基于再入轨迹和气动热环境的返回舱烧蚀研究

doi:10.7527/S1000-6893.2013.0167

流体力学与飞行力学

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基于再入轨迹和气动热环境的返回舱烧蚀研究

王俊¹, 裴海龙², 王乃洲¹

1. 华南理工大学自主系统与网络控制教育部重点实验室, 广东广州 510640;
2. 华南理工大学自动化科学与工程学院, 广东广州 510640

收稿日期:2013-02-14 修回日期:2013-03-11 出版日期:2014-01-25 发布日期:2013-03-19
通讯作者: 裴海龙，Tel.：020-87113594 E-mail：auhlpei@scut.edu.cn E-mail:auhlpei@scut.edu.cn
作者简介:王俊男，博士研究生。主要研究方向：航天器的再入飞行控制和空气动力学。Tel：020-87113594 E-mail：jwangsunny@gmail.com；裴海龙男，博士，教授，博士生导师。主要研究方向：空气动力学与飞行控制。Tel：020-87113594 E-mail：auhlpei@scut.edu.cn；王乃洲男，博士研究生。主要研究方向：飞行器的模型以及抗饱和优化控制算法。Tel：020-87113594 E-mail：wangnzhou@sina.com
基金资助:
国家自然科学基金（61174053）；高等学校博士学科点专项科研基金（20100172110023）

Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment

WANG Jun¹, PEI Hailong², WANG Naizhou¹

1. Key Laboratory of Autonomous Systems and Networked Control, Ministry of Education, South China University of Technology, Guangzhou 510640, China;
2. School of Automation Science and Engineering, South China University of Technology, Guangzhou 510640, China

Received:2013-02-14 Revised:2013-03-11 Online:2014-01-25 Published:2013-03-19
Supported by:
National Natural Science Foundation of China (61174053);Research Fund for the Doctoral Program of Higher Education of China (20100172110023)

摘要/Abstract

摘要：

针对再入全过程合理预测热防护罩表面材料烧蚀深度和温度的动态变化问题，提出融合再入轨迹、气动热以及Newton-Raphson和三对角矩阵算法（TDMA）构建动态烧蚀的方法。该方法建立直入式和跳跃式三自由度再入轨迹，应用修正的牛顿流体理论估算气动参数，以及修正的Fay-Riddell和Sutton-Grave理论计算驻点区域的热流密度，利用一维非线性热传导方程模拟了热防护材料的烧蚀过程。仿真结果表明：此方法实现了再入全过程热防护材料烧蚀深度和温度连续动态变化的预测，同样适用于更为复杂结构飞行器的动态烧蚀预测，与热平衡积分法（HBI）相比其结果可靠合理，为进一步优化热防护系统（TPS）提供了一定的参考依据。

关键词: 返回舱, 再入, 气动热, 烧蚀, 有限元法

Abstract:

The ablation of a heat shield subjected to dynamic changes of the surface material depth and temperature can be reasonably predicted in the whole re-entry process. The approach of constructing a dynamic ablation process is presented by combining the reentry trajectory and aerodynamic heat with Newton-Raphson and tridiagonal matrices (TDMA) algorithms. A three degrees of freedom direct and skip re-entry trajectory model is established. The modified Newtonian flow theory,Fay-Riddell and Sutton-Grave theory are adopted to calculate respectively the aerodynamic parameters and stagnation heat flux. A one dimensional nonlinear heat conduction model is employed to simulate the process of thermal protective material ablation. The results of ablation prediction demonstrate that continuous dynamic change of the surface material depth and the temperature can be realized. The proposed method can be applied to more complicated structures of the flight vehicles and the results of it are shown to be reliable and reasonable by comparing them with those of the heat balance integral (HBI) method. This study provides a reference for further optimization of the design of thermal protection systems (TPS).

Key words: crew return vehicle, re-entry, aerodynamic heating, ablation, finite element method

中图分类号:

V411.8

王俊, 裴海龙, 王乃洲. 基于再入轨迹和气动热环境的返回舱烧蚀研究[J]. 航空学报, 2014, 35(1): 80-89.

WANG Jun, PEI Hailong, WANG Naizhou. Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 80-89.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于再入轨迹和气动热环境的返回舱烧蚀研究

Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment

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