CFDとFEM熱解析連成による熱空力環境の同定と宇宙往還機再突入飛行実験への応用

• Material Type: 規格・テクニカルリポート類
• Title: CFDとFEM熱解析連成による熱空力環境の同定と宇宙往還機再突入飛行実験への応用
• Author/Editor: 山本, 行光; Yamamoto, Yukimitsu
• Author Heading: 山本, 行光; Yamamoto, Yukimitsu
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 2000-12
• Publication Date (W3CDTF): 2000-12
• Alternative Title: Evaluation of aerothermodynamic environments by Coupling CFD and FEM thermal response analysis and its application for re-entry flight experiments of OREX, HYFLEX and HOPE-X
• Periodical title: 航空宇宙技術研究所特別資料
• No. or year of volume/issue: 46
• Volume: 46
• Pages: 105-114
• ISSN (Periodical Title): ISSN : 0289-260X
• Text Language Code: jpn
• Subject Heading: 宇宙輸送機; 再突入飛行; 熱空力環境; CFD; ナビエ-ストークスCFDコード; 熱応答解析; OREX; HYFLEX; 極超音速飛行; 熱防護システム; 計算流体力学; 有限要素法; 軌道再突入実験機; 極超音速飛行実験; space transportation vehicle; reentry flight; aerothermodynamic environment; Navier Stokes CFD code; thermal response analysis; hypersonic flight; thermal protection system; computational fluid dynamics; finite element method; Orbital Reentry Experiment; Hypersonic Flight Experiment
• Target Audience: 一般
• Note (General): 航空宇宙技術研究所 7-9 Jun. 2000 東京 日本; National Aerospace Laboratory 7-9 Jun. 2000 Tokyo Japan; Navier-Stokes CFD (Computational Fluid Dynamics) code and FEM (Finite Element Method) thermal response analysis are coupled in order to simulate more completely the aerothermal environments of hypersonic flight of space transportation vehicles. Present coupling methods are first applied to the analysis of the infrared aerothermodynamic heating measurements of a sphere model at NAL Mach 10 hypersonic wind tunnel. Through this analysis, basic validation has been made by comparisons of the temperature increase on the sphere surface. The present coupling analysis is also made to simulate aerothermodynamic environments of OREX (Orbital Re-Entry Experiment) and HYFLEX (Hypersonic Flight Experiment) re-entry flights. Numerical computations are performed along each flight trajectory. For HYFLEX flight analysis, simulations are further extended to the total thermal-structural analysis including internal aluminum structures, such as frames and stringers. Numerical results are compared with the flight data of OREX and HYFLEX experiments and it is demonstrated that the aerothermodynamic heating and temperature history can be almost completely reproduced by the present coupling simulations. Finally, TPS (Thermal Protection System) thermal response analyses of HOPE-X (H-2 Orbiting Plane-Experimental) re-entry flight are being made and recent numerical results are introduced.; 資料番号: AA0028635020; レポート番号: NAL SP-46
• Access Restrictions: インターネット公開
• Periodical Title (NCID): AN10097345; https://ci.nii.ac.jp/ncid/AN10097345
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ

• Summary, etc.: ナビエ-ストークスCFD(計算流体力学)コードとFEM(有限要素法)熱応答解析を連成させて宇宙輸送機の極超音速飛行の熱空力環境のより完全なシミュレーションを行った。今回の連成手法を、最初に航空宇宙技術研究所のマッハ10極超音速風洞における球型モデルの周りの赤外線空力加熱計測の解析に適用した。この手法...