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SA0200012.pdf4.98 MB
titleChemical Nonequilibrium Viscous Shock-Layer Analysis over Ablating Surface of Superorbital Re-Entry Capsule
Author(jpn)鈴木, 宏二郎; 藤田, 和央; 安部, 隆士
Author(eng)Suzuki, Kojiro; Fujita, Kazuhisa; Abe, Takashi
Author Affiliation(jpn)東京大学 大学院新領域創成科学研究科; 宇宙科学研究所; 宇宙科学研究所
Author Affiliation(eng)Department of Advanced Energy, Graduate School of Frontier Sciences, The University of Tokyo; Institute of Space and Astronautical Science (ISAS); Institute of Space and Astronautical Science (ISAS)
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 page23
End page42
Publication date2003-03
Languageeng
AbstractThe aerodynamic heating environment with ablation injection and the mass loss rate of the ablator under the superorbital re-entry condition of the MUSES-C sample return capsule are numerically studied by solving the Viscous shock-layer (VSL) equations with the nonequilibrium chemistry of both the air and the ablation gas. The boundary conditions at the ablator surface are formulated by considering the surface oxidation and surface sublimation. Computational results on the variation of the surface mass loss rate with the wall temperature demonstrate that the diffusion-controlled regime and the sublimation regime are successfully described by the present model. The time history of the wall temperature at the stagnation point is estimated along the re-entry trajectory by assuming the energy balance at the surface. The streamwise distributions of the convective heating rate and the surface mass loss rate over the forebody of the capsule are calculated at the peak heating flight condition and their characteristics are clarified. The effects of the pyrolysis gas of hydrocarbon species on the convective heating rate are investigated. The possibility of wall heating augmentation due to the turbulence induced by the ablation injection is also discussed.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所
ISSN0288-433X
NCIDAA10455137
SHI-NOSA0200012000
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/12578


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