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SA0200027.pdf3.38 MB
titleAn Integrated Numerical Method for Predicting Aerodynamic Heating Environment for MUSES-C Entry Capsule with Ablation
Author(jpn)澤田, 恵介
Author(eng)Sawada, Keisuke
Author Affiliation(jpn)東北大学大学院 工学研究科 航空宇宙工学専攻
Author Affiliation(eng)Department of Aeronautics and Space Engineering, Tohoku University
Issue Date2003-03
Institute of Space and Astronautical Science
Publication titleThe Institute of Space and Astronautical Science report. S.P.
Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
Start page233
End page244
Publication date2003-03
AbstractAn integrated numerical method to obtain trajectory-based aerodynamic heating environment for entry probe vehicles with ablation is briefly described. In this method, a thermochemical nonequilibrium CFD code is loosely coupled with an ablation module along the entry trajectory. Radiative heating is estimated by the use of multi-band radiation module. The effect of earlier turbulent transition of the boundary layer due to ablation product gas is included. Calculated results for MUSES-C sample return capsule are shown and are compared with the results of existing analysis.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所

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