Advances in the Thermal Design of the “MERS” Satellite

This paper reports on the evolution of the thermal design of the “MERS” recoverable microsatellite. “MERS” – the Microgravity Experiment Recoverable Satellite - is a very unique LEO spacecraft which, following a period spent conducting microgravity experiments in Low Earth Orbit, must re-enter the Earth’s atmosphere and complete a safe landing on the ground. An initial system analysis1 led to the decision to re-enter the entire spacecraft. Consequently, the very demanding aerothermal requirements of the re-entry portion of the mission, which strongly drive the external shape of the spacecraft, also heavily influence its on-orbit thermal design.