This paper discusses the co-design of an electric aircraft propulsion system for minimum weight and maximum power-to-thrust efficiency. The system under consideration for preliminary exploration of the methodology consists of a fully superconducting synchronous motor and a ducted, fixed-pitch propeller. In order to ensure a viable propulsor, a minimum required thrust bound is imposed on the system design. Both analytical methods and finite-element analysis (FEA) are used to size the motor, and a blade-element momentum (BEM) model is implemented for predicting performance of the ducted propeller. A genetic algorithm optimization scheme is applied on a hydrogen-powered electric aircraft propulsion system proposed for the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA) project. Sensitivity of the combined system efficiency to motor weight is evaluated.


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    Title :

    Co-design of an Integrated Direct-drive Electric Motor and Ducted Propeller for Aircraft Propulsion




    Publication date :

    2020-08-26


    Size :

    2334856 byte



    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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