火星着陆发动机气凝胶材料热防护装置设计

doi:10.7527/S1000-6893.2021.26568

Abstract

Abstract: The thermal protection technology for the large thrust landing engine is crucial for the safety of Martian landing mission.When the conventional high-temperature thermal shield based on the multi-stage heat radiation reflection structure is used in the Martian atmospheric environment, its heat insulation performance is significantly attenuated due to internal convection heat transfer.To solve this problem, a new type of engine thermal protector is developed based on the aerogel material.According to the operation environment for Mars exploration mission, transient simulation models with both low-pressure atmosphere and high-temperature heat flux boundaries are established, and the key design parameters such as shape taper and material thickness are optimized.The effectiveness of the design is verified by three-dimensional transient simulation analysis and the ground test with landing engine.The aerogel-based thermal protector has been successfully applied to the Tianwen-1 Mars lander, which has effectively shielded the landing engine from a high temperature of 1500℃.Based on the analysis of on orbit telemetry data, directions for improving the high temperature insulation technology based on the aerogel material are proposed.

Key words: Mars exploration, landing engine, aerogel, thermal protection, high-temperature insulation

CLC Number:

V476.4

ZHENG Kai, RAO Wei, XIANG Yanchao, ZHANG Dong, ZHANG Bingqiang, XUE Shuyan, DAI Chenghao, YE Qing. Design of aerogel-based thermal protector for Mars landing engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 626568-626568.

References

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Design of aerogel-based thermal protector for Mars landing engine

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