Mars Geyser Hopper

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Mars Geyser Hopper
Operator NASA
Mission type Mars lander
Launch date March 1, 2016 (proposed)
Launch vehicle Atlas V-401
Launch site Florida, USA
Mission duration One Martian year (22 months) on the surface.
Landing October 8, 2016 (proposed)
Landing site south pole of Mars
Mass Launch weight: 1,092 kilograms (2,407 lb)
Lander: 500 kilograms (1,100 lb)
Power Cruise stage: solar array for 150 W,
Lander: ASRG for 133 W

The Mars Geyser Hopper is a NASA design reference mission for a Discovery-class spacecraft concept that would investigate the springtime carbon dioxide Martian geysers found in regions around the south pole of Mars.[1][2]

Mission overview[edit]

The mission is projected to cost $350 million USD and to meet a cost cap of no more than $425 million USD, not including the launch cost. It must have a March 1, 2016 launch date requirement (or no later than December 31, 2016) to land during the Mars southern summer. In order to reduce the cost and minimize risk, the spacecraft concept is based on a previous spacecraft design, the Mars Phoenix lander, which has a demonstrated flight heritage that incorporates soft landing capability and incorporates a restartable rocket propulsion system, suitable to be repurposed for this mission requirements.[2] The spacecraft would land at a target landing area near the south pole of Mars, where geysers exist over a stretch of several hundred kilometers with densities of at least one geyser every 1 to 2 kilometres (0.62 to 1.24 mi) and have the ability to "hop" at least twice from its landed location after a summertime landing to reposition itself close to a geyser site, and wait through the winter until the first sunlight of spring to witness first-hand the Martian geyser phenomenon and investigate the debris pattern and channel.[2]

Artist concept showing sand-laden jets erupting from Martian geysers. (Published by NASA; artist: Ron Miller.)
A large 'spider' feature apparently emanating sediment to give rise to dark dune spots. Image size: 1 km (0.62 mi) across.
According to Sylvain Piqueux, sun light causes sublimation from the bottom, leading to a buildup of pressurized CO2 gas which eventually bursts out, entraining dust and leading to dark fan-shaped deposits with clear directionality indicative of wind action.

Martian geysers are unlike any terrestrial geological phenomenon. The shapes and unusual spider appearance of these features have stimulated a variety of scientific hypotheses about their origin, ranging from differences in frosting reflectance, to explanations involving biological processes. However, all current geophysical models assume some sort of geyser-like activity.[3][4][5][6][7][8][9][10][11] Their characteristics and formation process are still a matter of debate.

The seasonal frosting and defrosting of CO2 ice results in the appearance of a number of features, such dark dune spots with spider-like rilles or channels below the ice,[4] where spider-like radial channels are carved between the ground and ice, giving it an appearance of spider webs, then, pressure accumulating in their interior ejects gas and dark basaltic sand or dust, which is deposited on the ice surface and thus, forming dark dune spots.[3][4][5][6][7][8][9] This process is rapid, observed happening in the space of a few days, weeks or months, a growth rate rather unusual in geology – especially for Mars.[12]

Mission concept[edit]

The primary mission duration, starting from launch, is 30 months, comprising 8 months of interplanetary cruise followed by a primary mission of 22 months (one Mars year) on the surface. The spacecraft will enter the atmosphere, and make a rocket-powered soft landing in a region of the south pole where geysers are known to form. This landing will take place during the polar summer, when the surface is free of ice. The predicted landing ellipse is 20 by 50 kilometres (12 mi × 31 mi) and hence the landing will be targeted to a region, and not to a specific geyser location. During the first post-landing phase, it will conduct science operations to characterize the landing site, to understand the surface geology of the area during the ice-free summer period.[1]

The spacecraft will then stow its science instruments and re-ignite the engines for a first hop of a distance of up to 2 kilometers (1.2 mi).[2] This hop is designed to place the lander in a location where it can directly probe the geyser region, examining the surface at a spot where a geyser had been.

Once again, the spacecraft will stow its instruments and activate the engines for a second hop, a distance of ~100 meters (330 ft). This hop will place the lander onto the winter-over site, a spot chosen to be a relatively high elevation where the lander can get a good view of the surroundings, close to but not located on the site of a known geyser, and outside the fall-out pattern of the expected debris plume. The spacecraft will characterize the local area during the remaining sunlight, and then go into "winter-over mode". The lander will continue to transmit engineering status data and meteorological reports during the winter, but will not conduct major science operations.[1]

On the arrival of polar spring, the lander will study the geyser phenomenon from the location selected for optimum viewing. Automated geyser detection on board the spacecraft will scan the environment, although the routine imagery will be buffered on the spacecraft, images will not be relayed to Earth until the spacecraft detects a geyser. This triggers high-speed, high-resolution imagery, including LIDAR characterization of particle motion and infrared spectroscopy. Simultaneously, the science instruments will do chemical analysis of any fallout particles spewed onto the surface of the lander.[2] Geysers erupt at a rate of about one a day during peak springtime season. If more than one is detected simultaneously, the spacecraft algorithm will focus on the nearest or "best". The lander will continue this primary geyser science for a period of about 90 days. Tens of geyser observations are expected over the spring/summer season. Extended mission operations, if desired, would continue the observation from August 11, 2018 through a full Martian year and into the second Martian summer.[2]

