極短時間用多分力free-flight力計測法の研究開発

Material type: 文書・図像類

Author: 丹野, 英幸ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-11-01

Material Format: Digital

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Note (General)：: Multi-component force measurement technique within short test period has been researched for the free-piston shock tunnel HIEST. With the technique, a...

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Material Type: 文書・図像類
Title: 極短時間用多分力free-flight力計測法の研究開発
Author/Editor: 丹野, 英幸
佐藤, 和雄
小室, 智幸
伊藤, 勝宏
Tanno, Hideyuki
Sato, Kazuo
Komuro, Tomoyuki
Ito, Katsuhiro
Author Heading: 丹野, 英幸
佐藤, 和雄
小室, 智幸
伊藤, 勝宏
Tanno, Hideyuki
Sato, Kazuo
Komuro, Tomoyuki
Ito, Katsuhiro
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-11-01
Publication Date (W3CDTF): 2006-11-01
Alternative Title: Research and development on multi-component free-flight force measurement technique within short test duration
Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度　宇宙航空研究開発機構　総合技術研究本部　宇宙科学研究本部　研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
No. or year of volume/issue: JAXA-SP-06-006
Volume: JAXA-SP-06-006
Pages: 119-122
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: フリーフライト試験装置
高エンタルピ衝撃風洞
風洞試験
空力天秤
空力測定
動特性
よどみ点
風洞模型
固有振動
計算流体力学
free flight test apparatus
high enthalpy shock tunnel
wind tunnel test
aerodynamic balance
aerodynamic measurement
dynamic response
stagnation point
wind tunnel model
characteristic vibration
computational fluid dynamics
Target Audience: 一般
Note (General): Multi-component force measurement technique within short test period has been researched for the free-piston shock tunnel HIEST. With the technique, aerodynamic force was obtained as measured acceleration and mass of the model, which was weakly suspended with thin wires. To improve time resolution, digital signal recovery scheme with de-convolution calculation was also applied. For the force measurement in HIEST, time resolution of the measurement was expected to order of 1 x 10(exp -5) sec. Feasibility of the measurement technique will be evaluated in near future through the wind tunnel test in HIEST with the standard hypersonic model HB-2.
資料番号: AA0049500026
レポート番号: JAXA-SP-06-006
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