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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.

収録刊行物

  • 宇宙科学研究所報告. 特集

    宇宙科学研究所報告. 特集 6, 55-106, 1983-03

    宇宙航空研究開発機構

各種コード

  • NII論文ID(NAID)
    110000222623
  • NII書誌ID(NCID)
    AN00354485
  • 本文言語コード
    JPN
  • ISSN
    02859920
  • NDL 記事登録ID
    2587623
  • NDL 雑誌分類
    ZM33(科学技術--宇宙科学)
  • NDL 請求記号
    Z15-410
  • データ提供元
    NDL  NII-ELS 
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