上段用後方点火方式ロケットにおける推進薬の低燃速化(負触媒添加法)

Material type: 文書・図像類

Author: 新岡, 嵩ほか

Publisher: 航空宇宙技術研究所

Publication date: 1984-04

Material Format: Digital

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Note (General)：: Composite soild propellants catalyzed to lower the burning rate were investigated in this paper. To increase nozzle expansion ratio with a fixed rocke...

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Material Type: 文書・図像類
Title: 上段用後方点火方式ロケットにおける推進薬の低燃速化(負触媒添加法)
Author/Editor: 新岡, 嵩
三谷, 徹
高橋, 守
泉川, 宗男
岸, 和男
楢田, 敏寛
NIIOKA, Takashi
MITANI, Toru
TAKAHASHI, Mamoru
IZUMIKAWA, Muneo
KISHI, Kazuo
NARATA, Toshihiro
Author Heading: 新岡, 嵩
三谷, 徹
高橋, 守
泉川, 宗男
岸, 和男
楢田, 敏寛
NIIOKA, Takashi
MITANI, Toru
TAKAHASHI, Mamoru
IZUMIKAWA, Muneo
KISHI, Kazuo
NARATA, Toshihiro
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1984-04
Publication Date (W3CDTF): 1984-04
Alternative Title: Catalyzed low burning rate propellants for upper-stage solid rocket motor
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-805
No. or year of volume/issue: 805
Volume: 805
Pages: 21-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Composite soild propellants catalyzed to lower the burning rate were investigated in this paper. To increase nozzle expansion ratio with a fixed rocket motor length, a smaller nozzle throat, and thus a lower-burning-rate propellant are needed for upper stage motors. A few types of catalysis were selected for experiments in consideration of their propellant flame structure : additives such as oxamide and urea considered for their effect on the solid-phase or decomposition flame of AP, additives such as alkali-metal and halogen compounds for their effect on the diffusion flame of released oxygen and fuel binder, and inert material such as aluminum oxide. Alkali-metal and halogen compounds had no effect on solid propellant, although they are well known as flame suppressants. Urea was the best for decreasing the burning rate, and the specific impulse decrease obtained by the chemical equilibrium calculation was the smallest, but there was a problem with its accomodation to the binder. In the end oxamide turned out to be the best synthetic additive. Utilizing the standard propellant (12％｡HTPB, 72％AP and 16％Al) and the propellant catalyzed by oxamide, 400 mm diameter spherical motors with aft-end igniter were made and demonstration firing tests were conducted.
資料番号: NALTR0805000
レポート番号: NAL TR-805
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