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

doi:10.16708/j.cnki.1000-758X.2022.0072

Abstract

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

ZHENG Kai, XIANG Yanchao, RAO Wei, ZHANG Bingqiang, XUE Shuyan, DAI Chenghao, ZHANG Dong, WANG Yuying. Design and verification of thermal control system for Tianwen-1 Mars entry capsule[J]. Chinese Space Science and Technology, 2022, 42(5): 108-116.

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URL: https://journal26.magtechjournal.com/kjkxjs/EN/10.16708/j.cnki.1000-758X.2022.0072

https://journal26.magtechjournal.com/kjkxjs/EN/Y2022/V42/I5/108

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

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