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Chapter 6 Conclusion and Outlook A comprehensive development of conceptual design methods was proposed in this thesis in or- der to resolve the shortcomings of traditional methods for the sizing and performance analysis of hybrid-electric transport aircraft. Concerned by the utilization of legacy programs in in- dustry, the methods were developed with the constraints of being implemented in traditional sizing and performance programs. In particular, the consideration of the electricity as an ad- ditional energy source to the fuel energy within the sizing and performance environment was dealt within the methods. In traditional sizing and performance environment, the propulsion system is commonly interfaced via thrust and fuel flow tables. By conserving the format of these tables and adding the electric power required at the electric energy and power device as an additional output in the fuel flow table, the electric energy could be mapped out in the sizing and performance environment while ensuring the compatibility of the methods with traditional programs. The engineering components constituting the hybrid-electric system including the electric energy and power devices as well as their interfaces within the propul- sion and power system were established by the methods. The integration of the propulsion system enabled to compute the electric energy consumed and the maximum thrust available as a function of the operational utilization, intrinsic efficiency and power characteristics of the hybrid-electric propulsion system. Finally, the methods established the overall aircraft sizing process to determine the sizing and integrated performance analysis of hybrid-electric transport aircraft. The design of hybrid-electric transport aircraft required the formulation of metrics for the evaluation of optimum flight techniques. Methods for optimum flight techniques identification of hybrid-electric transport aircraft were consequently proposed. Considering the different market prices of the energy sources, the cost specific air range (COSAR) metric was developed to enable the flight profile optimization of hybrid-electric transport aircraft according to min- imum energy cost. Moreover, cost index (CI) metrics definition for hybrid-electric aircraft were developed to determine the economical flight profile of hybrid-electric aircraft by taking into consideration the cost of time in addition to the cost of energy. The methods were employed for the design of fuel-battery narrow-body transport aircraft accommodating 180 passengers (PAX) in order to investigate the integration implications of hybrid-electric propulsion system at aircraft level and to establish design heuristics and 105PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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