Scientific and Technical Aerospace Reports Volume 39 April 6, 2001

20010023118 NASA Ames Research Center, Moffett Field, CA USA
The Pascal Discovery Mission: A Mars Climate Network Mission
Haberle, R. M., NASA Ames Research Center, USA; Catling, D. C., Search for Extraterrestrial Intelligence Inst., USA; Chassefiere,
E., Centre National de la Recherche Scientifique, France; Forget, F., Centre National de la Recherche Scientifique, France;
Hourdin, F., Centre National de la Recherche Scientifique, France; Leovy, C. B., Washington Univ., USA; Magalhaes, J., San Jose
State Univ., USA; Mihalov, J., NASA Ames Research Center, USA; Pommereau, J. P., IPSL, France; Murphy, J. R., New Mexico
State Univ., USA; Concepts and Approaches for Mars Exploration; July 2000, Part 1, pp. 135; In English; See also 20010023036;
No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
The climate of Mars is a major focus of Mars exploration. With the loss of MCO, however, it remains uncertain how it will
be achieved. We argue that a truly dedicated climate mission to Mars should have both orbital and landed components, and that
these should operate simultaneously for at least 1 Mars year if not longer. Pascal is a Discovery mission that emphasizes the landed
component. Its principal goal is to establish a network of 24 small weather stations on the surface of Mars that will operate for
2 Mars years, with an extended mission option for an additional 8 Mars years bringing the total mission lifetime up to 10 Mars
years. The stations will collect hourly measurements of pressure, temperature, and optical depth. After delivering the probes to
Mars, Pascal’s carrier spacecraft will go into an elliptical orbit which will serve as a relay for the landers, and a platform for synoptic
imaging. These simultaneous measurements from the surface and from orbit will allow us to characterize the planet’s general
circulation and its interaction with the dust, water, and CO2 cycles. During entry, descent, and landing, each of Pascal’s 24 probes
will also measure the temperature structure of the atmosphere and acquire images of the surface. These data will allow us to determine
the global structure of the atmosphere between 15 and 130 km, and characterize the local terrain to help interpret the landed
data. The descent images are part of Pascal’s outreach program, as the probe camera system will be developed by faculty-supervised
student project. The intent is to generate enthusiasm for the Pascal mission by directly involving students. Pascal will be
launched on a Delta II-7925 in August of 2005. A type I trajectory will deliver Pascal to Mars in January of 2006. On approach,
the three-axis stabilized carrier spacecraft will spring deploy the Pascal probes in 4 separate salvo’s of 6 each. Global coverage
is achieved with small time-of-arrival adjustments in between each salvo. Pascal’s probes utilize an aeroshell, parachute, and
crushable material for entry, descent and landing. On the surface, their long life and global coverage is enabled by a Micro Thermal
Power Source with demonstrated heritage. After all probes are released, the carrier spacecraft will execute a small burn for insertion
into an elliptical orbit. The long lifetime of the Pascal network was chosen in part to maximize the chances that orbital sounding,
like that planned with MCO, would occur at some point during the mission. If Pascal is selected for launch in ’05, this could
occur if MCO-like science is reflown in the ’05 opportunity or, if it is reflown in ’03, the mission is extended to overlap with Pascal.
The combination of temperature sounding from orbit, and surface pressure mapping from the surface will allow a direct determination
of the full 3-D wind field for the first time.
Derived from text
Mars Missions; Mars Environment; Atmospheric Sounding; Mars Landing; Mars Probes; Automatic Weather Stations
20010023119 British National Space Centre, London, UK
Beagle 2
Hall, D. S., British National Space Centre, UK; Pillinger, C. T., Open Univ., UK; Sims, M. R., Leicester Univ., UK; Pullan, D.,
Leicester Univ., UK; Whitehead, S., Leicester Univ., UK; Thatcher, J., Astrium Ltd., UK; Clemmet, J., Astrium Ltd., UK; Linguard,
S., Martin-Baker Aircraft Co. Ltd., UK; Underwood, J., Martin-Baker Aircraft Co. Ltd., UK; Richter, L., Deutsche Forschungsanstalt
fuer Luft- und Raumfahrt, Germany; Concepts and Approaches for Mars Exploration; July 2000, Part 1, pp. 136;
In English; See also 20010023036; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
Beagle 2 is the British-led lander of the ESA Mars Express mission. The prime objectives of Beagle 2 are to (1) search for
criteria relating to past life on Mars, (2) seek trace atmospheric species indicative of extant life, (3) measure the detailed atmospheric
composition to establish the geological history of the planet and to document the processes involved in seasonal climatic
changes or diurnal cycling, (4) investigate the oxidative state of the Martian surface, rock interiors and beneath boulders, (5)
examine the geological nature of the rocks, their chemistry, mineralogy, petrology and age, (6) characterise the geomorphology
of the landing site, and (7) appraise the environmental conditions including temperature, pressure, wind speed, UV flux, etc. The
entry system comprises a front shield/aeroshell, a back cover/bioshield and release mechanisms. The descent system depends on
a mortar, pilot chute, main parachute and main parachute release mechanism. The Lander itself has a clam-like structure and lands
cocooned within gas-filled airbags. The outer shell provides energy absorption and thermal insulation within a CASIng that must
spread the impact loads and resists tearing. Many of the Beagle 2 science instruments are integrated with a robotic arm that transports
them to deploy them in positions where they can study or obtain samples of the rocks and soil. Sub-surface samples are
obtained using a Pluto (PLanetary Undersurface TOol) which has the ability to crawl across, and burrow below the planetary surface.
The constraints placed on Beagle 2 by mass restrictions of the Mars Express mission has meant that many innovations are
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