Several thrust system design concepts were evaluated and compared using the specifications of the most advanced 30 cm engineering model thruster as the technology base. Emphasis was placed on relatively high power missions. The extensions in thruster performance required for the Halley's comet mission were defined and alternative thrust system concepts were designed in sufficient detail for comparing mass, efficiency, reliability, structure, and thermal characteristics. Confirmation testing and analysis of thruster and power-processing components were performed. A baseline design was selected from the alternatives considered, and the design analysis and documentation were refined. A program development plan was formulated that outlines the work structure considered necessary for developing, qualifying, and fabricating the flight hardware for the baseline thrust system within the time frame of a project to rendezvous with Halley's comet. An assessment was made of the costs and risks associated with a baseline thrust system as provided to the mission project under this plan. Critical procurements and interfaces were identified and defined.


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    Title :

    Extended performance solar electric propulsion thrust system study. Volume 3: Tradeoff studies of alternate thrust system configurations


    Contributors:

    Publication date :

    1977-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Extended performance solar electric propulsion thrust system design

    CAKE, J. / HAWTHORNE, E. / POESCHEL, R. | AIAA | 1978


    Extended performance solar electric propulsion thrust system design

    Cake, J.E. / Hawthorne, E.I. / Poeschel, R.L. | Tema Archive | 1978




    Tradeoff Performance of Hybrid Low-Thrust Propulsion System

    Giovanni Mengali / Alessandro Quarta | AIAA | 2007