Analytical solution of the temperature distribution for this fin (along center axis
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Heat radiation is the only way for heat rejection from the spacecraft without reducing the working fluid. This fact points to an important role of space radiators in the energy balance of a vehicle. New high-power nuclear-electric spacecraft require the development of more advanced, highly efficient, and lightweight heat rejection systems. However, typical radiators comprise a substantial portion of the total vehicle mass. Therefore, development of lower-density and higher-thermal conductivity coating materials will improve the space radiator performance. Herein, an analytical solution of a problem of the temperature distribution along the radiating fin is presented. The implementation of the analytical solution allows engineers to have more exact equations for the following optimization of the radiator design.
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