class SeriellHybrid(Propulsion):
'''
Konstruktor für seriellen Hybrid
initialisiert "ICE", "Battery"
'''
def __init__(self, config):
self.Pemot_max = config["pmax"]
self.m_pl = config["mpl"]
self.Pice_max = config["pice"]
self.ice = ICE(Pmax=self.Pice_max)
self.Pice_opt = self.ice.Popt
self.m_pl = config["mpl"]
self.Nice = self.ice.N_opt
self.Mice = self.Pice_opt / N2omega(self.Nice)
self.emot = Emotor(self.Pemot_max)
self.Pmax = self.Pemot_max
self.bat = Battery(config["cbat"], config["pbat"])
self.fuel = config["fuel"]
super(self.__class__, self).__init__()
'''
Rückgabe: Propellerdrehzahl, passen zu Leistung "P"
'''
def calcNProp(self, P):
#return self.ice.calcNProp(self.Pmax)
return self.ice.getNforP(P, self.Pmax, verbose=False) / c.GEAR_RATIO
'''
berechnet die nötige Wellenleistung
Rückgabe: Pshaft, Nprop
'''
def calcPshaft(self, h, tas, F):
Pold = self.Pshaft
Nprop = self.calcNProp(Pold)
Pshaft = self.Pshaft #first guess
eta, Nprop = self.prop.calcEfficiency(h,
tas,
Nprop,
Pshaft,
NpropMax=c.PROP_MAX_N,
fixN=True)
Pshaft = self.calcNeededP(tas, F, eta, c.GEAR_EFF_SERI)
itegrationLimit = 0.1
i = 0
while (abs(Pshaft - Pold) > itegrationLimit):
Pold = Pshaft
etaOld = eta
Nprop = self.calcNProp(Pshaft)
eta, Nprop = self.prop.calcEfficiency(h,
tas,
Nprop,
Pshaft,
NpropMax=c.PROP_MAX_N,
fixN=True)
Pshaft = self.calcNeededP(tas, F, eta, c.GEAR_EFF_SERI)
i += 1
if (i > 100 and Pshaft > Pold):
if (self.verbose):
print("endlosschleife -> " + str(Pshaft) + " != [" +
str(Pold) + "]")
Pshaft = (Pshaft + Pold) / 2
eta = (eta + etaOld) / 2
Nprop = self.calcNProp(Pshaft)
eta, Nprop = self.prop.calcEfficiency(h,
tas,
Nprop,
Pshaft,
NpropMax=c.PROP_MAX_N,
fixN=True)
Pshaft = self.calcNeededP(tas, F, eta, c.GEAR_EFF_PARA)
break
#SHOW FINAL DEBUG INFO
self.prop.calcEfficiency(h,
tas,
Nprop,
Pshaft,
NpropMax=c.PROP_MAX_N,
verbose=True)
self.Pshaft = Pshaft
if (self.verbose):
print('[Propulsion] needed Thrust = ' + str(F))
print('[Propulsion] TAS = ' + str(tas))
print('[Propulsion] Pshaft = ' + str(Pshaft))
print('[Propulsion] Nprop = ' + str(Nprop))
print('[Propulsion] etaProp = ' + str(eta))
print(
'[Propulsion] needed Iterations for calculation of Pshaft: ' +
str(i))
return Pshaft, Nprop
'''
berechnet erst benötigte Wellenleistung und dann motorverbrauch und Betriebsparameter
Rückgabe: Pshaft, Nprop, m_f, We, Pice, Nice, Pemot, Wcharge
'''
def calcConsumption(self, h, tas, F, dt):
if (F <= 0 and self.bat.full()):
Pshaft = 0
Nprop = 0
else:
Pshaft, Nprop = self.calcPshaft(h, tas, F)
return self.calcMotorConsumption(h, Pshaft, Nprop, dt)
'''
berechnet motorverbrauch und Betriebsparameter
Rückgabe: Pshaft, Nprop, m_f, We, Pice, Nice, Pemot, Wcharge
'''
def calcMotorConsumption(self, h, Pshaft, Nprop, dt):
if (Pshaft <= 0 and self.bat.full()):
Nprop = 0
Mprop = 0
Nice = self.ice.getNidle()
m_f = 0
FF = 0
Pice = 0
We_ice = 0
We = 0
We_bat = 0
else:
Mprop = Pshaft / N2omega(Nprop)
Nice = self.Nice
Mice = self.Mice
Pice = self.Pice_opt
#needed elec-Power
We = self.emot.calcConsumption(Nprop, Mprop, dt)
We_ice = We
if (self.bat.empty()):
We_ice = We + self.bat.getMaxChargeRate()
Pice = self.ice.calcNeededICEPower(We_ice, dt)
Pice = min(Pice, self.ice.Pmax)
Nice = self.ice.calcNIce(Pice)
Mice = Pice / N2omega(Nice)
m_f, FF = self.ice.calcConsumption(Nice, Mice, dt)
We_ice = self.ice.calcGeneratorWe(Pice, dt)
We_bat = We_ice - We
self.SoF -= self.ice.calcConsumtionToL(m_f,
dt) / self.fuel #self.V_tank
We, Wcharge = self.bat.charge(We_bat, dt)
if (self.verbose):
print('[Propulsion] Nice = ' + str(Nice))
print('[Propulsion] Pice = ' + str(Pice))
print('[Propulsion] FF = ' + str(FF))
print('[Propulsion] SoC = ' + str(self.bat.SoC))
print('[Propulsion] SoF = ' + str(self.SoF))
return Pshaft, Nprop, m_f, We, Pice, Nice, Pshaft, Wcharge
'''
Berechnet Antriebskomponentenmassen und speichert sie in Klassenvariable "mass" (dict)
Rückgabe: Gesamtantriebsmasse
'''
def calcPropulsionMasses(self):
self.mass["ICE"] = 0.
self.mass["Gen"] = 0.
self.mass["Umr2"] = 0.
if (self.Pice_max > 0):
self.mass["ICE"] = (self.Pice_max / c.PD_ice) + c.PD_ice_add
self.mass["Gen"] = (self.Pice_max / c.PD_emot) + c.PD_emot_add
self.mass["Umr2"] = (self.Pice_max / c.PD_inv) + c.PD_inv_add
self.mass["EMot"] = (self.Pmax / c.PD_emot) + c.PD_emot_add
self.mass["Umr"] = (self.Pmax / c.PD_inv) + c.PD_inv_add
self.mass["Bat"] = 0.
if (self.bat.C > 0.):
self.mass["Bat"] = self.bat.calcMass()
return sum(self.mass.values())
