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为研究卫星热平衡试验误差,建立“希望一号”卫星热试验的联合热数学模型,对热平衡试验进行模拟,并与理想状态进行比较,发现仪器试验温度值在低温工况中偏低13～20℃,高温工况中偏低11～17℃;高温工况中-Y舱板表面到达热流不均匀度高达27.3%。此外,分析了热试验中热沉的温度、表面发射率、与卫星的表面积比,支架的导热、辐射漏热,电缆的导热、辐射漏热,以及热流计温度测量误差对卫星温度场的影响。
In order to study the error of the satellite thermal equilibrium test, a joint thermal mathematical model of the “No. 1” solar thermal experiment was established and the thermal equilibrium test was simulated and compared with the ideal state. The experimental temperature of the instrument was found to be low at low temperature 13 ~ 20 ℃, 11 ~ 17 ℃ lower in the high temperature condition; and 27.3% in the surface of the -Y tank reaching the heat flux in the high temperature condition. In addition, the influence of heat sink temperature, surface emissivity, surface area ratio with satellites, thermal conductivity of the support, radiation heat leak, thermal conductivity of the cables, heat leakage from the radiation, and temperature measurement errors of the heat flow meter on the satellite temperature field are analyzed .