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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 45 The power required at the combustion engine ππΆπΈ is expressed in Equation 3.26 according to ππΊ under the consideration of the electric power off-take at the generator ππΈπππ,ππππ‘πππ and the power off-take at the combustion engine ππΆπΈ,ππππ‘πππ. ππΆπΈ = ππΊ + ππΈπππ,ππππ‘πππ + ππΆπΈ,ππππ‘πππ (3.26) ππΊ The fuel power supplied and the corresponding amount of fuel flow, first output of the energy table, are determined according to Equation 3.19 and Equation 3.20 respectively. For takeoff and climb, the energy table is computed according to the power lever settings π πΏπΆπΈ and π πΏπΈπΈπ π· set for the creation of the respective thrust table. The power of the com- bustion engine is calculated according to Equation 3.18. The resulting fuel flow is computed with Equation 3.19 and Equation 3.20. ππΈπππ is the result of Equation 3.23. 3.2.4.3.3 Partial Parallel Hybrid System In a partial parallel hybrid system, the conventional and the electrical system are independently computed. The calculation of the πΉπΉ and of ππΈπππ formulated in Equation 3.27 and Equation 3.28 is a function of the shaft power required at the conventional system (ππhπππ‘,πΆπππ£) and of the shaft power required at the electrical system (ππhπππ‘,πΈπππ). ππhπππ‘,πΆπππ£ and ππhπππ‘,πΈπππ are determined with respect to the propulsive device model according to the flight state conditions (π₯πΌππ΄, π΄ππ‘, π) and the thrust determined according to the propulsive device fan speed ππππ,ππ· as discussed in Section 3.2.3.2. πΉπΉ = ππhπππ‘,πΆπππ£ (3.27) πΉπ»π Β·ππΆπΈ ππΈπππ = ππhπππ‘,πΈπππ (3.28) ππππ΄π· Β·ππΈπ In the case of a partial parallel hybrid system, the energy management is directly an outcome of the propulsion system sizing and more specifically of π»π . The methods for the sizing of partial parallel hybrid system are described in Section 3.2.6. Two different energy manage- ment strategies for an aircraft concept equipped with a partial parallel hybrid system are investigated in Section 5.4. 3.2.4.4 Summary of Energy Characteristics The mapping of the energy consumption within the aircraft design environment needed to establish the energy characteristics of hybrid-electric propulsion system is summarized in Table 3.2.PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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