@inproceedings{oai:jaxa.repo.nii.ac.jp:00014357,
 author = {渡邉, 保真 and 鈴木, 宏二郎 and 山田, 和彦 and Watanabe, Yasumasa and Suzuki, Kojiro and Yamada, Kazuhiko},
 book = {宇宙航行の力学シンポジウム: 平成22年度, Symposium on Flight Mechanics and Astrodynamics: 2010},
 month = {Aug},
 note = {宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Symposium on Flight Mechanics and Astrodynamics,  2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, An atmospheric-entry capsule needs to endure intense aerodynamic heating during supersonic flight in the atmosphere. Especially in the case of an aeroshell membrane reentry capsule, severe heating over the membranous surface could be a serious problem in its thermal protection. Hence, it is necessary to clarify the effect of design parameters on aerodynamic and aerothermodynamic characteristics such as aerodynamic heating and drag coefficients. In this work, the effect of several design parameters on the maximum heating rate over the membrane are estimated based on CFD parametric study under the most severe condition fom a viewpoint of the aerodynamic heating along the trajectory of the sub-orbital flight experiment by the sounding rocket that will be planned to be launched in the next year. In the numerical analysis, the capsule shape is assumed to be axisymmetric and the flow field is calculated based on two-dimensional axisymmetric Navier-Stokes equations. In addition to the flow analysis, the membrane deformation due to aerodynamic force is estimated based on a simple deformation model proposed in this study. It is revealed that the heating rate attains maxima at a certain point on the torus membrane. In order to lessen the maximum heating rate over membranous surface, the flare angle of the membrane should be over 65 degrees. It is also shown that the attachment between the outer frame of torus and the membrane should be made in flush manner for the torus not to protrude from the membrane surface in the upstream direction., 資料番号: AA0065106038},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {柔構造エアロシェル大気突入機における形状パラメータの膜面加熱率への影響に関する数値解析},
 year = {2011}
}