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86 Aircraft mass breakdown Structure Propulsion system - Conventional powerplant - Electric motor (incl. controller) 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] 18097 [kg] 4035 [kg] 4035 [kg] NA [kg] 9972 [kg] 4435 [kg] 173 [kg] 4420 [kg] NA [kg] 4420 [kg] 944 [kg] 3580 [kg] 35684 [kg] 18360 [kg] 5312 [kg] NA [kg] 59356 Hybrid Aircraft 21163 5709 4951 740 11791 4435 173 6239 1577 4662 944 3580 42243 18360 4655 8765 74023 π₯ Ref. 17% 41% 23% NA 18% 0% 0% 41% NA 5% 0% 0% 18% 0% -12% NA 25% Table 5.7: Mass breakdown of the hybrid-electric aircraft sized at a design range of 1100 nm and a battery specific energy of 1.5 kWh/kg at cell-level [126] 5.5 Partial Parallel Hybrid Clean-Sheet Design In the search of analysing the implications of increasing π»π π’π π on aircraft design, integrated performance as well as flight technique optimization, a partial parallel hybrid system was assessed by Pornet and Isikveren [14]. The hybrid-electric quad-fans concept illustrated in Figure 2.2 is investigated. The electrification concerns all operational phases of the mission except the taxi-in/out, descent, landing and hold, which are performed only with the tur- bofans. The intrinsic thrust and power characteristics of the electric fan are key aspects to be well understood in order to size the propulsion system. They are detailed in Section 5.5.1 which focuses on the sizing strategy of the hybrid-electric propulsion. Based upon the sizing of the propulsion system, two different operational schemes of the hybrid-electric propulsion during cruise are investigated. During the cruise operation presented in Section 5.5.2, the turbofans are throttled back while the electric fans deliver the maximal available thrust. In Section 5.5.4, the second operational cruise strategy is assessed which consists of throttling the electric fans during cruise while the turbofans run close to their maximum efficiency [15]. 5.5.1 Hybrid-Electric Propulsion System Sizing The flow path sizing of the geared turbofans and the electric fans are performed at TOC conditions. With respect to the level of π»ππ’π π and the thrust requirement at TOC, ππππΆ, which includes a 300 fpm residual climb rate, the design thrust of the electric fan ππ ππΆπΈπΉ andPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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