中国空间科学技术

中国空间科学技术 ›› 2022, Vol. 42 ›› Issue (5): 108-116.doi: 10.16708/j.cnki.1000-758X.2022.0072

• 论文 • 上一篇    下一篇

天问一号火星进入舱热控系统设计与验证

ZHENG Kai，XIANG Yanchao，RAO Wei，ZHANG Bingqiang，XUE Shuyan，DAI Chenghao， ZHANG Dong，WANG Yuying   

  1. 1 北京空间飞行器总体设计部，北京100094
    2 空间热控技术北京市重点实验室，北京100094
  • 出版日期:2022-09-09 发布日期:2022-09-09

Design and verification of thermal control system for Tianwen-1 Mars entry capsule

郑凯，向艳超，饶炜，张冰强，薛淑艳，戴承浩，张栋，王玉莹   

  1. 1 Beijing Institute of Spacecraft System Engineering，Beijing 100094，China
    2 Beijing Key Laboratory of Space Thermal Control Technology，Beijing 100094，China
  • Published:2022-09-09 Online:2022-09-09

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摘要： 天问一号火星进入舱携带祝融号火星车实施进入、下降、着陆过程，其热控系统设计主要面临地火转移外热流大幅变化、进入火星舱壁气动烧蚀长时高温、着陆发动机点火局部超高温等技术挑战。为此，综合采用隔热设计、等温化设计、主动控温设计等热控手段，针对外热流大幅变化应用了新型SAL-2热控涂层，为解决局部超高温问题研制了新型气凝胶热防护装置，完整构建了进入舱的高效可靠热控系统。飞行遥测数据表明，全飞行过程设备温度和热控功耗均优于指标要求，进入、下降、着陆过程工作设备温度范围5.0~40.3℃，整舱平均控温功耗不超过43W，验证了进入舱热控系统设计的有效性。

关键词: 火星探测, 着陆, 热控系统, 热控涂层, 气凝胶

Abstract: Tianwen-1 Mars entry capsule took Zhurong Mars rover to accomplish the entry，descent and landing process.Its thermal control system met lots of technical challenges，including wide variations of external heat fluxes during the flight from Earth to Mars，high temperature of entry capsule surface caused by aerodynamic ablation during the Mars entry process，and ultra-high temperature caused by the landing engine during the descent and landing process.Accordingly，comprehensive methods consisting of thermal isolation，thermal transmission and temperature compensation were applied.New thermal control coating SAL-2 was applied to overcome the changes of external heat fluxes.To insulate the ultra-high temperature from the landing engine，a new aerogel-based thermal protector was developed.With these measures，the efficient and reliable thermal control system for Tianwen-1 Mars entry capsule was completely constructed.The in-orbit telemetric data shows that working equipments of Tianwen-1 Mars entry capsule all have suitable temperature ranging from 5.0℃ to 40.3℃ during EDL process，and power consumption for temperature compensation does not exceed 43W，which verifies the effectiveness of this thermal control system.

Key words:  , Mars probe；landing；thermal control system；thermal control coating；aerogel