During operation, electrically powered aircraft could instantly reduce greenhouse gas emissions to zero. However, their realization usually fails due to the significant increase in mass of electrified powertrains. Thus, the scope of research should not be limited to the powertrain but consider new technologies that are enabled by the electrification of the aircraft. An initial ranking of possible technology options carried out as part of the GNOSIS research project shows that distributing the propellers on the aircraft has the greatest impact on emissions and costs. Therefore, this thesis evaluates the potential of distributed propellers by designing 9-, 19-, and 50-seat electrified regional aircraft at aircraft level. Substitute models for the powertrain components, the mass estimation of the wing and the electrical systems are implemented in the conceptual aircraft design environment MICADO to design the electrified regional aircraft. The blade element momentum theory provides the induced velocities behind the propeller plane. They are integrated into a multiple lifting line method to determine the wing aerodynamics. Up to four propellers are installed at the leading edge of the outboard wing, which leads to the highest shaft power reduction. Due to the low gravimetric energy density of the batteries, a partial turboelectric powertrain is integrated in the aircraft designs with an entry into service in 2025. Predicting an energy density of the batteries of 500 Wh/kg in2050 results in a serial hybrid-electric powertrain, which uses gas turbines or fuel cells in combination with a battery. In cruise flight, the optimized arrangement of the propellers increases the lift-to-drag ratio by up to 8.3%. However, even in all-electric 9- and 19-seataircraft, the additional mass of the distributed propulsion systems does not result in any energy savings compared to the conventional version. In addition, integrating the fuel cells with the required heat exchanger in the engine nacelles at the leading edge of the wing increases the viscous drag of the nacelles three times. Higher direct operating costs owe to the additional maintenance required for the electric propulsion systems and the high cost of hydrogen. Despite all this, aircraft designs that do not emit greenhouse gases during operation are possible using fuel cells and batteries.


    Access

    Download

    Check availability in my library


    Export, share and cite



    Title :

    Potential assessment of regional aircraft concepts with distributed hybrid-electric propulsion


    Additional title:

    Potentialabschätzung von Regionalflugzeug-Konzepten mit verteilten hybrid-elektrischen Antrieben


    Contributors:

    Publication date :

    2025-01-01


    Size :

    1 Online-Ressource : Illustrationen pages


    Remarks:

    Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2025; Aachen : RWTH Aachen University 1 Online-Ressource : Illustrationen (2025). = Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2025



    Type of media :

    Miscellaneous


    Type of material :

    Electronic Resource


    Language :

    English





    HYBRID ELECTRIC AIRCRAFT SYSTEM WITH DISTRIBUTED PROPULSION

    SCHWARZ FREDERICK M / BAIG ZUBAIR AHMED | European Patent Office | 2019

    Free access

    Hybrid electric aircraft system with distributed propulsion

    SCHWARZ FREDERICK M / BAIG ZUBAIR AHMED | European Patent Office | 2020

    Free access


    Conceptual Assessment of Hybrid Electric Aircraft with Distributed Propulsion and Boosted Turbofans

    Hoogreef, Maurice / Vos, Roelof / de Vries, Reynard et al. | AIAA | 2019