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24 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft Aircraft Top Level Requirements Range Payload Δ mFuel Aircraft Sizing Parameters Ptotal/MTOW MTOW/Sref MTOW Δ mBattery Hp PEM max PSLS Power Lever PLCE PLEM PLEEPD Sref Aircraft Disciplines Propulsion and Power System Aerodynamics Weights Combustion Engine Propulsive Device Electric Motor Power Management & Distribution Electrical Energy Power Device - Drag Polar - High-Speed - Low-Speed - Lift Curves - OEW - Structure - Propulsion - Systems - Furnishings - Operating Items - Payload - Total Fuel Mass - Total Battery Mass Power Map Efficiency Map Performance Map Performance Map In: PPMAD Out: ɳPMAD In: PElec Out: PEEPD max, ɳEEPD In: ΔISA, Alt, M In: ΔISA, Alt, M, PCE, NrelCE In: ΔISA, Alt, M, TdesPD, FPRdesPD, NrelPD In: CrelEM, NrelEM Out: PCE max Out: ɳCE Out: TPD, PShaftPD, ɳPD Out: PEM, ɳEM Thrust Tables In: ΔISA, Alt, M Out: Tmax In: ΔISA, Alt, M, T Out: Fuel Flow, PElec Flight Performance Point Performance Integrated Mission Performance - Performance constraint analysis - High-Speed Performance - Low-Speed Performance - Calculation of fuel mass required mFuel - Electric power profile computation at electric energy power device - SOC computation with battery model No Performance constraints fulfilled Yes No No Figure 3.2: Synthesis procedure for hybrid-electric aircraft. Adapted from Pornet et al. [27]. and performance maps as well as physics-based models to determine the behaviour of the hybrid-electric propulsion system components. However, due to the utilization of legacy pro- grams in industry, the methods are developed with the constraint of being implemented in a traditional sizing and performance program environment. The synthesis of the methods de- veloped, adapted from Pornet et al. [27], is illustrated in Figure 3.2. It represents graphically the introduced design parameters for the design of hybrid-electric aircraft, the characteristics of the hybrid-electric propulsion components and subsequent integration within the aircraft sizing environment, the process for the integrated performance analysis as well as the itera- tion scheme for the sizing of hybrid-electric aircraft. Figure 3.2 will be described in the subsequent sections to present in detail the overall hybrid- electric aircraft design and sizing procedure. The procedure is applicable to each of the hybrid topologies discussed in Section 2.1. In the case of a partial parallel hybrid system, a more practical procedure can be represented. This approach followed for the integrated perform- Energy Tables Convergence criteria of battery system SOCend ≥ SOClimit PMaxBattery ≥ PElec Convergence criteria of fuel-based energy storage: mFuel = Total Fuel Mass Yes Sized AircraftPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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