论文部分内容阅读
根据摄像机所处空间环境和结构特点,设计它的热控系统,同时进行了热平衡试验来验证热设计的合理性。首先,总结了摄像机热设计的准则,分析了摄像机所处的空间热环境。然后,对摄像机的各个部分进行了热设计;采用被动热控措施进行热隔离和热疏导,充分利用了摄像机所搭载的卫星平台的热容;采用主动热控措施将温度控制在热控指标范围之内。最后,根据摄像机的热环境和各种工作模式设计了4种极端试验工况,并进行了热平衡试验。试验结果表明,摄像机在存储工况时,其温度与安装面温度相差3℃左右,满足存储温度指标要求;低温工况和高温工况时,其整机温度为-3.1℃和45.7℃,镜头温度为-4.5℃和46.8℃,均满足热控指标要求。试验结果证实设计的空间摄像机热控系统合理可行。
According to the space environment and the structure of the camera, the thermal control system is designed and the heat balance test is carried out to verify the rationality of thermal design. First of all, summarizes the thermal design guidelines for cameras and analyzes the thermal environment in which the cameras are located. Then, the thermal design of each part of the camera was carried out. The passive thermal control measures were adopted to isolate and heat the heat, which fully utilized the heat capacity of the satellite platform mounted by the camera. The active thermal control measures were used to control the temperature in the thermal control index range within. Finally, according to the thermal environment of the camera and various working modes, four extreme test conditions are designed and the thermal equilibrium test is carried out. The test results show that when the camera is in the storage condition, the temperature of the camera is about 3 ° C. less than the temperature of the mounting surface, which meets the requirements of the storage temperature index. In the low temperature condition and the high temperature condition, the whole temperature of the camera is -3.1 ° C. and 45.7 ° C., Temperature -4.5 ℃ and 46.8 ℃, all meet the thermal control requirements. The test results confirm that the designed space camera thermal control system is reasonable and feasible.