#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
