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The Small Explorer power system electronicsThe power system electronics for the NASA Goddard Space Flight Center Small Explorer Satellites are intended to satisfy various planned missions. The selected topology is a direct energy transfer (DET) system with the battery connected directly to the bus. The shunt control technique is a linear sequential full shunt which provides a simple solar array interface and can support both 3 axis stabilized and spinner satellites. In addition, it can meet stringent electromagnetic interference requirements which are expected on some Small Explorer Missions. The Power Systems Electronics (PSE) performs battery charge control using both temperature compensated charge/discharge ratio ampere hour integration and voltage-temperature control. The PSE includes all the circuits needed to perform telemetry and command functions using an optical MIL-STD-1773 interface.
Document ID
19920003955
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dakermanji, G.
(Fairchild Space and Electronics Co. Germantown, MD., United States)
Carlsson, U.
(Fairchild Space and Electronics Co. Germantown, MD., United States)
Temkin, D.
(Fairchild Space Co. Germantown, MD., United States)
Culver, H.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Rodriguez, G. E.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Ahmad, A.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1991
Publication Information
Publication: ESA, European Space Power Conference. Volume 1: Power Systems, Power Electronics, Batteries and Fuel Cells
Subject Category
Spacecraft Propulsion And Power
Accession Number
92N13173
Distribution Limits
Public
Copyright
Other
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