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')
