Against a background of increasing energy demand and rising fuel prices, hybrid-electric propulsion systems have the potential to significantly reduce fuel consumption in the aviation industry, particularly in the lighter sectors. By taking advantage of both electric motor and internal combustion engine, hybrid-electric propulsion systems provide not only a benefit in fuel saving but also a reduction in takeoff noise and the emission levels. This research considers the design and sizing process of a hybrid-electric propulsion system for a single-seat demonstrator aircraft, the experimental derivation of the internal combustion engine map, and the electric motor parameters. In addition to the experimental data, a novel modeling approach including several linked desktop PC software packages is presented to analyze and optimize hybrid-electric technology for aircraft. Further to the analysis of a parallel hybrid-electric, midscale aircraft, this paper also presents a scaling approach for a 20 kg unmanned aerial vehicle and a 50 ton intercity airliner. At the smaller scale, two different mission profiles are analyzed: an intelligence, surveillance, and reconnaissance mission profile and a maximum-duration profile. At the larger scale, the performance of a 50 ton intercity airliner is modeled, based on a hybrid-electric gas turbine, assuming a range of electric boost powers and battery masses. Presented as Paper 2013-3806 at the 11th International Energy Conversion Engineering Conference, San Jose, CA, 14-17 July 2013


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    Title :

    Hybrid-Electric Propulsion for Aircraft


    Contributors:

    Published in:

    Publication date :

    2015




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040



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