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Chapter 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft The conceptual design methods developed for sizing and performance of hybrid-electric air- craft are presented in this chapter. This construct relies on traditional methods employed for the design of conventional kerosene fuel-based aircraft. To fully understand the departure of the developed methods, the conventional methods are reviewed first in Section 3.1. Conven- tional design methods for sizing and performance analysis of fuel-based aircraft are offered in many textbooks [84–91]. The objective of this chapter is therefore not to provide a complete description of the traditional methods but rather to emphasize on the characteristics which lay the foundation for the design methods of hybrid-electric aircraft. The extension of the methods for sizing and performance analysis of hybrid-electric aircraft are then presented in Section 3.2. 3.1 Traditional Sizing and Performance Methods Sizing is the process of finding a constrained balance between size, thrust and energy re- quirements of an aircraft under the objective of fulfilling all its transport tasks specified in the aircraft top-level requirements (ATLRS) and of the compliance with the airworthiness regulations. Further definitions of the aircraft sizing process can be found in the compendium proposed by Nam [92]. At least two main categories of requirements can be itemized for the sizing and performance of an aircraft: • performance constraint requirements which relate the thrust to the size of the aircraft in order to fulfil point performance requirements, • mission performance requirements which relate the amount of energy to the size of the aircraft in order to transport a design payload along a specified design mission. A third category of requirements deals with operating economics objectives to offer a com- petitive product to the market. As highlighted in Chapter 1, further requirements of future 17PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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