from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K from scalar.units import AsUnit from Aerothon.AeroUtil import STDCorrection 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
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'AXI_4130_16' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.063 * OHM #Coil resistance Motor.Io = 1.3 * A #Idle current Motor.Kv = 385 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 409 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
import cmath as math from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K from scalar.units import AsUnit from Aerothon.AeroUtil import STDCorrection #sys.path.append(os.path.join(BAPDir,r'Propulsion\Batteries')) #from Electrolux_6Cell_3100 import Electrolux_6Cell_3100 from Batteries.Turnigy_6Cell_3000 import Turnigy_6Cell_3000 #sys.path.append(os.path.join(BAPDir,r'Propulsion\SpeedControllers')) from SpeedControllers.Phoenix import Phoenix100 # note: Phoenix contains multiple models # Set Motor properties Motor = ACMotor() Motor.name = 'Scorpion250KV' Motor.Battery = Turnigy_6Cell_3000 Motor.SpeedController = Phoenix100 #Manufacturer Data # Motor.Ri = 0.02*OHM #Coil resistance # Motor.Io = 1.5*A #Idle current # Motor.Kv = 250*RPM/V #RPM/Voltage ratio #Matched Data Motor.Ri = 0.037 * OHM Motor.Io = 0.69 * A Motor.Kv = 250 * RPM / V # Motor.Vmax = 23.5 * V Motor.Imax = 65 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf'
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'AXI_4120_20' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.082 * OHM #Coil resistance Motor.Io = 1.5 * A #Idle current Motor.Kv = 465 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 52 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 320 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A50_12L_Turnado_V3' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.019 * OHM #Coil resistance Motor.Io = 1.2 * A #Idle current Motor.Kv = 450 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 455 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K from scalar.units import AsUnit from Aerothon.AeroUtil import STDCorrection from Aircraft_Models.Reg2015Aircraft_AeroCats.Propulsion.Batteries.Turnigy_6Cell_3000 import Turnigy_6Cell_3000 # Set Motor properties Motor = ACMotor() Motor.name = 'Hacker_A60_7XS' Motor.Battery = Turnigy_6Cell_3000 #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 = 0.16 * OHM #.15 Motor.Io = .5 * A #1.5 Motor.Kv = 380 * RPM / V #370 # Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A50_12S' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.016 * OHM #Coil resistance Motor.Io = 1.8 * A #Idle current Motor.Kv = 480 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 208 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A60_5S' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.015 * OHM #Coil resistance Motor.Io = 1.7 * A #Idle current Motor.Kv = 295 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 595 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A50_16S' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.026 * OHM #Coil resistance Motor.Io = 1.4 * A #Idle current Motor.Kv = 365 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 345 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'AXI_4130_20' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.099 * OHM #Coil resistance Motor.Io = 1.2 * A #Idle current Motor.Kv = 305 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 409 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'AXI_5320_18' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.023 * OHM #Coil resistance Motor.Io = 1.4 * A #Idle current Motor.Kv = 370 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 78 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 495 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A60_5XS28' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.012*OHM #Coil resistance Motor.Io = 2.4*A #Idle current Motor.Kv = 420*RPM/V #RPM/Voltage ratio Motor.Vmax = 23.5*V Motor.Imax = 55*A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 480*GRAM*gacc Motor.LenDi = [46.8*MM, 59.98*MM] # # This data has been corrected for standard day
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 0.025 * OHM #Coil resistance Motor.Io = 1.1 * A #Idle current Motor.Kv = 440 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 85 * 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 #
from __future__ import division # let 5/2 = 2.5 rather than 2 # Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K from scalar.units import AsUnit from Aerothon.AeroUtil import STDCorrection 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
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'AXI_5325_16' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.026*OHM #Coil resistance Motor.Io = 2.1*A #Idle current Motor.Kv = 350*RPM/V #RPM/Voltage ratio Motor.Vmax = 23.5*V Motor.Imax = 85*A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 575*GRAM*gacc Motor.LenDi = [46.8*MM, 59.98*MM] # # This data has been corrected for standard day
from __future__ import division # let 5/2 = 2.5 rather than 2 # Optimum Prop None from Aerothon.ACMotor import ACMotor import numpy as npy import cmath as math from scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K from scalar.units import AsUnit from Aerothon.AeroUtil import STDCorrection from Adv2020Aircraft.Hardware.Batteries.Gens_6Cell_5000 import Gens_6Cell_5000 # Set Motor properties Motor = ACMotor() Motor.name = 'Hacker_A50_V3' Motor.Battery = Gens_6Cell_5000 # Manufacturer Data # Motor.Ri = 0.026*OHM #Coil resistance # Motor.Io = 1.1*A #Idle current # Motor.Kv = 400*RPM/V #RPM/Voltage ratio # Matched data Motor.Ri = .12 * OHM Motor.Io = .5 * A Motor.Kv = 400 * RPM / V Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A40_12L_14' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.025*OHM #Coil resistance Motor.Io = 1.5*A #Idle current Motor.Kv = 410*RPM/V #RPM/Voltage ratio Motor.Vmax = 23.5*V Motor.Imax = 55*A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 272*GRAM*gacc Motor.LenDi = [46.8*MM, 59.98*MM] # # This data has been corrected for standard day
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A60_20S' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.027 * OHM #Coil resistance Motor.Io = 1.7 * A #Idle current Motor.Kv = 245 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 595 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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 = 'Hacker_A50_14L_Turnado' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.026 * OHM #Coil resistance Motor.Io = 1.1 * A #Idle current Motor.Kv = 400 * RPM / V #RPM/Voltage ratio Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 455 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #
from __future__ import division # let 5/2 = 2.5 rather than 2 # Optimum Prop None from Aerothon.ACMotor import ACMotor 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
from __future__ import division # let 5/2 = 2.5 rather than 2 # 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_HKIII_5035_380' Motor.Battery = ThunderPower_4Cell_4400 Motor.Ri = 0.013 * OHM #Coil resistance Motor.Io = 1.44 * A #Idle current Motor.Kv = 380 * 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 = 744 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # # This data has been corrected for standard day #