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H-2ロケットにおけるSRB分離の数値解析
https://jaxa.repo.nii.ac.jp/records/37317
https://jaxa.repo.nii.ac.jp/records/373173abd2045-a303-4a6c-8c16-fb052763576a
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | H-2ロケットにおけるSRB分離の数値解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | H-2ロケット | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SRB分離 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れ場解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ナビエ・ストークス方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | LU-ADI手法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 3次元薄層 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SRB | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 固体燃料ロケットブースタ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 上下交互方向陰的差分法 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | H 2 rocket | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SRB separation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow field analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Navier Stokes equations | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | LU ADI procedure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | three dimensional thin layer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SRB | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | solid rocket booster | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lower upper alternating direction implicit procedure | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Numerical analysis of SRB separation from H-2 rocket | |||||
著者 |
大山, 健一
× 大山, 健一× 海田, 武司× 清水, 隆三× Oyama, Kenichi× Kaiden, Takeshi× Shimizu, Ryuzo |
|||||
著者所属 | ||||||
三菱重工業 | ||||||
著者所属 | ||||||
三菱重工業 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Heavy Industries Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Heavy Industries Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 41, p. 23-28, 発行日 1999-02 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 航空宇宙技術研究所 24-26 Jun. 1998 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | H-2ロケットにおけるSRB(固体燃料ロケットブースタ)分離の数値解析を運動解析にCFD(計算流体力学)の適用することの妥当性を確認するため運動方程式と連合した時間精度の良好な解法によって行った。流れ場の数値解析にはChimera手法を用いた。幾何学的成分は重ね合わせ格子法で表し、3次元薄層ナビエ・ストークス方程式の解法にはLU-ADI(Lower-Upper Alternating Direction Implicit)法を採用した。H-2ロケットから分離後のSRBの運動は運動方程式を解くことにより求めた。計算結果は実際の飛行におけるSRB分離の映像と比較した。また、現在開発中のH-2AロケットにおけるSRB-Aの分離解析も行った。H-2AロケットにおけるSRB-Aの分離はH-2ロケットの場合と大きく異なった。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The phenomena of the SRB (Solid Rocket Booster) separation from the H-2 rocket are simulated numerically by the time-accurate flow solver coupled with the equations of motion for the validation of CFD (Computational Fluid Dynamics) application to dynamic problems. The numerical method for the flow simulation is based on the Chimera technique. Overset grid technique is used to represent the each geometric component and LU-ADI (Lower-Upper Alternating Direction Implicit) procedure is adopted to solve the three dimensional thin layer Navier-Stokes equations. The motion of the SRB after the separation from the H-2 rocket is calculated by solving the equations of motion. Computational result is compared with the picture obtained during the SRB separation in the actual launch. And also the phenomena of the SRB-A separation from the H-2A rocket which is being developed are simulated. The phenomena of the SRB-A separation from the H-2A rocket are quite different from those of the case of the H-2 rocket. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0001958003 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-41 |