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Aerospace 2018, 5, 123 Aerospace 2018, 5, x FOR PEER REVIEW Aerospace 2018, 5, x FOR PE 8 of 21 8 of 21 8 of 21 ER REVIEW Figure 9. Mach number profifile. Figure 9. Mach number profile. In the Figure 10, the mission profile (altitude vs time) is plotted for the take-off, climb, and cruise In the Figure 10, the mission profile (altitude vs time) is plotted for the take-off, climb, and In the Figure 10, the mission profile (altitude vs time) is plotted for the take-off, climb, and phases. The results carried out from simulations are reported in the Figures 11 and 12. cruisecrpuihsaespehsa.sTehs.eTrheesurelstuslctsarcrairerdiedouotutfrforomssiimulationssaarreererpeporotretdedinitnhethFeigFuirgeusr1e1sa1n1da1n2.d 12. e 6000 1 6000 4000 4000 2000 2000 0 0 0 2000 Time[s] 4000 6000 Engine1 Engin 0 2000 4000 6000 Figure 10. Mission profile. Figure 10. Mission profile. Time[s] In particular, in Figure 11, the shFaifgtuproew10e.rMisispsliotntepdrdofuilrein. g the mission phases: the maximum In particular, in Figure 11, the shaft power is plotted during the mission phases: the maximum value is reached during the take-off phase. The profile of power is calculated through the value is reached during the take-off phase. The profile of power is calculated through the Iimnplaermtiecnutlaatiro,ninofFimguecrhea1n1ic,atlhfeligshtafetqpuaotwioenrsi[s24p]lointteadMdAuTrLinAgBthscerimpti;susisoingpahsaisnepsu:tthdeatma,athxeimum implementation of mechanical flight equations [24] in a MATLAB script; using as input data, aerodynamics data of ATR42-300 (Table 2) and the altitude and speed profile, the values of the value is reached during the take-off phase. The profile of power is calculated through the the aerodynamics data of ATR42-300 (Table 2) and the altitude and speed profile, the values of power in each point of the flight mission are calculated. In Figure 12, the specific fuel consumption implementation of mechanical flight equations [24] in a MATLAB script; using as input data, the the power in each point of the flight mission are calculated. In Figure 12, the specific fuel consumption (BSFC) is shown, with the left (a) and right sides (b) being several mission phases characterized by aerodynamics data of ATR42-300 (Table 2) and the altitude and speed profile, the values of the (BSFC) is shown, with the left (a) and right sides (b) being several mission phases characterized by different scales; the lower value is obtained at the beginning of the cruise at load variation, at that power in each point of the flight mission are calculated. In Figure 12, the specific fuel consumption point, keeping a rather constant value. According to the trend of required power, the thrust presents different scales; the lower value is obtained at the beginning of the cruise at load variation, at that point, (BSFC) is shown, with the left (a) and right sides (b) being several mission phases characterized by keepitnhegmaarxaitmheurmcovnalsuteanatvflaigluhet.stAarctcinogrd(itnakge-tofft)h.eThtreenredsuoltfsroebqtuairned pinowFiegru,rteh1e1thareusctrupcriealsefonrts the different scales; the lower value is obtained at the beginning of the cruise at load variation, at that maximbuuilmdinvgaltuhe ahtyflbriigdhtsyssttaermti.nDgu(trainkge-tohfef)c.rTuhiserpehsauslets, tohbetapionwederinofFtihgeutruer1b1inaeriesclrouwceiarlthfoarnbtuheilding take-off and climbing phase: this could allow the use of a smaller size turboprop with a reduced point, keeping a rather constant value. According to the trend of required power, the thrust presents the hybrid system. During the cruise phase, the power of the turbine is lower than the take-off and the mnaoxmiminaulmpowvaelruuentaitl tfhliegphotwsetrarctriunigse (pthaaksee-,oafnf)d. sTuhpeplryetshueltdsifofebrteanicneeidn pinowFeirgubertew1e1enatrhe cruicsieal for climbing phase: this could allow the use of a smaller size turboprop with a reduced nominal power buildpinowgetrhaendhythberimdasxyimstuem.poDwuerrinugsinthgeancreuleicstericpmhaosteo,r.the power of the turbine is lower than the until the power cruise phase, and supply the difference in power between the cruise power and the take-off and climbing phase: this could allow the use of a smaller size turboprop with a reduced maximum power using an electric motor. nominal power until the power cruise phase, and supply the difference in power between the cruise power and the maximum power using an electric motor. Altitude [m] Altitude [m]PDF Image | Turboprop Hybrid Electric Propulsion System
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