Thermal Control Techniques for Spacecraft Devices

Abstract

Nowadays one of the most developing area in the space industry, is that pertaining to the thermal controlling of spacecrafts. The thermo-optical properties play a major role in designing of the spacecraft components. This paper describes the issues concerned and the major categories of space craft failures. The function of the thermal control subsystem (TCS) is to preserve all spacecraft and payload components and subsystems within their required temperature limits for each mission phase. Two limits are frequently defined: operational limits that the component must remain within while operating and survival limits that the component must remain within at all times, even when not powered. In this study the thermal control techniques, approaches and the thermal control components that commonly used in observation and remote sensing satellites are identified. The study shows that most observation satellites use passive control as it is more reliable in comparison to active thermal control and need less power. The thermal control techniques are crucial for the safety and long term utility of spacecrafts and satellites as has proved so in the case of recent failures such as Mars Observer, Chandrayan I and Columbia Space Shuttle.