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@PHDTHESIS{Aigner:971858,
author = {Aigner, Benedikt},
othercontributors = {Stumpf, Eike and Strohmayer, Andreas},
title = {{E}valuation of electric propulsion systems in preliminary
aircraft design},
school = {Rheinisch-Westfälische Technische Hochschule Aachen},
type = {Dissertation},
address = {Aachen},
publisher = {RWTH Aachen University},
reportid = {RWTH-2023-09845},
pages = {1 Online-Ressource : Illustrationen},
year = {2023},
note = {Veröffentlicht auf dem Publikationsserver der RWTH Aachen
University 2024; Dissertation, Rheinisch-Westfälische
Technische Hochschule Aachen, 2023},
abstract = {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.},
cin = {415310},
ddc = {620},
cid = {$I:(DE-82)415310_20140620$},
typ = {PUB:(DE-HGF)11},
doi = {10.18154/RWTH-2023-09845},
url = {https://publications.rwth-aachen.de/record/971858},
}
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