The HERMES space plane is a manned, reusable vehicle, to be launched on the new ARIANE 5 launcher into low earth circular and polar orbits. After separation from ARIANE 5, HERMES is manoeuvered to its required operational orbit. Two propulsion concepts for orbit insertion are under discussion: an integrated reusable system and a separated, expendable system. The integrated system was used as a baseline in this study. The impact on the study results, when using an expendable system, was analysed. The design steps of the baseline flow scheme of the propulsion system are discussed. Results of several trade-offs which led to the selection of the baseline propulsion system flow scheme are presented. The impact of the recent reconfiguration of HERMES on the flow scheme is shown.


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    Title :

    Hermes propulsion system design


    Additional title:

    Auslegung des Hermes-Antriebssystems


    Contributors:
    Immich, H. (author) / Hopmann, H. (author) / Calabro, M. (author)

    Published in:

    AIAA-Papers ; Jul ; 1-7


    Publication date :

    1987


    Size :

    7 Seiten, 4 Bilder, 3 Tabellen, 3 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Hermes propulsion system design

    IMMICH, H. / HOPMANN, H. / CALABRO, M. | AIAA | 1987


    Hermes Propulsion System

    H. Immich / H. Hopmann / T. Caussin | NTIS | 1987


    HERMES propulsion system design and modelization

    HAESELER, D. / IMMICH, H. / SCHMIDT, G. et al. | AIAA | 1988



    HERMES propulsion system design and modelization : AIAA-ASME-SAE-ASEE 24th Joint Propulsion Conference, 11.-13.7.1988, Boston, Massachusetts

    Unternehmensbereich Raumfahrt, Messerschmitt-Bölkow-Blohm GmbH (MBB), Ottobrunn | TIBKAT | 1988