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The Small Explorer power systemA direct-energy-transfer (DET) power system design with the battery connected directly to the bus was selected as the generic power system to satisfy the various Small Explorer spacecraft missions. The power system electronics (PSE) are designated to handle power levels up to a 250-W load with minimum changes in the electronics. The command and telemetry interface is through an optical MIL-STD-1773 interface that is contained in the PSE. The system provides high performance, low weight, and low EMI (electromagnetic interference) generation. The design and performance of the power system have been verified through analysis and extensive tests on a breadboard.
Document ID
19910053311
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dakermanji, George (Fairchild Space Co. Germantown, MD, United States)
Carlsson, Uno (Fairchild Space Germantown, MD, United States)
Culver, H. (Fairchild Space Co. Germantown, MD, United States)
Rodriguez, G. E. (Fairchild Space Co. Germantown, MD, United States)
Ahmad, A. (Fairchild Space Co. Germantown, MD, United States)
Jagielski, J. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Intersociety Energy Conversion Engineering Conference
Location: Reno, NV
Country: United States
Start Date: August 12, 1990
End Date: August 17, 1990
Accession Number
91A37934
Distribution Limits
Public
Copyright
Other

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