加速度場におけるコンポジット推進薬の燃焼

Material type: 文書・図像類

Author: 石井, 進一ほか

Publisher: 航空宇宙技術研究所

Publication date: 1973-12

Material Format: Digital

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Note (General)：: Up to the present all theories, that were described by the parameter including some unknown variables, were not able to express explicitly the acceler...

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Material Type: 文書・図像類
Title: 加速度場におけるコンポジット推進薬の燃焼
Author/Editor: 石井, 進一
新岡, 嵩
三谷, 徹
高橋, 守
泉川, 宗男
ISHII, Shinichi
NIIOKA, Takashi
MITANI, Tohru
TAKAHASHI, Mamoru
IZUMIKAWA, Muneo
Author Heading: 石井, 進一
新岡, 嵩
三谷, 徹
高橋, 守
泉川, 宗男
ISHII, Shinichi
NIIOKA, Takashi
MITANI, Tohru
TAKAHASHI, Mamoru
IZUMIKAWA, Muneo
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1973-12
Publication Date (W3CDTF): 1973-12
Alternative Title: Combustion of Composite Propellants in Acceleration Field
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-354
No. or year of volume/issue: 354
Volume: 354
Pages: 13-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Up to the present all theories, that were described by the parameter including some unknown variables, were not able to express explicitly the acceleration sensitivity of the buring rate of solid propellants. This analysis containing the formation mechanism of a pit can predict unmerically the effects of aluminum content, the mass median diameter and the variance of aluminum particle size distribution. Furthemore, using slab motors, we carried out our tests for ten kinds of composite propellants with acceleration loads(0～350g) directed normal into the combustion surface, and the experimental results were compared with the analytical ones. The increasing aluminum particle size is likely to induce the more sensitive burning rate, but the effect of the aluminum content do not show the general character for the burning rate augmentation. The acceleration sensitivity of the burning rate would rather depend strongly upon the static burning rate, and it should be noticed that the pressure dependence of the burning rate augmentation for the composite propellants is completely opposite to that for the CMDB propellants.
資料番号: NALTR0354000
レポート番号: NAL TR-354
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