Python ACMotor Examples

Example #1

File: Hacker_A60_7XS.py Project: Aerothon-2020/Adv2020Aircraft

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_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

Example #2

File: untested_Hacker_A50_12L_Turnado_V3.py Project: Aerothon-2020/Adv2020Aircraft

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
#

Example #3

File: untested_Hyperion_ZS4045_10.py Project: Aerothon-2020/Adv2020Aircraft

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_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 = 621*GRAM*gacc
Motor.LenDi = [46.8*MM, 59.98*MM]

#
# This data has been corrected for standard day

Example #4

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
#

Example #5

File: Scorpion_SII_4025_330.py Project: Aerothon-2020/Adv2019Aircraft

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 Adv2019Aircraft.Propulsion.Turnigy_6Cell_3000 import Turnigy_6Cell_3000
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 = Turnigy_6Cell_3000
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

Example #6

# import Aerothon modules
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.ACMotor import ACMotor
from Aerothon.AeroUtil import STDCorrection

# (USER) import Aerothon components
from Adv2019Aircraft.Propulsion.Turnigy_6Cell_3000 import Turnigy_6Cell_3000
from Adv2019Aircraft.Propulsion.Phoenix import Phoenix100  # note: Phoenix contains multiple models

#==============================================================================#
# MOTOR MODEL
#==============================================================================#
# Set Motor properties
Motor = ACMotor()
Motor.name = 'Hacker_A50_14L'

# Associate the motor with a battery and a speed controller (imported above)
Motor.Battery = Turnigy_6Cell_3000
Motor.SpeedController = Phoenix100

# Motor dimensions # SPH: confirm these values 151113
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'

Example #7

File: Scorpion250KV.py Project: Aerothon-2020/Reg2020Aircraft

import numpy as npy
import cmath as math
from Aerothon.scalar.units import MM, IN, OZF, RPM, HP, V, A, OHM, GRAM, gacc, mAh, W, LBF, inHg, K
from Aerothon.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