Micro-Mars: a low cost mission to planet Mars with scientific orbiter and lander applications

Details Micro-Mars: a low cost mission to planet Mars with scientific orbiter and lander applications Micro-Mars: a low cost mission to planet Mars with scientific orbiter and lander applications

Nov 2003

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003esasp.542...17k&link_type=abstract

In: Proceedings of the Fifth IAA International Conference on Low-Cost Planetary Missions, 24-26 September 2003, Noordwijk, The N

Mathematics

Logic

Space Missions, Mars

Scientific paper

The proposed Micro-Mars Mission can contribute substantially to the international Mars exploration programme within the framework of a future low cost mission. The concept consists of an orbiter integrating a total scientific payload of 30 kg including a lightweight lander of 15 kg. The spacecraft will be launched as piggyback payload by an Ariane 5 ASAP with a total launch mass of 360 kg. It will use a bipropellant propulsion system with 210 kg of fuel and four thrusters of 22 N, and four of 10 N for orbit and attitude control. Further attitude actuation shall be performed by three reaction wheels and a gyropackage, a star sensor and a sun sensor for attitude sensing. Communication will be performed in S- and X-Band to earth and in UHF between orbiter and lander. From a highly elliptical orbit with a periapsis below 200 km, four instruments will perform high-resolution remote sensing observations and the payload consists of a camera system, a magnetometer, a dosimeter, and an ultrastable osciallator for radio science. The light-weight micro lander is a challenging technological experiment by itself. It is equiped with a suite of scientific instruments which will supplement the orbiter measurements and concentrate on the environment (temperature cycle, atmosphere, magnetosphere and radiation).

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