def setUpClass(cls):
cls.n = 10
cls.p = Problem(model=Group())
ivc = cls.p.model.add_subsystem('ivc',
IndepVarComp(),
promotes_outputs=['*'])
ivc.add_output('alt',
val=3000 * np.ones(cls.n),
units='m',
desc='altitude above MSL')
ivc.add_output('TAS',
val=250.0 * np.ones(cls.n),
units='m/s',
desc='true airspeed')
# ivc.add_output('TAS_rate', val=np.zeros(cls.n), units='m/s**2', desc='acceleration')
ivc.add_output('gam',
val=np.zeros(cls.n),
units='rad',
desc='flight path angle')
# ivc.add_output('gam_rate', val=np.zeros(cls.n), units='rad/s',
# desc='flight path angle rate')
ivc.add_output('S',
val=427.8 * np.ones(cls.n),
units='m**2',
desc='reference area')
ivc.add_output('mach',
val=0.8 * np.ones(cls.n),
units=None,
desc='mach number')
ivc.add_output('W_total',
val=200000 * 9.80665 * np.ones(cls.n),
units='N',
desc='aircraft total weight')
ivc.add_output('q',
val=0.5 * 250.0**2 * np.ones(cls.n),
units='Pa',
desc='dynamic pressure')
cls.p.model.add_subsystem(
'flight_equilibrium',
subsys=SteadyFlightEquilibriumGroup(num_nodes=cls.n),
promotes_inputs=['aero.*'],
promotes_outputs=['aero.*'])
cls.p.model.connect('alt', ('aero.alt'))
# cls.p.model.connect('TAS', 'aero.TAS')
# cls.p.model.connect('TAS_rate', 'flight_equilibrium.TAS_rate')
cls.p.model.connect('gam', 'flight_equilibrium.gam')
# cls.p.model.connect('gam_rate', 'flight_equilibrium.gam_rate')
cls.p.model.connect('S', ('aero.S', 'flight_equilibrium.S'))
cls.p.model.connect('mach', 'aero.mach')
cls.p.model.connect('W_total', 'flight_equilibrium.W_total')
cls.p.model.connect('q', ('aero.q', 'flight_equilibrium.q'))
cls.p.setup(check=True, force_alloc_complex=True)
cls.p.run_model()
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='mass_comp', subsys=MassComp(num_nodes=nn))
self.connect('mass_comp.W_total', 'flight_equilibrium.W_total')
self.add_subsystem(name='atmos', subsys=USatm1976Comp(num_nodes=nn))
self.connect('atmos.pres', 'propulsion.pres')
self.connect('atmos.sos', 'tas_comp.sos')
self.connect('atmos.rho', 'q_comp.rho')
self.add_subsystem(name='tas_comp',
subsys=TrueAirspeedComp(num_nodes=nn))
self.connect('tas_comp.TAS',
('gam_comp.TAS', 'q_comp.TAS', 'range_rate_comp.TAS'))
self.add_subsystem(name='gam_comp',
subsys=SteadyFlightPathAngleComp(num_nodes=nn))
self.connect('gam_comp.gam',
('flight_equilibrium.gam', 'range_rate_comp.gam'))
self.add_subsystem(name='q_comp',
subsys=DynamicPressureComp(num_nodes=nn))
self.connect('q_comp.q',
('aero.q', 'flight_equilibrium.q', 'propulsion.q'))
self.add_subsystem(name='flight_equilibrium',
subsys=SteadyFlightEquilibriumGroup(num_nodes=nn),
promotes_inputs=['aero.*'],
promotes_outputs=['aero.*'])
self.connect('flight_equilibrium.CT', 'propulsion.CT')
self.add_subsystem(name='propulsion',
subsys=PropulsionGroup(num_nodes=nn))
self.add_subsystem(name='range_rate_comp',
subsys=RangeRateComp(num_nodes=nn))