200mm径固体ロケットのスピン燃焼実験

Material type: 文書・図像類

Author: 泉川, 宗男ほか

Publisher: 航空宇宙技術研究所

Publication date: 1978-03

Material Format: Digital

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Note (General)：: Spinning combustion tests for a 200mm-dia. class solid propellant rocket were conducted and compared with numerical results. The combustion surface ob...

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Material Type: 文書・図像類
Title: 200mm径固体ロケットのスピン燃焼実験
Author/Editor: 泉川, 宗男
高橋, 守
三谷, 徹
新岡, 嵩
IZUMIKAWA, Muneo
TAKAHASHI, Mamoru
MITANI, Tohru
NIIOKA, Takashi
Author Heading: 泉川, 宗男
高橋, 守
三谷, 徹
新岡, 嵩
IZUMIKAWA, Muneo
TAKAHASHI, Mamoru
MITANI, Tohru
NIIOKA, Takashi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1978-03
Publication Date (W3CDTF): 1978-03
Alternative Title: Spinning Combustion Tests of 200mm-dia. Solid Propellant Rocket Motor
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-530
No. or year of volume/issue: 530
Volume: 530
Pages: 13-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Spinning combustion tests for a 200mm-dia. class solid propellant rocket were conducted and compared with numerical results. The combustion surface obtained by the extinction test shows that the acceleration-produced burning effect is limited to the region having the angle 85.5 deg to 90 deg between the combustion surface and the acceleration vector. This angle extent was independent of the burning time and the grain configuration. The aspects of the combustion surface, together with the transient burning-rate augmentation data given by the strand experiment, were included in a model for computer programming of the predicted pressure-time diagram. The predicted pressure history and the variation of grain configuration with time show a qualitatively good comparison.
資料番号: NALTR0530000
レポート番号: NAL TR-530
Access Restrictions: 限定公開
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