The results are presented of an investigation of the factors which affect the determination of Spacelab (S/L) minimum interface main dc voltage and available power from the orbiter. The dedicated fuel cell mode of powering the S/L is examined along with the minimum S/L interface voltage and available power using the predicted fuel cell power plant performance curves. The values obtained are slightly lower than current estimates and represent a more marginal operating condition than previously estimated.
Space shuttle engineering and operations support. Orbiter to spacelab electrical power interface. Avionics system engineering
1976-06-30
Report
No indication
English
Space shuttle orbiter avionics
Tema Archive | 1977
|Space Shuttle orbiter avionics
AIAA | 1977
|Shuttle Orbiter European Spacelab - ECLS Systems
Tema Archive | 1974
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