MYRIADE is a microsatellite concept initiated by CNES, designed to produceseveral spacecrafts for different purposes. Its main goal is to set a commonstructure for microsatellite product line. This program intends to develop lowcostspacecraft for LEO missions, mainly to perform scientific experiments, usingthe existing concepts to reduce costs and leadtime.DEMETER is the first application of the MYRIADE micro-satellite program.Launched in 2004 with a two years expected lifetime, DEMETER was designedneither for a fluidic passivation nor an electric one. Since 2008, the Europeancode concerning the space debris mitigation requires to limit to 25years the orbital lifetime after the end of operational mission for LEOspacecrafts and the passivation of all components with risks of explosion orcreation of debris. In 20l0, after seven years of successful operational lifetime,it has been decided to stop the DEMETER mission and to realize the fluidicand electric passivation of the spacecraft to comply with the European code.The paper will introduce the DEMETER spacecraft. It will present thedeorbitation strategy adapted to the spacecraft architecture. Then, it will focuson the G&C studies performed to demonstrate the adequacy of the controlspacecraft subsystem with the strategy. It will also describe the tools developedto follow the deorbitation. After the description of the on-ground strategy validation,it will present the in-orbit results of the fluidic and electric passivationof the spacecraft.
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