#Motor.Ri = Motor.Ri + 0.04*OHM Motor.Battery = Battery Motor.SpeedController = Phoenix100 Motor.Battery.WeightGroup = 'Electronics' Motor.SpeedController.WeightGroup = 'Electronics' Motor.WeightGroup = "Propulsion" Prop.WeightGroup = "Propulsion" Vmax = 50 # Set Propulsion properties Propulsion = ACPropulsion(Prop, Motor) Propulsion.Alt = 0 * FT Propulsion.Vmax = Vmax * FT / SEC Propulsion.nV = 30 if __name__ == '__main__': import pylab as pyl V = npy.linspace(0, Vmax, 30) * FT / SEC Vprop = npy.linspace(0, Vmax, 6) * FT / SEC N = Motor.NRange() Propulsion.PlotMatched(V, N, Vprop, fig=2, ylimits=[None, None, None, None]) #Propulsion.PlotTPvsN(N, Vprop, fig=3)
#Motor.Ri = Motor.Ri + 0.04*OHM Motor.Battery = Battery Motor.SpeedController = Phoenix100 Motor.Battery.WeightGroup = 'Electronics' Motor.SpeedController.WeightGroup = 'Electronics' Motor.WeightGroup = "Propulsion" Prop.WeightGroup = "Propulsion" Vmax = 50 # Set Propulsion properties Propulsion = ACPropulsion(Prop, Motor) Propulsion.Alt = 650 * FT Propulsion.Vmax = Vmax * FT / SEC Propulsion.nV = 30 if __name__ == '__main__': import pylab as pyl V = npy.linspace(0, Vmax, 30) * FT / SEC Vprop = npy.linspace(0, Vmax, 6) * FT / SEC N = Motor.NRange() Propulsion.PlotMatched(V, N, Vprop, fig=2, ylimits=[None, None, None, None]) #Propulsion.PlotTPvsN(N, Vprop, fig=3)
#Motor.Ri = Motor.Ri + 0.04*OHM Motor.Battery = Turnigy_6Cell_3000 Motor.SpeedController = Phoenix100 Motor.Battery.WeightGroup = 'Electronics' Motor.SpeedController.WeightGroup = 'Electronics' Motor.WeightGroup = "Propulsion" Prop.WeightGroup = "Propulsion" Vmax = 50 # Set Propulsion properties Propulsion = ACPropulsion(Prop, Motor) Propulsion.Alt = 721 * FT Propulsion.Vmax = Vmax * FT / SEC Propulsion.nV = 30 if __name__ == '__main__': import pylab as pyl V = npy.linspace(0, Vmax, 30) * FT / SEC Vprop = npy.linspace(0, Vmax, 6) * FT / SEC N = Motor.NRange() Propulsion.PlotMatched(V, N, Vprop, fig=2, ylimits=[None, None, None, None]) #Propulsion.PlotTPvsN(N, Vprop, fig=3)
from Aerothon.ACPropeller import ACPropeller from Aerothon.ACEngine import ACEngine from Aerothon.ACPropulsion import ACPropulsion from Engine.OS61FX_04 import Engine as OS from Engine.MAGNUM import Engine as Magnum from Prop.APC_12_25x3_75 import Prop #from APC_13_5x6 import Prop #from GRAUPNER_13_5x6 import Prop import numpy as npy from scalar.units import IN, LBF, PSFC, SEC, ARCDEG, FT, OZF, RPM, HP from scalar.units import AsUnit # Set Propulsion properties PropulsionOS = ACPropulsion(Prop, OS) PropulsionOS.Alt = 0 * FT PropulsionOS.Vmax = 100 * FT / SEC PropulsionOS.nV = 20 PropulsionMAG = ACPropulsion(Prop, Magnum) PropulsionMAG.Alt = 0 * FT PropulsionMAG.Vmax = 100 * FT / SEC PropulsionMAG.nV = 20 if __name__ == '__main__': import pylab as pyl print "Static Thrust :", AsUnit(PropulsionOS.T(0 * FT / SEC), "lbf") print "Static Thrust :", AsUnit(PropulsionMAG.T(0 * FT / SEC), "lbf") Vmax = 100