Spacecraft thermal design: Particular problems with small satellites

Abstract

Small satellites (less than 100 kg) are becoming increasingly utilized as an economical means of experimentation and research in orbit. The analysis of such systems presents unique challenges to the thermal engineer since the mass, power and volume available are all very limited, prohibiting use of some methods of thermal control. The experiments and subsystems must still be maintained within specified temperature limits, regardless of these problems and the extreme environments and changing power conditions (internally and externally) of the satellites. Analysis techniques, together with a comprehensive testing programme, ensure the thermal success of satellites throughout all phases of their intended missions. DERA has experience in the design of small satellites following the successful missions of the STRV 1a and 1b [1]. This technical paper details the unique thermal problems and their solution to achieve a functioning design of the subsequent satellites (STRV 1c and 1d).