electret. The sound sampling and processing system relies on an RSC-164 speech processor chip, which performs 8-bit A/ D sampling and sound compression. An onboard flight program enables several modes for the instrument, including varying sample ranges of 5 kHz and 20 kHz, and a selectable gain setting with 64x dynamic range. The device automatically triggers on the loudest sound during a collection period for storage in an internal flash memory. Data returned by the lander consist of a compressed time-series acoustic waveform, between 2 and 10 s long, depending on the sample rate. In addition to the discrete waveform. capture, the instrument continuously records the mean power in each of six frequency bands in order to provide an average characterization of the martian acoustic environment. Once the data are retrieved from the telemetry, the compressed time series is expanded into a standard PC-compatible WAV file for analysis, which will include representation in spectral format using FFTs for quantitative characterization of the sound data. The WAV files will be used to share the data with the public via the Internet. The Mars Microphone will thus fulfill a dual role on the Mars Surveyor mission, one as a possible precursor to a more sophisticated acoustic instrument on future landers. and one as a mechanism to increase public awareness of efforts to explore and understand the martian climate and planetary history.

Happy Mars Solstice!

NASA Technical Reports Server (NTRS)

2008-01-01

This image was acquired by NASA's Phoenix Mars Lander's Surface Stereo Imager (SSI) in the late afternoon of the 30th Martian day of the mission, or Sol 30 (June 25, 2008). This is hours after the beginning of Martian northern summer. SSI used its natural-color filters, therefore the color is the color you would see on Mars. The image shows shadows from the SSI (left) and from the meteorological station mast (right) stretching toward the east as the sun dropped low in the west.

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

Phoenix Telltale Movie with Clouds, Sol 103

NASA Technical Reports Server (NTRS)

2008-01-01

NASA's Phoenix Mars Lander's telltale catches a breeze as clouds move over the landing site on Sol 103 (Sept. 7, 2008), the 103rd Martian day since landing.

Phoenix's Surface Stereo Imager took this series of images during daily telltale monitoring around 3 p.m. local solar time and captured the clouds moving over the landing site.

Phoenix can measure wind speed and direction by imaging the telltale, which is about about 10 centimeters (4 inches) tall. The telltale was built by the University of Aarhus, Denmark.

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.

Delivering Images for Mars Rover Science Planning

NASA Technical Reports Server (NTRS)

Edmonds, Karina

2008-01-01

A methodology has been developed for delivering, via the Internet, images transmitted to Earth from cameras on the Mars Explorer Rovers, the Phoenix Mars Lander, the Mars Science Laboratory, and the Mars Reconnaissance Orbiter spacecraft. The images in question are used by geographically dispersed scientists and engineers in planning Rover scientific activities and Rover maneuvers pertinent thereto.

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.

Viking lander battery performance, degradation, and reconditioning

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

Britting, A.O. Jr.

1981-01-01

On July 20 and September 3, 1976, Viking Landers 1 and 2 touched down on the surface of Mars. Prior to launch each lander, including its batteries was subjected to a sterilization temperature of 233 F for 54 hours. The results of battery performance, degradation and reconditioning are presented, including charge/discharge cycles, reconditioning technique, temperature history, early and current capacity. A brief description of the power system operation is also included.

Effects of cold-water corals on fish diversity and density (European continental margin: Arctic, NE Atlantic and Mediterranean Sea): Data from three baited lander systems

NASA Astrophysics Data System (ADS)

Linley, T. D.; Lavaleye, M.; Maiorano, P.; Bergman, M.; Capezzuto, F.; Cousins, N. J.; D'Onghia, G.; Duineveld, G.; Shields, M. A.; Sion, L.; Tursi, A.; Priede, I. G.

2017-11-01

Autonomous photographic landers are a low-impact survey method for the assessment of mobile fauna in situations where methods such as trawling are not feasible or ethical. Three institutions collaborated through the CoralFISH project, each using differing lander systems, to assess the effects of cold-water corals on fish diversity and density. The Biogenic Reef Ichthyofauna Lander (BRIL, Oceanlab), Autonomous Lander for Biological Experiments (ALBEX, NIOZ) and the Marine Environment MOnitoring system (MEMO, CoNISMa) were deployed in four CoralFISH European study regions covering the Arctic, NE Atlantic and Mediterranean, namely Northern Norway (275-310 m depth), Belgica Mound Province (686-1025 m depth), the Bay of Biscay (623-936 m depth), and Santa Maria di Leuca (547-670 m depth). A total of 33 deployments were carried out in the different regions. Both the time of first arrival (Tarr) and the maximum observed number of fish (MaxN) were standardised between the different lander systems and compared between coral and reference stations as indicators of local fish density. Fish reached significantly higher MaxN at the coral stations than at the reference stations. Fish were also found to have significantly lower Tarr in the coral areas in data obtained from the BRIL and MEMO landers. All data indicated that fish abundance is higher within the coral areas. Fish species diversity was higher within the coral areas of Atlantic Ocean while in Northern Norway and Santa Maria di Leuca coral areas, diversity was similar at coral and reference stations but a single dominant species (Brosme brosme and Conger conger respectively) showed much higher density within the coral areas. Indicating that, while cold-water coral reefs have a positive effect on fish diversity and/or abundance, this effect varies across Europe's reefs.

Lunar lander ground support system

NASA Technical Reports Server (NTRS)

1991-01-01

This year's project, like the previous Aerospace Group's project, involves a lunar transportation system. The basic time line will be the years 2010-2030 and will be referred to as a second generation system, as lunar bases would be present. The project design completed this year is referred to as the Lunar Lander Ground Support System (LLGSS). The area chosen for analysis encompasses a great number of vehicles and personnel. The design of certain elements of the overall lunar mission are complete projects in themselves. For this reason the project chosen for the Senior Aerospace Design is the design of specific servicing vehicles and additions or modifications to existing vehicles for the area of concern involving servicing and maintenance of the lunar lander while on the surface.

Extended duration lunar lander

NASA Technical Reports Server (NTRS)

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

1993-01-01

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

Lunar lander conceptual design: Lunar base systems study task 2.2

NASA Technical Reports Server (NTRS)

1988-01-01

This study is a first look at the problem of building a lunar lander to support a small lunar surface base. One lander, which can land 25 metric tons, one way, or take a 6 metric ton crew capsule up and down is desired. A series of trade studies are used to narrow the choices and provide some general guidelines. Given a rough baseline, the systems are then reviewed. A conceptual design is then produced. The process was only carried through one iteration. Many more iterations are needed. Assumptions and groundrules are considered.

Search for the Mars 2 Debris Field

NASA Image and Video Library

2014-10-29

NASA Mars Reconnaissance Orbiter acquired this image to aid in the search for the missing lander, Mars 2. If the debris field is found, it could serve as a future landing location to study the effects of crash landing on the Martian surface. Despite the recent successes of missions landing on Mars, like the Mars Science Laboratory (Curiosity) or the arrival of new satellites, such as India's MOM orbiter, the Red Planet is also a graveyard of failed missions. The Soviet Mars 2 lander was the first man-made object to touch the surface of the Red Planet when it crashed landed on 27 November 1971. It is believed that the descent stage malfunctioned after the lander entered the atmosphere at too steep an angle. Attempts to contact the probe after the crash were unsuccessful. http://photojournal.jpl.nasa.gov/catalog/PIA18888

Phobos lander coding system: Software and analysis

NASA Technical Reports Server (NTRS)

Cheung, K.-M.; Pollara, F.

1988-01-01

The software developed for the decoding system used in the telemetry link of the Phobos Lander mission is described. Encoders and decoders are provided to cover the three possible telemetry configurations. The software can be used to decode actual data or to simulate the performance of the telemetry system. The theoretical properties of the codes chosen for this mission are analyzed and discussed.

KSC-2012-3941

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. - Just north of the Kennedy Space Center’s Shuttle Landing Facility, or SLF, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-4008

NASA Image and Video Library

2012-07-16

CAPE CANAVERAL, Fla. –This panoramic view shows a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prot otype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3942

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. - Just north of the Kennedy Space Center’s Shuttle Landing Facility runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

Surface elements and landing strategies for small bodies missions - Philae and beyond

NASA Astrophysics Data System (ADS)

Ulamec, Stephan; Biele, Jens

2009-10-01

The investigation of small bodies, comets and asteroids, can contribute substantially to our understanding of the formation and history of the Solar System. In-situ observations by Landers play a prominent role in this field. The Rosetta Lander - Philae - is currently on its way to comet 67P/Churyumov-Gerasimenko. It will land in November 2014 and perform numerous experiments with a suite of 10 scientific instruments. Philae has been designed to cope with a wide range of possible comet properties. The considerations taken during its development are relevant for future Lander missions to small bodies in the Solar System. In addition the paper provides a review of alternative concepts, studied or developed for various missions like Phobos, Hayabusa/Minerva or Géocroiseur/Leonard. Various missions to small bodies in the Solar System, including Landers, are currently studied (e.g., Marco Polo). The paper will address the mission options and compare applicable technologies with the solutions chosen for Philae.

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.

SNAP 19 Viking Program. Bimonthly technical progress report, February 1980-March 1980

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

Not Available

1980-01-01

Viking 1 Lander power system data has not been available during this reporting period, but summary reports indicate no anomalies in performance. Monitoring and evaluation of Viking 2 Lander power system data continued. Temperature data were similar to those 23 months ago, but combined RTG output power was down by 7 watts from the 75 watts recorded in February of 1978. On February 7, 1980, during a scheduled relay transmission the Lander 2 battery voltage dropped below 26.5 volts. With the orbiter attitude control gas supply nearly depleted and the space network stations required for Voyager encounter with Saturn latermore » this year, the final relay from Viking Lander 2 had been scheduled to take place on April 11. The attempt was made but no data were received. Power system performance data for Pioneer 10 and Pioneer Saturn (initially designated Pioneer 11) were monitored. The estimated RTG system net power was 115 watts for both, Pioneer 10 and Pioneer Saturn. The telemetry signal quality from Pioneer Saturn remains excellent. Pioneer 10, for the first time, shows a loss of signal strength.« less

Analyses of outcrop and sediment grains observed and collected from the Sirena Deep and Middle Pond of the Mariana Trench

NASA Astrophysics Data System (ADS)

Hand, K. P.; Bartlett, D. H.; Fryer, P.

2012-12-01

During a March 2012 expedition we recovered sediments from two locales within the Marina Trench - Middle Pond and Sirena Deep. Samples were recovered from a Niskin bottle deployed on a passive lander platform that released an arm after touching down on the seafloor. The impact of the arm holding the Niskin bottle caused sediments to enter the bottle; this process was seen in images and on video captured by the lander. The combination of imagery and preliminary analyses of the sediments indicates that the Sirena Deep locale is a region of serpentinization and active microbial communities. Images show several outcrops consistent with serpentinization, some of which are coated with filamentous microbial mats. Results and analyses of these samples will be presented.

Three mars years: Viking lander 1 imaging observations

USGS Publications Warehouse

Arvidson, R. E.; Guinness, E.A.; Moore, H.J.; Tillman, J.; Wall, S.D.

1983-01-01

The Mutch Memorial Station (Viking Lander 1) on Mars acquired imaging and meteorological data over a period of 2245 martian days (3:3 martian years). This article discusses the deposition and erosion of thin deposits (ten to hundreds of micrometers) of bright red dust associated with global dust storms, and the removal of centimeter amounts of material in selected areas during a dust storm late in the third winter. Atmospheric pressure data acquired during the period of intense erosion imply that baroclinic disturbances and strong diurnal solar tidal heating combined to produce strong winds. Erosion occurred principally in areas where soil cohesion was reduced by earlier surface sampler activities. Except for redistribution of thin layers of materials, the surface appears to be remarkably stable, perhaps because of cohesion of the undisturbed surface material.

Three Mars years: viking lander 1 imaging observations.

PubMed

Arvidson, R E; Guinness, E A; Moore, H J; Tillman, J; Wall, S D

1983-11-04

The Mutch Memorial Station (Viking Lander 1) on Mars acquired imaging and meteorological data over a period of 2245 martian days (3:3 martian years). This article discusses the deposition and erosion of thin deposits (ten to hundreds of micrometers) of bright red dust associated with global dust storms, and the removal of centimeter amounts of material in selected areas during a dust storm late in the third winter. Atmospheric pressure data acquired during the period of intense erosion imply that baroclinic disturbances and strong diurnal solar tidal heating combined to produce strong winds. Erosion occurred principally in areas where soil cohesion was reduced by earlier surface sampler activities. Except for redistribution of thin layers of materials, the surface appears to be remarkably stable, perhaps because of cohesion of the undisturbed surface material.

Three Mars years - Viking Lander 1 imaging observations

NASA Technical Reports Server (NTRS)

Arvidson, R. E.; Guinness, E. A.; Moore, H. J.; Tillman, J.; Wall, S. D.

1983-01-01

The Mutch Memorial Station (Viking Lander 1) on Mars acquired imaging and meteorological data over a period of 2245 martian days (3.3 martian years). This article discusses the deposition and erosion of thin deposits (ten to hundreds of micrometers) of bright red dust associated with global dust storms, and the removal of centimeter amounts of material in selected areas during a dust storm late in the third winter. Atmospheric pressure data acquired during the period of intense erosion imply that baroclinic disturbances and strong diurnal solar tidal heating combined to produce strong winds. Erosion occurred principally in areas where soil cohesion was reduced by earlier surface sampler activities. Except for redistribution of thin layers of materials, the surface appears to be remarkably stable, perhaps because of cohension of the undisturbed surface material.

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.

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;

Modeling and experimental validation of sawing based lander anchoring and sampling methods for asteroid exploration

NASA Astrophysics Data System (ADS)

Zhang, Jun; Dong, Chengcheng; Zhang, Hui; Li, Song; Song, Aiguo

2018-05-01

This paper presents a novel lander anchoring system based on sawing method for asteroid exploration. The system is composed of three robotic arms, three cutting discs, and a control system. The discs mounted at the end of the arms are able to penetrate into the rock surface of asteroids. After the discs cut into the rock surface, the self-locking function of the arms provides forces to fix the lander on the surface. Modeling, trajectory planning, simulations, mechanism design, and prototype fabrication of the anchoring system are discussed, respectively. The performances of the system are tested on different kinds of rocks, at different sawing angles, locations, and speeds. Results show that the system can cut 15 mm deep into granite rock in 180 s at sawing angle of 60°, with the average power of 58.41 W, and the "weight on bit" (WOB) of 8.637 N. The 7.8 kg anchoring system is capable of providing omni-directional anchoring forces, at least 225 N normal and 157 N tangent to the surface of the rock. The system has the advantages of low-weight, low energy consumption and balance forces, high anchoring efficiency and reliability, and could enable the lander to move and sample or assist astronauts and robots in walking and sampling on asteroids.

After Attempted Sample Delivery on Sol 60, False Color

NASA Technical Reports Server (NTRS)

2008-01-01

This view from the Surface Stereo Imager on NASA's Phoenix Mars Lander on the mission's 60th Martian day, or sol, (July 26, 2008) was taken after the lander's scoop sprinkled a soil sample over Thermal and Evolved-Gas Analyzer (TEGA).

The upper part of the picture shows the robotic arm scoop parked open-face down above the TEGA after delivery. The TEGA doors farthest to the right were open to receive the sample into one of TEGA's eight ovens. Not enough material reached the oven to allow an analysis to begin. Some of the soil sample can be seen at the bottom of the adjacent pair of doors.

This view is presented in false color, which makes the reddish color of the soil-sample material easy to see.

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.

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.

The MVACS Robotic Arm Camera

NASA Astrophysics Data System (ADS)

Keller, H. U.; Hartwig, H.; Kramm, R.; Koschny, D.; Markiewicz, W. J.; Thomas, N.; Fernades, M.; Smith, P. H.; Reynolds, R.; Lemmon, M. T.; Weinberg, J.; Marcialis, R.; Tanner, R.; Boss, B. J.; Oquest, C.; Paige, D. A.

2001-08-01

The Robotic Arm Camera (RAC) is one of the key instruments newly developed for the Mars Volatiles and Climate Surveyor payload of the Mars Polar Lander. This lightweight instrument employs a front lens with variable focus range and takes images at distances from 11 mm (image scale 1:1) to infinity. Color images with a resolution of better than 50 μm can be obtained to characterize the Martian soil. Spectral information of nearby objects is retrieved through illumination with blue, green, and red lamp sets. The design and performance of the camera are described in relation to the science objectives and operation. The RAC uses the same CCD detector array as the Surface Stereo Imager and shares the readout electronics with this camera. The RAC is mounted at the wrist of the Robotic Arm and can characterize the contents of the scoop, the samples of soil fed to the Thermal Evolved Gas Analyzer, the Martian surface in the vicinity of the lander, and the interior of trenches dug out by the Robotic Arm. It can also be used to take panoramic images and to retrieve stereo information with an effective baseline surpassing that of the Surface Stereo Imager by about a factor of 3.

Phoenix Lidar Operation Animation

NASA Image and Video Library

2008-05-29

This image from NASA Phoenix Mars Lander of the Canadian-built meteorological station lidar, which was successfully activated on Sol 2 by first opening its dust cover, then emitting rapid pulses of light.

Athabasca Valles, Mars: a lava-draped channel system.

PubMed

Jaeger, W L; Keszthelyi, L P; McEwen, A S; Dundas, C M; Russell, P S

2007-09-21

Athabasca Valles is a young outflow channel system on Mars that may have been carved by catastrophic water floods. However, images acquired by the High-Resolution Imaging Science Experiment camera onboard the Mars Reconnaissance Orbiter spacecraft reveal that Athabasca Valles is now entirely draped by a thin layer of solidified lava-the remnant of a once-swollen river of molten rock. The lava erupted from a fissure, inundated the channels, and drained downstream in geologically recent times. Purported ice features in Athabasca Valles and its distal basin, Cerberus Palus, are actually composed of this lava. Similar volcanic processes may have operated in other ostensibly fluvial channels, which could explain in part why the landers sent to investigate sites of ancient flooding on Mars have predominantly found lava at the surface instead.

Two Holes from Using Rasp in 'Snow White' (Stereo)

NASA Technical Reports Server (NTRS)

2008-01-01

This view from the Surface Stereo Imager on NASA's Phoenix Mars Lander shows a portion of the trench informally named 'Snow White,' with two holes near the top of the image that were produced by the first test use of Phoenix's rasp to collect a sample of icy soil.

The test was conducted on July 15, 2008, during the 50th Martian day, or sol, since Phoenix landed, and the image was taken later the same day. The two holes are about one centimeter (0.4 inch) apart. The image appears three-dimensional when viewed through blue-red glasses.

