The resupplying of orbital spacecraft using the Space Shuttle, Orbital Maneuvering Vehicle, Orbital Transfer Vehicle or a depot supply at a Space Station is studied. The governing factor in fluid resupply designs is the system size with respect to fluid resupply quantities. Spacecraft propellant management for tankage via diaphragm or surface tension configurations is examined. The capabilities, operation, and application of adiabatic ullage compression, ullage exchange, vent/fill/repressurize, and drain/vent/no-vent fill/repressurize, which are proposed transfer methods for spacecraft utilizing tankage configurations, are described. Selection of the appropriate resupply method is dependent on the spacecraft design features. Hydrazine adiabatic compression/detonation, liquid-free vapor venting to prevent freezing, and a method for no-vent liquid filling are analyzed. Various procedures for accurate measurements of propellant mass in low gravity are evaluated; a system of flowmeters with a PVT system was selected as the pressurant solubility and quantity gaging technique. Monopropellant and bipropellant orbital spacecraft consumable resupply system tanks which resupply 3000 lb of hydrazine and 7000 lb of MMH/NTO to spacecraft on orbit are presented.


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    Title :

    Orbital spacecraft resupply technology


    Contributors:

    Publication date :

    1986-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Orbital spacecraft resupply technology

    EBERHARDT, R. / TRACEY, T. | AIAA | 1986


    Orbital spacecraft consumables resupply

    Dominick, Sam M. / Eberhardt, Ralph N. / Tracey, Thomas R. | NTRS | 1988


    Orbital spacecraft consumables resupply

    DOMINICK, SAM / EBERHARDT, RALPH / TRACEY, THOMAS | AIAA | 1988