Conceptual Design Methods Hybrid-Electric Transport Aircraft

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5.3 Parallel Hybrid Retrofit Aircraft 75 Table 5.4. The TOW of the reference aircraft to operate this off-design mission is 68697 kg and the release fuel which includes the block fuel and the reserves is 6453 kg. In order to maximize the electric energy on-board the aircraft, the hybrid retrofit aircraft operates the 900 nm stage length at MTOW with 78990 kg. It is a 15% increase in TOW compared to the reference aircraft. The propulsion system of the hybrid aircraft is increased by 6% due to the installation of the electric motors sized for a total power of 5100 kW. The installation of the electric propulsion system results in a 31% increase in electrical system weight and an additional 8900 kg of batteries. The decrease in release fuel of 10% is less than the previously quoted block fuel reduction of 16% as the reserves flown with fuel only are accounted for in the release fuel. Aircraft mass breakdown Structure Propulsion system - Conventional powerplant - Electric motors (incl. control- lers) Equipment - Furnishing - Hydraulic system (anti-icing) - Electrical system - Instruments - Operational items OEW Payload Release fuel (block and reserves) Total battery TOW Unit Reference Aircraft [kg] 20819 [kg] 8991 [kg] 8991 [kg] NA [kg] 14073 [kg] 4435 [kg] 173 [kg] 4941 [kg] 944 [kg] 3580 [kg] 43883 [kg] 18360 [kg] 6453 [kg] NA [kg] 68697 Hybrid Aircraft 20819 9501 8991 510 15593 4435 173 6461 944 3580 45913 18360 5818 8900 78990 𝛥 Ref. 0% 6% 0% NA 11% 0% 0% 31% 0% 0% 5% 0% -10% NA 15% Table 5.4: Mass breakdown of the reference and hybrid-electric aircraft for an off-design mission of 900 nm [27] The retrofitting of an aircraft with a hybrid-electric system enables to gain insights into the design parameters, constraints and behavior of the propulsion system as well as to establish first design heuristics. However, in view of examining the sizing effects resulting from the integration of hybrid-electric propulsion at aircraft level and of investigating the potential market range application for hybrid-electric narrow-body transport aircraft, the integrated performance of clean sheet designs need to be assessed. 5.3.4 Optimum Flight Technique The optimum flight technique for the retrofit aircraft equipped with a parallel hybrid-electric propulsion system is analysed in this paragraph. It was published by Pornet et al. [115]. The optimum altitude-speed schedule is assessed according to the vehicular efficiency metrics introduced in Chapter 4. The relative value of SAR and ESAR are illustrated in Figure

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