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

Introduction to Japanese exploration study to the moon

NASA Astrophysics Data System (ADS)

Hashimoto, T.; Hoshino, T.; Tanaka, S.; Otake, H.; Otsuki, M.; Wakabayashi, S.; Morimoto, H.; Masuda, K.

2014-11-01

The Japan Aerospace Exploration Agency (JAXA) views the lunar lander SELENE-2 as the successor to the SELENE mission. In this presentation, the mission objectives of SELENE-2 are shown together with the present design status of the spacecraft. JAXA launched the Kaguya (SELENE) lunar orbiter in September 2007, and the spacecraft observed the Moon and a couple of small satellites using 15 instruments. As the next step in lunar exploration, the lunar lander SELENE-2 is being considered. SELENE-2 will land on the lunar surface and perform in-situ scientific observations, environmental investigations, and research for future lunar utilization including human activity. At the same time, it will demonstrate key technologies for lunar and planetary exploration such as precise and safe landing, surface mobility, and overnight survival. The lander will carry laser altimeters, image sensors, and landing radars for precise and safe landing. Landing legs and a precisely controlled propulsion system will also be developed. A rover is being designed to be able to travel over a wide area and observe featured terrain using scientific instruments. Since some of the instruments require long-term observation on the lunar surface, technology for night survival over more than 2 weeks needs to be considered. The SELENE-2 technologies are expected to be one of the stepping stones towards future Japanese human activities on the moon and to expand the possibilities for deep space science.

Mars Mobile Lander Systems for 2005 and 2007 Launch Opportunities

NASA Technical Reports Server (NTRS)

Sabahi, D.; Graf, J. E.

2000-01-01

A series of Mars missions are proposed for the August 2005 launch opportunity on a medium class Evolved Expendable Launch Vehicle (EELV) with a injected mass capability of 2600 to 2750 kg. Known as the Ranger class, the primary objective of these Mars mission concepts are: (1) Deliver a mobile platform to Mars surface with large payload capability of 150 to 450 kg (depending on launch opportunity of 2005 or 2007); (2) Develop a robust, safe, and reliable workhorse entry, descent, and landing (EDL) capability for landed mass exceeding 750 kg; (3) Provide feed forward capability for the 2007 opportunity and beyond; and (4) Provide an option for a long life telecom relay orbiter. A number of future Mars mission concepts desire landers with large payload capability. Among these concepts are Mars sample return (MSR) which requires 300 to 450 kg landed payload capability to accommodate sampling, sample transfer equipment and a Mars ascent vehicle (MAV). In addition to MSR, large in situ payloads of 150 kg provide a significant step up from the Mars Pathfinder (MPF) and Mars Polar Lander (MPL) class payloads of 20 to 30 kg. This capability enables numerous and physically large science instruments as well as human exploration development payloads. The payload may consist of drills, scoops, rock corers, imagers, spectrometers, and in situ propellant production experiment, and dust and environmental monitoring.

Improved inflatable landing systems for low cost planetary landers

NASA Astrophysics Data System (ADS)

Northey, Dave; Morgan, Chris

2006-10-01

Inflatable landing systems have been traditionally perceived as a cost-effective solution to the problem of landing a spacecraft on a planetary surface. To date, the systems used have all employed the approach of surrounding the lander with non-vented airbags where the lander on impact bounces a number of times until the impact energy is dissipated. However, the reliability record of such systems is not at all good. This paper examines the problems involved in the use of non-vented airbags, and how these problems have been overcome by the use of vented airbags in terrestrial systems. Using a specific case study, it is shown that even the basic passive type of venting can give significant mass reductions. It is also shown that actively controlling the venting based on the landing scenario can further enhance the performance of vented airbags.

Improved inflatable landing systems for low cost planetary landers

NASA Astrophysics Data System (ADS)

Northey, Dave; Morgan, Chris

2003-11-01

Inflatable landing systems have been traditionally perceived as a cost-effective solution to the problem of landing a spacecraft on a planetary surface. To date the systems used have all employed the approach of surrounding the lander with non-vented airbags where the lander bounces on impact a number of times until the impact energy is dissipated. However the reliability record of such systems is not at all good. This paper examines the problems involved in the use of non-vented airbags, and how these problems have been overcome by the use of vented airbags in terrestrial systems. Using a specific case study, it is shown that even the basic passive type of venting can give significant mass reductions. It is also shown that actively controlling the venting based on the landing scenario can further enhance the performance of vented airbags.

On the Thermal Protection Systems of Landers for Venus Exploration

NASA Astrophysics Data System (ADS)

Ekonomov, A. P.; Ksanfomality, L. V.

2018-01-01

The landers of the Soviet Venera series—from Venera-9 to Venera-14—designed at the Lavochkin Association are a man-made monument to spectacular achievements of Soviet space research. For more than 40 years, they have remained the uneclipsed Soviet results in space studies of the Solar System. Within the last almost half a century, the experiments carried out by the Venera-9 to Venera-14 probes for studying the surface of the planet have not been repeated by any space agency in the world, mainly due to quite substantial technical problems. Since that time, no Russian missions with landers have been sent to Venus either. On Venus, there is an anoxic carbon dioxide atmosphere, where the pressure is 9.2 MPa and the temperature is 735 K near the surface. A long-lived lander should experience these conditions for an appreciable length of time. What technical solutions could provide a longer operation time for a new probe investigating the surface of Venus, if its thermal scheme is constructed similar to that of the Venera series? Onboard new landers, there should be a sealed module, where the physical conditions required for operating scientific instruments are maintained for a long period. At the same time, new high-temperature electronic equipment that remains functional under the above-mentioned conditions have appeared. In this paper, we consider and discuss different variants of the system for a long-lived sealed lander, in particular, the absorption of the penetrating heat due to water evaporation and the thermal protection construction for the instruments with intermediate characteristics.

Martian Arctic Dust Devil and Phoenix Meteorology Mast

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager on NASA's Phoenix Mars Lander caught this dust devil in action west-southwest of the lander at 11:16 a.m. local Mars time on Sol 104, or the 104th Martian day of the mission, Sept. 9, 2008.

Dust devils have not been detected in any Phoenix images from earlier in the mission, but at least six were observed in a dozen images taken on Sol 104.

Dust devils are whirlwinds that often occur when the Sun heats the surface of Mars, or some areas on Earth. The warmed surface heats the layer of atmosphere closest to it, and the warm air rises in a whirling motion, stirring dust up from the surface like a miniature tornado.

The vertical post near the left edge of this image is the mast of the Meteorological Station on Phoenix. The dust devil visible at the horizon just to the right of the mast is estimated to be 600 to 700 meters (about 2,000 to 2,300 feet) from Phoenix, and 4 to 5 meters (10 to 13 feet) in diameter. It is much smaller than dust devils that have been observed by NASA's Mars Exploration Rover Spirit much closer to the equator. It is closer in size to dust devils seen from orbit in the Phoenix landing region, though still smaller than those.

The image has been enhanced to make the dust devil easier to see.

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.

Selection of the InSight landing site

USGS Publications Warehouse

Golombek, M.; Kipp, D.; Warner, N.; Daubar, Ingrid J.; Fergason, Robin L.; Kirk, Randolph L.; Beyer, R.; Huertas, A.; Piqueux, Sylvain; Putzig, N.E.; Campbell, B.A.; Morgan, G. A.; Charalambous, C.; Pike, W. T.; Gwinner, K.; Calef, F.; Kass, D.; Mischna, M A; Ashley, J.; Bloom, C.; Wigton, N.; Hare, T.; Schwartz, C.; Gengl, H.; Redmond, L.; Trautman, M.; Sweeney, J.; Grima, C.; Smith, I. B.; Sklyanskiy, E.; Lisano, M.; Benardini, J.; Smrekar, S.E.; Lognonne, P.; Banerdt, W. B.

2017-01-01

The selection of the Discovery Program InSight landing site took over four years from initial identification of possible areas that met engineering constraints, to downselection via targeted data from orbiters (especially Mars Reconnaissance Orbiter (MRO) Context Camera (CTX) and High-Resolution Imaging Science Experiment (HiRISE) images), to selection and certification via sophisticated entry, descent and landing (EDL) simulations. Constraints on elevation (≤−2.5 km">≤−2.5 km≤−2.5 km for sufficient atmosphere to slow the lander), latitude (initially 15°S–5°N and later 3°N–5°N for solar power and thermal management of the spacecraft), ellipse size (130 km by 27 km from ballistic entry and descent), and a load bearing surface without thick deposits of dust, severely limited acceptable areas to western Elysium Planitia. Within this area, 16 prospective ellipses were identified, which lie ∼600 km north of the Mars Science Laboratory (MSL) rover. Mapping of terrains in rapidly acquired CTX images identified especially benign smooth terrain and led to the downselection to four northern ellipses. Acquisition of nearly continuous HiRISE, additional Thermal Emission Imaging System (THEMIS), and High Resolution Stereo Camera (HRSC) images, along with radar data confirmed that ellipse E9 met all landing site constraints: with slopes <15° at 84 m and 2 m length scales for radar tracking and touchdown stability, low rock abundance (<10 %) to avoid impact and spacecraft tip over, instrument deployment constraints, which included identical slope and rock abundance constraints, a radar reflective and load bearing surface, and a fragmented regolith ∼5 m thick for full penetration of the heat flow probe. Unlike other Mars landers, science objectives did not directly influence landing site selection.

Terrestrial Clay under Microscope

NASA Image and Video Library

2008-09-30

A scanning electron microscope captured this image of terresterial soil containing a phyllosilicate mineral from Koua Bocca, Ivory Coast, West Africa. This soil shares some similarities with Martian soil scooped by NASA Phoenix Lander.

Linear Covariance Analysis for a Lunar Lander

NASA Technical Reports Server (NTRS)

Jang, Jiann-Woei; Bhatt, Sagar; Fritz, Matthew; Woffinden, David; May, Darryl; Braden, Ellen; Hannan, Michael

2017-01-01

A next-generation lunar lander Guidance, Navigation, and Control (GNC) system, which includes a state-of-the-art optical sensor suite, is proposed in a concept design cycle. The design goal is to allow the lander to softly land within the prescribed landing precision. The achievement of this precision landing requirement depends on proper selection of the sensor suite. In this paper, a robust sensor selection procedure is demonstrated using a Linear Covariance (LinCov) analysis tool developed by Draper.

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;

Self-unloading, unmanned, reusable lunar lander project

NASA Technical Reports Server (NTRS)

Cowan, Kevin; Lewis, Ron; Mislinski, Philip; Rivers, Donna; Smith, Solar; Vasicek, Clifford; Verona, Matt

1991-01-01

A payload delivery system will be required to support the buildup and operation of a manned lunar base. In response, a self-unloading, unmanned, reusable lunar lander was conceptually designed. The lander will deliver a 7000 kg payload, with the same dimensions as a space station logistics module, from low lunar orbit to any location on the surface of the moon. The technical aspects of the design is introduced as well as the management structure and project cost.

Overhead View of Pathfinder Landing Site

NASA Technical Reports Server (NTRS)

1997-01-01

Planimetric (overhead view) map of the landing site, to a distance of 20 meters from the spacecraft. North is at the top in this and Plates 3-5. To produce this map, images were geometrically projected onto an assumed mean surface representing the ground. Features above the ground plane (primarily rocks) therefore appear displaced radially outward; the amount of distortion increases systematically with distance. The upper surfaces of the lander and rover also appear enlarged and displaced because of their height. Primary grid (white) is based on the Landing Site Cartographic (LSC) coordinate system, defined with X eastward, Y north, and Z up, and origin located at the mean ground surface immediately beneath the deployed position of the IMP camera gimbal center. Secondary ticks (cyan) are based on the Mars local level (LL) frame, which has X north, Y east, Z down, with origin in the center of the lander baseplate. Rover positions (including APXS measurements) are commonly reported in the LL frame. Yellow grid shows polar coordinates based on the LSC system. Cartographic image processing by U.S. Geological Survey.

NOTE: original caption as published in Science Magazine

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).

Surface Experiments on a Jupiter Trojan Asteroid in the Solar Powered Sail Mission

NASA Astrophysics Data System (ADS)

Okada, Tatsuaki

2016-04-01

Introduction: A new mission to a Jupiter Trojan asteroid is under study us-ing a solar-powered sail (SPS), and a science lander is being investigated in the joint study between Japan and Europe [1]. We present here the key sci-entific objectives and the strawman payloads of science experiments on the asteroid. Science Objectives: Jupiter Trojan asteroids are located around the Sun-Jupiter Lagrange points (L4 or L5) and most of them are classified as D- or P-type in asteroid taxonomy, but their origin still remains unknown. A classi-cal (static) model of solar system evolution indicates that they were formed around the Jupiter region and survived until now as the outer end members of asteroids. A new (dynamical) model such as Nice model suggests that they were formed at the far end of the solar system and transferred inward due to dynamical migration of giant planets [2]. Therefore physical, miner-alogical, and isotopic studies of surface materials and volatile compounds could solve their origin, and then the solar system formation [3]. Strawman Payloads: The SPS orbiter will be able to carry a 100 kg class lander with 20 kg mission payloads. Just after landing of the lander, geolog-ical, mineralogical, and geophysical observations will be performed to char-acterize the site using a panoramic optical camera, an infrared hyperspectral imager, a magnetometer, and a thermal radiometer. The surface and subsur-face materials of the asteroid will be collected into a carousel by the bullet-type and the pneumatic drill type samplers, respectively. Samples in the carousel will be investigated by a visible and an infrared microscope, and transferred for performing high resolution mass spectrometry (HRMS). Mass resolution m/dm > 30,000 is expected to investigate isotopic ratios of D/H, 15N/14N, and 18O/16O, as well as molecules from organic matters. A set of strawman payloads are tentatively determined during the lander system study [4]. The constraints to select the strawman payloads have the total mass of 20 kg, and the total consumption energy of 600 WHr. In the SPS mission, the sample-return is also studied as an option, and the lander should bring the mechanisms for sample collection and sample transfer to the mother ship. [1] Mori O. et al. (2015) 11th Low-Cost Planetary Missions Conf., S3-10. [2] Morbidelli A. et al. (2005) Nature 435, 462-466. [3] Yano H. et al., (2014) CO-SPAR 2014, B0.4-2-14. [4] Mori O. et al., Lunar Planet. Sci. Conf., 47, #1822.

Phoenix's Laser Beam in Action on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image to view the animation

The Surface Stereo Imager camera aboard NASA's Phoenix Mars Lander acquired a series of images of the laser beam in the Martian night sky. Bright spots in the beam are reflections from ice crystals in the low level ice-fog. The brighter area at the top of the beam is due to enhanced scattering of the laser light in a cloud. The Canadian-built lidar instrument emits pulses of laser light and records what is scattered back.

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.

Frost seen on Snow White Trench

NASA Technical Reports Server (NTRS)

2008-01-01

The Surface Stereo Imager (SSI) on NASA's Phoenix Mars Lander took this shadow-enhanced false color image of the 'Snow White' trench, on the eastern end of Phoenix's digging area. The image was taken on Sol 144, or the 144th day of the mission, Oct. 20, 2008. Temperatures measured on Sol 151, the last day weather data were received, showed overnight lows of minus128 Fahrenheit (minus 89 Celsius) and day time highs in the minus 50 F (minus 46 C) range. The last communication from the spacecraft came on Nov. 2, 2008.

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

How Phoenix Talks to Earth

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on the image for the animation

This animation shows how NASA's Phoenix Mars Lander stays in contact with Earth. As NASA's Mars Odyssey orbiter passes overhead approximately every two hours, Phoenix transmits images and scientific data from the surface to the orbiter, which then relays the data to NASA's Deep Space Network of antennas on Earth. Similarly, NASA's Deep Space Network transmits instructions from Earth to Odyssey, which then relays the information to Phoenix.

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.

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

NASA Astrophysics Data System (ADS)

Benton, Mark G.

2008-01-01

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

Spirit and Its Now-Empty Mother Ship

NASA Technical Reports Server (NTRS)

2004-01-01

This overhead polar image was captured after the Mars Exploration Rover Spirit took a few baby rolls away from the spacecraft that bore it millions of miles to Mars. The empty lander, now named the Columbia Memorial Station, can be seen to the right of the rover. This image was taken by Spirit's navigation camera.

Acousto-Optic Imaging Spectrometers for Mars Surface Science

NASA Technical Reports Server (NTRS)

Glenar, D. A.; Blaney, D. L.

2000-01-01

NASA's long term plan for Mars sample collection and return requires a highly streamlined approach for spectrally characterizing a landing site, documenting the mineralogical make-up of the site and guiding the collections of samples which represent the diversity of the site. Ideally, image data should be acquired at hundreds of VIS and IR wavelengths, in order to separately distinguish numerous anticipated species, using principal component analysis and linear unmixing. Cameras with bore-sighted point spectrometers can acquire spectra of isolated scene elements, but it requires 10(exp 2) to 10(exp 2) successive motions and precise relative pointing knowledge in order to create a single data cube which qualifies as a spectral map. These and other competing science objectives have to be accomplished within very short lander/rover operational lifetime (a few sols). True, 2-D imaging spectroscopy greatly speeds up the data acquisition process, since the spectra of all pixels in the scene are collected at once. This task can be accomplished with cameras that use electronically tunable acousto-optic tunable filters (AOTFs) as the optical tuning element. AOTFs made from TeO2 are now a mature technology, and operate at wavelengths from near-UV to about 5 microns. Because of incremental improvements in the last few years, present generation devices are rugged, radiation-hard and operate at temperatures down to at least 150K so they can be safely integrated into the ambient temperature optics of in-situ instruments such as planetary or small-body landers. They have been used for ground-based astronomy, and were also baselined for the ST-4 Champollion IR comet lander experiment (CIRCLE), prior to cancellation of the ST-4 mission last year. AIMS (for Acousto-optic Imaging spectrometer), is a prototype lander instrument which is being built at GSFC with support by the NASA OSS Advanced Technologies and Mission Studies, Mars Instrument Definition and Development Program (MIDP). AIMS is capable of tunable spectroscopic imaging of surface mineralogy, ices and dust between 0.5 and 2.4 microns, at a resolving power (lambda/delta lambda) which is typically several hundred. The design spatial resolution, similar to IMP and SSI, will allow mapping at scales down to about 1 cm.

