The technical feasibility of an Orbital Propulsion Module (OPM) comprising coni-spherical surface tension tanks, attached to a heavy satellite (Spacebus 400, mass in GEO = 1600 kg BoM) for launch by Ariane 44L was investigated. The OPM (having a bipropellant mass capability of nominal 2900 kg) consists of a load-carrying primary structure, and of 4 propellant and 2 pressure-gas tanks, supported by a secondary structure. A 3 kN pressure-gas-fed engine is assumed as the main transfer engine. Coni-spherical propellant tanks, polar mounted, were compared with spherical tanks, equatorial mounted. Both tank types are equipped with surface tension zero-g propellant management devices. The applicability of the super plastic forming (SPF) process compared to a forging process for this propellant tank size (1100 mm dia) was studied. Concerning the primary structure, a truss-framework structure was analyzed versus a sandwich-shell structure. The favorable OPM-candidate for the medium/longer term future comprises coni-spherical propellant tanks, SPF-processed and polar mounted, and a truss framework structure connecting the heavy spacecraft to the launcher.


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    Title :

    Orbital Propulsion Module (OPM). Study on Coni-Spherical Surface Tension Tanks (Costa)


    Contributors:
    W. Kleinau (author) / H. Guenther (author) / J. Kollien (author) / H. Schweig (author) / M. Wuermseer (author)

    Publication date :

    1987


    Size :

    580 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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