An engineering evaluation of the Multimission Modular Spacecraft power supply is presented. The spacecraft has one charger with eight commandable voltage versus temperature levels. Graphs are presented which represent: (1) cell voltage limits vs. temperature; (2) charge ratio vs. temperature; (3) effect of 0.0 percent impedance unbalance at 10 C; (4) shorted cell at 10 C; and (5) discharge voltage profile at 10 C.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Multimission modular spacecraft parallel battery tests


    Contributors:


    Publication date :

    1977-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English