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

The first Indian planetary mission to moon, Chandrayaan-1, launched on 22nd October, 2008 with a suite of Indian and International payloads on board, collected very significant data over its mission duration of close to one year. Important new findings from this mission include, discovery of hydroxyl and water molecule in sunlit lunar surface region around the poles, exposure of large anorthositic blocks confirming the global lunar magma hypothesis, signature of sub surface ice layers in permanently shadowed regions near the lunar north pole, evidence for a new refractory rock type, mapping of reflected lunar neutral atoms and identification of mini-magnetosphere, possible signature of water molecule in lunar exosphere, preserved lava tube that may provide site for future human habitation and radiation dose en-route and around the moon. Chandrayaan-2:, The success of Chandrayaan-1 orbiter mission provided impetus to implement the second approved Indian mission to moon, Chandrayaan-2, with an Orbiter-Lander-Rover configuration. The enhanced capabilities will enable addressing some of the questions raised by the results obtained from the Chandrayaan-1 and other recent lunar missions and also to enhance our understanding of origin and evolution of the moon. The orbiter that will carry payloads to further probe the morphological, mineralogical and chemical properties of the lunar surface material through remote sensing observations in X-ray, visible, infra-red and microwave regions. The Lander-Rover system will enable in-depth studies of a specific lunar location and probe various physical properties of the moon. The Chandrayaan-2 mission will be collaboration between Indian Space Research Organization (ISRO) and the Federal Space Agency of Russia. ISRO will be responsible for the Launch Vehicle, the Orbiter and the Rover while the Lander will be provided by Russia. Initial work to realize the different elements of the mission is currently in progress in both countries. Mission Elements:, On board segment of Chandrayaan-2 mission consists of a lunar Orbiter and a lunar Lander-Rover. The orbiter for Chandrayaan-2 mission is similar to that of Chandrayaan-1 from structural and propulsion aspects. Based on a study of various mission management and trajectory options, such as, separation of the Lander-Rover module in Earth Parking Orbit (EPO) or in lunar transfer trajectory (LTT) or in lunar polar orbit (LPO), the option of separating of this module at LTT, after required midcourse corrections, was selected as this offers an optimum mass and overall mission management advantage. The orbiter propulsion system will be used to transfer Orbiter-Lander-Rover composite from EPO to LTT. On reaching LTT, the Lander-Rover module will be separated from the orbiter module. The Lander-Rover and Orbiter modules are configured with individual propulsion and housekeeping systems. The indigenously developed Geostationary Satellite Launch Vehicle GSLV (Mk-II) will be used for this mission. The most critical aspect of its feasibility was an accurate evaluation of the scope for taking a 3200kg lift off mass into EPO. A Lander-Rover mass of 1270kg (including the propellant for soft landing) will provide sufficient margin for such a lift off within the capability of flight proven GSLV (Mk-II) for the EPO. Mission Scenario: ,GSLV (Mk-II) will launch the Lunar Orbiter coupled to the Lunar Lander-Rover into EPO (170 x 16980 km) following which the Orbiter will boost the orbit from EPO to LTT where the two modules will be separated. Both of them will make their independent journey towards moon and reach lunar polar orbit independently. The orbiter module will be initially placed in a circular polar orbit (200km) and the Lander-Rover module descends towards the lunar surface. After landing, a motorized rover with robotic arm and scientific instruments would be released on to the lunar surface. Although the exact landing location is yet to be finalized, a high 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 India and Russia. Preliminary Design Reviews of the Mission elements are also completed.

Geodesy and cartography methods of exploration of the outer planetary systems: Galilean satellites and Enceladus

NASA Astrophysics Data System (ADS)

Zubarev, Anatoliy; Kozlova, Natalia; Kokhanov, Alexander; Oberst, Jürgen; Nadezhdina, Irina; Patraty, Vyacheslav; Karachevtseva, Irina

Introduction. While Galilean satellites have been observed by different spacecrafts, including Pioneer, Voyager-1 and -2, Galileo, New Horizons, and Enceladus by Cassini and Voyager-2, only data from Galileo, Cassini and the two Voyagers are useful for precise mapping [1, 2]. For purposes of future missions to the system of outer planets we have re-computed the control point network of the Io, Ganymede and Enceladus to support spacecraft navigation and coordinate knowledge. Based on the control networks, we have produced global image mosaics and maps. Geodesy approach. For future mission Laplace-P we mainly focused on Ganymede which coverage is nearly complete except for polar areas (which includes multispectral data). However, large differences exist in data resolutions (minimum global resolution: 30 km/pixel). Only few areas enjoy coverage by highest resolution images, so we suggest to obtain regional Digital Elevation Models (DEMs) from stereo images for selected areas. Also using our special software, we provide calculation of illumination conditions of Ganymede surface in various representations [3]. Finally, we propose a careful evaluation of all available data from the previous Voyager and Galileo missions to re-determine geodetic control and rotation model for other Galilean satellites - Callisto and Europe. Mapping. Based on re-calculated control point networks and global mosaics we have prepared new maps for Io, Ganymede and Enceladus [4]. Due to the difference in resolution between the images, which were also taken from different angles relative to the surface, we can prepare only regional high resolution shape models, so for demonstrating of topography and mapping of the satellites we used orthographic projection with different parameters. Our maps, which include roughness calculations based on our GIS technologies [5], will also be an important tool for studies of surface morphology. Conclusions. Updated data collection, including new calculation of elements of external orientation, provides new image processing of previous missions to outer planetary system. Using Photomod software (http://www.racurs.ru/) we have generated a new control point network in 3-D and orthomosaics for Io, Ganymede and Enceladus. Based on improved orbit data for Galileo we have used larger numbers of images than were available before, resulting in a more rigid network for Ganymede. The obtained results will be used for further processing and improvement of the various parameters: body shape parameters and shape modeling, libration, as well as for studying of the surface interesting geomorphological phenomena, for example, distribution of bright and dark surface materials on Ganymede and their correlations with topography and slopes [6]. Acknowledgments: The Ganymede study was partly supported by ROSKOSMOS and Space Research Institute under agreement No. 36/13 “Preliminary assessment of the required coordinate and navigation support for selection of landing sites for lander mission “Laplace” and partly funding by agreement No. 11-05-91323 for “Geodesy, cartography and research satellites Phobos and Deimos” References: [1] Nadezhdina et al. Vol. 14, EGU2012-11210, 2012. [2] Zhukov et al. International Colloquium and Workshop "Ganymede Lander: scientific goals and experiments", Space Research Institute, Moscow, Russia, 4-8 March, 2013. [3] Zubarev et al. International Colloquium and Workshop "Ganymede Lander: scientific goals and experiments", Space Research Institute, Moscow, Russia, 4-8 March, 2013. [4] Lazarev et al. Izvestia VUZov. 2012, No 6, pp. 9-11 http://miigaik.ru/journal.miigaik.ru/2012/20130129120215-2593.pdf (in Russian). [5] Kokhanov et al. Current problems in remote sensing of the Earth from space. 2013. Vol. 10. No 4. pp. 136-153. http://d33.infospace.ru/d33_conf/sb2013t4/136-153.pdf (in Russian). [6] Oberst et al., 2013 International Colloquium and Workshop "Ganymede Lander: scientific goals and experiments", Space Research Institute, Moscow, Russia, 4-8 March, 2013.

First Image from MarCO-B

NASA Image and Video Library

2018-05-15

The first image captured by one of NASA's Mars Cube One (MarCO) CubeSats. The image, which shows both the CubeSat's unfolded high-gain antenna at right and the Earth and its moon in the center, was acquired by MarCO-B on May 9. MarCO is a pair of small spacecraft accompanying NASA's InSight (Interior Investigations Using Seismic Investigations, Geodesy and Heat Transport) lander. Together, MarCO-A and MarCO-B are the first CubeSats ever sent to deep space. InSight is the first mission to ever explore Mars' deep interior. If the MarCO CubeSats make the entire journey to Mars, they will attempt to relay data about InSight back to Earth as the lander enters the Martian atmosphere and lands. MarCO will not collect any science, but are intended purely as a technology demonstration. They could serve as a pathfinder for future CubeSat missions. An annotated version is available at https://photojournal.jpl.nasa.gov/catalog/PIA22323

Hydrogeology of Basins on Mars

NASA Technical Reports Server (NTRS)

Arvidson, Raymond E.

2001-01-01

This document summarizes the work accomplished under NASA Grant NAG5-3870. Emphasis was put on the development of the FIDO rover, a prototype for the twin-Mers which will be operating on the surface of Mars in 2004, specifically the primary work was the analysis of FIDO field trials. The grantees also analyzed VIKING Lander 1 XRFS and Pathfinder APXS data. Results show that the Viking site chemistry is consistent with an andesite, and the Pathfinder site is consistent with a basaltic andesite. The grantees also worked to demonstrate the capability to simulate annealing methods to apply to the inversion of remote sensing data. They performed an initial analyses of Sojourner engineering telemetry and imaging data. They performed initial analyses of Viking Lander Stereo Images, and of Hematite deposits in Terra Meridiani. They also acquired and analyzed the New Goldstone radar data.

KSC-2012-3954

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the 15,000-foot long Shuttle Landing Facility at the Kennedy Space Center, Fla. At the north end of the runway, to the bottom, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3943

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s 15,000-foot long Shuttle Landing Facility. On the far left at the end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3946

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows a rock and crater-filled planetary scape that has been built at the north end of the Kennedy Space Center’s Shuttle Landing Facility. The site will allow engineers to test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3944

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway, in the upper right, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3952

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway, to the right, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3951

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3953

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the 15,000-foot long Shuttle Landing Facility at the Kennedy Space Center, Fla. At the north end of the runway, to the right, is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3947

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3945

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. –This aerial view shows a rock and crater-filled planetary scape that has been built at the north end of the Kennedy Space Center’s Shuttle Landing Facility. The site will allow engineers to test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

KSC-2012-3950

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the north end of the Kennedy Space Center’s Shuttle Landing Facility. At the end of the runway is a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

Mars Pathfinder Wheel Abrasion Experiment Ground Test

NASA Technical Reports Server (NTRS)

Keith, Theo G., Jr.; Siebert, Mark W.

1998-01-01

The National Aeronautics and Space Administration (NASA) sent a mission to the martian surface, called Mars Pathfinder. The mission payload consisted of a lander and a rover. The primary purpose of the mission was demonstrating a novel entry, descent, and landing method that included a heat shield, a parachute, rockets, and a cocoon of giant air bags. Once on the surface, the spacecraft returned temperature measurements near the Martian surface, atmosphere pressure, wind speed measurements, and images from the lander and rover. The rover obtained 16 elemental measurements of rocks and soils, performed soil-mechanics, atmospheric sedimentation measurements, and soil abrasiveness measurements.

Progress Towards the Development of a Long-Lived Venus Lander Duplex System

NASA Technical Reports Server (NTRS)

Dyson, Roger W.; Bruder, Geoffrey A.

2010-01-01

NASA has begun the development of a combined Stirling cycle power and cooling system (duplex) to enable the long-lived surface exploration of Venus and other harsh environments in the solar system. The duplex system will operate from the heat provided by decaying radioisotope plutonium-238 or its substitute. Since the surface of Venus has a thick, hot, and corrosive atmosphere, it is a challenging proposition to maintain sensitive lander electronics under survivable conditions. This development effort requires the integration of: a radioisotope or fission heat source; heat pipes; high-temperature, corrosion-resistant material; multistage cooling; a novel free-displacer Stirling convertor for the lander; and a minimal vibration thermoacoustic Stirling convertor for the seismometer. The first year effort includes conceptual system design and control studies, materials development, and prototype hardware testing. A summary of these findings and test results is presented in this report.

Progress Towards the Development of a Long-Lived Venus Lander Duplex System

NASA Technical Reports Server (NTRS)

Dyson, Rodger, W.; Bruder, Geoffrey A.

2011-01-01

NASA has begun the development of a combined Stirling cycle power and cooling system (duplex) to enable the long-lived surface exploration of Venus and other harsh environments in the solar system. The duplex system will operate from the heat provided by decaying radioisotope plutonium-238 or its substitute. Since the surface of Venus has a thick, hot, and corrosive atmosphere, it is a challenging proposition to maintain sensitive lander electronics under survivable conditions. This development effort requires the integration of: a radioisotope or fission heat source; heat pipes; high-temperature, corrosion-resistant material; multistage cooling; a novel free-displacer Stirling convertor for the lander; and a minimal vibration thermoacoustic Stirling convertor for the seismometer. The first year effort includes conceptual system design and control studies, materials development, and prototype hardware testing. A summary of these findings and test results is presented in this report.

Lunar Lander Offloading Operations Using a Heavy-Lift Lunar Surface Manipulator System

NASA Technical Reports Server (NTRS)

Jefferies, Sharon A.; Doggett, William R.; Chrone, Jonathan; Angster, Scott; Dorsey, John T.; Jones, Thomas C.; Haddad, Michael E.; Helton, David A.; Caldwell, Darrell L., Jr.

2010-01-01

This study investigates the feasibility of using a heavy-lift variant of the Lunar Surface Manipulator System (LSMS-H) to lift and handle a 12 metric ton payload. Design challenges and requirements particular to handling heavy cargo were examined. Differences between the previously developed first-generation LSMS and the heavy-lift version are highlighted. An in-depth evaluation of the tip-over risk during LSMS-H operations has been conducted using the Synergistic Engineering Environment and potential methods to mitigate that risk are identified. The study investigated three specific offloading scenarios pertinent to current Lunar Campaign studies. The first involved offloading a large element, such as a habitat or logistics module, onto a mobility chassis with a lander-mounted LSMS-H and offloading that payload from the chassis onto the lunar surface with a surface-mounted LSMS-H. The second scenario involved offloading small pressurized rovers with a lander-mounted LSMS-H. The third scenario involved offloading cargo from a third-party lander, such as the proposed ESA cargo lander, with a chassis-mounted LSMS-H. In all cases, the analyses show that the LSMS-H can perform the required operations safely. However, Chariot-mounted operations require the addition of stabilizing outriggers, and when operating from the Lunar surface, LSMS-H functionality is enhanced by adding a simple ground anchoring system.

Integrated Pressure-Fed Liquid Oxygen / Methane Propulsion Systems - Morpheus Experience, MARE, and Future Applications

NASA Technical Reports Server (NTRS)

Hurlbert, Eric; Morehead, Robert; Melcher, John C.; Atwell, Matt

2016-01-01

An integrated liquid oxygen (LOx) and methane propulsion system where common propellants are fed to the reaction control system and main engines offers advantages in performance, simplicity, reliability, and reusability. LOx/Methane provides new capabilities to use propellants that are manufactured on the Mars surface for ascent return and to integrate with power and life support systems. The clean burning, non-toxic, high vapor pressure propellants provide significant advantages for reliable ignition in a space vacuum, and for reliable safing or purging of a space-based vehicle. The NASA Advanced Exploration Systems (AES) Morpheus lander demonstrated many of these key attributes as it completed over 65 tests including 15 flights through 2014. Morpheus is a prototype of LOx/Methane propellant lander vehicle with a fully integrated propulsion system. The Morpheus lander flight demonstrations led to the proposal to use LOx/Methane for a Discovery class mission, named Moon Aging Regolith Experiment (MARE) to land an in-situ science payload for Southwest Research Institute on the Lunar surface. Lox/Methane is extensible to human spacecraft for many transportation elements of a Mars architecture. This paper discusses LOx/Methane propulsion systems in regards to trade studies, the Morpheus project experience, the MARE NAVIS (NASA Autonomous Vehicle for In-situ Science) lander, and future possible applications. The paper also discusses technology research and development needs for Lox/Methane propulsion systems.

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. Finally, the advantages and disadvantages of both power systems with regard to science return, risk, and cost are briefly compared. The design of the radioisotope power system is considerably riskier because it is novel and would require additional years of further refinement, manufacturing, safety analysis, and testing that the primary batteries do not need. However, the lifetime of the radioisotope power system makes its science return more promising.

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

NASA Technical Reports Server (NTRS)

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

2017-01-01

This paper explores the impact of human Mars mission architecture decisions on the design and performance of a lander using the HIAD entry system: (a) Earth departure options, (b) Mars arrival options, (c) Entry Descent and Landing options.

Names Chip Placed on InSight Lander Deck

NASA Image and Video Library

2015-12-17

A spacecraft specialist in a clean room at Lockheed Martin Space Systems in Denver affixes a dime-size chip onto the lander deck in November 2015. This chip carries 826,923 names, submitted by the public online from all over the world.

A new Concept for High Resolution Benthic Mapping and Data Aquisition: MANSIO-VIATOR

NASA Astrophysics Data System (ADS)

Flögel, S.

2015-12-01

Environmental conditions within sensitive seafloor ecosystems such as cold-seep provinces or cold-water coral reef communities vary temporally and spatially over a wide range of scales. Some of these are regularly monitored via short periods of intense shipborne activity or low resolution, fixed location studies by benthic lander systems. Long term measurements of larger areas and volumes are ususally coupled to costly infrastructure investments such as cabled observatories. In space exploration, a combination of fixed and mobile systems working together are commonly used, e.g. lander systems coupled to rovers, to tackle observational needs that are very similar to deep-sea data aquisition. The analogies between space and deep-sea research motivated the German Helmholtz Association to setup the joint research program ROBEX (Robotic Exploration under extreme conditions). The program objectives are to identify, develop and verify technological synergies between the robotic exploration of e.g. the moon and the deep-sea. Within ROBEX, the mobility of robots is a vital element for research missions due to valuable scientifice return potential from different sites as opposed to static landers. Within this context, we developed a new mobile crawler system (VIATOR, latin for traveller) and a fixed lander component for energy and data transfer (MANSIO, latin for housing/shelter). This innovative MANSIO-VIATOR system has been developed during the past 2.5 years. The caterpillar driven component is developed to conduct high resolution opitcal mapping and repeated monitoring of physical and biogeochemical parameters along transects. The system operates fully autonomously including navigational components such as camera and laser scanners, as well as marker based near-field navigation used in space technology. This new concept of data aquisition by a submarine crawler in combination with a fixed lander further opens up marine exploration possibilities.

A Reusable Design for Precision Lunar Landing Systems

NASA Technical Reports Server (NTRS)

Fuhrman, Linda; Brand, Timothy; Fill, Tom; Norris, Lee; Paschall, Steve

2005-01-01

The top-level architecture to accomplish NASA's Vision for Space Exploration is to use Lunar missions and systems not just as an end in themselves, but also as testbeds for the more ambitious goals of Human Mars Exploration (HME). This approach means that Lunar missions and systems are most likely going to be targeted for (Lunar) polar missions, and also for long-duration (months) surface stays. This overacting theme creates basic top-level requirements for any next-generation lander system: 1) Long duration stays: a) Multiple landers in close proximity; b) Pinpoint landings for "surface rendezvous"; c) Autonomous landing of pre-positioned assets; and d) Autonomous Hazard Detection and Avoidance. 2) Polar and deep-crater landings (dark); 3) Common/extensible systems for Moon and Mars, crew and cargo. These requirements pose challenging technology and capability needs. Compare and contrast: 4) Apollo: a) 1 km landing accuracy; b) Lunar near-side (well imaged and direct-to-Earth com. possible); c) Lunar equatorial (landing trajectories offer best navigation support from Earth); d) Limited lighting conditions; e) Significant ground-in-the-loop operations; 5) Lunar Access: a) 10-100m landing precision; b) "Anywhere" access includes polar (potentially poor nav. support from Earth) and far side (poor gravity and imaging; no direct-to-Earth com); c) "Anytime" access includes any lighting condition (including dark); d) Full autonomous landing capability; e) Extensible design for tele-operation or operator-in-the-loop; and f) Minimal ground support to reduce operations costs. The Lunar Access program objectives, therefore, are to: a) Develop a baseline Lunar Precision Landing System (PLS) design to enable pinpoint "anywhere, anytime" landings; b) landing precision 10m-100m; c) Any LAT, LON; and d) Any lighting condition; This paper will characterize basic features of the next generation Lunar landing system, including trajectory types, sensor suite options and a reference system architecture.

