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108 6 Conclusion and Outlook However, if the strategy of the long range cruise (LRC) speed is followed, it does not affect the contemporary altitude-speed flight technique of conventional aircraft. These integrated aircraft performance analyses indicate that the application of fuel-battery hybrid-electric propulsion to transport aircraft seems limited to the high-density PAX re- gional market segment and for low-to-moderate values of 𝐻𝑃 . However, the investigation of higher synergistic integration of the hybrid-electric propulsion system needs to be further pur- sued particularly in combination with technologies such as distributed propulsion. Moreover, in view of notably reducing the technological requirements imposed to the batteries, partial turboelectric systems need to be assessed in future work. For achieving optimum energy management strategies, the methods will need to be further developed to introduce optimum power allocation schedule and control into the sizing scheme. The synergistic integration of the propulsion system at aircraft level through tightly inter- laced coupling with the airframe and the other systems on-board the aircraft as well as the establishment of optimum control strategies will enable to reveal the full potential of the application of hybrid-electric propulsion system to transport aircraft. Although optimisation studies were not constructed in the thesis, the presented methods offer the methodological components to facilitate hyper-dimensional, multi-objective and multi-constraint optimiza- tion. In the context of the hybrid-electric aircraft concepts investigated, the analyse of aircraft performance were focused on the design mission. Off-design mission performance and in par- ticular the trade between the payload and the range determined by the combined use of fuel and batteries as energy source need to be established to compare the operational transport capability of hybrid-electric aircraft against conventional fuel-only aircraft. While the introduction of the COSAR metric bridged technical evaluation to economics analysis, the inclusion in design charts of constraint lines related to economics in order to select “best and balanced” aircraft concepts requires rigorous assessment of the economics implications resulting from the integration and operation of hybrid-electric propulsion sys- tem. Moreover, economics analysis need to be included in further work as they can drive the aircraft morphological selection. The economics analysis must be further expanded to cover the overall life cycle assessment of hybrid-electric aircraft to provide wells-to-wheels comparison to kerosene-based aircraft.PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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