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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 51 With growing levels of π»ππ’π π, the role of the electric fan in providing the required thrust during take-off and climb becomes more predominant. As a result the sizing of the electric motor is constrained by take-off and climb performance such that the electrical fan delivers the required thrust. Typically the take-off field length (TOFL), the climb gradient require- ments as well as the time-to-climb become the sizing constraints. In order to minimize the impact of the electrical system weight, the sizing of the electric motor is set as an optimization scheme whose constraints are the take-off and climb performance requirements. The critical sizing cases of an electric motor equipping a partial parallel hybrid-electric propulsion system are discussed in the integrated performance analysis of a narrow-body aircraft featuring a quad-fans arrangement in Section 5.5. In this context, it is worthwhile highlighting that for a universally electric aircraft, the elec- tric motor has to be sized for take-off conditions which results in a large propulsion system weight [10]. This sizing criterion results in an oversized electric motor in cruise condition as in contrast to a gas-turbine the electric motor maximal power remains invariant with flight speed and altitude assuming it is suitably thermally managed. For a hybrid-electric aircraft, according to the topology and the utilization of the hybrid-electric propulsion system, the electric motor power does not have to be sized to the take-off power requirement diminishing the impact of the electric motor sizing on the propulsion system weight. According to ππΈπ,πππ₯, the weight and volume of the electric motor are determined applying scaling laws based on gravimetric and volumetric specific power or relying on physics-based model as discussed in Section 3.2.3.4. The weight of the electric motor is interfaced with the components weight build-up methods within the aircraft sizing environment for the compu- tation of the overall propulsion system weight. 3.2.6.3 Power Management and Distribution System Sizing The PMAD is sized according to the highest power requirement occurring in the electrical system under consideration of abnormal modes. With respect to the power resulting from the sizing case and the layout of the PMAD system, the weight and volume of the PMAD are calculated according to the methods indicated in Section 3.2.3.5. The weight of the PMAD is linked to the weight component build-up methods of the propulsion system. According to the representation of the PMAD in Figure 3.4 and Figure 3.3, the sizing case for ππππ΄π· is given by Equation 3.35. ππππ΄π· = ππΈπ,πππ₯ (3.35) ππΈπ 3.2.7 Methods for Sizing of Hybrid-Electric Aircraft The overall procedure for the sizing of hybrid-electric aircraft illustrated in Figure 3.2 is described in this paragraph. First of all, the transport tasks and the complete set of perform- ance requirements to be achieved are stipulated in the ATLRS. For a transport aircraft, thePDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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