The initial baseline concept of the storable bipropellant propulsion system of the Hermes spaceplane is discussed. The general architecture of the propulsion system is shown. The design features of the engines of the main propulsion system and of the thrusters of the auxiliary propulsion system are demonstrated. Operational requirements as safety, reliability, life, and maintainability are discussed. The initial baseline flow scheme of the Hermes propulsion system is described. The main propulsion system consists of 2 reusable pressure fed rocket engines with a nominal steady state thrust of 20 kN per engine in vacuum. An auxiliary system provides thrust for attitude maneuvers and small velocity changes along the vehicle axis. It consists of 28 thrusters (10 to 400 N) distributed forward and aft.


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    Title :

    Hermes Propulsion System


    Contributors:
    H. Immich (author) / H. Hopmann (author) / T. Caussin (author)

    Publication date :

    1987


    Size :

    17 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Hermes propulsion system design

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


    Hermes propulsion system design

    Immich, H. / Hopmann, H. / Calabro, M. | Tema Archive | 1987


    HERMES propulsion system design and modelization

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