著者
森 大吉郎
出版者
三菱重工業
雑誌
三菱重工技報 (ISSN:03872432)
巻号頁・発行日
vol.3, no.5, pp.493-499, 1966-09
著者
森 大吉郎
出版者
公益社団法人 低温工学・超電導学会
雑誌
低温工学 (ISSN:03892441)
巻号頁・発行日
vol.17, no.4, pp.215-221, 1982-08-30 (Released:2010-02-26)

Noticing the excellent performance of liquid hydrogen-liquid oxygen (LH2/LOX) propulsion system, the Institute of Space & Astronautical Science (ISAS) has started the preliminary study in 1971, and since 1975, full-scale development program of the engine, which has the capability of 7ton thrust in vacuum, has been undertaken.Various development tests of the engine components (thrust chamber, turbopump, gas-generator and turbine spinner etc.) have been conducted at the Noshiro Testing Center of ISAS.Integration tests of the stage, comprised of thrust chamber, turbopump, gas-generator and tank, have been carried out from September through December in 1981 with fairy good results.In the present paper, major features and characteristics of this 7ton engine are summarized.
著者
森 大吉郎
出版者
東京大学生産技術研究所
雑誌
生産研究 (ISSN:0037105X)
巻号頁・発行日
vol.13, no.10, pp.332-335, 1961-10-01
著者
森 大吉郎 三石 智 野口 瞭 浦川 明
出版者
東京大学生産技術研究所
雑誌
生産研究 (ISSN:0037105X)
巻号頁・発行日
vol.16, no.11, pp.349-351, 1964-11-01

p.351からp.393へ続く
著者
森 大吉郎 橋元 保雄 中田 篤 上杉 国憲 西田 稔夫 福沢 清
出版者
宇宙航空研究開発機構
雑誌
宇宙科学研究所報告 (ISSN:02852853)
巻号頁・発行日
vol.17, pp.1-69, 1984-02
被引用文献数
1

Mu rocket assembly and launch system was renewed on the same place where the former one had stood on. After breaking down of the former one, the foundation work started on April 1981,and all of the construction finished on August 1982. This system consists of a rocket assembly tower and a launcher. The assembly tower is a steel-framed truss structure building which has 11 floors and contains cranes, big doors, and movable floors necessary to bring in, assemble, and check out the Mu rocket. This tower is 43m high, 18m wide, 13m deep, and 700 ton in weight. The launcher is 300 ton in weight and made up of a boom structure and guide rails on which a rocket slides away. This launcher can revolve by bogies on a circular rail from the assembly tower toward the launching point. A flame deflector cooled by water is automatically installed to the launcher during its revolution. On February 20 1983,M-3S-3 rocket was successfully launced as the first satellite launch using this system.