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Abstract The European Flightpath 2050 and corresponding Strategic Research and Innovation Agenda as well as the NASA Environmentally Responsible Aviation N+ series have elaborated am- bitious emissions and external noise reduction targets according to chronological waypoints. However, the evolutionary improvements of conventional technologies might not be sufficient to fulfil the declared objectives. Disruptive technologies need consequently to be envisioned to reach the set of future goals. In order to deliver ultra-low or even zero in-flight emissions levels, there exists an increasing amount of international research and development focusing on the electrification of aircraft propulsion and power systems. While aiming for the ulti- mate goal of universally electric transport aircraft, a hybrid-electric approach will be first necessary to match the requirements of aircraft propulsion systems and the development pace of electrical components technology. The introduction of hybrid-electric technology expands dramatically the design space and the full-potential of these technologies will be drawn through synergistic morphological and systems integration. Perturbing the conven- tional design paradigms, the design of hybrid-electric aircraft poses a genuine challenge to traditional sizing and performance methods. Conceptual design methods for sizing, performance analysis and identification of flight tech- niques for hybrid-electric transport aircraft are proposed in this thesis. Considering the available legacy industry programs, the methods are developed with the capability of being integrated in traditional sizing and performance environment. The models of the stand- alone engineering components which constitute hybrid-electric propulsion systems are first described. By establishing the interfaces between the engineering component modules, the layout of the hybrid-electric propulsion architecture and the system integration at aircraft level are then comprehensively detailed. The conventional methods are extended to map the intrinsic characteristics of hybrid-electric propulsion system within the aircraft design and performance environment. The tracking of the electric energy consumed and the calcula- tion of the maximum thrust available are in the focus of the methods development. New degrees-of-freedom such as the degrees-of-hybridization and new constraints associated with the sizing of hybrid-electric propulsion system are introduced. The specificities related to the sizing of hybrid-electric propulsion system are explained by describing the sizing criterion of the components. The overall aircraft sizing process and the evaluation of the aircraft integrated performance are finally highlighted. iiiPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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