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Thermal Responses of Ablator for Reentry Capsules with Superorbital Velocity
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Description
This 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.
資料番号: SA0200025000
Journal
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- The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
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The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule 17 201-215, 2003-03
宇宙科学研究所
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Details 詳細情報について
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- CRID
- 1050566774915439488
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- NII Article ID
- 120006834557
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- NII Book ID
- AA10455137
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- ISSN
- 0288433X
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- Web Site
- http://id.nii.ac.jp/1696/00033246/
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- Text Lang
- en
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- Article Type
- departmental bulletin paper
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- Data Source
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- IRDB
- CiNii Articles
