In aerospace instruments, the problem of temperature control can become severe because convettive cooling cannot be used; heat must be transferred by radiative means alone. Systems are exposed to a rigorous thermal environment and there are strict limitations on the power, weight and volumes available. A surprisingly high degree of temperature control can be accomplished, however, by the use of a passive system of spectrally selective surfaces.
In this paper, one approach to the design of passive temperature control systems is discussed by detailed reference to an instrument intended for use on the lunar surface.
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