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推力中断型固体ロケット用プロペラントの消火圧力
https://jaxa.repo.nii.ac.jp/records/44587
https://jaxa.repo.nii.ac.jp/records/4458708ab986f-7c9b-4156-b6cf-17245e4735f7
名前 / ファイル | ライセンス | アクション |
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naltr00341.pdf (6.8 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 推力中断型固体ロケット用プロペラントの消火圧力 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Low-Pressure Deflagration Limit of Controllable Solid Rocket Propellants | |||||
著者 |
五代, 富文
× 五代, 富文× 清水, 盛生× 伊藤, 克弥× 西村, 久男× 種村, 利春× 藤原, 勉× GODAI, Tomifumi× SHIMIZU, Morio× ITO, Katsuya× NISHIMURA, Hisao× TANEMURA, Toshiharu× FUJIWARA, Tsutomu |
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著者所属 | ||||||
航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属 | ||||||
東京都庁 | ||||||
著者所属 | ||||||
元・航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所宇宙研究グループ | ||||||
著者所属(英) | ||||||
en | ||||||
Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Metropolitan Government | ||||||
著者所属(英) | ||||||
en | ||||||
Former Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory(NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-341 巻 341, p. 16, 発行日 1973-10 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Low-pressure deflagration limit(Pdl) of controllable solid rocket propellants was experimentally investigated using low-pressure combustion chambers and micro video-recorder. Pdl was affected by the specimen size, and this scale effect is explained by heat losses from the burning propellant to the surroundings. The dependence of Pdl on specimen size and inert gas composition was observed and it would seem that the main heat loss should be by radiation in the extinguishment of propellant at subatmospheric pressures. Initial temperature of propellant had a minor effect on Pdl. The effect of compositional variables of propellant on subatmospheric combustion and Pdl was studied. These variables were oxidizer blend ratio, binder type, oxidizer-fuel mixture ratio, aluminium content, mean particle diameter of oxidizers and shape and size of aluminium powders. Pdl was not so much affected by compositional variablee as expected. Aluminium agglomeration resulted in larger variations in subatmospheric combustion and subsequent extinguishment. Behavior of combustion at subatmospheric pressures and Pdl trend can be explained by qualitative theoretical consideration. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0341000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-341 |