Numerical simulations, experimental investigation and optimization of hybrid space thermal radiators

Abstract

Spacecraft thermal management is a critical issue as power requirements for high-capacity satellites and human space flights continue to grow. Radiators play a vital role in heat transportation and act as sinks in this process. This study focuses on the optimization of a novel space thermal radiator. Conventionally, space thermal radiators have parallel tubes. Recent studies have evaluated the performance of serial radiators for heat transportation in spacecraft. In this study, a hybrid radiator that combines the advantages of both parallel and serial radiators is proposed for space applications. Performance analysis through conjugate heat transfer analysis is conducted on hybrid radiators and compared with parallel and serial radiators. Hybrid radiators effectively reduce the impact of micro-meteoroids and orbital debris. By appropriately isolating the leaking tube, hybrid radiators can maintain 95.4% heat rejection even in the event of tube leaks caused by orbital debris impact. Using Taguchi signal-to-noise ratio analysis, the optimal radiator geometry only incurs a 10 Pa pressure drop, compared to the 572 Pa baseline configuration, and has a lower mass of 4.3 kg instead of 6.8 kg. The study also found that when reduction in pressure drop is a priority, increasing tube diameter is crucial, but when mass reduction is important, decreasing fin thickness should be prioritized. The study demonstrates that hybrid radiator is a better alternative to parallel and serial radiators in spacecraft heat transportation process, especially when reduction in mass and pressure drop are equally crucial.