JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
SA0200014.pdf3.52 MB
titleInfluences of Transport Model on Heating Rate of Reentry Vehicles
Author(jpn)大津, 広敬; 藤田, 和央; 安部, 隆士
Author(eng)Otsu, Hirotaka; Fujita, Kazuhisa; Abe, Takashi
Author Affiliation(jpn)静岡大学; 宇宙科学研究所; 宇宙科学研究所
Author Affiliation(eng)Shizuoka University; 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 page53
End page65
Publication date2003-03
Languageeng
AbstractWe assessed the effect of the models of transport properties for the estimation of the hypersonic reentry heating environment from an engineering point of view. Among the transport properties, we focus on the diffusion of chemical species. For this purpose, the following three models; Stefan-Maxwell model, Yos model, and Lee model are evaluated. The nominal flight condition for the evaluation is the reentry speed of 11.6 km/s at the altitude of 64 km which corresponds to the most severe reentry flight condition for a super-orbital reentry such MUSES-C mission. In the nominal flight condition case, under both the non-catalytic wall condition and the full-catalytic wall condition, the Lee model shows a discrepancy with the other two models and gives a higher heat flux. On the contrary, the Stefan-Maxwell model and the Yos model show a reasonably good agreement between them. The discrepancy between the Lee model and the others is caused by the contribution of diffusion of enthalpy. The discrepancy between the Lee model and the others increases with an increase of the flight velocity while the discrepancy shows only a negligible dependency on the atmospheric density. The increase of the discrepancy is attributed to the increase of the chemical species of dissociated air with the increase of the flight velocity. Because of this, even the Lee model is acceptable in a low reentry speed range such a reentry from LEO. However the Lee model is hardly acceptable for an application to the higher velocity reentry such as a super-orbital reentry. On the other hand, the discrepancy between the Stefan-Maxwell model and the Yos model is reasonably small in all the circumstance. As for the calculation cost, the Stefan-Maxwell model is about two times expensive than other two models. Therefore, in a view point of estimating the heat flux for the hypersonic reentry flight vehicle with a reasonable accuracy and a reasonable computation cost, the Yos model is the most recommendable among the three models considered in this study.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所
ISSN0288-433X
NCIDAA10455137
SHI-NOSA0200014000
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/3334


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.