Thermal vacuum design supporting thruster tests indicate no problems under the worst case conditions of sink temperature and spin rate. The reliability of the system was calculated to be 0.92 for a five-year mission. Minus the main energy storage capacitor it is 0.98.


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    Title :

    Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite


    Contributors:

    Publication date :

    1971-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English