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5.3 Parallel Hybrid Retrofit Aircraft Component Environmental control system Flight controls Landing gear Anti-icing Cables and busses Fuel cell system (incl. liquid hydrogen and tank mass) Generator 69 Power and weight estimation Number of PAX [119] according to a specific weight of 0.36 kW/kg [120] Flight control area [67] according to a spe- cific weight of 3.73 kW/kg [121] Based on MTOW [122] according to a spe- cific weight of 0.19 kW/kg [122] Scaled icing area based on B787 reference area [123] Based on maximum subsystem power ac- cording to [42] Based on maximum subsystem power ac- cording to [55] Based on maximum power according to a specific weight of 5 kW/kg [34] Table 5.2: Technology assumption for the electric components of the power system [27] The power demand and mass estimations of the important subsystems like environmental control system or flight controls are estimated according to methods described by Vratny [42]. The power demand for the cabin systems and the instruments is estimated according to the methods published by Xia [124]. For the controller, converter and SSPC the same technological level as summarized in Table 5.1 is assumed. 5.3 Parallel Hybrid Retrofit Aircraft The retrofit of a narrow-body transport aircraft equipped with a fuel-battery hybrid-electric propulsion system was assessed by Pornet et al. [27]. The reference aircraft is sized for a design range of 3300 nm. The hybrid-electric propulsion system is composed of a HTS electric motor powered by batteries mounted on the low-pressure shaft of the gas-turbine to support its operation during some segments of the mission. Both gas-turbines are equipped with an electric motor. The layout of the electric propulsion system is illustrated in Figure 5.1. The hybridization approaches investigated are discussed in Section 5.3.2. The geometry of the reference aircraft is kept fixed. Possible increase of the nacelle wetted area due to the integration of the electric engine has not been considered in this aircraft study. It was decided not to downsize the combustion engine to give the capability to the aircraft to still fly medium range missions based on the conventional system only. The design mission in comparison to the reference aircraft was found to be reduced to 2770 nm because of the installation of the necessary electrical components. Due to the nature of the retrofit, the installation of the additional electrical components is limited by the MTOW of the reference aircraft. In off-design, the reference aircraft is taking- off at a take-off weight (TOW) less than MTOW according to the block fuel required to fly the off-design mission. Off-design missions open consequently the possibility to install and toPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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