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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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44 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft During takeoff and climb the maximal thrust is provided according to the thrust ratings. Rearranging Equation 3.10, the power of the combustion engine is given by Equation 3.18. 𝑃𝐢𝐸 = 𝑃 𝐿𝐢𝐸 Β· 𝑃𝐢𝐸,π‘šπ‘Žπ‘₯ (3.18) The fuel power supply (𝑃𝑆𝑒𝑝𝑝𝑙𝑦,𝐹𝑒𝑒𝑙) is formulated in Equation 3.19 according to the effi- ciency of the combustion engine πœ‚πΆπΈ. The efficiency πœ‚πΆπΈ is obtained from the efficiency map described in Section 3.2.3.3. 𝑃𝑆𝑒𝑝𝑝𝑙𝑦,𝐹𝑒𝑒𝑙 = 𝑃𝐢𝐸 (3.19) πœ‚πΆπΈ According to the fuel heating value 𝐹 𝐻 𝑉 , the fuel flow of the combustion engine, first output of the energy table, is calculated according to Equation 3.20. 𝐹𝐹 = 𝑃𝑆𝑒𝑝𝑝𝑙𝑦,𝐹𝑒𝑒𝑙 𝐹𝐻𝑉 The second output of the energy table, 𝑃𝐸𝑙𝑒𝑐, is formulated in Equation 3.21. 𝑃𝐸𝑙𝑒𝑐 = 𝑃𝐿𝐸𝑀 Β· 𝑃𝐸𝑀,π‘šπ‘Žπ‘₯ + 𝑃𝐸𝑙𝑒𝑐,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’ (3.20) (3.21) πœ‚π‘ƒπ‘€π΄π· Β·πœ‚πΈπ‘€ If the power of the EEPD turns to be limiting in Equation 3.11, the power of the combustion engine is determined by Equation 3.22. 𝑃𝐢𝐸 = 𝑃𝑆hπ‘Žπ‘“π‘‘ βˆ’ (𝑃𝐿𝐸𝐸𝑃𝐷 Β· 𝑃𝐸𝐸𝑃𝐷,π‘šπ‘Žπ‘₯ βˆ’ 𝑃𝐸𝑙𝑒𝑐,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’) Β· πœ‚π‘ƒπ‘€π΄π· Β· πœ‚πΈπ‘€ (3.22) In this case the 𝑃𝐸𝑙𝑒𝑐 is formulated in Equation 3.23. 𝑃𝐸𝑙𝑒𝑐 = 𝑃 𝐿𝐸𝐸𝑃 𝐷 Β· 𝑃𝐸𝐸𝑃 𝐷,π‘šπ‘Žπ‘₯ (3.23) 3.2.4.3.2 Serial Hybrid System For a given flight state (π›₯𝐼𝑆𝐴, 𝐴𝑙𝑑, 𝑀) and according to a required thrust, the electric power required at the electric motor is determined according to Equation 3.24. 𝑃𝐸𝑀 = 𝑇 Β· 𝑀 Β· π‘Ž (3.24) πœ‚π‘ƒπ· The power delivered by the generator (𝑃𝐺) is calculated as a function of 𝑃𝐸𝑀 and 𝑃𝐸𝐸𝑃 𝐷,π‘šπ‘Žπ‘₯ according to Equation 3.25. 𝑃𝐺 = 𝑃𝐸𝑀 βˆ’ 𝑃𝐿𝐸𝐸𝑃𝐷 Β· 𝑃𝐸𝐸𝑃𝐷,π‘šπ‘Žπ‘₯ (3.25) πœ‚π‘ƒπ‘€π΄π· Β·πœ‚πΈπ‘€ 𝑃𝐸𝑙𝑒𝑐 is determined according to Equation 3.23.

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