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Conceptual Design Methods Hybrid-Electric Transport Aircraft

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Conceptual Design Methods Hybrid-Electric Transport Aircraft ( conceptual-design-methods-hybrid-electric-transport-aircraft )

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5.2 Propulsion and Power Systems 67 Figure 5.1: Electric propulsion system [27] It is composed of an electric motor equipped with controller which are powered by batteries. According to the YEIS, HTS technology was assumed for the electric motor and for the elec- tric cables. Each battery pack is controlled by a battery controller unit (BCU). The battery technological level is a key factor in determining the performance of the integrated hybrid- electric aircraft concepts. Consequently, sensitivity analysis based on the battery gravimetric specific energy are conducted at aircraft level. According to the prediction of the evolution of the battery technology indicated in Section 2.2.3.1, the battery gravimetric specific energy cell-level (𝑒𝐵𝑎𝑡) is varied in the analysis between 750 Wh/kg and 1500 Wh/kg. Component Battery HTS Motor HTS Cables Controller Converter SSPC Specific weight Efficiency 750-1500Wh/kg[9,16] 90-95% 20.0 kW/kg [6] 9.2 kg/m [39] 20.0 kW/kg [6] 18.0 kW/kg [6] 44.0 kW/kg [42] 99.5 % 100 % 99.5 % 99.5 % 99.5 % Table 5.1: Technology assumption for the electrical components of the propulsion system [27] The PMAD enables the transmission and distribution of the electrical power through elec- trical buses. Protection in the system is provided by the implementation of SSPC. For the propulsion system architecture equipped with several electric motors, each electric bus dedic- ated to a propulsion system is interconnected via a SSPC to ensure redundancy in the system. The potential technological evolution of the electrical components beyond the state-of-the-art were discussed in Section 2.2. The technological level of the electrical components assumed in terms of specific weight and efficiency for aircraft level assessment are summarized in Table

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