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 light-weight 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 oscillator for radio science.
The light-weight micro lander is a challenging technological experiment by itself. It is equipped with a suite of scientific instruments which will supplement the orbiter measurements and concentrate on the environment (temperature cycle, atmosphere, magnetosphere, and radiation).
Since 1994, space debris has been an agenda item at the Science and Technical Committee of the United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS). Meanwhile progress has been made with the implementation of “Space Debris Safety and Mitigation Standard Handbooks” However no binding agreement has been reached on international level, only recommendations for debris minimisation have been formulated: ”measures should be applied uniformly and consistently by the entire international space faring community; studies should be continued on future possible solutions to reduce the population of onorbit debris”. In support of the a.m. recommendations ESA has issued the ROGER (“Robotic Geostationary Orbit Restorer) systems study which concentrate on the situation in the most valuable geostationary orbit, in particular on collision probability and on re-orbiting of satellites into disposal orbit. This paper provides the technical and programmatic results of the a. m. ESA study. Specifically, the paper will: • Describe the main tasks of the ROGER System, which consists of inspection services for satellite operators on request and the transportation of out-of-order satellites into a special graveyard orbit • Describe the special means of the ROGER satellite to be capable to fulfill these task • Describe the operational concept and its constraints • Describes the justification of the selected scenario w.r.t. the arguments for the commercial applications The concept foresees to approach a selected target satellite using rendezvous sensors and perform an inspection orbit. This inspection service by a zoom camera could be ordered by e.g. a satellite operator or a space assurance company. Another order could be the transportation of an end-of-life satellite into the graveyard orbit. Satellite operators are normally responsible to bring their satellites into graveyard by their own propulsion system and propellant mass. This residual propellant can be used to enhance the operational lifetime for the satellite and hence could make more profit. A part of this profit could be spent for the ROGER graveyard transportation service. ROGER in its layout has specifically designed devices, to approach to the target, capture it, stabilize the attitude and transport it into a graveyard orbit. The necessary technical devices, the operational procedures and an overview about the commercial aspects will be given in this paper. The presentation will be supported by a brief video film and models of the demonstrator and the proposed operational vehicle.
