The invention discloses a thermal vacuum test method for a spacecraft, which comprises the following steps of: 1, finishing preliminary heating partition design of an infrared heating device, and establishing a whole-satellite thermal analysis model in a test state; 2, infrared heating device-cabin plate closed-loop temperature control is established; carrying out iterative analysis by using the whole-satellite thermal analysis model in the test state and taking the requirement that the on-satellite equipment participates in the whole-satellite thermal vacuum test as a target, and determining a temperature feedback point temperature control target value under the thermal vacuum low-temperature working condition; 3, predicting a thermal vacuum test process by using a whole-satellite thermal analysis model in a test state and a thermal vacuum high-low temperature working condition temperature control target value; putting forward temperature control point implementation requirements and control requirements; 4, pasting a temperature sensor at a corresponding position on the surface of the outer cabin plate, arranging an infrared heating device, and establishing an infrared heating device-whole-satellite temperature closed-loop temperature control system; the infrared heating device can be subjected to partition design according to the equipment layout, the interference influence between partitions is weakened, and the whole satellite equipment temperature is accurately controlled.
本发明公开一种航天器热真空试验方法,一、完成红外加热装置初步加热分区设计,建立试验状态下的整星热分析模型;二、建立红外加热装置‑舱板闭环控温;利用试验状态下的整星热分析模型,以星上设备参加整星热真空试验要求为目标进行迭代分析,确定热真空低温工况下的温度反馈点控温目标值;三、利用试验状态下的整星热分析模型、热真空高低温工况控温目标值,预示热真空试验进程;提出控温点实施要求和控制要求;四、在外舱板表面相应位置粘贴温度传感器,布置红外加热装置,建立红外加热装置‑整星温度闭环控温系统;本发明能够根据设备布局对红外加热装置进行分区设计,减弱分区之间的干扰影响,准确控制整星设备温度。
Thermal vacuum test method for spacecraft
一种航天器热真空试验方法
2024-09-13
Patent
Electronic Resource
Chinese
Spacecraft thermal vacuum testing
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