def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='atmos',
subsys=StandardAtmosphereGroup(num_nodes=nn),
promotes_inputs=['h'])
self.add_subsystem(
name='aero',
subsys=AeroGroup(num_nodes=nn),
promotes_inputs=['v', 'alpha'],
)
self.connect('atmos.sos', 'aero.sos')
self.connect('atmos.rho', 'aero.rho')
self.add_subsystem(name='prop',
subsys=PropGroup(num_nodes=nn),
promotes_inputs=['h', 'throttle'])
self.connect('aero.mach', 'prop.mach')
self.add_subsystem(name='flight_dynamics',
subsys=FlightPathEOM2D(num_nodes=nn),
promotes_inputs=['m', 'v', 'gam', 'alpha'])
self.connect('aero.f_drag', 'flight_dynamics.D')
self.connect('aero.f_lift', 'flight_dynamics.L')
self.connect('prop.thrust', 'flight_dynamics.T')
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='atmos', subsys=USatm1976Comp(num_nodes=nn))
if not self.options['ballistic']:
self.add_subsystem(name='water_engine',
subsys=WaterEngine(num_nodes=nn),
promotes_inputs=['rho_w'])
self.add_subsystem(name='mass_adder',
subsys=_MassAdder(num_nodes=nn),
promotes_inputs=['rho_w'])
self.add_subsystem(name='dynamic_pressure',
subsys=DynamicPressureComp(num_nodes=nn))
self.add_subsystem(name='aero', subsys=LiftDragForceComp(num_nodes=nn))
self.add_subsystem(name='eom', subsys=FlightPathEOM2D(num_nodes=nn))
self.connect('atmos.rho', 'dynamic_pressure.rho')
self.connect('dynamic_pressure.q', 'aero.q')
self.connect('aero.f_drag', 'eom.D')
self.connect('aero.f_lift', 'eom.L')
if not self.options['ballistic']:
self.connect('atmos.pres', 'water_engine.p_a')
self.connect('water_engine.F', 'eom.T')
self.connect('mass_adder.m', 'eom.m')
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='atmos',
subsys=USatm1976Comp(num_nodes=nn),
promotes_inputs=['h'])
self.add_subsystem(name='aero',
subsys=AeroGroup(num_nodes=nn),
promotes_inputs=['v', 'alpha', 'S'])
self.connect('atmos.sos', 'aero.sos')
self.connect('atmos.rho', 'aero.rho')
self.add_subsystem(name='prop',
subsys=PropGroup(num_nodes=nn),
promotes_inputs=['h', 'Isp', 'throttle'])
self.connect('aero.mach', 'prop.mach')
self.add_subsystem(name='flight_dynamics',
subsys=FlightPathEOM2D(num_nodes=nn),
promotes_inputs=['m', 'v', 'gam', 'alpha'])
foo = self.add_subsystem('foo', om.IndepVarComp())
foo.add_output('rho', val=100 * np.ones(nn), units='g/cm**3')
self.connect('aero.f_drag', 'flight_dynamics.D')
self.connect('aero.f_lift', 'flight_dynamics.L')
self.connect('prop.thrust', 'flight_dynamics.T')
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='atmos',
subsys=USatm1976Comp(num_nodes=nn),
promotes_inputs=['h'])
self.add_subsystem(name='aero',
subsys=AeroGroup(num_nodes=nn),
promotes_inputs=['v', 'alpha', 'S'])
self.connect('atmos.sos', 'aero.sos')
self.connect('atmos.rho', 'aero.rho')
self.add_subsystem(name='prop',
subsys=PropGroup(num_nodes=nn),
promotes_inputs=['h', 'Isp', 'throttle'])
self.connect('aero.mach', 'prop.mach')
self.add_subsystem(name='flight_dynamics',
subsys=FlightPathEOM2D(num_nodes=nn),
promotes_inputs=['m', 'v', 'gam', 'alpha'])
self.connect('aero.f_drag', 'flight_dynamics.D')
self.connect('aero.f_lift', 'flight_dynamics.L')
self.connect('prop.thrust', 'flight_dynamics.T')
self.add_subsystem('testcomp',
om.ExecComp('testout=test', shape=40),
promotes=['*'])
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem('sum', om.ExecComp('m_tot = sum(m)',
