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

WANG Jun; PEI Hailong; WANG Naizhou

doi:10.7527/S1000-6893.2013.0167

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2014 , Vol. 35 >Issue 1: 80 - 89

DOI: https://doi.org/10.7527/S1000-6893.2013.0167

Fluid Mechanics and Flight Mechanics

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

WANG Jun ,
PEI Hailong ,
WANG Naizhou

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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 date: 2013-02-14

Revised date: 2013-03-11

Online 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)

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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

Cite this article

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 . DOI: 10.7527/S1000-6893.2013.0167

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