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高膨張ノズル内の液体二次噴射推力方向制御
https://jaxa.repo.nii.ac.jp/records/44709
https://jaxa.repo.nii.ac.jp/records/44709bcdd2e01-4b39-4a7d-94a0-506169e621d8
名前 / ファイル | ライセンス | アクション |
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naltr00458.pdf (1.0 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 | 高膨張ノズル内の液体二次噴射推力方向制御 | |||||
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 | Liquid Injection Thrust Vector Control in High Expansion Rocket Nozzles | |||||
著者 |
升谷, 五郎
× 升谷, 五郎× 鎮西, 信夫× 石井, 進一× 工藤, 賢司× 小室, 智幸× MASUYA, Goro× CHINZEI, NOBUO× ISHII, Shinichi× KUDO, Kenji× KOMURO, Tomoyuki |
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著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, 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-458 巻 458, p. 14, 発行日 1976-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This paper describes an experimental study conducted on LITVC in high expansion rocket nozzles utilizing a 3kN thrust solid rocket motor. The nozzles were 15 deg conical. Freon 114B2, 70% strontium perchlorate/water solutions and 90% hydrogen peroxide were used as the injectant. More than thirteen different combinations of nozzle expansion ratio and injection location were tested with each injectant. All firings were conducted at the Rocket Engine High Altitude Test Facility of NAL. Main thrust, side force and yaw moment were measured by the four component thrust stand, after which the point of action of side force and main thrust augmentation were calculated. The performance of LITVC was evaluated by the moment about the center of gravity of a rocket. The effects of injectant, nozzle expansion ratio, injection location and location of the center of gravity of a rocket were illustrated. | |||||
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: NALTR0458000 | |||||
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-458 |