Thermal Control Subsystem for Free Flying Satellites

The design, fabrication, development testing, and growth potential of an advanced design thermal control subsystem for the free flying P80-2 satellite is described. Free flying satellite applications can have large payload heat rejection requirements. For example, the P80-2 heat rejection requirement was in excess of 4 kilowatts. An inherent requirement for these vehicles is to incorporate a means for transferring heat from a source, frequently electronic components, to a sink, typically a space radiator. This heat transfer can be accomplished by a liquid coolant loop that is pumped and temperature controlled by a coolant pumping and conditioning assembly (CPCA) system. Major CPCA components typically include a long life space qualified pump, power inverter, thermal control valve, accumulator, and miscellaneous sensors.