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.

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.

Positioning for the Chang'E-3 lander and rover using Earth-based Observations

NASA Astrophysics Data System (ADS)

Li, P.; Huang, Y.; Hu, X.; Shengqi, C.

2016-12-01

The Chinese first lunar lander, Chang'E-3, performed a lunar soft-landing on 14 Dec, 2013. Precise positioning for the lander and rover was the most important precondition and guarantee for a successful lunar surface exploration. In this study, first, the tracking system, measurement models and positioning method are discussed in detail. Second, the location of the CE-3 lander was determined: 44.1206°N, -19.5124°E, -2632 m (altitude was relative to the assumed lunar surface with a height of 1737.4 km), and the analysis showed the VLBI Very Long Base Interferometry data were able to significantly improve the positioning accuracy. Furthermore, the positioning error was evaluated in various ways; the result was better than 50 m. Finally, the relative positioning of the rover and lander using earth-based observations was studied and compared with the optical positioning method using photographs taken by the lander and rover. The method applied in this study was not limited by the visible range of the lander, and the relative positioning accuracy did not decrease as the distance between the lander and rover increased. The results indicated that under the current tracking and measuring conditions, the relative positioning accuracy was about 100 m using the same beam VLBI group delay data with ns nanosecond level noise. Furthermore, using the same beam VLBI phase delay data with ps picosecond level noise it was possible to significantly improve the relative positioning accuracy to the order of 1 m.

Phoenix's Lay of the Land

NASA Technical Reports Server (NTRS)

2008-01-01

This image from NASA's Phoenix Mars Lander shows the spacecraft's recent activity site as of the 23rd Martian day of the mission, or Sol 22 (June 16, 2008), after the spacecraft touched down on the Red Planet's northern polar plains. The mosaic was taken by the lander's Surface Stereo Imager (SSI). Parts of Phoenix can be seen in the foreground.

The first two trenches dug by the lander's Robotic Arm, called 'Dodo' and 'Goldilocks,' were enlarged on the 19th Martian day of the mission, or Sol 18 (June 12, 2008), to form one trench, dubbed 'Dodo-Goldilocks.' Scoops of material taken from those trenches are informally called 'Baby Bear' and 'Mama Bear.' Baby Bear was carried to Phoenix's Thermal and Evolved-Gas Analyzer, or TEGA, instrument for analysis, while Mama Bear was delivered to Phoenix's Microscopy, Electrochemistry and Conductivity Analyzer instrument suite, or MECA, for a closer look.

The color inset picture of the Dodo-Goldilocks trench, also taken with Phoenix's SSI, reveals white material thought to be ice.

More recently, on Sol 22 (June 16, 2008), Phoenix's Robotic Arm began digging a trench, dubbed 'Snow White,' in a patch of Martian soil near the center of a polygonal surface feature, nicknamed 'Cheshire Cat.' The 'dump pile' is located at the top of the trench, and has been dubbed 'Croquet Ground.' The digging site has been nicknamed 'Wonderland.'

The Snow White trench, seen here in an SSI image from Sol 22 (June 16, 2008) is about 2 centimeters (.8 inches) deep and 30 centimeters (12 inches) long. As of Sol 25 (June 19, 2008), the trench is 5 centimeters (2 inches deep) and the trench has been renamed 'Snow White 1,' as a second trench has been dug to its right and nicknamed 'Snow White 2.'

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.

Sample Handling in Extreme Environments

NASA Technical Reports Server (NTRS)

Avellar, Louisa; Badescu, Mircea; Sherrit, Stewart; Bar-Cohen, Yoseph

2013-01-01

Harsh environments, such as that on Venus, preclude the use of existing equipment for functions that involve interaction with the environment. The operating limitations of current high temperature electronics are well below the actual temperature and pressure found on Venus (460 deg C and 92 atm), so proposed lander configurations typically include a pressure vessel where the science instruments are kept at Earth-like temperature and pressure (25 deg C and 1 atm). The purpose of this project was to develop and demonstrate a method for sample transfer from an external drill to internal science instruments for a lander on Venus. The initial concepts were string and pneumatically driven systems; and the latter system was selected for its ability to deliver samples at very high speed. The pneumatic system was conceived to be driven by the pressure difference between the Venusian atmosphere and the inside of the lander. The pneumatic transfer of a small capsule was demonstrated, and velocity data was collected from the lab experiment. The sample transfer system was modeled using CAD software and prototyped using 3D printing. General structural and thermal analyses were performed to approximate the proposed system's mass and effects on the temperature and pressure inside of the lander. Additionally, a sampler breadboard for use on Titan was tested and functionality problems were resolved.

Telltale Instrument Waving in the Martian Wind

NASA Image and Video Library

2008-10-16

This frame from a series of images shows NASA Phoenix Mars Lander telltale instrument waving in the Martian wind. Documenting the telltale movement helps mission scientists and engineers determine what the wind is like on Mars.

Animation of MARDI Instrument

NASA Image and Video Library

2008-09-30

This frame from an animation shows a zoom into the Mars Descent Imager MARDI instrument onboard NASA Phoenix Mars Lander. The Phoenix team will soon attempt to use a microphone on the MARDI instrument to capture sounds of Mars.

How to Take a Picture of A Robotic Arm

NASA Image and Video Library

2008-05-27

This image shows an artist concept of NASA Phoenix Mars Lander snapping a picture of its arm, then transitions to the actual picture of the arm in its stowed configuration, with its biobarrier unpeeled.

Wolf: What's On the Lunar Farside?

NASA Technical Reports Server (NTRS)

2008-01-01

WOLF (What's On the Lunar Farside?) is a lunar sample return mission to the South Pole-Aitken (SPA) Basin, located on the farside of the moon, seeking to answer some of the remaining questions about our solar system. Through the return and analysis of SPA samples, scientists can constrain the period of inner solar system late heavy bombardment and gain momentous knowledge of the SPA basin. WOLF provides the opportunity for mankind's progression in further understanding our solar system, its history, and unknowns surrounding the lunar farside. The orbiter will provide intermittent, direct communication between the lander and ground operations via the Deep Space Network (DSN). Received images and spectrometry will aid in real-time sample selection.

Lunar and Planetary Science XXXV: Education Programs Demonstrations

NASA Technical Reports Server (NTRS)

2004-01-01

Reports from the session on Education Programs Demonstration include:Hands-On Activities for Exploring the Solar System in K-14; Formal Education and Informal Settings;Making Earth and Space Science and Exploration Accessible; New Thematic Solar System Exploration Products for Scientists and Educators Engaging Students of All Ages with Research-related Activities: Using the Levers of Museum Reach and Media Attention to Current Events; Astronomy Village: Use of Planetary Images in Educational Multimedia; ACUMEN: Astronomy Classes Unleashed: Meaningful Experiences for Neophytes; Unusual Guidebook to Terrestrial Field Work Studies: Microenvironmental Studies by Landers on Planetary Surfaces (New Atlas in the Series of the Solar System Notebooks on E tv s University, Hungary); and The NASA ADS: Searching, Linking and More.

Macromolecular Networks Containing Fluorinated Cyclic Moieties

DTIC Science & Technology

2015-12-12

Approved for public release.  Distribution is unlimited.   Cyanate Esters Around the Solar System 4 Images:  courtesy  NASA  (public release) • The...science decks on the Mars Phoenix lander are made from M55J/cyanate ester composites • The solar panel supports on the MESSENGER space probe use cyanate...thermonuclear fusion reactor Fusion reactor, photo  courtesy of Gerritse ((Wikimedia Commons) • Unique cyanate ester composites have been designed by NASA

Analysis-test correlation of airbag impact for Mars landing

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

Salama, M.; Davis, G.; Kuo, C.P.

1994-12-31

The NASA Mars Pathfinder mission is intended to demonstrate key low cost technologies for use in future science missions to Mars. Among these technologies is the landing system. Upon entering in Martian atmosphere at about 7000 m/sec., the spacecraft will deploy a series of breaking devices (parachute and solid rockets) to slow down its speed to less than 20 m/sec. as it impacts with the Martian ground. To cushion science instruments form the landing impact, an airbag system is inflated to surround the lander approximately five seconds before impact. After multiple bounces, the lander/airbags comes to rest, the airbags aremore » deflated and retracted, and the lander opens up its petals to allow a microrover to begin exploration. Of interest here, is the final landing phase. Specifically, this paper will focus on the methodology used to simulate the nonlinear dynamics of lander/airbags landing impact, and how this simulation correlates with initial tests.« less

Digital image transformation and rectification of spacecraft and radar images

NASA Technical Reports Server (NTRS)

Wu, S. S. C.

1985-01-01

The application of digital processing techniques to spacecraft television pictures and radar images is discussed. The use of digital rectification to produce contour maps from spacecraft pictures is described; images with azimuth and elevation angles are converted into point-perspective frame pictures. The digital correction of the slant angle of radar images to ground scale is examined. The development of orthophoto and stereoscopic shaded relief maps from digital terrain and digital image data is analyzed. Digital image transformations and rectifications are utilized on Viking Orbiter and Lander pictures of Mars.

Terrain and Rock Yogi

NASA Image and Video Library

1997-07-06

The left portion of this image, taken by the Imager for Mars Pathfinder (IMP) on July 5, 1997 (Sol 2), shows a portion of the large rock nicknamed "Yogi." Portions of a petal and deflated airbag are in the foreground. The dark circular object at right is a portion of the lander's high-gain antenna. http://photojournal.jpl.nasa.gov/catalog/PIA00630

Characterisation of potential landing sites for the European Space Agency's Lunar Lander project

NASA Astrophysics Data System (ADS)

De Rosa, Diego; Bussey, Ben; Cahill, Joshua T.; Lutz, Tobias; Crawford, Ian A.; Hackwill, Terence; van Gasselt, Stephan; Neukum, Gerhard; Witte, Lars; McGovern, Andy; Grindrod, Peter M.; Carpenter, James D.

2012-12-01

This article describes the characterisation activities of the landing sites currently envisaged for the Lunar Lander mission of the European Space Agency. These sites have been identified in the South Pole Region (-85° to-90° latitude) based on favourable illumination conditions, which make it possible to have a long-duration mission with conventional power and thermal control subsystems, capable of enduring relatively short periods of darkness (in the order of tens of hours), instead of utilising Radioisotope Heating Units. The illumination conditions are simulated at the potential landing sites 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. Long baseline slopes are assessed based on LOLA, while craters and boulders are detected both visually and using computer tools in Lunar Reconnaissance Orbiter Camera (LROC) images, down to a size of less than 2 m, and size-frequency distributions are generated. Shadow hazards are also assessed via LROC images. The preliminary results show that areas with quasi-continuous illumination of several months exist, but their size is small (few hundred metres); the duration of the illumination period drops quickly to less than one month outside the areas, and some areas present gaps with short illumination periods. Concerning hazard distributions, 50 m slopes are found to be shallow (few degrees) based on LOLA, whereas at the scale of the lander footprint (˜5 m) they are mostly dominated by craters, expected to be mature (from geological context) and shallow (˜11°). The preliminary conclusion is that the environment at the prospective landing sites is within the capabilities of the Lander design.

KSC-2012-4016

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4017

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - A forklift is used at the Kennedy Space Center in Florida to unload NASA's Morpheus lander, a vertical test bed vehicle. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4019

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is inspected after unloading at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4023

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - Wheels are assembled for transporting NASA's Morpheus lander, a vertical test bed vehicle after its arrival at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4028

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4020

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is uncrated after unloading at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4013

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4029

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4012

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4021

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4025

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - A crane supports unloading of NASA's Morpheus lander, a vertical test bed vehicle, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4014

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

Mars 2001 Lander Mission: Measurement Synergy Through Coordinated Operations Planning and Implementation

NASA Astrophysics Data System (ADS)

Arvidson, R.

1999-01-01

The 2001 Mars Surveyor Program Mission includes an orbiter with a gamma ray spectrometer and a multispectral thermal imager, and a lander with an extensive set of instrumentation, a robotic arm, and the Marie Curie Rover. The Mars 2001 Science Operations Working Group (SOWG), a subgroup of the Project Science Group, has been formed to provide coordinated planning and implementation of scientific observations, particularly for the landed portion of the mission. The SOWG will be responsible for delivery of a science plan and, during operations, generation and delivery of conflict-free sequences. This group will also develop an archive plan that is compliant with Planetary Data System (PDS) standards, and will oversee generation, validation, and delivery of integrated archives to the PDS. In this abstract we cover one element of the SOWG planning activities, the development of a set of six science campaign themes that maximize the scientific return from lander-based observations by treating the instrument packages as an integrated payload. Scientific objectives for the lander mission have been defined. They include observations focused on determining the bedrock geology of the site through analyses of rocks and also local materials found in the soils, and the surficial geology of the site, including windblown deposits and the nature and history of formation of indurated sediments such as duricrust. Of particular interest is the identification and quantification of processes related to early warm, wet conditions and the presence of hydrologic or hydrothermal cycles. Determining the nature and origin of duricrust and associated salts is very important in this regard. Specifically, did these deposits form in the vadose zone as pore water evaporated from soils or did they form by other processes, such as deposition of volcanic aerosols? Basic information needed to address these questions includes the morphology, topography, and geologic context of landforms and materials exposed at the site, 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). Observations from the APEX, MECA, and MIP Experiments, including use of the robotic arm robotic arm camera (RAC) and the Marie Curie rover, will be used to address these parameters in a synergistic way. Further, calibration targets on APEX will provide radiometric and mineralogical control surfaces, and magnet targets will allow observations of magnetic phases. Patch plates on MECA will be 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.

Requirements for maintaining cryogenic propellants during planetary surface stays

NASA Technical Reports Server (NTRS)

Riccio, Joseph R.; Schoenberg, Richard J.

1991-01-01

Potential impacts on the planetary surface system infrastructure resulting from the use of liquid hydrogen and oxygen propellants for a stage and half lander are discussed. Particular attention is given to techniques which can be incorporated into the surface infrastructure and/or the vehicle to minimize the impact resulting from the use of these cryogens. Methods offered for reducing cryogenic propellant boiloff include modification of the lander to accommodate boiloff, incorporation of passive thermal control devices to the lander, addition of active propellant management, and use of alternative propellants.

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.

KSC-2013-4322

NASA Image and Video Library

2013-12-10

CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the engine fires and the lander lifts off at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett

KSC-2013-4321

NASA Image and Video Library

2013-12-10

CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the engine fires and the lander begins to lift off at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett

Concurrent Multidisciplinary Preliminary Assessment of Space Systems (COMPASS) Final Report: Advanced Long-Life Lander Investigating the Venus Environment (ALIVE)

NASA Technical Reports Server (NTRS)

Oleson, Steven R.

2018-01-01

The COncurrent Multidisciplinary Preliminary Assessment of Space Systems (COMPASS) Team partnered with the Applied Research Laboratory to perform a NASA Innovative Advanced Concepts (NIAC) Program study to evaluate chemical based power systems for keeping a Venus lander alive (power and cooling) and functional for a period of days. The mission class targeted was either a Discovery ($500M) or New Frontiers ($750M to $780M) class mission.

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.

Robotic Arm Unwrapped

NASA Technical Reports Server (NTRS)

2008-01-01

This image, taken shortly after NASA's Phoenix Mars Lander touched down on the surface of Mars, shows the spacecraft's robotic arm in its stowed configuration, with its biobarrier successfully unpeeled. The 'elbow' of the arm can be seen at the top center of the picture, and the biobarrier is the shiny film seen to the left of the arm.

The biobarrier is an extra precautionary measure for protecting Mars from contamination with any bacteria from Earth. While the whole spacecraft was decontaminated through cleaning, filters and heat, the robotic arm was given additional protection because it is the only spacecraft part that will directly touch the ice below the surface of Mars.

Before the arm was heated, it was sealed in the biobarrier, which is made of a trademarked film called Tedlar that holds up to baking like a turkey-basting bag. This ensures that any new bacterial spores that might have appeared during the final steps before launch and during the journey to Mars will not contact the robotic arm.

After Phoenix landed, springs were used to pop back the barrier, giving it room to deploy.

The base of the lander's Meteorological Station can be seen in this picture on the upper left. Because only the base of the station is showing, this image tells engineers that the instrument deployed successfully.

The image was taken on landing day, May 25, 2008, by the spacecraft's Surface Stereo Imager.

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.

Photovoltaic power system operation in the Mars environment

NASA Technical Reports Server (NTRS)

Appelbaum, Joseph; Flood, Dennis J.

1989-01-01

Detailed information on the environmental conditions on Mars are very desirable for the design of photovoltaic systems for establishing outposts on the Martian surface. The variation of solar insolation (global, direct, and diffuse) at the Viking lander's locations is addressed. It can be used, to a first approximation, for other latitudes. The radiation data is based on measured optical depth of the Martian atmosphere derived from images taken of the sun with a special diode on the Viking cameras; and computation based on multiple wavelength and multiple scattering of the solar radiation. The data are used to make estimates of photovoltaic system power, area and mass for a surface power system using regenerative fuel cells for storage and nighttime operation.

Snow White Trench After Scraping

NASA Image and Video Library

2008-07-24

This view from the Surface Stereo Imager on NASA Phoenix Mars Lander shows the trench informally named Snow White after a series of scrapings were done in preparation for collecting a sample for analysis from a hard subsurface layer.

Spacecraft exploration of Phobos and Deimos

NASA Astrophysics Data System (ADS)

Duxbury, Thomas C.; Zakharov, Alexander V.; Hoffmann, Harald; Guinness, Edward A.

