The aeronautics industry has been challenged to increase efficiency, reduce noise and emissions, and decrease dependency on carbon-based fuels. To address these needs, NASA has identified and begun to pursue electrified aircraft as a possible solution. The power system for an electric aircraft can exist in many different forms, however; at the early design stage the engineer(s) must identify whether a hybrid- or turbo- electric solution may be best, whether the power transmission system is to be AC or DC, and to ultimately answer the question: does the electric solution provide a net system benefit compared to the fully mechanical solution? This paper describes a generalized power system architecture sizing and analysis framework to provide a mechanism to answering these questions, along with an example based on the STARC-ABL Architecture.


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    Title :

    A Generalized Power System Architecture Sizing and Analysis Framework


    Contributors:

    Conference:

    AIAA Propulsion and Energy Forum ; 2018 ; Cincinnati/Ohio, United States


    Publication date :

    2018-07-07


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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