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iv Abstract The vehicular efficiency function is an essential metric in conceptual design phase as it eval- uates the overall efficiency of the aircraft to perform its dedicated transport task. Used notably for identification of optimum flight techniques it enables to match the altitude-speed operations of the aircraft with its aerodynamic, weight and propulsion characteristics. New figures-of-merit which take into account the novel characteristics of hybrid-electric propulsion system are established in this thesis for the flight techniques optimization of hybrid-electric transport aircraft. The proposed conceptual design methods are applied to evaluate integrated performance of hybrid-electric narrow-body transport aircraft. The assessment focuses on fuel-battery hybrid-electric propulsion system technology targeting a 2035 year entry-into-service. The investigations of a retrofitted narrow-body transport aircraft with a parallel hybrid-electric propulsion system and of narrow-body clean-sheet designs with parallel and partial parallel hybrid-electric propulsion system enable the derivation of design heuristics and sizing ax- ioms. The sizing sensitivities of hybrid-electric narrow-body aircraft are investigated against the design range, the degree-of-hybridization for power and the battery technology level. Increasing design range results in a degradation of the integrated performance in terms of fuel consumption, aircraft weight and vehicular efficiency due to the raising electric energy demand which translates basically into increasing battery system mass installation. Lower battery gravimetric specific energy results in the installation of a larger battery mass for a given amount of energy which results in penalizing weight sizing cascading effects. Growing degree-of-hybridization for power up to a moderate level results in an increasing block fuel reduction, however, at the expense of a degradation in vehicular efficiency. The fuel saving benefit obtained by increasing degree-of-hybridization for power is explained by the increasing use of electrical energy and by the improvement in overall propulsion system efficiency. The degradation in vehicular efficiency is caused by the sizing of the electric propulsion system for higher power and by the increase in electric energy demand requirement which result in higher battery system mass installation. In the context of the hybrid-electric transport aircraft integrated performance investigation, the market application of these concepts is found to be subject to the regional segment with design ranges in the order of 900 nautical miles (nm) to 1300 nm and for low-to-moderate degree-of-hybridization for power considering battery technology above 1000 Wh/kg. In terms of the influence on flight techniques optimiz- ation, increasing the degree-of-hybridization for power has a tendency to lower the optimum speed. However, by mirroring cruise flight technique strategy of conventional aircraft such as the long-range cruise speed, this effect should not drastically change the contemporary altitude-speed flight profiles.PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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