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34 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft and ππΆπΈ with the efficiency map. It is integrated within the aircraft design environment as shown in Figure 3.2. Following the rubberised engine modelling approach, by normalizing ππΆπΈ with a reference power, the efficiency characteristics of the engine are assumed to be independent of the engine size in a given power range. 3.2.3.4 Methods for Electric Motor Integration In contrast to air-breathing machines, the performance of an electric motor is independent of the flight state. The characteristics of an electric motor can be represented in a torque and speed diagram (for a given direct current voltage value) as illustrated in Figure 3.17 [38]. The operational envelope is drawn according to three limitations: the maximum torque lim- itation being represented by the region I; the maximum power and the maximum rotational speed limitations indicated by the region II. These boundaries depend upon the technology of the machine and the design point selected. Methods for the calculation of the geometrical characteristics of the electric motor can be elaborated based on the electric motor compon- ents design as detailed by Vratny et al. [38]. Based upon the geometric properties of the components, the total weight of the electric motor is calculated using component build-up methods. Figure 3.17: Generic design and efficiency chart of a conventional electric motor from [38]. The design and off-design power of an electric motor can be mapped at aircraft level ac- cording to the relative torque of the electric motor (πΆπππ,πΈπ) and the relative speed of the electric motor (ππππ,πΈπ) measured against the design point. With πΆπππ,πΈπ and ππππ,πΈπ the power of the electric motor (ππΈπ) is defined. Thermal limitations are considered using a thermal model to determine the achievable performance of the machine within the operat- ing environment. The efficiency contours of a conventional electric motor are represented in the torque and speed diagram in Figure 3.17. Considering the different losses occurring within an electric motor namely the copper losses, iron losses, aerolic and frictions losses of the rotor, the efficiency of the electric motor (ππΈπ ) can be mapped out for each operational point [38]. The efficiency and power characteristics of the electric motor can be consequently interfaced at aircraft level using a multidimensional table with πΆπππ,πΈπ and ππππ,πΈπ as inputsPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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