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10 • • 2 Hybrid-Electric Technology State-of-the-Art and Beyond The efficiency of the components, 𝜂, ratio of the useful power to the input power, is a relevant parameter for the system performance as it enables to quantify its overall efficiency and its losses. For energy sources, the gravimetric specific energy denoted as e, the amount of energy contained per unit of mass, is another important sizing parameter as it defines the mass of an energy source or of an energy storage required to deliver a given amount of energy. The technological level assumed for these characteristics are reviewed for each components constituting the electrical system in the following sections. 2.2.1 Electric Motor For aircraft application, high gravimetric specific power and efficiency of electric motors are of importance along with high volumetric specific power. Current conventional electric motors for aircraft application exhibit specific powers up to 5 kW/kg [34] and efficiency value around 95% [35]. When considering application requiring several megawatts, HTS technology is one interesting option [7, 8]. The characteristic of HTS technology is discussed in 2.3.1. Replacing the rotor and/or the stator of the electric motor architecture with HTS material leads to a significant increase in specific power [7] as well as improvement in efficiency. In contrast to conventional electric motors whose specific power remains nearly independent of the size, HTS electric motor specific power increases with power [36]. HTS electric motors are expected to achieve specific power exceeding 15 kW/kg and efficiency above 99% (cooling system not included) in the power and rotational range speed required for transport aircraft [6, 7, 37, 38]. HTS technology is assumed for the electric motor architecture constituting the hybrid-electric propulsion systems investigated in Chapter 5. 2.2.2 Power Management and Distribution System The distribution and the management of the electrical energy from the energy source to the multiple electric consumers on-board the aircraft is performed by the PMAD system. This system is generally composed of: • Cables that transmit the power through the electrical system. While using conventional technology for the power cables would result in heavier weight, HTS cables are projected to reach a specific weight of 9.2 kg/m [39] and by dropping the resistivity to zero offer a transmission efficiency of almost 100% (see Section 2.3.1). An important design consideration is the influence of the pressure change on breakdown voltage according to the Paschen’s law [40] which determines the amount of insulation and shielding required. • Circuit breakers, which protect the system from short circuits. In any high power system, semiconductor devices known as solid state power controller (SSPC) are used to control the power supplied to a load and to prevent fault current. State-of-the-artPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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