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1.3 Scope and Structure of the Thesis 3 first-order equations for the modelling of the aircraft and the propulsion system. As a result, detailed secondary effects cannot be taken into account in the evaluation of integrated hybrid- electric propulsion systems. Besides overcoming the limitations of contemporary methods, the newly developed methods need to offer higher fidelity modelling than pre-design methods. Concerned by the use in industry of legacy or commercial sizing and performance programs, a constraint in the methods development is set on their capability to be integrated into a tra- ditional sizing and performance programs. The development of a completely new sizing and performance environment is not the focus of this thesis. Hence, the first objective can be for- mulated by the development of new conceptual design methods which can be implemented in contemporary program to enable the sizing and the performance assessment of hybrid-electric aircraft and to enhance the fidelity of the modelling compared to pre-design methods. The identification of optimum flight techniques is essential in conceptual design phase to match the speed-altitude operations to the aircraft characteristics. The classical metrics for flight technique optimization are deficient when introducing an additional source of energy for the propulsion system. Consequently, the second research objective of the thesis is the devel- opment of methods for the determination of flight technique optimality of hybrid-electric aircraft. Finally, the investigation of the integrated prospects of hybrid-electric aircraft in terms of market segment range application, potential reduction in emissions and change in vehicular efficiency is the third research objective defined in this thesis. 1.3 Scope and Structure of the Thesis With respect to the research objectives formulated previously, the scope and the structure of the thesis are outlined. The thesis focuses on the development of conceptual design methods for sizing, performance and flight technique optimality of hybrid-electric aircraft in order to assess hybrid-electric propulsion systems at aircraft level and to examine the integration implications. Visualized in Figure 1.1, the perimeter of the thesis is drawn around the sizing and performance module of the aircraft and it includes the establishment of the interfaces with the expert modules to capture the sensitivities of hybrid-electric propulsion techno- logy at aircraft level. As indicated the modelling of the component characteristics and the architectural layout of the conventional and the electrical system are provided by external engineering modules. In Chapter 2, the state-of-the-art in electric components technology and the development perspectives are reviewed. Potential key technological enablers for the application of electric drive to propulsion and power system of transport aircraft are then discussed. The topological options for the layout of hybrid-electric propulsion system are finally identified. The review is then extended to aircraft level offering a compendium of advanced transport aircraft concepts employing electric drive to the propulsion system. The classical methods for aircraft sizing and performance are reviewed in Chapter 3 and their limitations for the integrated assess- ment of hybrid-electric propulsion technology are identified. The proposed methods for the sizing and performance assessment of hybrid-electric aircraft are then detailed. The methods developed for the identification of optimum flight technique of hybrid-electric aircraft are de-PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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