星载光机电设备兼有光学系统和运动机构的特点, 前者温度指标要求高, 后者构型复杂并且相对星体其他部分运动, 这给热设计的验证带来困难。文章以光机电设备激光通信终端为例, 提出了热设计的间接验证方法, 即通过地面试验数据修正热分析模型、再由热分析模型预示在轨温度, 进而验证热设计。设计了热平衡试验, 并根据试验结果修正了模型, 修正后的试验模型计算结果与试验结果基本一致, 81%的测温点偏差小于5 ℃, 模型较好地反映了真实的热物理状态, 其预示的在轨温度可用于验证热设计。对比了轨道计算温度与飞行温度, 81%的测温点偏差小于4 ℃, 证明了间接验证方法的正确和有效, 满足星载激光通信终端的应用要求。所述的验证方法显著降低了热试验的难度, 对多姿态与高温度指标的光机电设备具有借鉴意义。

Satellite-borne opto-electromechanical instruments preserve both optical systems and mechanism properties; the former has a strict requirement for temperature, and the latter has a complex structure and is constantly moving. This is a challenge to the test validation of the thermal characteristics. A case study of the indirect validation method of the thermal design for the optical communication terminal is presented. The indirect validation method may be utilized to predict the in-orbit temperature through the thermal analytical model, which is corrected using temperature data in the thermal balance test. The thermal balance test and model correction have been made. Very good correlation was demonstrated between the computed results of the proposed model and the measured test data; a deviation of 81% is less than 5 ℃. Thus, the model is appropriate for use in validation of thermal design. Comparing the thermal analytical results to the flight results, the deviation of 81% is less than 4 ℃. This demonstrates the accuracy and the effectiveness of the indirect validation method, and the method meets the application requirements of optical communication terminals on satellites. The proposed indirect validation method greatly reduces the difficulty of thermal testing and is of certain reference value to altitude-varied and high temperature precision opto-electromechanical instruments.