The test results of small LOX/LH2 engines for two propulsion systems, a pump fed system and a pressure fed system are reported. The pump fed system has the advantages of higher performances and higher mass fraction. The pressure fed system has the advantages of higher reliability and relative simplicity. Adoption of these cryogenic propulsion systems for upper stage of launch vehicle increases the payload capability with low cost. The 1,000 kg thrust class engine was selected for this cryogenic stage. A thrust chamber assembly for the pressure fed propulsion system was tested. It is indicated that it has good performance to meet system requirements.


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    Title :

    LOX/LH2 propulsion system for launch vehicle upper stage, test results


    Contributors:
    Ikeda, T. (author) / Imachi, U. (author) / Yuzawa, Y. (author) / Kondo, Y. (author) / Miyoshi, K. (author) / Higashino, K. (author)

    Publication date :

    1984-09-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Lox/LH2 Propulsion System for Launch Vehicle Upper Stage, Test Results

    T. Ikeda / U. Imachi / Y. Yuzawa et al. | NTIS | 1984



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