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 Motor.Weight = 445 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] #
# 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 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' Motor.xRm = 100000 Motor.Pz = 0.0 Motor.Weight = 450 * GRAM * gacc Motor.LenDi = [48.8 * MM, 64.9 * MM] # Assign objects to weight classes
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 = '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 = '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 #
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 = '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 #
Motor.Weight = 445 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] # Assign objects to weight classes Motor.Battery.WeightGroup = 'Electronics' Motor.SpeedController.WeightGroup = 'Electronics' Motor.WeightGroup = 'Propulsion' ## Manufacturer Data(SPH: Why are we not using these? are they not valid? 151113) # Motor.Ri = 0.025*OHM #Coil resistance # Motor.Io = 1*A #Idle current # Motor.Kv = 300*RPM/V #RPM/Voltage ratio # Matched data - Model 2 Motor.Ri = .077 * OHM #.09 Motor.Io = 1.5 * A Motor.Kv = 310 * RPM / V #320 # SPH: Test data here?? (151113) Motor.Vmax = 23.5 * V Motor.Imax = 55 * A Motor.ThrustUnit = LBF Motor.ThrustUnitName = 'lbf' Motor.xRm = 100000 Motor.Pz = 0.0 # This data has been corrected for standard day #SPH: confirm the methodology behind these calculations 151113 STD = STDCorrection(29.9 * inHg, (23.9 + 273.15) * K) Arm = 19.5 * IN
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 Motor.Weight = 480 * GRAM * gacc Motor.LenDi = [46.8 * MM, 59.98 * MM] #
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 #
