def __init__(self,aircraft,overrideColumn=0): self.aircraft = aircraft self.constants = constants.load('mass',overrideColumn) self.aircraftMass = aircraft.mass self.aircraftMass.airframe = MassList('Airframe') #atm =fc.ISAtmosphere(aircraft.designGoals.designAltitude) self._designQ =aircraft.designGoals.fc.dynamicPressure self._designM =aircraft.designGoals.fc.Mach self._Wdg =float((aircraft.designGoals.designGrossMass*qu.kg).rescale('pound')) self._Nz =aircraft.designGoals.designLoadFactor*1.5 self._q =float((self._designQ*qu.Pa).rescale('pound_force/ft**2')) self._Nen =float(len(aircraft.engine.engineList)) self._wing() self._hStab() self._vStab() self._fuselage() self._landingGear() self._engine() self._fuel() self._misc() # self.emptyMass =0.0 # self.payloadMass =0.0 # self.totalMass =0.0 self.CG=np.zeros(3) self.get_inertia() self.aircraftMass.update_total()
def __init__(self,aircraft): self.ac = aircraft self.emptyMass = MassList(self.ac.name) self.fuelProp = constants.load('fuel_density') self.constMass = constants.load('mass')