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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Electrical power system for low earth orbit spacecraft applications


    Additional title:

    Elektrisches Energienetz fuer Raumfahrzeuge mit niedriger Erdumlaufbahn


    Contributors:


    Publication date :

    1987


    Size :

    7 Seiten, 11 Bilder, 7 Tabellen, 4 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English