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Appendix A Appendix The aircraft synthesis procedure presented in Figure 3.2 is applicable for any hybrid-electric topologies discussed in Section 2.1. However, in the case of partial parallel hybrid systems, a more practical sizing procedure can be deployed as represented in Figure A.1. This procedure was followed for the integrated performance assessment of a partial parallel hybrid system presented in Section 5.5. 121 Aircraft Top Level Requirements Range Payload Δ mFuel Aircraft Sizing Parameters Tdes/MTOW MTOW/Sref MTOW Hpuse Tdes TF Tdes EF Power Lever PLEM PLEEPD Sref Aircraft Disciplines Propulsion and Power System Aerodynamics Weights Turbofan Model 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 Thrust Maps Fuel Flow Map Performance Map Performance Map In: PPMAD Out: ɳPMAD In: PElec Out: PEEPD max, ɳEEPD In: Tdes TF, ΔISA, Alt, M In: Tdes TF, ΔISA, Alt, M, TTF In: ΔISA, Alt, M, TdesEF, FPRdesEF, NrelEF In: CrelEM, NrelEM Out: TmaxTF Out: Fuel Flow Out: TEF, PShaftEF, ɳEF Out: PEM , ɳEM Thrust Tables Energy 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 Convergence criteria of battery system SOCend ≥ SOClimit PMaxBattery ≥ PElec Convergence criteria of fuel-based energy storage: mFuel = Total Fuel Mass Δ mBattery Yes Figure A.1: Aircraft synthesis procedure for partial hybrid parallel system Sized AircraftPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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