GTO卫星飞行温度预计方法与在轨验证

Prediction Method and In-orbit Validation of Flight Temperature of GTO Satellite

为了提高GTO轨道卫星温度预计的准确度,文章建立了卫星瞬态热分析模型。针对GTO特定工况,采用时段平均当量法模拟太阳翼变化规律供电时仪器间断工作热耗,并在整星热分析中应用PSCHG函数模拟贮箱推进剂相变换热以及推进系统管路温度预计方法等,准确地预计了GTO卫星在轨瞬时温度及变轨期间推进系统温度,验证结果表明:温度预计值与在轨实测数据偏差小于5℃的情况达79%以上。

To improve the precision of the predicted temperature for GTO satellite,a thermal model is built.The average simulation methods,in the light of GTO specific case,are used to simulate the heat dissipation of the instruments versus the solar array＇s power supply.In the thermal analysis,the PSCHG function is used to simulate the propellant phase-change heat exchange and the pipes temperature prediction method are applied.The transient temperature of GTO satellite is predicted precisely.Reasult shows that the difference between the predicted results and the telemetered data is within range of 5℃ in more than 79% case.