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68 5 Integrated Performance of Hybrid-Electric Propulsion Systems 5.1. The specific weights of the components are assumed invariant with scale. Except for the batteries, the efficiency of the components is assumed constant with the operating con- ditions. The efficiency of the electric propulsion system implemented in the aircraft models depends consequently only on the variation of the battery efficiency with respect to its dis- charge characteristic according to the battery model presented in Section 3.2.3.6.1 as well as the efficiency change of the propulsive device with the flight state and the power settings according to the model introduced in Section 3.2.3.2. 5.2.2 All-Electric Power System The layout of the all-electric power system architecture implemented in the hybrid-electric aircraft concepts investigated in this chapter is illustrated in Figure 5.2. Figure 5.2: Layout of the all-electric power system architecture [27] Following the trends already set by state-of-the-art aircraft such as the Boeing B787 [116], it consists of an all-electric subsystem architecture. The main operating voltage of the sub- systems is 540 VDC, which was identified as the future operating voltage [117]. The Boeing B787 has already demonstrated a subsystem voltage level of 270 VDC [118]. The assump- tions with regards to the specific weight of the components constituting the all-electric power subsystem are summarized in Table 5.2. In addition to a zero-bleed architecture, it features zero-power off-take from the engine in normal modes as the power required by the subsystems is provided by proton exchange mem- brane fuel-cells operated with liquid hydrogen. The weight of the fuel cell system, including the liquid hydrogen and tank mass, was estimated according to [55]. The stored liquid hydro- gen was also used as coolant to maintain the HTS materials of the electric motors and cables constituting the propulsion system below critical temperature. However, to ensure redund- ancy in the system, a generator is installed on each combustion engine to provide electric energy in abnormal modes. The weight of the generators was calculated according to [34].PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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