著者
棚次 亘弘 成尾 芳博 倉谷 健治 秋葉 鐐二郎 岩間 彬
出版者
宇宙航空研究開発機構
雑誌
宇宙科学研究所報告. 特集 (ISSN:02859920)
巻号頁・発行日
vol.6, pp.55-106, 1983-03

The Institute of Space and Astronautical Science (ISAS) has developed the two thrust level of LH_2/LOX propulsion system; one is the 7-ton thrust level one and the other is the 10-ton thrust level one. The 7-ton thrust level engine was aimed at usimed at using for the second stage of the Mu vehicle. And the 10-ton thrust level engine is planned to back up the H-1 project being performed by the National Space Development Agency (NASDA). The both engines are the gas generator cycle which consists of the tubular wall thrust chamber, the "ISAS Arrangement" turbopump, the "reverse-flow" type gas generator and the solidpropellant turbine spinner. The development of the 7-ton thrust level engine has started in 1976. By 1980 have almost finished the development tests of its major components. In early 1980 the engine system has been integrated and then the verification tests have been carried out. On the other hand, the development study of the 10-ton thrust level engine started in 1979. In midyear 1981 the engine system has been completed. The both engines were combined with the battle-ship type of tank system, and stage firing tests were carried out successfully from Sep. 1981 through Apr. 1982. The 7-ton thrust level engine worked well within the range from 78% to 1l8% of its rated power. And the 10-ton thrust one worked well within the range from 75% to ll3%. In the present paper, an outline of the LH_2/LOX engine systems developed in ISAS, the progress in the establishing of an operation of engine systems and the performance capability of two systems are described.
著者
岩間 彬 青柳 鐘一郎 木村 元雄 井原 博之
出版者
一般社団法人 日本エネルギー学会
雑誌
燃料協会誌 (ISSN:03693775)
巻号頁・発行日
vol.51, no.2, pp.79-95, 1972-02-20 (Released:2011-02-23)
参考文献数
31

From a view point of safety measure against the fire hazard involved with aircraft crash or ditch and singular hydrodynamical fluid motions in space flight and refueling with liquid rocket tankage, feasibility of gelled hydrocarbon fuels and propellants is discussed. It is concluded that O/W (oil-in-water) type gelled hydrocarbons are most promising as the safety fuels, resulting from a comparison in the rheological and combustion properties with the other gelled fuels; slurry, scaffold and thickened (highly viscous) ones. Physical properties and flammability of very high internal phase ratio gelled JP-4 and kerosene, ranged 96 to 99 vol% fuel content, and of N2H4/JP-4 gelled propellant developed by ISAS, Univ. of Tokyo and Mitsubishi Oil Company are described.
著者
棚次 亘弘 成尾 芳博 長友 信人 岩間 彬 秋葉 鐐二郎 倉谷 健治
出版者
宇宙航空研究開発機構
雑誌
東京大学宇宙航空研究所報告 (ISSN:05638100)
巻号頁・発行日
vol.16, no.2, pp.859-891, 1980-05

推力7トン級液水/液酸ロケットエンジン用ターボポンプを駆動するガスジェネレーターの設計および試験を昭和52年から実施し,その開発を完了した.このガスジェネレーターはリバースフロー型のものであり,撹拌リング付の球形燃焼室と12個の均一混合比型の同軸インジェクターおよびスタートバルブから構成されている.8回のガスジェネレーター単体での試験および10回のターボポンプとの組合せ試験によって,性能および機能の確認を行った.インジェクター,燃焼室およびタービン部に焼損は認められず,燃焼および混合が良好に行われているものと思われる.現在までの総燃焼時間は204秒である.ここでは,東大宇宙研において開発したガスジェネレーターの設計諸元,試験設備および試験結果を報告する.