中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (4): 142-152.doi: 10.16708/j.cnki.1000-758X.2024.0065

• 论文 • 上一篇    下一篇

基于热模型相关性验证的火面环境热平衡试验

张冰强，薛淑艳，周晓舟   

  1. 1.北京空间飞行器总体设计部，北京100094
    2.航天器热控全国重点实验室，北京100094
  • 出版日期:2024-08-25 发布日期:2024-07-26

Thermal test of Martian environment based on thermal model correlation verification

ZHANG Bingqiang，XUE Shuyan，ZHOU Xiaozhou   

  1. 1.Beijing Institute of Spacecraft System Engineering，Beijing 100094，China
    2.National Key Laboratory of Spacecraft Thermal Control，Beijing 100094，China
  • Published:2024-08-25 Online:2024-07-26

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摘要： 针对热平衡试验中难以综合模拟火面复杂多变服役热环境的困难，建立一种基于热模型相关性验证的热平衡试验方法。采用真空、低压变温自然对流和低压定温强迫对流验证相结合的方式，验证高低温条件下热分析模型的对流、导热、辐射网络系数和热容等参数，并由相关性检验后的热分析模型验证设计的正确性。结果表明，板温度高于气温11～86℃条件下（气温-91℃）的自然对流传热系数为0.19～0.57W/（m2·K），4～15m/s风速下的强迫对流换热系数为1.24～2.4W/（m2·K）修正后的热分析模型与试验结果偏差在±3.5℃以内。该方法在不完全模拟服役热环境条件下实现航天器热设计验证，提供有效的热分析模型，已成功应用于祝融号火星车热平衡试验。

关键词: 火星表面, 热平衡试验, 热模型, 对流换热

Abstract: Considering the difficulty in comprehensively simulating the complex and changeable thermal environment of the Martian surface with a thermal balance test，a thermal balance test method based on the correlation verification of the thermal model is established.In addition，vacuum，low-pressure variable-temperature natural convection and low-pressure constant-temperature forced convection are combined to verify the convection，heat conduction，radiation network coefficient and thermal capacity of the analysis model under high- and low-temperature conditions，and the correctness of the design is verified using the thermal analysis model after correlation verification.The results show that the natural convection heat transfer coefficient under the condition that the plate temperature is 11.86℃ higher than the air temperature（-91℃） was 0.19-0.57W/（m2·K），and the forced convection heat transfer coefficient under the wind speed of 4.15m/s is 1.24-2.4W/（m2·K）.The deviation between the modified thermal analysis model and the test results is within ±3.5℃.This method realizes the thermal design verification of spacecraft under incompletely simulating the thermal environment，provides an effective thermal analysis model，and has been successfully applied to the thermal balance test of the Zhu Rong Mars rover.

Key words: Martian surface, thermal test, thermal model, convective heat