2014-11-01

We review the previous exploration of Phobos and Deimos by spacecraft. The first close-up images of Phobos and Deimos were obtained by the Mariner 9 spacecraft in 1971, followed by much image data from the two Viking orbiters at the end of the 70s, which formed the basis for early Phobos and Deimos shape and dynamic models. The Soviet Phobos 2 spacecraft came within 100 km of landing on Phobos in 1988. Mars Global Surveyor (1996-2006) and Mars Reconnaissance Orbiter (since 2005) made close-up observations of Phobos on several occasions. Mars Express (since 2003) in its highly elliptical orbit is currently the only spacecraft to make regular Phobos encounters and has returned large volumes of science data for this satellite. Landers and rovers on the ground (Viking Landers, Mars Pathfinder, MER rovers, MSL rover) frequently made observations of Phobos, Deimos and their transits across the solar disk.

KSC-98pc1352

NASA Image and Video Library

1998-10-16

In the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2), the Mars Climate Orbiter (foreground) and the Mars Polar Lander are on display for the media. The scheduled launch date for the Mars Climate Orbiter is Dec. 10, 1998, aboard a Boeing Delta II rocket. It is heading for Mars where it will primarily support its companion Mars Polar Lander spacecraft, planned for launch on Jan. 3, 1999. After that, the Mars Climate Orbiter's instruments will monitor the Martian atmosphere and image the planet's surface on a daily basis for one Martian year (two Earth years). It will observe the appearance and movement of atmospheric dust and water vapor, as well as characterize seasonal changes on the surface. The detailed images of the surface features will provide important clues to the planet's early climate history and give scientists more information about possible liquid water reserves beneath the surface

The Mars Climate Orbiter is prepared for a spin test in the SAEF- 2

NASA Technical Reports Server (NTRS)

1998-01-01

In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF- 2), workers prepare the Mars Climate Orbiter for a spin test. Targeted for launch aboard a Delta II rocket on Dec. 10, 1998, the orbiter is heading for Mars where it will primarily support its companion Mars Polar Lander spacecraft, which is planned for launch on Jan. 3, 1999. At the extreme right can be seen the lander in another work area. The orbiter's instruments will monitor the Martian atmosphere and image the planet's surface on a daily basis for 687 Earth days. It will observe the appearance and movement of atmospheric dust and water vapor, as well as characterize seasonal changes on the surface. The detailed images of the surface features will provide important clues to the planet's early climate history and give scientists more information about possible liquid water reserves beneath the surface.

Landing Site Dispersion Analysis and Statistical Assessment for the Mars Phoenix Lander

NASA Technical Reports Server (NTRS)

Bonfiglio, Eugene P.; Adams, Douglas; Craig, Lynn; Spencer, David A.; Strauss, William; Seelos, Frank P.; Seelos, Kimberly D.; Arvidson, Ray; Heet, Tabatha

2008-01-01

The Mars Phoenix Lander launched on August 4, 2007 and successfully landed on Mars 10 months later on May 25, 2008. Landing ellipse predicts and hazard maps were key in selecting safe surface targets for Phoenix. Hazard maps were based on terrain slopes, geomorphology maps and automated rock counts of MRO's High Resolution Imaging Science Experiment (HiRISE) images. The expected landing dispersion which led to the selection of Phoenix's surface target is discussed as well as the actual landing dispersion predicts determined during operations in the weeks, days, and hours before landing. A statistical assessment of these dispersions is performed, comparing the actual landing-safety probabilities to criteria levied by the project. Also discussed are applications for this statistical analysis which were used by the Phoenix project. These include using the statistical analysis used to verify the effectiveness of a pre-planned maneuver menu and calculating the probability of future maneuvers.

A View of Opportunity's Dance Moves

NASA Technical Reports Server (NTRS)

2004-01-01

This rear hazard-avoidance camera image taken by the Mars Exploration Rover Opportunity on the 37th martian day, or sol, of its mission (March 2, 2004) shows the tracks left by the rover during its latest 'dance,' or series of maneuvers, around the rock outcrop near its landing site. Note the view of the lander to the far left and the light-colored outcrop below the horizon. The rear solar panels, located above the rear hazard-avoidance cameras, are captured in the uppermost part of the image.

Since driving off the lander, Opportunity has traveled along the entire outcrop, trenched, and completed a U-turn to revisit scientifically rich spots. Two of these spots are the rock regions dubbed 'El Capitan' and 'Last Chance.' Scientists have used the instruments on the rover's arm to conclude that this area of Mars was once soaked in water for extended amounts of time, possibly providing an environment favorable for life.

KSC-98pc1719

NASA Image and Video Library

1998-11-16

KENNEDY SPACE CENTER, FLA. -- In the Spacecraft Assembly and Encapsulation Facility -2 (SAEF-2), workers prepare the Mars Climate Orbiter for a spin test. Targeted for launch aboard a Delta II rocket on Dec. 10, 1998, the orbiter is heading for Mars where it will primarily support its companion Mars Polar Lander spacecraft, which is planned for launch on Jan. 3, 1999. At the extreme right can be seen the lander in another work area. The orbiter's instruments will monitor the Martian atmosphere and image the planet's surface on a daily basis for 687 Earth days. It will observe the appearance and movement of atmospheric dust and water vapor, as well as characterize seasonal changes on the surface. The detailed images of the surface features will provide important clues to the planet's early climate history and give scientists more information about possible liquid water reserves beneath the surface

Polygon on Mars

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows a small-scale polygonal pattern in the ground near NASA's Phoenix Mars Lander. This pattern is similar in appearance to polygonal structures in icy ground in the arctic regions of Earth.

Phoenix touched down on the Red Planet at 4:53 p.m. Pacific Time (7:53 p.m. Eastern Time), May 25, 2008, in an arctic region called Vastitas Borealis, at 68 degrees north latitude, 234 degrees east longitude.

This image was acquired by the Surface Stereo Imager shortly after landing. On the Phoenix mission calendar, landing day is known as Sol 0, the first 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.

Phoenix's 'Dodo' Trench

NASA Technical Reports Server (NTRS)

2008-01-01

This image was taken by NASA's Phoenix Mars Lander's Robotic Arm Camera (RAC) on the ninth Martian day of the mission, or Sol 9 (June 3, 2008). The center of the image shows a trench informally called 'Dodo' after the second dig. 'Dodo' is located within the previously determined digging area, informally called 'Knave of Hearts.' The light square to the right of the trench is the Robotic Arm's Thermal and Electrical Conductivity Probe (TECP). The Robotic Arm has scraped to a bright surface which indicated the Arm has reached a solid structure underneath the surface, which has been seen in other images as well.

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.

3D flash lidar performance in flight testing on the Morpheus autonomous, rocket-propelled lander to a lunar-like hazard field

NASA Astrophysics Data System (ADS)

Roback, Vincent E.; Amzajerdian, Farzin; Bulyshev, Alexander E.; Brewster, Paul F.; Barnes, Bruce W.

2016-05-01

For the first time, a 3-D imaging Flash Lidar instrument has been used in flight to scan a lunar-like hazard field, build a 3-D Digital Elevation Map (DEM), identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control system, help to guide the Morpheus autonomous, rocket-propelled, free-flying lander to that safe site on the hazard field. The flight tests served as the TRL 6 demo of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) system and included launch from NASA-Kennedy, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range. The ALHAT project developed a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The Flash Lidar is a second generation, compact, real-time, air-cooled instrument. Based upon extensive on-ground characterization at flight ranges, the Flash Lidar was shown to be capable of imaging hazards from a slant range of 1 km with an 8 cm range precision and a range accuracy better than 35 cm, both at 1-σ. The Flash Lidar identified landing hazards as small as 30 cm from the maximum slant range which Morpheus could achieve (450 m); however, under certain wind conditions it was susceptible to scintillation arising from air heated by the rocket engine and to pre-triggering on a dust cloud created during launch and transported down-range by wind.

3-D Flash Lidar Performance in Flight Testing on the Morpheus Autonomous, Rocket-Propelled Lander to a Lunar-Like Hazard Field

NASA Technical Reports Server (NTRS)

Roback, Vincent E.; Amzajerdian, Farzin; Bulyshev, Alexander E.; Brewster, Paul F.; Barnes, Bruce W.

2016-01-01

For the first time, a 3-D imaging Flash Lidar instrument has been used in flight to scan a lunar-like hazard field, build a 3-D Digital Elevation Map (DEM), identify a safe landing site, and, in concert with an experimental Guidance, Navigation, and Control (GN&C) system, help to guide the Morpheus autonomous, rocket-propelled, free-flying lander to that safe site on the hazard field. The flight tests served as the TRL 6 demo of the Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) system and included launch from NASA-Kennedy, a lunar-like descent trajectory from an altitude of 250m, and landing on a lunar-like hazard field of rocks, craters, hazardous slopes, and safe sites 400m down-range. The ALHAT project developed a system capable of enabling safe, precise crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The Flash Lidar is a second generation, compact, real-time, air-cooled instrument. Based upon extensive on-ground characterization at flight ranges, the Flash Lidar was shown to be capable of imaging hazards from a slant range of 1 km with an 8 cm range precision and a range accuracy better than 35 cm, both at 1-delta. The Flash Lidar identified landing hazards as small as 30 cm from the maximum slant range which Morpheus could achieve (450 m); however, under certain wind conditions it was susceptible to scintillation arising from air heated by the rocket engine and to pre-triggering on a dust cloud created during launch and transported down-range by wind.

Integral design method for simple and small Mars lander system using membrane aeroshell

NASA Astrophysics Data System (ADS)

Sakagami, Ryo; Takahashi, Ryohei; Wachi, Akifumi; Koshiro, Yuki; Maezawa, Hiroyuki; Kasai, Yasko; Nakasuka, Shinichi

2018-03-01

To execute Mars surface exploration missions, spacecraft need to overcome the difficulties of the Mars entry, descent, and landing (EDL) sequences. Previous landing missions overcame these challenges with complicated systems that could only be executed by organizations with mature technology and abundant financial resources. In this paper, we propose a novel integral design methodology for a small, simple Mars lander that is achievable even by organizations with limited technology and resources such as universities or emerging countries. We aim to design a lander (including its interplanetary cruise stage) whose size and mass are under 1 m3 and 150 kg, respectively. We adopted only two components for Mars EDL process: a "membrane aeroshell" for the Mars atmospheric entry and descent sequence and one additional mechanism for the landing sequence. The landing mechanism was selected from the following three candidates: (1) solid thrusters, (2) aluminum foam, and (3) a vented airbag. We present a reasonable design process, visualize dependencies among parameters, summarize sizing methods for each component, and propose the way to integrate these components into one system. To demonstrate the effectiveness, we applied this methodology to the actual Mars EDL mission led by the National Institute of Information and Communications Technology (NICT) and the University of Tokyo. As a result, an 80 kg class Mars lander with a 1.75 m radius membrane aeroshell and a vented airbag was designed, and the maximum landing shock that the lander will receive was 115 G.

The observation and coverage analysis of the moon-based ultraviolet telescope on CE-3 lander

NASA Astrophysics Data System (ADS)

wang, f.; wen, w.-b.; liu, d.-w.; geng, l.; zhang, x.-x.; zhao, s.

2017-09-01

Through the analysis of all the observed images of MUVT, it is found that in the celestial coordinate system, all the images of the survey are concentrated at Latitude 65 degrees and Longtitude -90 degrees as the center, a ring of 15 degrees width. The observation data analysis: the coverage of the northern area is up to 2263.8 square degrees, accounting for about 5.487% of the all area. The task is completed the observation target. For the first time, the MUVT in a long time has carried out the astronomical observations, and accumulated abundant observational data for basic research on the evolution of stars, compact star and high energy astrophysics and so on.

Animation of 'Dodo' and 'Goldilocks' Trenches

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

A pan and zoom animation of the informally named 'Dodo' (on left) and 'Goldilocks' (on right) trenches as seen by the Surface Stereo Imager (SSI) aboard NASA's Phoenix Mars Lander. This animation was based on conditions on the Martian surface on Sol 17 (June 11, 2008), the 17th Martian day of the mission. 'Baby Bear' is the name of the sample taken from 'Goldilocks' and delivered to the Thermal and Evolved-Gas Analyzer (TEGA) instrument.

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.

Robotic Arm Camera Image of the South Side of the Thermal and Evolved-Gas Analyzer (Door TA4

NASA Technical Reports Server (NTRS)

2008-01-01

The Thermal and Evolved-Gas Analyzer (TEGA) instrument aboard NASA's Phoenix Mars Lander is shown with one set of oven doors open and dirt from a sample delivery. After the 'seventh shake' of TEGA, a portion of the dirt sample entered the oven via a screen for analysis. This image was taken by the Robotic Arm Camera on Sol 18 (June 13, 2008), or 18th 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.

Aeroshell for Mars Science Laboratory

NASA Technical Reports Server (NTRS)

2008-01-01

This image from July 2008 shows the aeroshell for NASA's Mars Science Laboratory while it was being worked on by spacecraft technicians at Lockheed Martin Space Systems Company near Denver.

This hardware was delivered in early fall of 2008 to NASA's Jet Propulsion Laboratory, Pasadena, Calif., where the Mars Science Laboratory spacecraft is being assembled and tested.

The aeroshell encapsulates the mission's rover and descent stage during the journey from Earth to Mars and shields them from the intense heat of friction with that upper atmosphere during the initial portion of descent.

The aeroshell has two main parts: the backshell, which is on top in this image and during the descent, and the heat shield, on the bottom. The heat shield in this image is an engineering unit for testing. The heat shield to be used in flight will be substituted later. The heat shield has a diameter of about 15 feet. For comparison, the heat shields for NASA's Mars Exploraton Rovers Spirit and Opportunity were 8.5 feet and the heat shields for the Apollo capsules that protected astronauts returning to Earth from the moon were just under 13 feet.

In addition to protecting the Mars Science Laboratory rover, the backshell provides structural support for the descent stage's parachute and sky crane, a system that will lower the rover to a soft landing on the surface of Mars. The backshell for the Mars Science Laboratory is made of an aluminum honeycomb structure sandwiched between graphite-epoxy face sheets. It is covered with a thermal protection system composed of a cork/silicone super light ablator material that originated with the Viking landers of the 1970s. This ablator material has been used on the heat shields of all NASA Mars landers in the past, but this mission is the first Mars mission using it on the backshell.

The heat shield for Mars Science Laboratory's flight will use tiles made of phenolic impregnated carbon ablator. The engineering unit in this image does not have the tiles.

JPL, a division of the California Institute of Technology, manages the Mars Science Laboratory Project for the NASA Science Mission Directorate, Washington.

KSC-2012-3955

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows the Shuttle Landing Facility’s air traffic control tower at the Kennedy Space Center in Florida. Just below the tower is the mid-field park site used for runway support vehicles. At the north end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

Orbiting Depot and Reusable Lander for Lunar Transportation

NASA Technical Reports Server (NTRS)

Petro, Andrew

2009-01-01

A document describes a conceptual transportation system that would support exploratory visits by humans to locations dispersed across the surface of the Moon and provide transport of humans and cargo to sustain one or more permanent Lunar outpost. The system architecture reflects requirements to (1) minimize the amount of vehicle hardware that must be expended while maintaining high performance margins and (2) take advantage of emerging capabilities to produce propellants on the Moon while also enabling efficient operation using propellants transported from Earth. The system would include reusable single- stage lander spacecraft and a depot in a low orbit around the Moon. Each lander would have descent, landing, and ascent capabilities. A crew-taxi version of the lander would carry a pressurized crew module; a cargo version could carry a variety of cargo containers. The depot would serve as a facility for storage and for refueling with propellants delivered from Earth or propellants produced on the Moon. The depot could receive propellants and cargo sent from Earth on a variety of spacecraft. The depot could provide power and orbit maintenance for crew vehicles from Earth and could serve as a safe haven for lunar crews pending transport back to Earth.

Safe Landings in Extreme Terrain

NASA Technical Reports Server (NTRS)

Rivellini, Tom; Ortiz, Gary; Steltzner, Adam

2000-01-01

Following the failure of the Mars Polar Lander and the re-evaluation of the Mars Sample Return mission status, a Safe Landing Tiger team was established on January 7, 2000. The charter of the team was to re-evaluate large scale (1000-2000 Kg) Mars lander designs with the principal objective being the assurance of safe landing in hazardous terrain. The tiger team developed a number of concepts, two of the most notable and promising concepts, are both based on a Mobile Lander paradigm. Unlike the Pathfinder and Surveyor class landers, this paradigm groups all of the landed equipment into one of two categories: (1) EDL only equipment (i.e., not used after touchdown) and (2) multi-use equipment, those used during and or after touchdown. The objective is to maximize the use of all equipment being brought to the surface by placing the bulk of the avionics and mechanical systems onto a much larger 'rover' and leaving only the bare essentials on a 'dead-on-arrival' landing system. All of the hardware that the surface roving mission needs is enlisted into performing the EDL tasks. Any EDL specific avionics not used after touchdown are placed on the landing system.

Multicolor observations of phobos with the viking lander cameras: evidence for a carbonaceous chondritic composition.

PubMed

Pollack, J B; Veverka, J; Pang, K; Colburn, D; Lane, A L; Ajello, J M

1978-01-06

The reflectivity of Phobos has been determined in the spectral region from 0.4 to 1.1 micrometers from images taken with a Viking lander camera. The reflectivity curve is flat in this spectral interval and the geometric albedo equals 0.05 +/- 0.01. These results, together with Phobos's reflectivity spectrum in the ultraviolet, are compared with laboratory spectra of carbonaceous chondrites and basalts. The spectra of carbonaceous chondrites are consistent with the observations, whereas the basalt spectra are not. These findings raise the possibility that Phobos may be a captured object rather than a natural satellite of Mars.

Martian Soil Delivery to Analytical Instrument on Phoenix

NASA Technical Reports Server (NTRS)

2008-01-01

The Robotic Arm of NASA's Phoenix Mars Lander released a sample of Martian soil onto a screened opening of the lander's Thermal and Evolved-Gas Analyzer (TEGA) during the 12th Martian day, or sol, since landing (June 6, 2008). TEGA did not confirm that any of the sample had passed through the screen.

The Robotic Arm Camera took this image on Sol 12. Soil from the sample delivery is visible on the sloped surface of TEGA, which has a series of parallel doors. The two doors for the targeted cell of TEGA are the one positioned vertically, at far right, and the one partially open just to the left of that one. The soil between those two doors is resting on a screen designed to let fine particles through while keeping bigger ones Efrom clogging the interior of the instrument. Each door is about 10 centimeters (4 inches) long.

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

A spectral reflectance estimation technique using multispectral data from the Viking lander camera

NASA Technical Reports Server (NTRS)

Park, S. K.; Huck, F. O.

