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考虑卫星本体表面包覆绝热材料的实际物理状态,根据数值传热学和有限容积法建立了目标表面温度场和红外辐射计算模型。建立卫星结构模型,基于热控涂层性能退化,提出红外辐射灵敏度概念,并建立了卫星红外辐射灵敏度计算模型。对在轨飞行卫星的瞬态温度场进行数值模拟,与遥测数据对比分析。最后,分析了空间卫星的红外辐射和红外辐射灵敏度。结果表明,建立的卫星温度场计算模型合理,同时,红外辐射灵敏度概念的提出避免了由于热控涂层性能退化而造成卫星温度场和红外辐射重复计算的繁琐工作。
Considering the actual physical state of the satellite insulation coating on the surface of the satellite body, the calculation model of target surface temperature field and infrared radiation is established based on numerical heat transfer and finite volume method. The satellite structure model was established. Based on the degradation of thermal control coating performance, the concept of infrared radiation sensitivity was put forward and the calculation model of satellite infrared radiation sensitivity was established. The transient temperature field of orbiting satellites is numerically simulated and compared with the telemetry data. Finally, the space satellite’s infrared radiation and infrared radiation sensitivity are analyzed. The results show that the established satellite temperature field calculation model is reasonable, meanwhile, the concept of infrared radiation sensitivity is proposed to avoid the tedious work of repeated calculation of satellite temperature field and infrared radiation due to the degradation of thermal control coating.