火星大气高温光谱建模与非平衡辐射热流预测

吕俊明; 李飞; 李齐; 程晓丽

doi:10.7527/S1000-6893.2021.26551

航空学报 >

2022 , Vol. 43 >Issue 3: 626551 - 626551

DOI: https://doi.org/10.7527/S1000-6893.2021.26551

天问一号着陆火星专栏

火星大气高温光谱建模与非平衡辐射热流预测

吕俊明 ,
李飞 ,
李齐 ,
程晓丽

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1. 中国航天空气动力技术研究院, 北京 100074;
2. 中国航天科技集团有限公司航天飞行器气动热防护实验室, 北京 100074;
3. 中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190;
4. 北京空间飞行器总体设计部, 北京 100094

收稿日期: 2021-10-25

修回日期: 2021-11-03

网络出版日期: 2021-12-01

基金资助

国家自然科学基金（11772315，11902025）

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Modeling of Martian atmospheric high temperature spectra and prediction of non-equilibrium radiative heating

LYU Junming ,
LI Fei ,
LI Qi ,
CHENG Xiaoli

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1. China Academy of Aerospace Aerodynamics, Beijing 100074, China;
2. Aerospace Vehicle Thermal Protection Laboratory, China Aerospace Science and Technology Corporation, Beijing 100074, China;
3. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;
4. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China

Received date: 2021-10-25

Revised date: 2021-11-03

Online published: 2021-12-01

Supported by

National Natural Science Foundation of China (11772315,11902025)

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摘要

火星科学实验室成功着陆后的热环境重构数据表明，气动辐射加热在火星进入防热设计中具有不同于以往认识的重要影响，未知机制和模型不确定性等问题有待进一步研究。探测器高速进入火星大气产生极高温非平衡气动环境，造成火星气动辐射与常规CO₂红外辐射研究显著不同。针对火星大气高温光谱和辐射热流预测，首先，建立适用于火星大气的高温非平衡光谱辐射模型，获得典型高温条件CO₂光谱结构和辐射强度，与NASA和JAXA试验结果对比，结果显示符合较好。其次，依靠激波管和发射光谱测量技术，开展典型进入条件的辐射强度测量试验，数值结果、试验值和NASA试验结果相互符合较好，验证了光谱模型。最后，对探路者号进行气动辐射加热分析，完成典型进入条件下的非平衡流动和辐射特性计算，基于光线法得到光谱辐射强度沿驻点线的变化，表明高速与低速条件的气动辐射机制存在显著差异；基于有限体积法获得进入器表面辐射热流分布，结果显示辐射热流的分布及变化规律与地球再入显著不同，进入速度6 km/s以下时辐射热流随进入速度增加而减小，同时进入器锥身及肩部的辐射热流高于驻点区域。

关键词： 火星进入; 热防护设计; 气动热力学; 气动辐射; 非平衡流动; 光谱辐射强度; 辐射加热

本文引用格式

吕俊明 , 李飞 , 李齐 , 程晓丽 . 火星大气高温光谱建模与非平衡辐射热流预测[J]. 航空学报, 2022 , 43(3) : 626551 -626551 . DOI: 10.7527/S1000-6893.2021.26551

Abstract

The aerothermodynamics data reconstructed after the successful landing of Mars Science Laboratory shows that radiative heating has an important impact on the design of thermal protection system of Mars entry vehicles, which is different from previous understanding.However, there are still unknown mechanism and model uncertainty need to be studied.Due to the high-temperature and non-equilibrium in the high-speed entry, the aerothermal environment is different from that of conventional CO₂ infrared radiation study.Firstly, a high-temperature non-equilibrium spectral radiation model applicable for Martian atmosphere has been established to obtain the spectral structure and radiation intensity, which in turn, were compared with test results from NASA and JAXA, and agreed well. Secondly, the radiation intensity under typical Mars entry velocity has been obtained by both computational method and experiment using shock tube and emission measurement techniques; the results of computation and test are in good agreement with NASA test results, validating the flow and spectrum models. Finally, numerical simulations and analysis of aero-radiation on Pathfinder have been conducted, non-equilibrium flow filed and radiation characteristics under typical conditions were completed, the spectral radiance along stagnation line based on ray tracing method was obtained, indicating that there is a significant difference between the aerodynamic radiation mechanism under high-speed and low-speed conditions; the radiative heating rate distribution on the surface was obtained based on finite volume method, and the results show the distribution and change of the radiative heating is significantly different from the reentry of the earth.The radiative heating rate decreases with the increase of the entry speed when the entry speed is below 6 km/s, and the radiative heating rate on the cone and shoulders is higher than the stagnation region.

Key words： Mars entry; thermal protection design; aerothermodynamics; aero-radiation; non-equilibrium flow; spectral radiation intensity; radiative heating

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