1976-01-01

A technique is formulated for constructing spectral reflectance curve estimates from multispectral data obtained with the Viking lander camera. The multispectral data are limited to six spectral channels in the wavelength range from 0.4 to 1.1 micrometers and most of these channels exhibit appreciable out-of-band response. The output of each channel is expressed as a linear (integral) function of the (known) solar irradiance, atmospheric transmittance, and camera spectral responsivity and the (unknown) spectral responsivity and the (unknown) spectral reflectance. This produces six equations which are used to determine the coefficients in a representation of the spectral reflectance as a linear combination of known basis functions. Natural cubic spline reflectance estimates are produced for a variety of materials that can be reasonably expected to occur on Mars. In each case the dominant reflectance features are accurately reproduced, but small period features are lost due to the limited number of channels. This technique may be a valuable aid in selecting the number of spectral channels and their responsivity shapes when designing a multispectral imaging system.

Ice Clouds in Martian Arctic (Accelerated Movie)

NASA Technical Reports Server (NTRS)

2008-01-01

Clouds scoot across the Martian sky in a movie clip consisting of 10 frames taken by the Surface Stereo Imager on NASA's Phoenix Mars Lander.

This clip accelerates the motion. The camera took these 10 frames over a 10-minute period from 2:52 p.m. to 3:02 p.m. local solar time at the Phoenix site during Sol 94 (Aug. 29), the 94th Martian day since landing.

Particles of water-ice make up these clouds, like ice-crystal cirrus clouds on Earth. Ice hazes have been common at the Phoenix site in recent days.

The camera took these images as part of a campaign by the Phoenix team to see clouds and track winds. The view is toward slightly west of due south, so the clouds are moving westward or west-northwestward.

The clouds are a dramatic visualization of the Martian water cycle. The water vapor comes off the north pole during the peak of summer. The northern-Mars summer has just passed its peak water-vapor abundance at the Phoenix site. The atmospheric water is available to form into clouds, fog and frost, such as the lander has been observing recently.

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.

Morpheus Campaign 1A Liftoff

NASA Image and Video Library

2014-01-21

CAPE CANAVERAL, Fla. – Technicians and engineers perform safing procedures on the Project Morpheus prototype lander after it touched down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field. The lander successfully completed its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett

Benthic long-term Observatories based on Lander Technology

NASA Astrophysics Data System (ADS)

Linke, P.; Pfannkuche, O.; Sommer, S.; Gubsch, S.; Gust, G.

2003-04-01

Landers are autonomous carrier systems for a wide range of scientific applications. The GEOMAR Lander System is based on a tripod-shaped platform for various scientific payloads to monitor, measure and experiment at the deep sea floor. These landers can be deployed using hybrid fibre optical or coaxial cables with a special launching device or in the conventional free falling mode. The launcher enables accurate positioning on meter scale, soft deployment and rapid disconnection of lander and launcher by an electric release. The bi-directional video and data telemetry provides on line video transmission, power supply and surface control of various relay functions. Within the collaborative project LOTUS novel long-term observatories have been developed and integrated into the GEOMAR Lander System. An overview of the recent developments is presented. Two new observatories are presented in detail to study the temporal variability of physico-chemical and biogeochemical mechanisms, flux- and turnover rates related to the decomposition and formation of near surface gas hydrates embedded in their original sedimentary matrix. With the Biogeochemical Observatory, BIGO, the temporal variability of the biologically facilitated methane turnover in the sediment and fluxes across the sediment water interface is studied in two mesocosms. Inside the mesocosms the oxygen content can be maintained by a chemostat. The in situ flow regime is measured outside the mesocosms and is reproduced within the chamber with an intelligent stirring system. This approach represents a major step in the development of benthic chambers from stationary to dynamic systems. The Fluid-Flux Observatory (FLUFO) measures the different types of fluid fluxes at the benthic boundary layer of sediments overlying near surface gas hydrates and monitors relevant environmental parameters as temperature, pressure and near bottom currents. FLUFO consists of two chamber units. Both units separate the gas phase from the aqueous phase and measure their individual contribution to the total fluid flux. Whereas the first (reference) chamber measures the aqueous flux without obtaining information about their direction, the second (FLUFO) chamber measures the aqueous flux including the direction discriminating between outward flow, stagnation and inward flow.

At Home in the Crater

NASA Technical Reports Server (NTRS)

2004-01-01

The wheel tracks seen above and to the left of the lander trace the path the Mars Exploration Rover Opportunity has traveled since landing in a small crater at Meridiani Planum, Mars. After this picture was taken, the rover excavated a trench near the soil seen at the lower left corner of the image. This image mosaic was taken by the rover's navigation camera.

Preface: The Chang'e-3 lander and rover mission to the Moon

NASA Astrophysics Data System (ADS)

Ip, Wing-Huen; Yan, Jun; Li, Chun-Lai; Ouyang, Zi-Yuan

2014-12-01

The Chang'e-3 (CE-3) lander and rover mission to the Moon was an intermediate step in China's lunar exploration program, which will be followed by a sample return mission. The lander was equipped with a number of remote-sensing instruments including a pair of cameras (Landing Camera and Terrain Camera) for recording the landing process and surveying terrain, an extreme ultraviolet camera for monitoring activities in the Earth's plasmasphere, and a first-ever Moon-based ultraviolet telescope for astronomical observations. The Yutu rover successfully carried out close-up observations with the Panoramic Camera, mineralogical investigations with the VIS-NIR Imaging Spectrometer, study of elemental abundances with the Active Particle-induced X-ray Spectrometer, and pioneering measurements of the lunar subsurface with Lunar Penetrating Radar. This special issue provides a collection of key information on the instrumental designs, calibration methods and data processing procedures used by these experiments with a perspective of facilitating further analyses of scientific data from CE-3 in preparation for future missions.

Moon based global field airglow: For Artemis or any common Lunar Lander

NASA Astrophysics Data System (ADS)

Kozlowski, R. W. H.; Sprague, A. L.; Sandel, B. R.; Hunten, D. M.; Broadfoot, A. L.

1994-06-01

An inexpensive, small mass, airglow experiment consisting of a suite of airglow detectors is planned for one or more lunar landers. Solid state detectors measuring light through narrow band filters or concave gratings can integrate emissions from lunar atmospheric constituents and store the information for relay to earth when convenient. The proposed instrument is a simplified version of the Shuttle-borne Arizona Imager-Spectrograph. These zenith and near horizon viewing detectors may allow us to monitor fluctuations in atomic species of oxygen, calcium, sodium, potassium, argon, and neon and OH, if present. This choice of observations would monitor outgassing from the interior (Ar), meteoritic dust flux (Na, K) solar wind sputtering (O, Ca), and outgassing from the surface (implanted Ne, Na, K). A global network could be inexpensively deployed aboard landers carrying a variety of other selenographic instrumentation. Powered by solar cells such a field network will return data applicable to a wide variety of interplanetary medium and solar-lunar interaction problems.

A Landing Site for ExoMars 2016

NASA Image and Video Library

2015-11-27

This image from NASA Mars Reconnaissance Orbiter spacecraft is of a landing site that the flattest, safest place on Mars: part of Meridiani Planum, close to where the Opportunity rover landed. In March 2016, the European Space Agency in partnership with Roscosmos will launch the ExoMars Trace Gas Orbiter. This orbiter will also carry an Entry, Descent, and Landing Demonstration Module (EDM): a lander designed primarily to demonstrate the capability to land on Mars. The EDM will survive for only a few days, running on battery power, but will make a few environmental measurements. The landing site is the flattest, safest place on Mars: part of Meridiani Planum, close to where the Opportunity rover landed. This image shows what this terrain is like: very flat and featureless. A full-resolution sample reveals the major surface features: small craters and wind ripples. HiRISE has been imaging the landing site region in advance of the landing, and will re-image the site after landing to identify the major pieces of hardware: heat shield, backshell with parachute, and the lander itself. The distribution of these pieces will provide information about the entry, descent and landing. http://photojournal.jpl.nasa.gov/catalog/PIA20159

Looking out Across the Martian Polar Plains

NASA Image and Video Library

2008-05-26

This image shows the vast plains of the northern polar region of Mars, as seen by NASA Phoenix Mars Lander shortly after touching down on the Red Planet. The flat landscape is strewn with tiny pebbles and shows polygonal cracking.

Martian Surface as Seen by Phoenix

NASA Image and Video Library

2008-07-28

This anaglyph was acquired by NASA Phoenix Lander; in the bottom left is a trench dug by Phoenix Robotic Arm. In the bottom right is one of Phoenix two solar panels. You will need 3-D glasses to view this image.

Engineers Test Roll-Off at JPL

NASA Technical Reports Server (NTRS)

2004-01-01

This image taken at JPL shows engineers testing the route by which the Mars Exploration Rover Opportunity will roll off its lander. Opportunity touched down at Meridiani Planum, Mars on Jan. 24, 9:05 p.m. PST, 2004, Earth-received time.

Mark Left by First Dig at Phoenix Site

NASA Technical Reports Server (NTRS)

2008-01-01

The hole in the ground produced by the first Robotic Arm dig at the landing site of NASA's Phoenix Mars Mission appears to the right of the three largest rocks near the center of this image.

The hole is the width of the scoop on the end of the arm, about 9 centimeters (3.5 inches). It resulted from a practice dig during the mission's seventh Martian day, or sol 7 (June 1, 2008). The lander's Surface Stereo Imager took this image later that sol. The image is in approximately true color, produced by combining exposures taken through different filters. The green band at upper left is a portion where imaging data was incomplete in for one of the filters.

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

Phoenix 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 Institute of Technology in Pasadena.

Types of rocks exposed at the Viking landing sites

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

Guinness, E.; Arvidson, R.; Dale-Bannister, M.

1985-01-01

Spectral estimates derived from Viking Lander multispectral images have been used to investigate the types of rocks exposed at both landing sites, and to infer whether the rocks are primary igneous rocks or weathering products. These analyses should aid interpretations of spectra to be returned from the Visual and Infrared Mapping Spectrometer on the upcoming Mars Observer Mission. A series of gray surfaces on the Landers were used to check the accuracy of the camera preflight calibrations. Results indicate that the pre-flight calibrations for the three color channels are probably correct for all cameras but camera 2 on Lander 1.more » The calibration for the infrared channels appears to have changed, although the cause is not known. For this paper, only the color channels were used to derive data for rocks. Rocks at both sites exhibit a variety of reflectance values. For example, reflectance estimates for two rocks in the blue (0.4-0.5 microns), green (0.5-0.6 microns), and red (0.6-0.75 microns) channels are 0.16, 0.23, and 0.33 and 0.12, 0.19, 0.37 at a phase angle of 20 degrees. These values have been compared with laboratory reflectance spectra of analog materials and telescopic spectra of Mars, both convolved to the Lander bandpasses. Lander values for some rocks are similar to earth based observations of martian dark regions and with certain mafic igneous rocks thinly coated with amorphous ferric-oxide rich weathering products. These results are consistent with previous interpretations.« less

SMART-1/CLEMENTINE Study of Humorum and Procellarum Basins

NASA Astrophysics Data System (ADS)

Carey, William; Foing, Bernard H.; Koschny, Detlef; Pio Rossi, Angelo; Josset, Jean-Luc

A study undertaken by ESA to define a European Reference Architecture for Space Exploration is due to be completed in September 2008. The development of this architecture over the past twelve months has identified a number of key capabilities, among them a lunar lander system, which could form the basis for Europe's contribution to the future exploration of space in collaboration with International Partners. The focus of this paper will be on the lunar lander system, and will present the results of an analysis of possible payloads that could be accommodated by the lander. As the industrial study is at the Phase 0 or Pre-Phase A level, the design of such a lander system is at a very early stage in its development, but an estimation of the payload capacity allows a general assessment of the types of possible payloads that could be carried, currently this capacity is estimated at 1.1 tonnes of gross payload mass to the lunar surface (assuming an Ariane 5 ECA launch). An important characteristic of the lunar lander is that it provides a versatile and flexible system for utilisation in a broad range of lunar missions which include: - Independent lunar exploration missions for science, technology demonstration and research. - Delivery of logistics and cargo to support human surface sortie missions. - Delivery of logistics to a lunar base/outpost. - Deployment of individual infrastructure elements in support of a lunar base/outpost. Based on the above different types of missions, a number of configurations of "reference payload" sets are in the process of being defined that cover specific exploration objectives related primarily to capability demonstration, exploration enabling research and enabled science. Aspects covered include: ISRU, robotics, mobility, human preparation, life science and geology. This paper will present the current status of definition of the Reference Payload sets.

Crew systems and architectural considerations for first lunar surface return missions

NASA Astrophysics Data System (ADS)

Winisdoerffer, F.; Ximenes, S.

1992-08-01

The design requirements for the habitability of the pressurized volumes of a typical first manned lander are presented. Attention is given to providing dual habitation/exploration services (EVA/IVA), supporting the separation of the surface/flight functions, allowing growth potential based on site characteristics, and in situ resources utilization. Lunar lander conceptual diagrams are provided for the basic system architecture, automatic cargo delivery, the piloted crew module, and the pressurized volumes.

Mars Lander/Rover vehicle development: An advanced space design project for USRA and NASA/OAST

NASA Technical Reports Server (NTRS)

1987-01-01

The results of the studies on one particular part of the Mars Lander/Rover (MLR) system are contained: the Balloon Rover. This component vehicle was selected for further research and design because of the lack of technical literature on this subject, as compared to surface rover technology. Landing site selection; balloon system development and deployment; optics and communications; and the payload power supply are described.

Application of the HeartLander Crawling Robot for Injection of a Thermally Sensitive Anti-Remodeling Agent for Myocardial Infarction Therapy

PubMed Central

Chapman, Michael P.; López González, Jose L.; Goyette, Brina E.; Fujimoto, Kazuro L.; Ma, Zuwei; Wagner, William R.; Zenati, Marco A.; Riviere, Cameron N.

2011-01-01

The injection of a mechanical bulking agent into the left ventricular (LV) wall of the heart has shown promise as a therapy for maladaptive remodeling of the myocardium after myocardial infarct (MI). The HeartLander robotic crawler presented itself as an ideal vehicle for minimally-invasive, highly accurate epicardial injection of such an agent. Use of the optimal bulking agent, a thermosetting hydrogel developed by our group, presents a number of engineering obstacles, including cooling of the miniaturized injection system while the robot is navigating in the warm environment of a living patient. We present herein a demonstration of an integrated miniature cooling and injection system in the HeartLander crawling robot, that is fully biocompatible and capable of multiple injections of a thermosetting hydrogel into dense animal tissue while the entire system is immersed in a 37°C water bath. PMID:21096276

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.

Best Practices for In-Situ Sediment-Water Incubations with Benthic Landers

NASA Astrophysics Data System (ADS)

Tengberg, Anders; Kononets, Mikhail; Hall, Per; Nilsson, Madeleine; Ekeroth, Nils

2017-04-01

Biological, chemical, physical and geological processes that take place at the seafloor are crucial in influencing and regulating many aquatic environments. One method to estimate exchange rates, fluxes, between the sediment and the overlying water is in-situ sediment-water incubations using autonomous chamber landers. As for all field sampling and measurements best practices methods are needed to obtain high quality data. With experiences form many years usage of the Gothenburg autonomous bottom lander systems this presentation will describe some of the experimental work that has been done with focus on quality control and data evaluation methods.

JPL-19680109-SURVEYf-0001-AVC2002083 Surveyor 7 Lands on Moon

NASA Image and Video Library

1968-01-09

Surveyor 7 was the last of the original series of Surveyor Moon landers. Includes images of scoop digging in the lunar soil. It was the only spacecraft of the series to land in the lunar highland region.

Phoenix La Mancha Trench in 3-D

NASA Image and Video Library

2008-10-09

This anaglyph was taken by NASA Phoenix Mars Lander Surface Stereo Imager Oct. 7, 2008. The anaglyph highlights the depth of the trench, informally named La Mancha, and reveals the ice layer beneath the soil surface. 3D glasses are necessary.

Mars sample return mission architectures utilizing low thrust propulsion

NASA Astrophysics Data System (ADS)

Derz, Uwe; Seboldt, Wolfgang

2012-08-01

The Mars sample return mission is a flagship mission within ESA's Aurora program and envisioned to take place in the timeframe of 2020-2025. Previous studies developed a mission architecture consisting of two elements, an orbiter and a lander, each utilizing chemical propulsion and a heavy launcher like Ariane 5 ECA. The lander transports an ascent vehicle to the surface of Mars. The orbiter performs a separate impulsive transfer to Mars, conducts a rendezvous in Mars orbit with the sample container, delivered by the ascent vehicle, and returns the samples back to Earth in a small Earth entry capsule. Because the launch of the heavy orbiter by Ariane 5 ECA makes an Earth swing by mandatory for the trans-Mars injection, its total mission time amounts to about 1460 days. The present study takes a fresh look at the subject and conducts a more general mission and system analysis of the space transportation elements including electric propulsion for the transfer. Therefore, detailed spacecraft models for orbiters, landers and ascent vehicles are developed. Based on that, trajectory calculations and optimizations of interplanetary transfers, Mars entries, descents and landings as well as Mars ascents are carried out. The results of the system analysis identified electric propulsion for the orbiter as most beneficial in terms of launch mass, leading to a reduction of launch vehicle requirements and enabling a launch by a Soyuz-Fregat into GTO. Such a sample return mission could be conducted within 1150-1250 days. Concerning the lander, a separate launch in combination with electric propulsion leads to a significant reduction of launch vehicle requirements, but also requires a large number of engines and correspondingly a large power system. Therefore, a lander performing a separate chemical transfer could possibly be more advantageous. Alternatively, a second possible mission architecture has been developed, requiring only one heavy launch vehicle (e.g., Proton). In that case the lander is transported piggyback by the electrically propelled orbiter.

Atmospheric Mining in the Outer Solar System: Outer Planet Orbital Transfer and Lander Analyses

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2016-01-01

Atmospheric mining in the outer solar system has been investigated as a means of fuel production for high energy propulsion and power. Fusion fuels such as Helium 3 (3He) and deuterium can be wrested from the atmospheres of Uranus and Neptune and either returned to Earth or used in-situ for energy production. Helium 3 and deuterium were the primary gases of interest with hydrogen being the primary propellant for nuclear thermal solid core and gas core rocket-based atmospheric flight. A series of analyses were undertaken to investigate resource capturing aspects of atmospheric mining in the outer solar system. This included the gas capturing rate, storage options, and different methods of direct use of the captured gases. While capturing 3He, large amounts of hydrogen and 4He are produced. Analyses of orbital transfer vehicles (OTVs), landers, and the issues with in-situ resource utilization (ISRU) mining factories are included. Preliminary observations are presented on near-optimal selections of moon base orbital locations, OTV power levels, and OTV and lander rendezvous points. For analyses of round trip OTV flights from Uranus to Miranda or Titania, a 10-Megawatt electric (MWe) OTV power level and a 200-metric ton (MT) lander payload were selected based on a relative short OTV trip time and minimization of the number of lander flights. A similar optimum power level is suggested for OTVs flying from low orbit around Neptune to Thalassa or Triton. Several moon base sites at Uranus and Neptune and the OTV requirements to support them are also addressed.

