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motor_test.py
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motor_test.py
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from gpkit import Model, parse_variables, SignomialsEnabled, SignomialEquality, units
from motor import Propulsor, Motor, MotorPerf
from gpkitmodels.GP.aircraft.prop.propeller import Propeller, ActuatorProp
from gpkitmodels.GP.aircraft.wing.wing_test import FlightState
class Propulsor_Test(Model):
"""Propulsor Test Model
"""
def setup(self):
fs = FlightState()
p = Propulsor()
pp = p.flight_model(p,fs)
pp.substitutions[pp.prop.T] = 100
#pp.substitutions[pp.prop.AR_b] = 15
self.cost = 1./pp.motor.etam + p.W/(1000*units('lbf')) + 1./pp.prop.eta
return fs,p,pp
class Actuator_Propulsor_Test(Model):
"""Propulsor Test Model
"""
def setup(self):
fs = FlightState()
Propulsor.prop_flight_model = ActuatorProp
p = Propulsor()
pp = p.flight_model(p,fs)
pp.substitutions[pp.prop.T] = 100
#pp.substitutions[pp.prop.AR_b] = 15
self.cost = pp.motor.Pelec/(1000*units('W')) + p.W/(1000*units('lbf'))
return fs,p,pp
def actuator_propulsor_test():
test = Actuator_Propulsor_Test()
#sol = test.debug()
sol = test.solve()
#sol = test.solve()
print sol.table()
def propulsor_test():
test = Propulsor_Test()
#sol = test.debug()
#sol = test.localsolve(iteration_limit = 400)
sol = test.solve()
print sol.table()
class Motor_P_Test(Model):
def setup(self):
fs = FlightState()
m = Motor()
mp = MotorPerf(m,fs)
self.mp = mp
mp.substitutions[m.Qmax] = 100
mp.substitutions[mp.Q] = 10
self.cost = 1./mp.etam + m.W/(100.*units('lbf'))
return self.mp, fs, m
class speed_280_motor(Model):
def setup(self):
fs = FlightState()
m = Motor()
mp = MotorPerf(m,fs)
self.mp = mp
mp.substitutions[m.Qmax] = 100
mp.substitutions[mp.R] = .7
mp.substitutions[mp.i0] = .16
mp.substitutions[mp.Kv] = 3800
mp.substitutions[mp.v] = 6
self.cost = 1./mp.etam
return self.mp, fs
class hacker_q150_45_motor(Model):
def setup(self):
fs = FlightState()
m = Motor()
mp = MotorPerf(m,fs)
self.mp = mp
mp.substitutions[m.Qmax] = 10000
mp.substitutions[mp.R] = .033
mp.substitutions[mp.i0] = 4.5
mp.substitutions[mp.Kv] = 29
self.cost = 1./mp.etam
return self.mp, fs
def speed_280_test():
test = speed_280_motor()
sol = test.solve()
print sol.table()
class graupner_cam_6x3(Model):
def setup(self):
self.fs = FlightState()
self.p = Propeller()
self.p.substitutions[self.p.R] = (3./12.) #Convert in to ft
return self.p, self.fs
class motorProp(Model):
def setup(self):
p = graupner_cam_6x3()
m = speed_280_motor()
p.fs.substitutions[p.fs.V] = 10
self.cost(1/p.eta)
def motor_test():
test = Motor_P_Test()
sol = test.solve()
#sol = test.debug()
#print sol.table()
def motor_eta_speed():
test = Motor_P_Test()
omega = [.01, 10, 100, 200, 400, 600, 800, 1000, 1200, 1400, 1600, 1800, 2000, 3000, 4000, 10000, 100000]
eta = []
for o in omega:
test = Motor_P_Test()
test.substitutions[test.mp.omega] = o
sol = test.solve()
eta.append(sol["freevariables"]["etam"])
print omega
print eta
#sol = test.debug()
plt.plot(omega, eta)
plot.show()
print sol.table()
def test():
motor_test()
actuator_propulsor_test()
propulsor_test()
if __name__ == "__main__":
test()
#speed_280_test()