Three approaches are presented for packaging the elements of a 30 cm ion thruster subsystem into a modular thrust subsystem. The individual modules, when integrated into a conceptual solar electric propulsion module are applicable to a multimission set of interplanetary flights with the space shuttle interim upper stage as the launch vehicle. The emphasis is on the structural and thermal integration of the components into the modular thrust subsystems. Thermal control for the power processing units is either by direct radiation through louvers in combination with heat pipes or an all heat pipe system. The propellant storage and feed system and thruster gimbal system concepts are presented. The three approaches are compared on the basis of mass, cost, testing, interfaces, simplicity, reliability, and maintainability. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Modular Thrust Subsystem Approaches to Solar Electric Propulsion Module Design


    Beteiligte:
    J. E. Cake (Autor:in) / G. R. Sharp (Autor:in) / J. C. Oglebay (Autor:in) / F. J. Shaker (Autor:in) / R. J. Zavesky (Autor:in)

    Erscheinungsdatum :

    1976


    Format / Umfang :

    25 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Modular thrust subsystem approaches to solar electric propulsion module design

    CAKE, J. / SHARP, G. / OGLEBAY, J. et al. | AIAA | 1976


    Modular thrust subsystem approaches to solar electric propulsion module design

    Cake, J. E. / Sharp, G. R. / Oglebay, J. C. et al. | NTRS | 1976


    Modular Thrust Subsystem Approaches to Solar Electric Propulsion Module Design

    James E. Cake / G. Richard Sharp / Jon C. Oglebay et al. | AIAA | 1977