伸展ノズルの研究:伸展ノズルに作用する動的荷重特性

Material type: 文書・図像類

Author: 長谷川, 恵一ほか

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)：: An extendible nozzle is considered to be a feasible device to improve the performance of booster engines because it has possibilities to provide altit...

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Material Type: 文書・図像類
Title: 伸展ノズルの研究:伸展ノズルに作用する動的荷重特性
Author/Editor: 長谷川, 恵一
日下, 和夫
佐藤, 政裕
只野, 真
森谷, 信一
佐藤, 正喜
Hasegawa, Keiichi
Kusaka, Kazuo
Sato, Masahiro
Tadano, Makoto
Moriya, Shinichi
Sato, Masaki
Author Heading: 長谷川, 恵一
日下, 和夫
佐藤, 政裕
只野, 真
森谷, 信一
佐藤, 正喜
Hasegawa, Keiichi
Kusaka, Kazuo
Sato, Masahiro
Tadano, Makoto
Moriya, Shinichi
Sato, Masaki
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: Research on an extendible nozzle: Characteristics of dynamic loads acting on an extendible nozzle
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: 43-48
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 伸展ノズル
ブースターエンジン
比推力
動荷重
燃焼試験
圧力分布
剥離流
境界層剥離
extendible nozzle
booster engine
specific impulse
dynamic load
firing test
pressure distribution
separated flow
boundary layer separation
Target Audience: 一般
Note (General): An extendible nozzle is considered to be a feasible device to improve the performance of booster engines because it has possibilities to provide altitude compensation and to achieve higher specific impulse. The booster engines with the extendible nozzle have to deploy the extendible nozzle during firing. For the design of the extendible nozzle and its driving mechanics, it is required to clarify the characteristics of dynamic loads acting on the extendible nozzle. In order to clarify the characteristics of dynamic loads, firing tests on a high altitude test stand were conducted with varying the ambient pressure to simulate the altitude change. The thrust and side loads acting on the extendible nozzle were evaluated quantitatively by use of a supporting system consisted of six rods. Using the measured load data and the calculated nozzle pressure distribution data the history of flow separation point was estimated. It was found that the large inverse thrust induced during the transition between full-flow and fully separated flow was caused by the pressure balance around the extendible nozzle.
資料番号: AA0049056009
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