Chemical Propulsion Systems for Mars Sample Return

Details Chemical Propulsion Systems for Mars Sample Return Chemical Propulsion Systems for Mars Sample Return

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e..94b&link_type=abstract

Proceedings of the 4th International Spacecraft Propulsion Conference (ESA SP-555). 2-9 June, 2004, Chia Laguna (Cagliari), Sard

Computer Science

Scientific paper

The European Space Agency (ESA) instigated the Aurora Solar System Exploration Programme in 2001. A cornerstone of the initial robotic phase of Aurora is Mars Sample Return, MSR. ESA has designed the first iteration of a "minimal complexity" (and cost) MSR mission centred around a dual Ariane V launch in 2011. Mission elements include an Orbiter, including an Earth return capsule, and separate descent module / Mars ascent vehicle composite will launch direct to Mars later. A Descent Module (DM) will propulsively slow the composite to a controlled soft landing near the Mars equator for a 14 week surface stay. A two stage Mars Ascent Vehicle (MAV) will then launch a 0.5kg Mars sample onto a rendezvous trajectory with the awaiting Orbiter upper stage for return to Earth. This paper critically examines the demanding propulsion requirements of the Orbiter, DM and MAV mission elements for the ESA MSR mission, which are all sent from Earth fully loaded with propellant. Design issues and suggested solutions from the inventory of European and non-European engines which have been identified in the first phase of the study are outlined. The Orbiter requires a high reliability high Isp engine of around 800N thrust and at least 50 restarts to minimise propulsive losses on the ~4ton platform during deceleration into Mars orbit. There are currently no European engines with this thrust level. The DM system is required to generate a total thrust of 8000-10000N (depending on the MAV mass), with an engine capable of throttling to ~10% of maximum thrust with a rapid response time. An Isp requirement has not been determined. Two MAV's of differing complexity and mass are being studied by European prime contractors, resulting in either first stage a thrust requirement of 2750 or 5500N, depending on the design. A comparable Isp to the Orbiter, in excess of 310s, is common to both, as is the survival a 14 week surface stay. All engines are intended to use storable liquid propellants. A preliminary table of engine options is included in this paper.

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