並列タイトル等Catalyzed low burning rate propellants for upper-stage solid rocket motor
タイトル(掲載誌)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-805
一般注記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
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45063&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース(IRDB)(機関リポジトリ)
提供元機関・データベース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