Electric aircraft propulsion is considered one of the key technologies for reducing commercial aviation's exhaust gas emissions. While, in the field of general aviation, a number of prototypes and in some cases even certified aircraft already exist, for large transport aircraft, the development is largely still in the preliminary design phase. A meaningful integration and analysis of electric propulsion systems is a complex task that can only be achieved with methods that consider the aircraft as an integrated system of systems. This thesis presents a methodology for the design and analysis of electric propulsion systems for transport aircraft. A generic propulsion system definition allows for consideration of arbitrary system architectures. The modular and object-oriented implementation enables flexible replacement of the propulsion components as well as further development of the implemented models. The methodology is part of the aircraft design environment MICADO (Multidisciplinary Integrated Conceptual Aircraft Design and Optimization), which is developed at the Institute of Aerospace Systems of RWTH Aachen University. In the context of this work, the approach is applied on comprehensive aircraft design studies. In particular, the difference between turbo-electric, battery-powered, and fuel-cell-powered propulsion systems is elaborated. While the former provide no sufficient reduction of mission energy even assuming optimistic technology scenarios for the investigated applications, fuel cell systems can contribute to a minimization of the climate impact in the medium term. In this context, replacing the conventional propulsion unit with a fuel cell system is suitable for regional aircraft. For short/medium-range configurations, a hybrid solution of fuel cell and direct hydrogen combustion is preferred. Here, systems utilizing aero-propulsive coupling, such as the propulsive fuselage concept, are beneficial. In order to realize the application of hydrogen-powered propulsion concepts, however, substantial technological improvements are necessary. Two of the most important issues are, for instance, minimizing the mass of the fuel cell and hydrogen tank. The presented methodology provides a platform to evaluate these technologies and also allows for an extension regarding future propulsion concepts and other aircraft types.
Evaluation of electric propulsion systems in preliminary aircraft design
Bewertung von elektrischen Antriebssystemen im Flugzeugvorentwurf
01.01.2024
1 Online-Ressource : Illustrationen pages
Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2023; Aachen : RWTH Aachen University 1 Online-Ressource : Illustrationen (2024). = Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2023
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Elektronische Ressource
Englisch
Evaluation of electric propulsion systems in preliminary aircraft design
TIBKAT | 2023
|PRELIMINARY DESIGN AND EXPERIMENTAL INVESTIGATION OF A DISTRIBUTED ELECTRIC PROPULSION AIRCRAFT
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