Micro Satellite Thermal Balance Testing: Orbit Heat Flux Simulation Method and Verification

Abstract

Comparing to conventional satellites, micro satellite features smaller envelop size, lower cost, and shorter R&D period. At the same time, while micro satellite generally runs within the LEO, it is more susceptible to the earth IR radiation. To simulate the orbital heat flux efficiently for the micro satellite, in this paper the thermal balance testing respectively using infrared cage and solar simulator are performed. The resulting differences between the two simulating approaches are examined with care. Conclusions can be drawn from analysis: in thermal balance testing of micro satellite, in terms of simulating orbital heat flux, the results of two simulators are close enough to consider that it is feasible to choose infrared cage as orbital heat flux simulator, given thermal coating material of typical IR emittance and solar absorptance ratio. Results demonstrate that by using infrared cage simulator, the actual temperature is about 5°C higher than theoretical value. The background heat flux interference stays stable at 17% of intensity of simulated orbital heat flux, and the value could be referred to in the thermal mathematical model modification.