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ノズル試験のための端面燃焼固体ロケット・モータの開発(<特集>観測ロケット基礎開発研究特集号)
https://jaxa.repo.nii.ac.jp/records/31731
https://jaxa.repo.nii.ac.jp/records/317317031c51a-008c-42b1-9896-2109704f8489
名前 / ファイル | ライセンス | アクション |
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SA0124757.pdf (2.5 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | ノズル試験のための端面燃焼固体ロケット・モータの開発(<特集>観測ロケット基礎開発研究特集号) | |||||
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_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Development of an End-Burning Solid Motor and the Application to Nozzle Insert Material Test | |||||
著者 |
霜田, 正隆
× 霜田, 正隆× 山谷, 寿夫× 祖父江, 照雄× 青柳, 鐘一郎× 斉藤, 猛男× 岩間, 彬× SHIMODA, Masataka× YAMAYA, Toshio× SOFUE, Teruo× AOYAGI, Shoichiro× SAITO, Takeo× IWAMA, Akira |
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著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
the Institute of Space and Aeronautical Science University of Tokyo | ||||||
出版者 | ||||||
出版者 | 東京大学宇宙航空研究所 | |||||
書誌情報 |
東京大学宇宙航空研究所報告 巻 13, 号 1_B, p. 403-445, 発行日 1977-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An end-burning solid motor has been developed, using hard-type polyvinyl chloride restrictor. This polyvinyl chloride tube capable of being expanded remarkably in the radial direction by the internal stress relaxation due to heating, was proved to be feasible as a restrictor for end-burning motors. The motors were applied for testing rocket nozzle insert materials: graphites, metal-oxide coating graphites, tungsten coating graphite, silicon-carbide coating graphite, sintered copper-tungsten, silicon nitride and miscellaneous fiber-reinforced plastics. Five propellants with widely different flame temperatures, contents of condensed combustion products, oxidation characteristics and firing durations were used. The material performing best with these propellant except in the case of oxygen-augmented motor was some graphites on which tungsten was deposited with the reduction of WFe- Simple graphite, refractory metal oxide and silicon carbide coating graphites, sintered copper-tungsten and silicon nitride indicated poor resistance to erosion or thermal cracking at severer conditions. Though fiber reinforced plastic nozzle inserts were the least erosion-resistant materials, they are promising for the application to giant rocket motors in view of good resistance to thermal stress, isotropic erosion rates and production feasibility. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0563-8100 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00161914 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0124757000 |