m={'value': np.zeros((2, 2)),
'units': 'kg'},
m_tot={'value': np.zeros(nn),
'units': 'kg'}))
self.add_subsystem('eom', FlightPathEOM2D(num_nodes=nn))
self.connect('sum.m_tot', 'eom.m')
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='kinetic_energy',
subsys=KineticEnergyComp(num_nodes=nn))
self.add_subsystem(name='atmos', subsys=USatm1976Comp(num_nodes=nn))
self.add_subsystem(name='dynamic_pressure',
subsys=DynamicPressureComp(num_nodes=nn))
self.add_subsystem(name='aero', subsys=LiftDragForceComp(num_nodes=nn))
self.add_subsystem(name='eom', subsys=FlightPathEOM2D(num_nodes=nn))
self.connect('atmos.rho', 'dynamic_pressure.rho')
self.connect('dynamic_pressure.q', 'aero.q')
self.connect('aero.f_drag', 'eom.D')
self.connect('aero.f_lift', 'eom.L')
def setup(self):
nn = self.options['num_nodes']
engine_heat_coeff = self.options['engine_heat_coeff']
pump_heat_coeff = self.options['pump_heat_coeff']
# Aero and mission
self.add_subsystem(name='atmos',
subsys=StandardAtmosphereGroup(num_nodes=nn),
promotes_inputs=['h'])
# self.add_subsystem(name='aero',
# subsys=AeroGroup(num_nodes=nn),
# promotes_inputs=['v', 'alpha', 'S'])
self.add_subsystem(name='aero',
subsys=AeroSMTGroup(num_nodes=nn),
promotes_inputs=['v', 'alpha', 'S', 'h'])
self.connect('atmos.sos', 'aero.sos')
self.connect('atmos.rho', 'aero.rho')
self.add_subsystem(name='prop',
subsys=PropGroup(num_nodes=nn),
promotes_inputs=['h', 'throttle'],
promotes_outputs=['m_dot'])
self.connect('aero.mach', 'prop.mach')
self.add_subsystem(name='flight_dynamics',
subsys=FlightPathEOM2D(num_nodes=nn),
promotes_inputs=['m', 'v', 'gam', 'alpha'])
self.connect('aero.f_drag', 'flight_dynamics.D')
self.connect('aero.f_lift', 'flight_dynamics.L')
self.connect('prop.thrust', 'flight_dynamics.T')
# Thermal
self.add_subsystem(
'm_burn_comp',
ExecComp('m_burn = - m_dot',
m_burn=np.zeros(nn),
m_dot=np.zeros(nn)),
promotes=['*'],
)
self.add_subsystem(
'm_fuel_comp',
ExecComp('m_fuel = m - W0',
m_fuel=np.zeros(nn),
m=np.zeros(nn),
W0=np.zeros(nn)),
promotes=['*'],
)
self.add_subsystem(
'm_flow_comp',
ExecComp('m_flow = m_burn + m_recirculated',
m_flow=np.zeros(nn),
m_burn=np.zeros(nn),
m_recirculated=np.zeros(nn)),
promotes=['*'],
)
self.add_subsystem(name='pump_heating_comp',
subsys=PumpHeatingComp(num_nodes=nn,
heat_coeff=pump_heat_coeff),
promotes_inputs=['m_flow'],
promotes_outputs=['Q_pump'])
self.add_subsystem(name='engine_heating_comp',
subsys=EngineHeatingComp(
num_nodes=nn, heat_coeff=engine_heat_coeff),
promotes_inputs=['throttle'],
promotes_outputs=['Q_engine'])
self.add_subsystem(
'Q_env_tot_comp',
ExecComp('Q_env_tot = Q_env + Q_pump + Q_engine',
Q_env_tot=np.zeros(nn),
Q_env=np.zeros(nn),
Q_pump=np.zeros(nn),
Q_engine=np.zeros(nn)),
promotes=['*'],
)
self.add_subsystem(name='cv',
subsys=CvComp(num_nodes=nn),
promotes_inputs=['T'],
promotes_outputs=['Cv'])
self.add_subsystem(name='tank',
subsys=TankMissionComp(num_nodes=nn),
promotes_inputs=[
'm_fuel', 'm_flow', 'm_burn', 'T', 'Q_env_tot',
'Q_sink', 'Q_out', 'Cv'
],
promotes_outputs=['T_dot', 'T_o'])
self.add_subsystem(name='power',
subsys=PowerComp(num_nodes=nn),
promotes=['m_flow', 'power'])
# Set solvers
self.linear_solver = DirectSolver(assemble_jac=True)
self.options['assembled_jac_type'] = 'csc'