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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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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 41 besides πœ‚π‘ƒ 𝐷 and the true airspeed only on the maximum shaft power delivered by the electrical system 𝑃𝑆hπ‘Žπ‘“π‘‘,𝐸𝑙𝑒𝑐,π‘šπ‘Žπ‘₯ as expressed in Equation 3.13. π‘‡π‘šπ‘Žπ‘₯ = πœ‚π‘ƒπ· Β· 𝑃𝑆hπ‘Žπ‘“π‘‘,𝐸𝑙𝑒𝑐,π‘šπ‘Žπ‘₯ (3.13) π‘€Β·π‘Ž The maximum power of the electrical system is determined in Equation 3.14. It is expressed according to the power of the electric motor as established in Equation 3.12 and the amount of electrical power delivered at the shaft of the electric motor which is a function of the maximum power of the generator (𝑃𝐺,π‘šπ‘Žπ‘₯), 𝑃𝐸𝐸𝑃𝐷,π‘šπ‘Žπ‘₯ and 𝑃𝐸𝑙𝑒𝑐,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’. 𝑃𝑆hπ‘Žπ‘“π‘‘,𝐸𝑙𝑒𝑐,π‘šπ‘Žπ‘₯ = min(𝑃𝐸𝑀, πœ‚π‘ƒπ‘€π΄π· Β· πœ‚πΈπ‘€ Β· (𝑃𝐺,π‘šπ‘Žπ‘₯ βˆ’ 𝑃𝐸𝑙𝑒𝑐,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’ + 𝑃𝐿𝐸𝐸𝑃𝐷 Β· 𝑃𝐸𝐸𝑃𝐷,π‘šπ‘Žπ‘₯)) (3.14) 𝑃𝐺,π‘šπ‘Žπ‘₯ is formulated in Equation 3.15. It is a function of the power delivered by the combus- tion engine according to 𝑃𝐢𝐸,π‘šπ‘Žπ‘₯, the power setting 𝑃𝐿𝐢𝐸, 𝑃𝐢𝐸,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’ and the efficiency of the generator (πœ‚πΊ). πœ‚πΊ is calculated according to the efficiency map as discussed for the electric motor in Section 3.2.3.4. 𝑃𝐺,π‘šπ‘Žπ‘₯ = (𝑃𝐿𝐢𝐸 Β· 𝑃𝐢𝐸,π‘šπ‘Žπ‘₯ βˆ’ 𝑃𝐢𝐸,π‘‚π‘“π‘“π‘‘π‘Žπ‘˜π‘’) Β· πœ‚πΊ (3.15) 3.2.4.1.3 Partial Parallel Hybrid System In a partial parallel hybrid system as il- lustrated in Figure 2.3, the maximum thrust available is consequently obtained according to Equation 3.16. π‘‡π‘šπ‘Žπ‘₯ = πœ‚π‘ƒπ·πΆπ‘œπ‘›π‘£ Β· 𝑃𝑆hπ‘Žπ‘“π‘‘,πΆπ‘œπ‘›π‘£,π‘šπ‘Žπ‘₯ + πœ‚π‘ƒπ·πΈπ‘™π‘’π‘ Β· 𝑃𝑆hπ‘Žπ‘“π‘‘,𝐸𝑙𝑒𝑐,π‘šπ‘Žπ‘₯ (3.16) π‘€Β·π‘Ž whereπœ‚π‘ƒπ·πΆπ‘œπ‘›π‘£ andπœ‚π‘ƒπ·πΈπ‘™π‘’π‘ characterizetheefficiencyofthepropulsivedeviceofthecombined conventional and electrical system respectively. The 𝑃𝑆hπ‘Žπ‘“π‘‘,πΆπ‘œπ‘›π‘£,π‘šπ‘Žπ‘₯ and the 𝑃𝑆hπ‘Žπ‘“π‘‘,𝐸𝑙𝑒𝑐,π‘šπ‘Žπ‘₯ are calculated similarly as in parallel system as highlighted in Equation 3.9 and Equation 3.11 respectively. 3.2.4.2 Summary of Thrust Characteristics In view of summarizing the determination of thrust characteristics of hybrid-electric propul- sion systems, a table recapitulating the calculation of the maximum thrust is presented in Table 3.1 according to the hybrid-electric propulsion system topologies considered.

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