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Aerospace 2018, 5, 123 19 of 21 of different power. The difference between the maximum take-off power and maximum turboprop power is supplied using an electric power-train. The thermal power-train is analyzed in three different cases of performance, and the evaluations of emissions and fuel consumption reduction are presented. Finally, the sizing of the battery storage system is obtained through a single objective optimization problem, solved using a random search approach. The results obtained, in terms of the number of non-revenue passengers, show that the actual feasibility of the hybrid flight is only during the take-off and the ascendant climb phase (Engine_2 results). Meanwhile, the use of the most convenient cases, in terms of emission/fuel consumption reduction, needs the increase of battery energy density and, considering the actual growth of battery technology, will become feasible in the next years. Author Contributions: “Conceptualization and methodology”: M.C.C., A.D.P., C.P.; “Software and Investigation”: L.P.D.N., M.F.; “Writing—original draft preparation”: M.C.C., L.P.D.N., M.F. Funding: This research received no external funding Acknowledgments: This paper is supported by the Project “Power-train ad elevate prestazioni energetiche e dimensionali per la propulsione elettrica/ibrida di veicoli aerei, marini e terrestri”. Conflicts of Interest: The authors declare no conflict of interest. Abbreviations ACARE BSFC (kg/kWh) DDC,max ∆ (J/kg) Eele,req (J) EI (g/kg) EMs F (N) HP h (m) HEPS LP ICE Ibatt (A) Imax,disch (A) LTO M MTOW (kg) mcell (kg) np ns p (kPa) Qb (Ah) Rb (Ω) S (g/kg) SOC SNOX (g/kg) TIT (K) TOC T/O t0 (s) tfin (s) VDC,link (V) Vout,batt (V) ηg Advisory Council for Aviation Research brake-specific fuel consumption maximum duty ratio of the DC–DC converter energy density of cell total electrical energy required during the flight emission index electric motors thrust high pressure altitude hybrid electric propulsion systems low pressure internal combustion engine current of a battery cell maximum discharge current of a battery cell landing take-off Mach number (-) max take-off weight mass of a single cell number of parallel branches of battery storage system number of series cells of battery pack pressure cell capacity cell resistance severity parameter state of charge NOX severity parameter turbine inlet temperature top of climb take-off initial time instant of hybrid flight final time instant of hybrid flight DC-link voltage output voltage of battery pack global efficiency of electrical power-trainPDF Image | Turboprop Hybrid Electric Propulsion System
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