The hopper concept could also be used for exploration missions other than the polar geyser observation mission discussed here. The ability to make multiple rocket-powered hops from an initial landing location to a science region of interest would be valuable across a large range of terrain on Mars, as well as elsewhere in the Solar System, and would demonstrate a new form of rover with the ability to traverse far more rugged terrain than any previous missions, a mission concept that would be applicable to exploration of many planets and moons.[2]

Spacecraft[edit]

Power source[edit]

The geyser phenomenon occurs following an extended period of complete darkness, and the geysers themselves occur at the beginning of polar spring, when temperatures are in the range of −150 °C (−238 °F), and the sun angle is only a few degrees above the horizon. The extreme environment, low sun angles during the geyser occurrence, and the fact that it would be desirable to emplace the probe well before the occurrence of the geysers, during a period of no sunlight, makes this a difficult environment for the use of solar arrays as the primary power source. Thus, this is an attractive mission for use of the Advanced Stirling Radioisotope Generator (ASRG) with a mass of 126 kilograms (278 lb) including a Li-ion battery for use during Entry/Descent/Landing (EDL) as well as during the hops when there is a short duration requirement for additional power.[2] Waste heat from the ASRG will ensure that the lander itself will remain ice-free during the winter.

Propulsion[edit]

Hopping propulsion is based on the Phoenix landing system, using integrated hydrazine monopropellant blow-down system with 15 Aerojet MR-107N thrusters with Isp 230 sec for landing and hopping. RCS is four pairs of Aerojet MR-103D thrusters at 215 sec Isp, and one Aerojet MR-102 thruster at 220 sec Isp.[2] The system will be fueled with 191 kg of propellant.

Communication[edit]

The lander will communicate through X-band direct to Earth on cruise deck for transit; it will then use UHF antenna. Imaging and all data relaying would be coordinated with the Mars Reconnaissance Orbiter operations team.[2]

Scientific instruments[edit]

The science instruments include stereo cameras (MastCam) to view the geyser events and a robotic arm (from Phoenix) to dig beneath the soil surface and gather soil samples for chemical analysis on the Hopper. A light detection and ranging instrument (LIDAR), a landing camera and a thermal spectrometer for remote geological analysis as well as weather sensing are included.[2]

See also[edit]

References[edit]

  1. ^ a b c Landis, Geoffrey A.; Oleson, Steven J.; McGuire, Melissa (9 January 2012). "Design Study for a Mars Geyser Hopper". NASA. Retrieved 2012-07-01. 
  2. ^ a b c d e f g h i j k Geoffrey A. Landis; Steven J. Oleson; Melissa McGuire. (9 January 2012), "Design Study for a Mars Geyser Hopper", 50th AIAA Aerospace Sciences Conference (PDF), Glenn Research Center, NASA, retrieved 2012-07-01  Check date values in: |year= (help)
  3. ^ a b Piqueux, Sylvain; Shane Byrne; Mark I. Richardson (8 August 2003). "Sublimation of Mars’s southern seasonal CO2 ice cap formation of spiders" (PDF). Journal of Geophysical Research 180 (E8): 5084. Bibcode:2003JGRE..108.5084P. doi:10.1029/2002JE002007. Retrieved 1 July 2012. 
  4. ^ a b c Manrubia, S. C. et al. (2004). "Comparative Analysis of Geological Features and Seasonal Processes in Inca City and PittyUSA Patera Regions on Mars". European Space Agency Publications (ESA SP): 545. 
  5. ^ a b Kieffer, H. H. (2000). "Mars Polar Science 2000" (PDF). Retrieved 1 July 2012.  |chapter= ignored (help)
  6. ^ a b "Third Mars Polar Science Conference (2003)". 2003. Retrieved 1 July 2012.  |first1= missing |last1= in Authors list (help); |chapter= ignored (help)
  7. ^ a b G. Portyankina, ed. (2006). "Fourth Mars Polar Science Conference" (PDF). Retrieved 1 July 2012.  |chapter= ignored (help)
  8. ^ a b Bérczi, Sz., ed. (2004). "Lunar and Planetary Science XXXV (2004)" (PDF). Retrieved 1 July 2012.  |chapter= ignored (help)
  9. ^ a b Kieffer, Hugh H.; Philip R. Christensen; Timothy N. Titus (30 May 2006). "CO2 jets formed by sublimation beneath translucent slab ice in Mars' seasonal south polar ice cap". Nature 442 (7104): 793–6. Bibcode:2006Natur.442..793K. doi:10.1038/nature04945. PMID 16915284. 
  10. ^ "NASA Findings Suggest Jets Bursting From Martian Ice Cap". Jet Propulsion Laboratory (NASA). 16 August 2006. Retrieved 1 July 2012. 
  11. ^ Hansen, C.J. et al. (2010). "HiRISE observations of gas sublimation-driven activity in Mars’ southern polar regions: I. Erosion of the surface". Icarus 205: 283–295. Bibcode:2010Icar..205..283H. doi:10.1016/j.icarus.2009.07.021. Retrieved 1 July 2012. 
  12. ^ Ness, Peter K.; Greg M. Orme (2002). "Spider-Ravine Models and Plant-like Features on Mars – Possible Geophysical and Biogeophysical Modes of Origin". Journal of the British Interplanetary Society (JBIS) 55: 85–108. Retrieved 1 July 2012. 

This article incorporates content copied from NASA sources.