Mikro-Mars, a Micro-Mission to Planet Mars

Mathematics – Logic

Scientific paper

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Scientific paper

In the context of the international Mars exploration Projects, the proposed micromission can contribute substantially in increasing the scientific results and to establish a future low cost lander mission. The Mikro- Mars Mission concept consists of an orbiter integrating a total scientific payload of 25 kg to Mars including a light-weight lander of 10 kg. The orbiter will be designed as multipurpose platform, allowing the utility for missions to other planets to reduce development cost. The micro lander is a very challenging task in the area of micro technology. The payload is based on scientific needs for high-resolution remote sensing from orbit by taking into account future mission plans in order to avoid overlaps. A major goal is the investigation of surface material and small-scale geologic processes by imaging which is also needed for the detailed characterization of landing sites and the preparation of future missions. These observations will be complemented by detailed measurements of the magnetic field, the gravity field, the radiation environment as well as atmospheric and ionospheric studies from orbit. The spacecraft will be launched in 2007 as piggyback payload by an Ariane 5 ASAP into GTO with a total launch mass of 360 kg . It will use a bipropellant propulsion system with 200 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-Band and in X-Band. The Mars orbit is highly elliptical with a periapsis below 200 km to enable high-resolution remote sensing.. The light-weight lander is a challenging technological experiment with scientific instruments which will supplement the orbiter measurements and concentrate on the temperature cycle, geochemistry and radiation environment.

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