高速飛行実証 | NDL Search | National Diet Library

高速飛行実証

Material type: 文書・図像類

Author: 宇宙航空研究開発機構総合技術研究本部ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-01-20

Material Format: Digital

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Note (General)：: The High-Speed Flight Demonstration (HSFD) project is the latest in a series of flight experiments in a research program into reusable space transport...

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Material Type: 文書・図像類
Title: 高速飛行実証
Author/Editor: 宇宙航空研究開発機構総合技術研究本部
Inst. of Space Technology and Aeronautics, Japan Aerospace Exploration Agency
Author Heading: 宇宙航空研究開発機構総合技術研究本部
Inst. of Space Technology and Aeronautics, Japan Aerospace Exploration Agency
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-01-20
Publication Date (W3CDTF): 2006-01-20
Alternative Title: High Speed Flight Demonstration
Periodical title: 宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
No. or year of volume/issue: JAXA-SP-05-010
Volume: JAXA-SP-05-010
Pages: 15-20
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 再利用型宇宙輸送システム
再突入機
高速飛行実証
風洞試験
計算流体力学
遷音速飛行
CNES
空力特性
トルク
reusable space transportation system
reentry vehicle
High Speed Flight Demonstration
wind tunnel test
computational fluid dynamics
transonic flight
aerodynamic characteristic
torque
Target Audience: 一般
Note (General): The High-Speed Flight Demonstration (HSFD) project is the latest in a series of flight experiments in a research program into reusable space transportation systems being conducted by Japan Aerospace Exploration Agency (JAXA). The project consists of two phases which use subscale demonstrators based on the HOPE-X (H-2 Orbiting Plane, Experimental) winged re-entry vehicle configuration. Phase 2 was a drop test from a stratospheric balloon to clarify the transonic aerodynamic characteristics of the HOPE-X configuration and to obtain data to validate wind tunnel tests and Computational Fluid Dynamics (CFD) predictions. The first Phase 2 flight was conducted in July 2003 in collaboration with Centre National d'Etudes Spatiales of France (CNES), which developed and operated the balloon system. Although the experiment had to be discontinued after an anomaly of the recovery system resulted in damage to the vehicle, flight test data were obtained at Mach 0.8, and fully autonomous flight control technologies for the transonic speed region were demonstrated. The data obtained from the HSFD project are expected to provide essential information for development of future reusable space transportation systems.
資料番号: AA0049056003
レポート番号: JAXA-SP-05-010
Access Restrictions: 限定公開
Periodical Title (NCID): AA11984031
https://ci.nii.ac.jp/ncid/AA11984031
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