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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26 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft Figure 3.5: Partial parallel hybrid propulsion system 3.2.1 Design Variables The design variables for hybrid-electric propulsion system need to be established within the sizing process. It was demonstrated that the parametric description of a dual energy propul- sion system requires the establishment of two fundamental algebraic parameters namely the degree-of-hybridization for power (𝐻𝑃 ) and the degree-of-hybridization for energy (𝐻𝐸 ) [13, 103]. The parameter 𝐻𝑃 describes the amount of electric power relative to the over- all total power. Commonly, the installed power or the useful power (power measured at the propulsive device) is quoted. The convention chosen herein is to denote the degree- of-hybridization for power referring to the useful power with the parameter 𝐻𝑃𝑢𝑠𝑒. The degree-of-hybridization for power is a new design variable in the sizing process as it determ- ines according to the overall power requirement, the sizing power of the electrical power system. The design parameter 𝐻𝑃 and 𝐻𝑃𝑢𝑠𝑒 are consequently represented in Figure 3.2 and in Figure A.1 respectively. The methods for sizing the hybrid-electric propulsion system according to 𝐻𝑃 are described in Section 3.2.6. The parameter 𝐻𝐸 is the ratio of electrical energy consumed over the total energy; it char- acterizes the so-called energy split. The quantity 𝐻𝐸 is evaluated along a specified segment or mission. The parameter 𝐻𝐸block refers, for instance, to the block mission. For a given hybrid-electric propulsion system architecture, 𝐻𝐸 is the outcome of the sizing as well as the energy and power management strategy defined for the hybrid system along a selected

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