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98 Aircraft mass breakdown Structure Propulsion system - Conventional powerplant - Electric motors - Ducted fans Equipment - Furnishing - Hydraulic system (anti-icing) - Electrical system - - PMAD propulsion - - Sub-systems - Instruments - Operational items OEW Payload Release fuel (block and reserves) Total battery MTOW 5 Integrated Performance of Hybrid-Electric Propulsion Systems Unit Reference Aircraft [kg] 18440 [kg] 4132 [kg] 3861 [kg] NA [kg] NA [kg] 10012 [kg] 4435 [kg] 173 [kg] 4460 [kg] NA [kg] 4460 [kg] 944 [kg] 3580 [kg] 36159 [kg] 18360 [kg] 6317 [kg] NA [kg] 60840 Hybrid Aircraft 21487 5117 3553 444 1119 11640 4435 173 6088 1348 4740 944 3580 41818 18360 5806 11740 77730 π₯ Ref. 17% 24% -14% NA NA 16% 0% 0% 37% NA 6% 0% 0% 16% 0% -8% NA 28% Table 5.9: Mass breakdown of the reference and hybrid-electric aircraft sized at a design range of 1300 nm and a π»ππ’π π of 30% [31] 5.5.3 Electric Fan Cruise Throttling The strategy of throttling back the geared-turbofan was assessed to be suitable up to a π»π π’π π of around 45% as for higher values of π»ππ’π π the efficiency of the geared-turbofan degrades due to stronger off-design part load operations. Consequently, a novel operational strategy consisting of throttling back the electric fans during cruise while the geared turbofans operate close to their efficiency peak is investigated in this section and the results are compared to the cruise strategy previously investigated in Section 5.5.2. The analysis of this strategy was published by Pornet [15]. The relative change in block fuel versus π»πΈπππππ is illustrated in Figure 5.23. Similar trends in terms of change in block fuel with respect to increasing π»π π’π π and growing design ranges are noticeable compared to the evolutions indicated in Section 5.5.2. For a given π»πΈπππππ, it can be observed that the achievement in block fuel reduction are about identical when comparing Figure 5.15 against Figure 5.23. However in the case of throttling the electric fans during cruise, the level of π»ππ’π π reached is higher for an identical π»πΈπππππ. In other words in order to achieve the same potential in block fuel reduction, a higher useful electric power relative to the total useful power is realized. Basically it means that for achieving the same block energy split, a larger electric motor power needs to be installed. This trend is elucidated by the fact that for an identical π»π π’π π the throttling of the electric fans during cruise results in a lower electrical energy consumption compared to the first energy management strategy highlighted in Section 5.5.2. For the same variation of π»ππ’π π, the reduction in electrical energy utilizedPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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