摘要

The overall thermal control of a satellite is achieved by balancing the energy emitted by the spacecraft as radiation against the energy dissipated by its internal components plus the energy absorbed from the environment. Since mass is at a premium on a spacecraft, the space radiator used in its temperature control system needs to be optimized with respect to mass. An experimental study was conducted to provide information about the heat radiated to the space from a pin fin with cylindrical and conical cavities. The pin fin with cylindrical cavity dissipates 1.3 times more heat and 3.2 times more heat loss per unit mass than a solid pin fin in vacuum. Further the pin fin with conical cavity losses 1.7 times more heat and 2.3 times more heat loss per unit mass compared to a solid pin fin in vacuum. It is a significant achievement in the enhancement of the heat transfer characteristics of the radiating fin.