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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 35 and as outputs ππΈπ and ππΈπ. The interfacing of the electric motor performance using a performance map is represented in Figure 3.2. In the framework of this thesis, HTS technology was assumed for the electric motor design. Simplified pre-design methods were implemented for the modelling of the electric motor. First order estimate of the weight and volume of the HTS motor were evaluated using linear scaling laws based on gravimetric and volumetric specific power values as discussed in Section 2.2.1. The sizing criterion of the electric motor was based on the power requirement at the se- lected design point. The matching of the electric motor with the propulsive device relies consequently on the power characteristics only. The torque and speed limitations were not considered in the design of the electric motor. Under the premise that the thermal environ- mental conditions of the electric motor are correctly managed by the cooling system, it was assumed that the maximum power of the electric motor (ππΈπ,πππ₯) is available at each point of the aircraft flight envelope. ππΈπ,πππ₯ drives consequently the thrust performance of the ducted fan according to the fan shaft power requirement as discussed in Section 3.2.3.2. The power requirement to maintain the HTS material below critical temperature were assessed based on relations established by Vratny et al. [38]. In the applications investigated in Chapter 5, the HTS electric motor is operated constantly or close to ππΈπ,πππ₯. The off-design efficiency characteristic of an HTS electric motor presen- ted in [60] and [38] indicates that the efficiency of an HTS electric motor remains nearly constant in a range of rated part power from 5% to 100% and rated torque from 20% to 100% [104]. Hence, the efficiency of the HTS motor was assumed constant for all its opera- tions. Appropriate values of electric motor efficiencies were taken from Section 2.2.1. This simplification is, however, only suitable for electric motors based on HTS technology. 3.2.3.5 Methods for Power Management and Distribution System Integration In conceptual design, weight, volume and efficiency of the PMAD components are the most relevant parameters for the integration at aircraft level. These characteristics need to be established for each component constituting the PMAD system. In this thesis, first order estimations of weight and volume were implemented based on linear scaling according to gravimetric and volumetric specific power. According to the layout of the PMAD and its sizing power-criterion, the total weight of the PMAD system is obtained by summing up the weight of each of its components. The efficiency of the PMAD compon- ents was assumed constant during the operations. The overall efficiency of the PMAD was determined by the product of each components efficiency. The efficiency of the power man- agement and distribution system (ππππ΄π·) is mapped in the design environment according to power required at the PMAD (ππππ΄π·) as indicated in Figure 3.2. With the availability of physics-based models of the PMAD components, the fidelity of the components modelling can be improved. For instance, off-design efficiency characteristics with respect to power variation can be interfaced at aircraft level. This is notably demon- strated by the physics-based models of an inverter and a controller developed by Vratny et al. [38] which enable to map the efficiency of these components within the required power range of the electric motor. More accurate weight predictions can be also achieved with thePDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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