摘要
本文采用基于热解层模型的烧蚀热响应计算方法,对轻质防热材料的烧蚀机理进行分析,预测了防热材料在火星气动热环境下的烧蚀、热解及传热特性.开展地面风洞试验设计,获取了多状态下的防热材料烧蚀数据.通过与地面试验数据的比对分析,对烧蚀传热计算模型中的不确定性参数进行了修正,最终确定了气动热防护系统的设计状态.飞行任务表明,天问一号火星探测器气动热防护系统设计正确、裕度合理,有力地保障了我国首次火星探测任务的圆满成功.
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.
作者
杨昌昊
祁玉峰
饶炜
孙泽洲
罗晓光
欧东斌
吴国庭
YANG ChangHao;QI YuFeng;RAO Wei;SUN ZeZhou;LUO XiaoGuang;OU DongBin;WU GuoTing(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2022年第2期253-263,共11页
Scientia Sinica(Technologica)
基金
行星探测重大工程资助项目。
关键词
火星
探测器
热防护系统
设计
实现
Mars
probe
thermal protection system
design
implementation
