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.
Multimission modular spacecraft parallel battery tests
01.01.1977
Aufsatz (Konferenz)
Keine Angabe
Englisch
Multimission modular spacecraft parallel battery tests
NTRS | 1981
|Multimission modular spacecraft (MMS)
AIAA | 1988
|Testing programs for the Multimission Modular Spacecraft
NTRS | 1978
|