The block diagram, subsystems, and components of the modular power subsystem for the multimission modular spacecraft (MMS) are described. The basic design studies were guided by considerations of cost, efficiency, simplicity, and flexibility to serve a variety of missions. Components discussed are the power regulator unit, the power control unit, the signal conditioning assembly, bus protection assembly, and the 20 Ah and 50 Ah batteries. The plan for the modular power subsystem protoflight module tests is shown. The testing has four phases: (1) component level tests, (2) subsystem integration and initial performance test, (3) subsystem protoflight environmental tests, and (4) subsystem final performance tests, qualification/acceptance review and delivery.
The modular power subsystem for the multimission modular spacecraft
Intersociety Energy Conversion Engineering Conference ; 1978 ; San Diego, CA
1978-01-01
Miscellaneous
No indication
English
Multimission modular spacecraft (MMS)
AIAA | 1988
|Multimission modular spacecraft parallel battery tests
NTRS | 1981
|Multimission modular spacecraft parallel battery tests
NTRS | 1977
|