Aerothermal computation research for re-entry vehicles in real gas effect

Paper number

IAC-11,C2,7,17,x10042

Author

Dr. Pan Sha, National University of Defense Technology, China

Coauthor

Dr. Guo-hao DING, National University of Defense Technology, China

Coauthor

Dr. Zhengyu Tian, College of Aerospace and Materials Engineering, National University of Defense Technology, China

Coauthor

Prof. Hua Li, National University of Defense Technology, China

Coauthor

Prof. Zhi-xun Xia, China

Year

2011

Abstract

The present paper is about research of aerothermal computation for re-entry vehicles using numerical simulation methods. The aerodynamic heating on craft’s surface, which is very serious in reentry, has become a remarkable problem for the development of reentry vehicles. As hypersonic flow encounters the vehicle, the kinetic energy associated with hypervelocity flight is converted into increasing the temperature of the air and into endothermic reaction, such as dissociation and ionization of the air near the vehicle surface. The high temperature air with dissociation and ionization reactions brings heat barrier and black barrier problems. 

The reacting Navier-Stokes equations including Park’s two temperature model, Gupta’s air multi-species reaction model and vibrational relaxation were solved to compute aerothermal load. Chemical and vibrational source terms are calculated implicitly.

The GSC (Generic Spherical Capsule) reentry configuration were calculated and studied. The researches on thermal loads and environment , heat flux constitute and surface catalysis property were discussed.

All the work could be instructive for design of re-entry vehicles’ TPS(Thermal Protect System).


Reference

[1]  Frank J. Regan.  Re-Eentry Vehicle Dynamics. [M] AIAA EDUCATION SERIES, 1984

[2]  John J. Bertin.  Hypersonic Aerothermodynamics. [M] AIAA EDUCATION SERIES, 1994

[3]  Ernst Heinrich Hirschel, Claus Weiland. Selected Aerothermodynmic Desigh Problems of Hypersonic Flight Vehicles. [M] Progress in Astronautics Aeronautics Volume 29, 2008

Abstract document

IAC-11,C2,7,17,x10042.brief.pdf

Manuscript document

IAC-11,C2,7,17,x10042.pdf (🔒 authorized access only).

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