The results of a tradeoff study to select an Electrical Power System configuration that is best suited for low-earth-orbit (LEO) spacecraft with various output power capabilities are presented. Two EPS configurations used for LEO spacecraft, i.e., (1) one using a Direct Energy Transfer (DET) Approach and (2) one using a Peak Power Transfer (PPT) Approach are described in detail and compared. At spacecraft power requirement of 800 watts or less, it is highly advantageous to choose the PPT Approach to the design of an Electrical Power System for low earth orbit spacecraft. However for a spacecraft in higher orbit and/or with higher power requirements, the DET-based power system is the optimum choice.
Electrical power system for low earth orbit spacecraft applications
Elektrisches Energienetz fuer Raumfahrzeuge mit niedriger Erdumlaufbahn
1987
7 Seiten, 11 Bilder, 7 Tabellen, 4 Quellen
Aufsatz (Konferenz)
Englisch
Electrical Breakdown Currents on Large Spacecraft in Low Earth Orbit
Online Contents | 1994
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