As space power systems grow and Computer Aided Engineering (CAE) workstations mature, computer modeling becomes a critical design step. Unfortunately, no single program suits all modeling jobs. The designer must base program selection on execution speed, convergence, available models, output options, hardware requirements, and user-friendliness. Occasionally, he must write his own program. The designer must also take care in modeling system components: computer programs are only as good as their models. This paper outlines the modeling process of a multi kW spacecraft power system comprised of eight solar powered converter/battery channels, three control loops including the peak power tracker, and a common output bus. The computer models predicted small signal stability margins, bus impedances, and fault induced voltage transients.


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    Title :

    1986 IECEC stability and transient modeling of a large spacecraft power system


    Additional title:

    1986 IECEC Modellerstellung fuer grosse Raumfahrzeugenergiesysteme hinsichtlich stabilem und transientem Verhalten


    Contributors:
    Chen, J. (author) / Glass, M. (author)


    Publication date :

    1986


    Size :

    5 Seiten, 9 Bilder, 3 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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