ABSTRACT
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Thermal control systems (TCS) are an integral part of all spacecraft and instru-
ments. Thermal engineers design TCS to allow spacecraft to function properly on-
orbit.1 In TCS design, both passive and active thermal control methods may be
applied. Passive thermal control methods are commonly adopted for their relatively
low cost and reliability, and are adequate for most applications. When passive
thermal control methods are insufficient to meet the mission thermal requirements,
active thermal control methods are warranted. Active thermal control methods may
be more effective in meeting stringent thermal requirements. For example, many
emerging sensor applications require very tight temperature control (to within 1 K)
or isothermality across a large area; such requirements can generally be achieved
only by active control techniques.
