Python ACMotor.Battery Beispiele

Beispiel #1

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

Beispiel #2

Datei: untested_Hacker_A60_20S.py Projekt: 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_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
#

Beispiel #3

Datei: Hacker_A50_14L.py Projekt: Aerothon-2020/Reg2015Aircraft_Aerocats

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

Beispiel #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 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