コード例 #1
0
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

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 = '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
#
コード例 #3
0
# 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
#
コード例 #4
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_5320_18'
Motor.Battery = ThunderPower_4Cell_4400
Motor.Ri = 0.07 * OHM  #Coil resistance
Motor.Io = 1.5 * A  #Idle current
Motor.Kv = 515 * 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 = 320 * GRAM * gacc
Motor.LenDi = [46.8 * MM, 59.98 * MM]

#
# This data has been corrected for standard day
#
コード例 #5
0
# 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
#
コード例 #6
0
# 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_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
#
コード例 #7
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_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
#
コード例 #8
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
#
コード例 #9
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_18'
Motor.Battery = ThunderPower_4Cell_4400
Motor.Ri = 0.032 * OHM  #Coil resistance
Motor.Io = 1.7 * A  #Idle current
Motor.Kv = 308 * RPM / V  #RPM/Voltage ratio
Motor.Vmax = 23.5 * V
Motor.Imax = 80 * A
Motor.ThrustUnit = LBF
Motor.ThrustUnitName = 'lbf'

Motor.xRm = 100000
Motor.Pz = 0.0

Motor.Weight = 574 * GRAM * gacc
Motor.LenDi = [46.8 * MM, 59.98 * MM]

#
# This data has been corrected for standard day
#
コード例 #10
0
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
# Test data from the test stand
コード例 #11
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 = '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
#
コード例 #12
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_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
#
コード例 #13
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
#
コード例 #14
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 = 0.032 * OHM  #Coil resistance
Motor.Io = 1.1 * A  #Idle current
Motor.Kv = 355 * 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 = 355 * GRAM * gacc
Motor.LenDi = [46.8 * MM, 59.98 * MM]

#
# This data has been corrected for standard day
#
コード例 #15
0
#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
Motor.Battery.WeightGroup = 'Electronics'