Thermal Balance of the Spacecraft Reflector Frame in Sun-Synchronous Orbit

Thermally curing polymer composites is an alternative method to produce inflatable structures in Earth orbit. This work studies thermal balance for framework of the orbital radar sounding probe in sun-synchronous orbit. The framework is composed of hollow layered cylindrical structures. Simplified model of Earth’s infrared and albedo radiation is described. The outer coating’s absorbing and reflective properties have profound value in resulting thermal balance. As a method of reaching desired temperatures, solar radiation absorbing stripe (made of copper foil) is used. By varying the size of said stripe for every cylindrical structure, the amount of absorbed solar flux can be changed. The resulting steady state temperatures are plotted for various stripe sizes and solar flux angles of incidence.