Abstract
<p indent="0mm">This paper introduces the technical parameters of the aerodynamic thermal protection system (TPS) for the Tianwen-1 Mars probe. The ablation mechanism of the lightweight materials is analyzed using the ablation thermal response calculation method, based on the pyrolysis layer model. The ablation, pyrolysis, and heat transfer characteristics of the selected materials are predicted in the Mars entry, descent, and landing environment. Wind tunnel tests were carried out to obtain ablation data of the materials in multiple states. Through comparison and analysis of test data, the uncertainty parameters in the ablation and heat transfer calculation model were modified, and the design value of the TPS thickness was verified. Finally, the actual mission shows that the aerodynamic TPS for the Tianwen-1 Mars probe is designed correctly and its margin is reasonable, ensuring the complete success of the first Chinese Mars exploration mission.
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