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SA0200025.pdf3.64 MB
titleThermal Responses of Ablator for Reentry Capsules with Superorbital Velocity
Author(jpn)山田, 哲哉; 稲谷, 芳文; 平井, 研一
Author(eng)Yamada, Tetsuya; Inatani, Yoshifumi; Hirai, Ken'ichi
Author Affiliation(jpn)宇宙科学研究所; 宇宙科学研究所; アイ・エイチ・アイ・エアロスペース
Author Affiliation(eng)Institute of Space and Astronautical Science (ISAS); Institute of Space and Astronautical Science (ISAS); IHI Aerospace Company
Issue Date2003-03
Publisher宇宙科学研究所
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
Volume17
Start page201
End page215
Publication date2003-03
Languageeng
AbstractThis paper summarizes thermal responses of ablator for reentry capsules with superorbital velocity together with analysis method and the experimental data acquisition in the designing and development process of the MUSES-C reentry capsule. On the prediction of thermo-chemical response of the carbon-phenolic ablator heat shield for the MUSES-C reentry capsule, an ablation analysis code has been developed taking account of the effect of the pyrolysis gas on the surface recession rate. A validation study of the mathematical model for the ablation has been conducted through the comparison between the numerical results and experimental ones which have been carried out in the arcjet facilities of ISAS and NASA/ARC.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所
ISSN0288-433X
NCIDAA10455137
SHI-NOSA0200025000
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/2108


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