Atmospheric Mining in the Outer Solar System: Outer Planet Orbital Transfer and Lander Analyses

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan

2016-01-01

Atmospheric mining in the outer solar system has been investigated as a means of fuel production for high energy propulsion and power. Fusion fuels such as Helium 3 (3He) and deuterium can be wrested from the atmospheres of Uranus and Neptune and either returned to Earth or used in-situ for energy production. Helium 3 and deuterium were the primary gases of interest with hydrogen being the primary propellant for nuclear thermal solid core and gas core rocket-based atmospheric flight. A series of analyses were undertaken to investigate resource capturing aspects of atmospheric mining in the outer solar system. This included the gas capturing rate, storage options, and different methods of direct use of the captured gases. While capturing 3He, large amounts of hydrogen and 4He are produced. Analyses of orbital transfer vehicles (OTVs), landers, and the issues with in-situ resource utilization (ISRU) mining factories are included. Preliminary observations are presented on near-optimal selections of moon base orbital locations, OTV power levels, and OTV and lander rendezvous points. For analyses of round trip OTV flights from Uranus to Miranda or Titania, a 10- Megawatt electric (MWe) OTV power level and a 200 metricton (MT) lander payload were selected based on a relative short OTV trip time and minimization of the number of lander flights. A similar optimum power level is suggested for OTVs flying from low orbit around Neptune to Thalassa or Triton. Several moon base sites at Uranus and Neptune and the OTV requirements to support them are also addressed.

Supporting lander and rover operation: a novel super-resolution restoration technique

NASA Astrophysics Data System (ADS)

Tao, Yu; Muller, Jan-Peter

2015-04-01

Higher resolution imaging data is always desirable to critical rover engineering operations, such as landing site selection, path planning, and optical localisation. For current Mars missions, 25cm HiRISE images have been widely used by the MER & MSL engineering team for rover path planning and location registration/adjustment. However, 25cm is not high enough resolution to be able to view individual rocks (≤2m in size) or visualise the types of sedimentary features that rover onboard cameras might observe. Nevertheless, due to various physical constraints (e.g. telescope size and mass) from the imaging instruments themselves, one needs to be able to tradeoff spatial resolution and bandwidth. This means that future imaging systems are likely to be limited to resolve features larger than 25cm. We have developed a novel super-resolution algorithm/pipeline to be able to restore higher resolution image from the non-redundant sub-pixel information contained in multiple lower resolution raw images [Tao & Muller 2015]. We will demonstrate with experiments performed using 5-10 overlapped 25cm HiRISE images for MER-A, MER-B & MSL to resolve 5-10cm super resolution images that can be directly compared to rover imagery at a range of 5 metres from the rover cameras but in our case can be used to visualise features many kilometres away from the actual rover traverse. We will demonstrate how these super-resolution images together with image understanding software can be used to quantify rock size-frequency distributions as well as measure sedimentary rock layers for several critical sites for comparison with rover orthorectified image mosaic to demonstrate optimality of using our super-resolution resolved image to better support future lander and rover operation in future. We present the potential of super-resolution for virtual exploration to the ˜400 HiRISE areas which have been viewed 5 or more times and the potential application of this technique to all of the ESA ExoMars Trace Gas orbiter CaSSiS stereo, multi-angle and colour camera images from 2017 onwards. Acknowledgements: The research leading to these results has received funding from the European Community's Seventh Framework Programme (FP7/2007-2013) under grant agreement No.312377 PRoViDE.

Remote microscopy and volumetric imaging on the surface of icy satellites

NASA Astrophysics Data System (ADS)

Soto, Alejandro; Nowicki, Keith; Howett, Carly; Feldkhun, Daniel; Retherford, Kurt D.

2017-10-01

With NASA PIDDP support we have applied recent advancements in Fourier-domain microscopy to develop an instrument capable of microscopic imaging from meter-scale distances for use on a planetary lander on the surface of an icy satellite or other planetary bodies. Without moving parts, our instrument projects dynamic patterns of laser light onto a distant target using a lightweight large-aperture reflector, which then collects the light scattered or fluoresced by the target on a fast photon-bucket detector. Using Fourier Transform based techniques, we reconstruct an image from the detected light. The remote microscope has been demonstrated to produce 2D images with better than 15 micron lateral resolution for targets at a distance of 5 meters and is capable of linearly proportionally higher resolution at shorter distances. The remote microscope is also capable of providing three-dimensional (3D) microscopic imaging capabilities, allowing future surface scientists to explore the morphology of microscopic features in surface ices, for example. The instrument enables microscopic in-situ imaging during day or night without the use of a robotic arm, greatly facilitating the surface operations for a lander or rover while expanding the area of investigation near a landing site for improved science targeting. We are developing this remote microscope for in-situ planetary exploration as a collaboration between the Southwest Research Institute, LambdaMetrics, and the University of Colorado.

A conceptual design and operational characteristics for a Mars rover for a 1979 or 1981 Viking science mission

NASA Technical Reports Server (NTRS)

Darnell, W. L.; Wessel, V. W.

1974-01-01

The feasibility of a small Mars rover for use on a 1979 or 1981 Viking mission was studied and a preliminary design concept was developed. Three variations of the concept were developed to provide comparisons in mobility and science capability of the rover. Final masses of the three rover designs were approximately 35 kg, 40 kg, and 69 kg. The smallest rover is umbilically connected to the lander for power and communications purposes whereas the larger two rovers have secondary battery power and a 2-way very high frequency communication link to the lander. The capability for carrying Viking rovers (including development system) to the surface of Mars was considered first. It was found to be feasible to carry rovers of over 100 kg. Virtually all rover systems were then studied briefly to determine a feasible system concept and a practical interface with the comparable system of a 1979 or 1981 lander vehicle.

Flight Testing of Guidance, Navigation and Control Systems on the Mighty Eagle Robotic Lander Testbed

NASA Technical Reports Server (NTRS)

Hannan, Mike; Rickman, Doug; Chavers, Greg; Adam, Jason; Becker, Chris; Eliser, Joshua; Gunter, Dan; Kennedy, Logan; O'Leary, Patrick

2015-01-01

During 2011 a series of progressively more challenging flight tests of the Mighty Eagle autonomous terrestrial lander testbed were conducted primarily to validate the GNC system for a proposed lunar lander. With the successful completion of this GNC validation objective the opportunity existed to utilize the Mighty Eagle as a flying testbed for a variety of technologies. In 2012 an Autonomous Rendezvous and Capture (AR&C) algorithm was implemented in flight software and demonstrated in a series of flight tests. In 2012 a hazard avoidance system was developed and flight tested on the Mighty Eagle. Additionally, GNC algorithms from Moon Express and a MEMs IMU were tested in 2012. All of the testing described herein was above and beyond the original charter for the Mighty Eagle. In addition to being an excellent testbed for a wide variety of systems the Mighty Eagle also provided a great learning opportunity for many engineers and technicians to work a flight program.

KSC-2012-4122

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4118

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4119

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - Technicians secure connections for a crane which will be used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4117

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4115

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4116

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being set up at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4121

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - A crane is being used to set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4114

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, arrives at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4107

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being moved out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4010

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - A truck transporting NASA's Morpheus lander, a vertical test bed vehicle, arrives at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for unloading. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4109

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out from its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4106

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being moved out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4110

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out from its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4104

NASA Image and Video Library

2012-07-30

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4009

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - A truck transporting NASA's Morpheus lander, a vertical test bed vehicle, heads towards the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for unloading. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4026

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - Support equipment for NASA's Morpheus lander, a vertical test bed vehicle, is unloaded at a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4108

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported out of its checkout building for a short trip to a launch position at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4031

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4113

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4032

NASA Image and Video Library

2012-07-27

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, has been moved into a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/ Charisse Nahser

KSC-2012-4112

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4105

NASA Image and Video Library

2012-07-30

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4111

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being transported along the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida for a short trip to a launch position along the runway. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4095

NASA Image and Video Library

2012-07-30

CAPE CANAVERAL, Fla. - NASA's Morpheus lander, a vertical test bed vehicle, is being checked out in a building at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

KSC-2012-4120

NASA Image and Video Library

2012-07-31

CAPE CANAVERAL, Fla. - Technicians set up NASA's Morpheus lander, a vertical test bed vehicle, at its launch position along the runway at the Shuttle Landing Facility, or SLF, at the Kennedy Space Center in Florida. Morpheus is designed to demonstrate new green propellant propulsion systems and autonomous landing and an Autonomous Landing and Hazard Avoidance Technology, or ALHAT, system. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Dimitri Gerondidakis

Martian Arctic Landscape Panorama Video

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on image for animation

Typical view if you were standing on Mars and slowly turned around for a look. Starting at the north, SSI sees its shadow and turns its head viewing solar arrays, the lander deck and landscape. Note very few rocks on the hummocky terrain and network of troughs, typical of polar surfaces here on Earth.

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.

'Rosy Red' Soil in Phoenix's Scoop

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows fine-grained material inside the Robotic Arm scoop as seen by the Robotic Arm Camera (RAC) aboard NASA's Phoenix Mars Lander on June 25, 2008, the 30th Martian day, or sol, of the mission.

The image shows fine, fluffy, red soil particles collected in a sample called 'Rosy Red.' The sample was dug from the trench named 'Snow White' in the area called 'Wonderland.' Some of the Rosy Red sample was delivered to Phoenix's Optical Microscope and Wet Chemistry Laboratory for analysis.

The RAC provides its own illumination, so the color seen in RAC images is color as seen on Earth, not color as it would appear on Mars.

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.

Images from Phoenix's MECA Instruments

NASA Technical Reports Server (NTRS)

2008-01-01

The image on the upper left is from NASA's Phoenix Mars Lander's Optical Microscope after a sample informally called 'Sorceress' was delivered to its silicon substrate on the 38th Martian day, or sol, of the mission (July 2, 2008).

A 3D representation of the same sample is on the right, as seen by Phoenix's Atomic Force Microscope. This is 100 times greater magnification than the view from the Optical Microscope, and the most highly magnified image ever seen from another world.

The Optical Microscope and the Atomic Force Microscope are part of Phoenix's Microscopy, Electrochemistry and Conductivity Analyzer instrument.

The Atomic Force Microscope was developed by a Swiss-led consortium in collaboration with Imperial College London.

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.

Martian Dust Collected by Phoenix's Arm

NASA Technical Reports Server (NTRS)

2008-01-01

This image from NASA's Phoenix Lander's Optical Microscope shows particles of Martian dust lying on the microscope's silicon substrate. The Robotic Arm sprinkled a sample of the soil from the Snow White trench onto the microscope on July 2, 2008, the 38th Martian day, or sol, of the mission after landing.

Subsequently, the Atomic Force Microscope, or AFM, zoomed in one of the fine particles, creating the first-ever image of a particle of Mars' ubiquitous fine dust, the most highly magnified image ever seen from another world.

The Atomic Force Microscope was developed by a Swiss-led consortium in collaboration with Imperial College London. The AFM is part of Phoenix's Microscopy, Electrochemistry and Conductivity Analyzer instrument.

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.

'Snow White' Trench

NASA Technical Reports Server (NTRS)

2008-01-01

This image was acquired by NASA's Phoenix Mars Lander's Surface Stereo Imager on Sol 43, the 43rd Martian day after landing (July 8, 2008). This image shows the trench informally called 'Snow White.'

Two samples were delivered to the Wet Chemistry Laboratory, which is part of Phoenix's Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The first sample was taken from the surface area just left of the trench and informally named 'Rosy Red.' It was delivered to the Wet Chemistry Laboratory on Sol 30 (June 25, 2008). The second sample, informally named 'Sorceress,' was taken from the center of the 'Snow White' trench and delivered to the Wet Chemistry Laboratory on Sol 41 (July 6, 2008).

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

Water Hammer Test

NASA Technical Reports Server (NTRS)

2008-01-01

[figure removed for brevity, see original site] Click on the image for the animation

This video shows the propulsion system on an engineering model of NASA's Phoenix Mars Lander being successfully tested. Instead of fuel, water is run through the propulsion system to make sure that the spacecraft holds up to vibrations caused by pressure oscillations.

The test was performed very early in the development of the mission, in 2005, at Lockheed Martin Space Systems, Denver. Early testing was possible because Phoenix's main structure was already in place from the 2001 Mars Surveyor program.

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.

Aseismic Slip Events along the Southern San Andreas Fault System Captured by Radar Interferometry

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

Vincent, P

2001-10-01

A seismic slip is observed along several faults in the Salton Sea and southernmost Landers rupture zone regions using interferometric synthetic aperture radar (InSAR) data spanning different time periods between 1992 and 1997. In the southernmost Landers rupture zone, projecting south from the Pinto Mountain Fault, sharp discontinuities in the interferometric phase are observed along the sub-parallel Burnt Mountain and Eureka Peak Faults beginning three months after the Landers earthquake and is interpreted to be post-Landers after-slip. Abrupt phase offsets are also seen along the two southernmost contiguous 11 km Durmid Hill and North Shore segments of the San Andreasmore » Fault with an abrupt termination of slip near the northern end of the North Shore Segment. A sharp phase offset is seen across 20 km of the 30 km-long Superstition Hills Fault before phase decorrelation in the Imperial Valley along the southern 10 km of the fault prevents coherent imaging by InSAR. A time series of deformation interferograms suggest most of this slip occurred between 1993 and 1995 and none of it occurred between 1992 and 1993. A phase offset is also seen along a 5 km central segment of the Coyote Creek fault that forms a wedge with an adjoining northeast-southwest trending conjugate fault. Most of the slip observed on the southern San Andreas and Superstition Hills Faults occurred between 1993 and 1995--no slip is observed in the 92-93 interferograms. These slip events, especially the Burnt Mountain and Eureka Peak events, are inferred to be related to stress redistribution from the June, 1992 M{sub w} = 7.3 Landers earthquake. Best-fit elastic models of the San Andreas and Superstition Hills slip events suggest source mechanisms with seismic moments over three orders of magnitude larger than a maximum possible summation of seismic moments from all seismicity along each fault segment during the entire 4.8-year time interval spanned by the InSAR data. Aseismic moment releases of this magnitude (equivalent to M{sub w} = 5.3 and 5.6 events on the Superstition Hills and San Andreas Faults respectively) are hitherto unknown and have not been captured previously by any geodetic technique.« less

Morpheus Campaign 2A Tether Test

NASA Image and Video Library

2014-03-27

CAPE CANAVERAL, Fla. – NASA's Project Morpheus prototype lander is positioned near a new launch site at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida for a tethered test. The test will be performed to verify the lander's recently installed autonomous landing and hazard avoidance technology, or ALHAT, sensors and integration system. The launch pad was moved to a different location at the landing facility to support the next phase of flight testing. Project Morpheus tests NASA’s ALHAT, and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Glenn Benson

KSC-2012-3956

NASA Image and Video Library

2012-07-19

CAPE CANAVERAL, Fla. – This aerial view shows a 50,000-square-foot hangar located on the Shuttle Landing Facility at the Kennedy Space Center, Fla., providing shelter and storage for NASA and non-NASA aircraft and maintenance operations. Adjacent to the hangar is an operations building housing personnel who support operations at the 15,000-foot long concrete runway. At the north end of the runway, a rock and crater-filled planetary scape has been built so engineers can test the Autonomous Landing and Hazard Avoidance Technology, or ALHAT system on the Project Morpheus lander. Testing will demonstrate ALHAT’s ability to provide required navigation data negotiating the Morpheus lander away from risks during descent. Checkout of the prototype lander has been ongoing at NASA’s Johnson Space Center in Houston in preparation for its first free flight. The SLF site will provide the lander with the kind of field necessary for realistic testing. Project Morpheus is one of 20 small projects comprising the Advanced Exploration Systems, or AES, program in NASA’s Human Exploration and Operations Mission Directorate. AES projects pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus/index.html Photo credit: NASA/Kim Shiflett

Testing Phoenix Mars Lander Parachute in Idaho

NASA Technical Reports Server (NTRS)

2008-01-01

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

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

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

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

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

During the first 25 seconds of the three-minute period when Phoenix descends on its parachute, the spacecraft will cast away its heat shield and extend its three legs. About 43 seconds before reaching the surface of Mars, the lander will shed the parachute by separating from the backshell. The lander will begin firing its descent thrusters half a second after the separation from the backshell and continue using them until touchdown.

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

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.

Erosional and depositional history of central Chryse Planitia

NASA Technical Reports Server (NTRS)

Crumpler, L. S.

1992-01-01

This map uses high resolution image data to assess the detailed depositional and erosional history of part of Chryse Planitia. This area is significant to the study of the global geology of Mars because it represents one of only two areas on the martian surface where planetary geologic mapping is assisted with 'ground truth.' In this case the ground truth was provided by Viking Lander 1. Additional questions addressed in this study are concerned with the following: the geologic context of the regional plains surface and the local surface of the Viking Lander 1 site; and the relative influence of volcanic, sedimentary, impact, aeolian, and tectonic processes at the regional and local scales.

Martian Terrain, Unfurled Rover Ramps & Deflated Airbags

NASA Image and Video Library

1997-07-05

The Imager for Mars Pathfinder (IMP) took this image of surrounding terrain in the mid-morning on Mars (2:30 PM Pacific Daylight Time) earlier today. Part of the small rover, Sojourner, is visible on the left side of the picture. The tan cylinder to the right of the rover is one of two rolled-up ramps by which the rover will descend to the ground. The white, billowy material in the center of the picture is part of the airbag system. Many rocks of different shapes and sizes are visible between the lander and the horizon. Two hills are visible on the horizon. The notch on the left side of the leftmost conical hill is an artifact of the processing of this picture. http://photojournal.jpl.nasa.gov/catalog/PIA00613

'Dodo' and 'Baby Bear' Trenches

NASA Technical Reports Server (NTRS)

2008-01-01

NASA's Phoenix Mars Lander's Surface Stereo Imager took this image on Sol 11 (June 5, 2008), the eleventh day after landing. It shows the trenches dug by Phoenix's Robotic Arm. The trench on the left is informally called 'Dodo' and was dug as a test. The trench on the right is informally called 'Baby Bear.' The sample dug from Baby Bear will be delivered to the Phoenix's Thermal and Evolved-Gas Analyzer, or TEGA. The Baby Bear trench is 9 centimeters (3.1 inches) wide and 4 centimeters (1.6 inches) deep.

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.

Snow White Trench Prepared for Sample Collection

NASA Technical Reports Server (NTRS)

2008-01-01

The informally named 'Snow White' trench is the source for the next sample to be acquired by NASA's Phoenix Mars Lander for analysis by the wet chemistry lab.

