Modeling External Heat Loads on the Spacecraft in a Thermal Vacuum Chamber

A method and an algorithm to solve the problem on reproduction, with maximum possible accuracy, of heat loads on the surface of the spacecraft in a thermal vacuum chamber with the aid of the radiating system incorporating thermal shields and halogen incandescent lamps have been presented. In simulation experiments conducted for the characteristic heat loading of the spacecraft surface, the possibility to substantially improve the accuracy of solution of the problem by combining the thermal shields and the incandescent lamps into a single radiating system has been demonstrated.