import numpy as npy import cmath as math from Aerothon.AeroUtil import STDCorrection from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_5000 import ThunderPower_4Cell_5000 from scalar.units import MM, IN, K, inHg, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4020' Motor.Battery = ThunderPower_4Cell_5000 Motor.Ri = 0.058*OHM #Coil resistance Motor.Io = 1.4*A #Idle current Motor.Kv = 585*RPM/V #RPM/Voltage ratio Motor.Vmax = 25.9*V Motor.Imax = 85*A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 1000000 Motor.Pz = 0.0 Motor.Weight = 304*GRAM*gacc Motor.LenDi = [60.2*MM, 48.9*MM] Arm=10.5*IN Arm2=19.5*IN # # This data has been corrected for standard day # # RPM, Torque Current Voltage
from Adv2020Aircraft.Hardware.Batteries.Turnigy_6Cell_3300 import Turnigy_6Cell_3300 # Set Motor properties Motor = ACMotor() Motor.name = 'ScorpionSII4035' Motor.Battery = Turnigy_6Cell_3300 # Manufacturer Data # Motor.Ri = 0.02*OHM #Coil resistance # Motor.Io = 1.5*A #Idle current # Motor.Kv = 320*RPM/V #RPM/Voltage ratio # Matched Data Motor.Ri = 0.037 * OHM # .15 Motor.Io = .69 * A # 1.5 Motor.Kv = 250 * RPM / V # 370 # Motor.Vmax = 41.53 * V Motor.Imax = 65 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 450 * GRAM * gacc Motor.LenDi = [46.8 * MM, 64.9 * MM] # # This data has been corrected for standard day STD = STDCorrection(30.2 * inHg, (16.1 + 273.15) * K) # RPM, Torque Current Voltage TestData = [(2072 * RPM, (47 * IN * OZF) * STD, 7.2 * A, 24.44 * V),
from Reg2015Aircraft_Aerocats.Propulsion.Batteries.Turnigy_6Cell_3000 import Turnigy_6Cell_3000 # Set Motor properties Motor = ACMotor() Motor.name = 'Hacker_A50_14L' Motor.Battery = Turnigy_6Cell_3000 #Manufacturer Data # Motor.Ri = 0.025*OHM #Coil resistance # Motor.Io = 1*A #Idle current # Motor.Kv = 300*RPM/V #RPM/Voltage ratio #Matched data Motor.Ri = .12 * OHM Motor.Io = .5 * A Motor.Kv = 355 * RPM / V Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 445 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day STD = STDCorrection(29.9 * inHg, (23.9 + 273.15) * K) Arm = 19.5 * IN # RPM, Torque Current Voltage
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4025_16' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.034 * OHM #Coil resistance Motor.Io = 1.89 * A #Idle current Motor.Kv = 320 * RPM / V #RPM/Voltage ratio Motor.Vmax = 26.250 * V Motor.Imax = 80 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 416 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4045_12' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.028 * OHM #Coil resistance Motor.Io = 2.9 * A #Idle current Motor.Kv = 247 * RPM / V #RPM/Voltage ratio Motor.Vmax = 30.526 * V Motor.Imax = 95 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 621 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'OS_OSMG9550' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.0275 * OHM #Coil resistance Motor.Io = 2 * A #Idle current Motor.Kv = 375 * RPM / V #RPM/Voltage ratio Motor.Vmax = 31 * V Motor.Imax = 50 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 405 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4035_12' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.024 * OHM #Coil resistance Motor.Io = 2.09 * A #Idle current Motor.Kv = 299 * RPM / V #RPM/Voltage ratio Motor.Vmax = 26.842 * V Motor.Imax = 95 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 521 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion_SII_4025_330' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.037 * OHM #Coil resistance Motor.Io = 0.74 * A #Idle current Motor.Kv = 330 * RPM / V #RPM/Voltage ratio Motor.Vmax = 26.6 * V Motor.Imax = 75 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 353 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion_SII_402_420' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.034 * OHM #Coil resistance Motor.Io = 0.91 * A #Idle current Motor.Kv = 420 * RPM / V #RPM/Voltage ratio Motor.Vmax = 21.43 * V Motor.Imax = 70 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 288 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion_HK_3226_900' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.034 * OHM #Coil resistance Motor.Io = 1.54 * A #Idle current Motor.Kv = 630 * RPM / V #RPM/Voltage ratio Motor.Vmax = 15.7 * V Motor.Imax = 95 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 346 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4025_14' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.024*OHM #Coil resistance Motor.Io = 2.19*A #Idle current Motor.Kv = 370*RPM/V #RPM/Voltage ratio Motor.Vmax = 23.33*V Motor.Imax = 90*A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 416*GRAM*gacc Motor.LenDi = [46.8*MM, 59.98*MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 *RPM, 7*IN*OZF, 9*A, 6.4*V)] #this is actual test data from a test stand
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion_SII_402_420' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.06 * OHM #Coil resistance Motor.Io = 2.7 * A #Idle current Motor.Kv = 400 * RPM / V #RPM/Voltage ratio Motor.Vmax = 18.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 346 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Hyperion_ZS4035_10' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.018 * OHM #Coil resistance Motor.Io = 2.29 * A #Idle current Motor.Kv = 354 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.182 * V Motor.Imax = 110 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 521 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
# Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from Aircraft_Models.Reg2014Aircraft_AeroCats.Propulsion.Batteries.ThunderPower_4Cell_4400 import ThunderPower_4Cell_4400 from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF from scalar.units import AsUnit # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion_SII_4025_250' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.037 * OHM #Coil resistance Motor.Io = .69 * A #Idle current Motor.Kv = 250 * RPM / V #RPM/Voltage ratio Motor.Vmax = 40 * V Motor.Imax = 65 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 450 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day # # RPM, Torque Current Voltage TestData = [(5500 * RPM, 7 * IN * OZF, 9 * A, 6.4 * V)
