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36 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft development of component weight methods based on the number of switches constituting the inverter and controller [38]. 3.2.3.6 Methods for Electric Energy and Power Device Integration The methods for the integration of electric and energy power device (EEPD) in the aircraft sizing and performance process are discussed in the following. In view of determining the energy requirement, the efficiency characteristics of the EEPD need to be modelled according to the evolution of the electric power requirement at the EEPD, ππΈπππ. In addition, the maximal power which can be delivered by the EEPD is of importance to size the system with respect to the maximal power requirement occurring within the operating flight envelope. As represented in Figure 3.2, the EEPD performance are interfaced according to ππΈπππ as input and with the efficiency of the electrical energy and power device (ππΈπΈππ·) and the maximum power of the electrical energy and power device (ππΈπΈπ π·,πππ₯) as outputs. Referring to Section 2.2.3, battery and fuel cell systems are considered as electric energy and power device in the layout of hybrid-electric propulsion system for transport aircraft. The modelling characteristics of the battery and fuel cell in view of generating these interfaces are described in Section 3.2.3.6.1 and in Section 3.2.3.6.2 respectively. 3.2.3.6.1 Methods for Battery System Integration The capability to deliver the en- ergy and power requirement is related to the sizing of the battery system. The determination of ππΈπΈππ·,πππ₯ requires the description of the battery system sizing approach. By sizing the battery system, the total battery mass required to fulfil the energy and power requirements at aircraft level is determined according to the battery characteristics. In the following, the fundamental characteristics involved in battery system sizing are established first by assum- ing a constant efficiency of the battery system (ππ΅ππ‘). In view of considering a variable ππ΅ππ‘ in the sizing of the battery system, a more sophisticated scheme using a physics-based model of a battery is then discussed. The latter approach is implemented in this thesis for the integrated evaluation of hybrid-electric propulsion systems. The battery gravimetric specific energy at system level (ππ΅ππ‘,ππ¦π π‘) and the battery gravimet- ric specific power at system level (ππ΅ππ‘,ππ¦π π‘) are the key parameters in conceptual design for the sizing of the battery mass. According to the energy and power requirements at aircraft level, either the specific energy or the specific power is the sizing criterion for the battery mass. Assuming that the power profile of the electric power required at the battery sys- tem characterized by the parameter, ππΈπππ, is known, the total battery mass required is the maximum of the battery mass obtained either by the energy requirement criterion or by the power requirement criterion as formulated in Equation 3.3. ππ΅ππ‘π‘πππ¦ = max(ππ΅ππ‘π‘πππ¦ ππππππ¦; ππ΅ππ‘π‘πππ¦ πππ€ππ) (3.3) where ππ΅ππ‘π‘πππ¦ ππππππ¦ denotes the mass of the battery sized according to the energy require- ment and ππ΅ππ‘π‘πππ¦ πππ€ππ characterizes the mass of the battery sized according to the powerPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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