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18 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft Figure 3.1: Traditional sizing and performance process according to Mattingly [90] aircraft products will need to respect environmental regulations expressing, for instance, lim- itations in terms of emissions. An illustration of the traditional sizing and performance process proposed by Mattingly et al. [90] is represented in Figure 3.1. Referring to this figure, the conventional methods will be described in the following. It is worthwhile noting that the two aforementioned itemized cat- egories are represented in Mattingly’s design process under the titles “constraints analysis” and “mission analysis”. As indicated in Figure 3.1, the aircraft performance assessment relies on the determination of aircraft aerodynamic quality, propulsion characteristics and weight properties. The representation of these disciplines in conceptual design is discussed in the following paragraphs. 3.1.1 Geometric Properties From an initial cloud of concepts, the most promising candidate, named in Figure 3.1 the “no- tional concept” or often refer to as the “baseline”, is selected following a qualitative and/or a semi-quantitative downselection process. An initial estimation of the geometrical properties of the main components such as the fuselage, the wing, the empennage, the propulsion system and the landing gears is the first step in the process. The detailed geometrical description of each component and their arrangement serve as inputs for the methods used to estimate the aerodynamic and weight characteristics of the concept. Initial geometric data are generally based on known aircraft referred as reference aircraft. In the context of the hybrid-electric aircraft concepts investigated in Section 5, traditional geometrical descriptions of aircraft components were utilized. For the parallel hybrid propul-PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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