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This paper will describe in some detail the results of study work recently conducted by the European Space Agency in respect of a Mercury Sample Return mission. It will also highlight the major design constraints that have been identified for the power systems of such a mission and then go on to summarise the fundamental system level and power supply differences, which would be required for similarly achieving the more challenging Venus Sample/return mission.

This paper will highlight the electrical power system topology and basic performance of the SOHO mission during the first two years of its operation. It will go on to relate the chronology of spacecraft and power system events that occurred from the initial loss of SOHO contact in June 1998, up until the time of its attitude recovery some three months later. It will describe the operational modes of the power system during this critical period and the fundamental lessons learnt, which could enhance recovery prospects in the event that other missions experience a similar anomaly.