The Surface Stereo Imager on Phoenix took this shadow-enhanced image of the trench, on the eastern end of Phoenix's work area, on Sol 103, or the 103rd day of the mission, Sept. 8, 2008. The trench is about 23 centimeters (9 inches) wide.

The wet chemistry lab is part of Phoenix's Microscopy, Electrochemistry and Conductivity suite of instruments.

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.

Self-position estimation using terrain shadows for precise planetary landing

NASA Astrophysics Data System (ADS)

Kuga, Tomoki; Kojima, Hirohisa

2018-07-01

In recent years, the investigation of moons and planets has attracted increasing attention in several countries. Furthermore, recently developed landing systems are now expected to reach more scientifically interesting areas close to hazardous terrain, requiring precise landing capabilities within a 100 m range of the target point. To achieve this, terrain-relative navigation (capable of estimating the position of a lander relative to the target point on the ground surface is actively being studied as an effective method for achieving highly accurate landings. This paper proposes a self-position estimation method using shadows on the terrain based on edge extraction from image processing algorithms. The effectiveness of the proposed method is validated through numerical simulations using images generated from a digital elevation model of simulated terrains.

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.

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.

Moon-Mars simulation campaign in volcanic Eifel: Remote science support and sample analysis

NASA Astrophysics Data System (ADS)

Offringa, Marloes; Foing, Bernard H.; Kamps, Oscar

2016-07-01

Moon-Mars analogue missions using a mock-up lander that is part of the ESA/ILEWG ExoGeoLab project were conducted during Eifel field campaigns in 2009, 2015 and 2016 (Foing et al., 2010). In the last EuroMoonMars2016 campaign the lander was used to conduct reconnaissance experiments and in situ geological scientific analysis of samples, with a payload that mainly consisted of a telescope and a UV-VIS reflectance spectrometer. The aim of the campaign was to exhibit possibilities for the ExoGeoLab lander to perform remotely controlled experiments and test its applicability in the field by simulating the interaction with astronauts. The Eifel region in Germany where the experiments with the ExoGeoLab lander were conducted is a Moon-Mars analogue due to its geological setting and volcanic rock composition. The research conducted by analysis equipment on the lander could function in support of Moon-Mars sample return missions, by providing preliminary insight into characteristics of the analyzed samples. The set-up of the prototype lander was that of a telescope with camera and solar power equipment deployed on the top, the UV-VIS reflectance spectrometer together with computers and a sample webcam were situated in the middle compartment and to the side a sample analysis test bench was attached, attainable by astronauts from outside the lander. An alternative light source that illuminated the samples in case of insufficient daylight was placed on top of the lander and functioned on solar power. The telescope, teleoperated from a nearby stationed pressurized transport vehicle that functioned as a base control center, attained an overview of the sampling area and assisted the astronauts in their initial scouting pursuits. Locations of suitable sampling sites based on these obtained images were communicated to the astronauts, before being acquired during a simulated EVA. Sampled rocks and soils were remotely analyzed by the base control center, while the astronauts assisted by placing the samples onto the sample holder and adjusting test bench settings in order to obtain spectra. After analysis the collected samples were documented and stored by the astronauts, before returning to the base. Points of improvement for the EuroMoonMars2016 analog campaign are the remote control of the computers using an established network between the base and the lander. During following missions the computers should preferably be operated over a larger distance without interference. In the bottom compartment of the lander a rover is stored that in future campaigns could replace astronaut functions by collecting and returning samples, as well as performing adjustments to the analysis test bench by using a remotely controlled robotic arm. Acknowledgements: we thank Dominic Doyle for ESTEC optical lab support, Aidan Cowley (EAC) and Matthias Sperl (DLR) for support discussions, and collaborators from EuroMoonMars Eifel 2015-16 campaign team.

Pathfinder Lander Rover Recharge System, and MARCO POLO Controls and ACME Regolith Feed System Controls and Integration

NASA Technical Reports Server (NTRS)

Tran, Sarah Diem

2015-01-01

This project stems from the Exploration, Research, and Technology Directorate (UB) Projects Division, and one of their main initiatives is the "Journey to Mars". Landing on the surface of Mars which is millions of miles away is an incredibly large challenge. The terrain is covered in boulders, deep canyons, volcanic mountains, and spotted with sand dunes. The robotic lander is a kind of spacecraft with multiple purposes. One purpose is to be the protective shell for the Martian rover and absorb the impact from the landing forces; another purpose is to be a place where the rovers can come back to, actively communicate with, and recharge their batteries from. Rovers have been instrumental to the Journey to Mars initiative. They have been performing key research on the terrain of the red planet, trying to unlock the mysteries of the land for over a decade. The rovers that will need charging will not all have the same kind of internal battery either. RASSOR batteries may differ from the PbAC batteries inside Red Rover's chassis. NASA has invested heavily in the exploration of the surface of Mars. A driving force behind further exploration is the need for a more efficient operation of Martian rovers. One way is to reduce the weight as much as possible to reduce power consumption given the same mission parameters. In order to reduce the mass of the rovers, power generation, communication, and sample analysis systems currently onboard Martian rovers can be moved to a stationary lander deck. Positioning these systems from the rover to the Lander deck allows a taskforce of smaller, lighter rovers to perform the same tasks currently performed by or planned for larger rovers. A major task in transferring these systems to a stationary lander deck is ensuring that power can be transferred to the rovers.

Jovian Tour Design for Orbiter and Lander Missions to Europa

NASA Technical Reports Server (NTRS)

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

2013-01-01

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 flyby mission, an orbiter mission, and a lander mission. This paper presents the moon tours for the lander and orbiter concepts. The total delta v and radiation dose would be reduced by exploiting multi-body dynamics and avoiding phasing loops in the Ganymede-to- Europa transfer. Tour 11-O3, 12-L1 and 12-L4 are presented in details and their performaces compared to other tours from previous Europa mission studies.

Sharp Tips on the Atomic Force Microscope

NASA Technical Reports Server (NTRS)

2008-01-01

This image shows the eight sharp tips of the NASA's Phoenix Mars Lander's Atomic Force Microscope, or AFM. The AFM is part of Phoenix's Microscopy, Electrochemistry, and Conductivity Analyzer, or MECA.

The microscope maps the shape of particles in three dimensions by scanning them with one of the tips at the end of a beam. For the AFM image taken, the tip at the end of the upper right beam was used. The tip pointing up in the enlarged image is the size of a smoke particle at its base, or 2 microns. This image was taken with a scanning electron microscope before Phoenix launched on August 4, 2007.

The AFM was developed by a Swiss-led consortium in collaboration with Imperial College London.

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

Lunar lander and return propulsion system trade study

NASA Technical Reports Server (NTRS)

Hurlbert, Eric A.; Moreland, Robert; Sanders, Gerald B.; Robertson, Edward A.; Amidei, David; Mulholland, John

1993-01-01

This trade study was initiated at NASA/JSC in May 1992 to develop and evaluate main propulsion system alternatives to the reference First Lunar Outpost (FLO) lander and return-stage transportation system concept. Thirteen alternative configurations were developed to explore the impacts of various combinations of return stage propellants, using either pressure or pump-fed propulsion systems and various staging options. Besides two-stage vehicle concepts, the merits of single-stage and stage-and-a-half options were also assessed in combination with high-performance liquid oxygen and liquid hydrogen propellants. Configurations using an integrated modular cryogenic engine were developed to assess potential improvements in packaging efficiency, mass performance, and system reliability compared to non-modular cryogenic designs. The selection process to evaluate the various designs was the analytic hierarchy process. The trade study showed that a pressure-fed MMH/N2O4 return stage and RL10-based lander stage is the best option for a 1999 launch. While results of this study are tailored to FLO needs, the design date, criteria, and selection methodology are applicable to the design of other crewed lunar landing and return vehicles.

Benefits of Nuclear Electric Propulsion for Outer Planet Exploration

NASA Technical Reports Server (NTRS)

Kos, Larry; Johnson, Les; Jones, Jonathan; Trausch, Ann; Eberle, Bill; Woodcock, Gordon; Brady, Hugh J. (Technical Monitor)

2002-01-01

Nuclear electric propulsion (NEP) offers significant benefits to missions for outer planet exploration. Reaching outer planet destinations, especially beyond Jupiter, is a struggle against time and distance. For relatively near missions, such as a Europa lander, conventional chemical propulsion and NEP offer similar performance and capabilities. For challenging missions such as a Pluto orbiter, neither chemical nor solar electric propulsion are capable while NEP offers acceptable performance. Three missions are compared in this paper: Europa lander, Pluto orbiter, and Titan sample return, illustrating how performance of conventional and advanced propulsion systems vary with increasing difficulty. The paper presents parametric trajectory performance data for NEP. Preliminary mass/performance estimates are provided for a Europa lander and a Titan sample return system, to derive net payloads for NEP. The NEP system delivers payloads and ascent/descent spacecraft to orbit around the target body, and for sample return, delivers the sample carrier system from Titan orbit to an Earth transfer trajectory. A representative scientific payload 500 kg was assumed, typical for a robotic mission. The resulting NEP systems are 100-kWe class, with specific impulse from 6000 to 9000 seconds.

BILLIARDS: Baseline Instrumented Lithology Lander, Inspector and Asteroid Redirection Demonstration System

NASA Technical Reports Server (NTRS)

Marcus, Matthew; Sloane, Joshua; Ortiz, Oliver; Barbee, Brent

2015-01-01

BILLIARDS Baseline Instrumented Lithology Lander, Inspector, and Asteroid Redirection Demonstration System Proposed demonstration mission for Billiard-Ball concept Select asteroid pair with natural close approach to minimize cost and complexity Primary Objectives Rendezvous with a small (10m), near Earth (alpha) asteroid Maneuver the alpha asteroid to a collision with a 100m (beta) asteroid Produce a detectable deflection or disruption of the beta asteroid Secondary objectives Contribute knowledge of asteroid composition and characteristics Contribute knowledge of small-body formation Opportunity for international collaboration

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.

Measurement of Martian boundary layer winds by the displacement of jettisoned lander hardware

NASA Astrophysics Data System (ADS)

Paton, M. D.; Harri, A.-M.; Savijärvi, H.

2018-07-01

Martian boundary layer wind speed and direction measurements, from a variety of locations, seasons and times, are provided. For each lander sent to Mars over the last four decades a unique record of the winds blowing during their descent is preserved at each landing site. By comparing images acquired from orbiting spacecraft of the impact points of jettisoned hardware, such as heat shields and parachutes, to a trajectory model the winds can be measured. We start our investigations with the Viking lander 1 mission and end with Schiaparelli. In-between we extract wind measurements based on observations of the Beagle 2, Spirit, Opportunity, Phoenix and Curiosity landing sites. With one exception the wind at each site during the lander's descent were found to be < 8 m s-1. High speed winds were required to explain the displacement of jettisoned hardware at the Phoenix landing site. We found a tail wind ( > 20 m s-1), blowing from the north-west was required at a high altitude ( > 2 km) together with a gust close to the surface ( < 500 m altitude) originating from the north. All in all our investigations yielded a total of ten unique wind measurements in the PBL. One each from the Viking landers and one each from Beagle 2, Spirit, Opportunity and Schiaparelli. Two wind measurements, one above about 1 km altitude and one below, were possible from observations of the Curiosity and Phoenix landing site. Our findings are consistent with a turbulent PBL in the afternoon and calm PBL in the morning. When comparing our results to a GCM we found a good match in wind direction but not for wind speed. The information provided here makes available wind measurements previously unavailable to Mars atmosphere modellers and investigators.

Opportunity Captures 'Lion King' Panorama

NASA Technical Reports Server (NTRS)

2004-01-01

[figure removed for brevity, see original site] Click on the image for Opportunity Captures 'Lion King' Panorama (QTVR)

This approximate true-color panorama, dubbed 'Lion King,' shows 'Eagle Crater' and the surrounding plains of Meridiani Planum. It was obtained by the Mars Exploration Rover Opportunity's panoramic camera on sols 58 and 60 using infrared (750-nanometer), green (530-nanometer) and blue (430-nanometer) filters.

This is the largest panorama obtained yet by either rover. It was taken in eight segments using six filters per segment, for a total of 558 images and more than 75 megabytes of data. Additional lower elevation tiers were added to ensure that the entire crater was covered in the mosaic.

This panorama depicts a story of exploration including the rover's lander, a thorough examination of the outcrop, a study of the soils at the near-side of the lander, a successful exit from Eagle Crater and finally the rover's next desination, the large crater dubbed 'Endurance'.

ARES V CONCEPT IMAGE

NASA Technical Reports Server (NTRS)

2008-01-01

THIS CONCEPT IMAGE SHOWS THE ARES V CARGO LAUNCH VEHICLE. THE HEAVY LIFTING ARES V IS NASA'S PRIMARY VEHICLE FOR SAFE AND RELIABLE DELIVERY OF LARGE SCALE HARDWARE TO SPACE. THIS INCLUDES THE LUNAR LANDER, MATERIALS FOR ESTABLISHING A PERMANENT MOON BASE, AND THE VEHICLES AND HARDWARE NEEDED TO EXTEND A HUMAN PRESENCE BEYOND EARTH ORBIT. ARES V CAN CARRY APPROXIMATELY 290,000 POUNDS TO LOW EARTH ORBIT AND 144,000 POUNDS TO LUNAR ORBIT.

Morpheus Campaign 1C

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

Morpheus Campaign 1C

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

KSC-2014-1606

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

KSC-2014-1607

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high and moves forward after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

KSC-2014-1609

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

KSC-2014-1613

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

KSC-2014-1610

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander begins to ascend on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

Morpheus Campaign 1C

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

KSC-2014-1604

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

KSC-2014-1612

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander soars high after launching on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

KSC-2014-1611

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander ascends on its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

KSC-2014-1603

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – Engineers and technicians prepare the Project Morpheus prototype lander for its sixth free flight test from a launch pad at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the automated landing and hazard avoidance technology, or ALHAT, hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Kim Shiflett

Morpheus Campaign 1A Liftoff

NASA Image and Video Library

2014-01-21

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touches down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field after launching on its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett

KSC-2014-1614

NASA Image and Video Library

2014-03-05

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touches down in the automated landing and hazard avoidance technology, or ALHAT, hazard field after completing its sixth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 82-second test began at 11:32 a.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending to 465 feet. The lander flew forward, covering 633 feet while performing a 55-foot divert to emulate a hazard avoidance maneuver before descending and landing on a dedicated pad inside the hazard field. Morpheus landed 10 inches west of its intended target. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov/. Photo credit: NASA/Frankie Martin

Morpheus Campaign 1A Liftoff

NASA Image and Video Library

2014-01-21

CAPE CANAVERAL, Fla. – The Project Morpheus prototype lander touched down in the autonomous landing and hazard avoidance technology, or ALHAT, hazard field after launching on its fourth free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. The 64-second test began at 1:15 p.m. EST with the Morpheus lander launching from the ground over a flame trench and ascending about 305 feet, significantly increasing the ascent velocity from the last test. The lander flew forward, covering about 358 feet in 25 seconds before descending and landing within 15 inches of its target on a dedicated pad inside the ALHAT hazard field. Project Morpheus tests NASA’s ALHAT and an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility provides the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://www.nasa.gov/centers/johnson/exploration/morpheus. Photo credit: NASA/Kim Shiflett

Federalism and Lander Autonomy: The Higher Education Policy Network in the Federal Republic of Germany. Studies in Higher Education Dissertation Series.

ERIC Educational Resources Information Center

Onestini, Cesare

This study traces the development of the German higher education system, examining the development of higher education policies from the postwar years to the postunification period. It focuses on federalism and the relative positions of"Lander" (German states) and the government of the Federal Republic (FRG) as revealed in higher…

Valuation of Real Options as Competitive Prototyping in System Development

DTIC Science & Technology

2014-07-01

Brealey & Meyers, 2000; Dixit & Pindyck, 1994; Kulatilaka, 1995; Lander, 1997; Lander & Pinches, 1998; McDonald, 2006; Quigg, 1993; Teisberg, 1995...Brennan & Trigeorgis, 2000; Dixit & Pindyck, 1994; Kemna, 1993; Miller & Lessard, 2000; Trigeorgis, 1995). Examples include valuation of options to... Dixit , A. K., & Pindyck, R. S. (1994). Investment under uncertainty. NJ: Princeton University Press. Ford, D. N., & Bhargav, S. (2006, Spring). Project

KSC-2013-4316

NASA Image and Video Library

2013-12-10

CAPE CANAVERAL, Fla. – Preparations are underway to prepare the Project Morpheus prototype lander for its first free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett

KSC-2013-4370

NASA Image and Video Library

2013-12-17

CAPE CANAVERAL, Fla. -- A technician prepares the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis

KSC-2013-4367

NASA Image and Video Library

2013-12-17

CAPE CANAVERAL, Fla. -- Preparations are underway to prepare the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis

KSC-2013-4369

NASA Image and Video Library

2013-12-17

CAPE CANAVERAL, Fla. -- Engineers and technicians prepare the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis

KSC-2013-4318

NASA Image and Video Library

2013-12-10

CAPE CANAVERAL, Fla. – The first free flight of the Project Morpheus prototype lander begins as the lander’s engine fires at the north of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett

KSC-2013-4315

NASA Image and Video Library

2013-12-10

CAPE CANAVERAL, Fla. – Preparations are underway to prepare the Project Morpheus prototype lander for its first free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to asteroids and other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Kim Shiflett

KSC-2013-4368

NASA Image and Video Library

2013-12-17

CAPE CANAVERAL, Fla. -- A technician prepares the Project Morpheus prototype lander for a second free flight test at the north end of the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida. Testing of the prototype lander was performed at NASA’s Johnson Space Center in Houston in preparation for tethered and free flight testing at Kennedy. Project Morpheus integrates NASA’s automated landing and hazard avoidance technology, or ALHAT, with an engine that runs on liquid oxygen and methane, or green propellants, into a fully-operational lander that could deliver cargo to other planetary surfaces. The landing facility will provide the lander with the kind of field necessary for realistic testing, complete with rocks, craters and hazards to avoid. Morpheus’ ALHAT payload allows it to navigate to clear landing sites amidst rocks, craters and other hazards during its descent. Project Morpheus is being managed under the Advanced Exploration Systems, or AES, Division in NASA’s Human Exploration and Operations Mission Directorate. The efforts in AES pioneer new approaches for rapidly developing prototype systems, demonstrating key capabilities and validating operational concepts for future human missions beyond Earth orbit. For more information on Project Morpheus, visit http://morpheuslander.jsc.nasa.gov. Photo credit: NASA/Dimitri Gerondidakis