def test_record_line_search_armijo_goldstein(self, m):
self.setup_endpoints(m)
recorder = WebRecorder(self._accepted_token, suppress_output=True)
self.setup_sellar_model()
model = self.prob.model
model.nonlinear_solver = NewtonSolver()
model.linear_solver = ScipyIterativeSolver()
model._nonlinear_solver.options['solve_subsystems'] = True
model._nonlinear_solver.options['max_sub_solves'] = 4
ls = model._nonlinear_solver.linesearch = ArmijoGoldsteinLS(
bound_enforcement='vector')
# This is pretty bogus, but it ensures that we get a few LS iterations.
ls.options['c'] = 100.0
ls.add_recorder(recorder)
self.prob.setup(check=False)
t0, t1 = run_driver(self.prob)
self.prob.cleanup()
expected_abs_error = 3.49773898733e-9
expected_rel_error = expected_abs_error / 2.9086436370499857e-08
solver_iteration = json.loads(self.solver_iterations)
self.assertAlmostEqual(solver_iteration['abs_err'], expected_abs_error)
self.assertAlmostEqual(solver_iteration['rel_err'], expected_rel_error)
self.assertEqual(solver_iteration['solver_output'], [])
self.assertEqual(solver_iteration['solver_residuals'], [])
def setup(self):
nn = self.options['num_nodes']
self.add_subsystem(name='pack',
subsys=packSize(num_nodes=nn),
promotes_inputs=['*'],
promotes_outputs=['*'])
self.add_subsystem(name='pcm',
subsys=pcmSize(num_nodes=nn),
promotes_inputs=['*'],
promotes_outputs=['*'])
self.add_subsystem(name='ohp',
subsys=OHP(num_nodes=nn),
promotes_inputs=['*'],
promotes_outputs=['*'])
self.add_subsystem(name='mass',
subsys=packMass(num_nodes=nn),
promotes_inputs=['*'],
promotes_outputs=['*'])
self.set_input_defaults('frame_mass', 0.01, units='kg')
self.nonlinear_solver = NewtonSolver(maxiter=30,
atol=1e-10,
rtol=1e-100)
self.nonlinear_solver.options['solve_subsystems'] = True
self.nonlinear_solver.options['max_sub_solves'] = 500
self.nonlinear_solver.linesearch = ArmijoGoldsteinLS()
self.linear_solver = DirectSolver()
self.nonlinear_solver.options['err_on_non_converge'] = True
def setup(self):
self.add_subsystem('n1',
Node(n_in=1, n_out=2),
promotes_inputs=[('I_in:0', 'I_in')])
self.add_subsystem('n2', Node()) # leaving defaults
self.add_subsystem('R1',
Resistor(R=100.),
promotes_inputs=[('V_out', 'Vg')])
self.add_subsystem('R2', Resistor(R=10000.))
self.add_subsystem('D1',
Diode(),
promotes_inputs=[('V_out', 'Vg')])
self.connect('n1.V', ['R1.V_in', 'R2.V_in'])
self.connect('R1.I', 'n1.I_out:0')
self.connect('R2.I', 'n1.I_out:1')
self.connect('n2.V', ['R2.V_out', 'D1.V_in'])
self.connect('R2.I', 'n2.I_in:0')
self.connect('D1.I', 'n2.I_out:0')
self.nonlinear_solver = NewtonSolver()
self.linear_solver = DirectSolver()
self.nonlinear_solver.options['iprint'] = 2
self.nonlinear_solver.options['maxiter'] = 10
self.nonlinear_solver.options['solve_subsystems'] = True
self.nonlinear_solver.linesearch = ArmijoGoldsteinLS()
self.nonlinear_solver.linesearch.options['maxiter'] = 10
self.nonlinear_solver.linesearch.options['iprint'] = 2
def test_record_line_search_armijo_goldstein(self, m):
self.setup_endpoints(m)
self.setup_sellar_model()
model = self.prob.model
model.nonlinear_solver = NewtonSolver()
model.linear_solver = ScipyKrylov()
model._nonlinear_solver.options['solve_subsystems'] = True
model._nonlinear_solver.options['max_sub_solves'] = 4
ls = model._nonlinear_solver.linesearch = ArmijoGoldsteinLS(bound_enforcement='vector')
# This is pretty bogus, but it ensures that we get a few LS iterations.
ls.options['c'] = 100.0
ls.add_recorder(self.recorder)
self.prob.setup(check=False)
t0, t1 = run_driver(self.prob)
self.prob.cleanup()
upload(self.filename, self._accepted_token)
expected_abs_error = 3.49773898733e-9
expected_rel_error = expected_abs_error / 2.9086436370499857e-08
solver_iteration = json.loads(self.solver_iterations)
expected_solver_output = [
{'name': 'con_cmp1.con1', 'values': [-22.42830237]},
{'name': 'd1.y1', 'values': [25.58830237]},
{'name': 'con_cmp2.con2', 'values': [-11.941511849]},
{'name': 'pz.z', 'values': [5.0, 2.0]},
{'name': 'obj_cmp.obj', 'values': [28.588308165]},
{'name': 'd2.y2', 'values': [12.058488150]},
{'name': 'px.x', 'values': [1.0]}
]
self.assertAlmostEqual(solver_iteration['abs_err'], expected_abs_error)
self.assertAlmostEqual(solver_iteration['rel_err'], expected_rel_error)
self.assertEqual(solver_iteration['solver_residuals'], [])
for o in expected_solver_output:
self.assert_array_close(o, solver_iteration['solver_output'])
def test_circuit_advanced_newton(self):
from openmdao.api import ArmijoGoldsteinLS, Problem, IndepVarComp
from openmdao.test_suite.scripts.circuit_analysis import Circuit
p = Problem()
model = p.model
model.add_subsystem('ground', IndepVarComp('V', 0., units='V'))
model.add_subsystem('source', IndepVarComp('I', 0.1, units='A'))
model.add_subsystem('circuit', Circuit())
model.connect('source.I', 'circuit.I_in')
model.connect('ground.V', 'circuit.Vg')
p.setup()
# you can change the NewtonSolver settings in circuit after setup is called
newton = p.model.circuit.nonlinear_solver
newton.options['iprint'] = 2
newton.options['maxiter'] = 10
newton.options['solve_subsystems'] = True
newton.linesearch = ArmijoGoldsteinLS()
newton.linesearch.options['maxiter'] = 10
newton.linesearch.options['iprint'] = 2
# set some initial guesses
p['circuit.n1.V'] = 10.
p['circuit.n2.V'] = 1e-3
p.run_model()
assert_rel_error(self, p['circuit.n1.V'], 9.90830282, 1e-5)
assert_rel_error(self, p['circuit.n2.V'], 0.73858486, 1e-5)
assert_rel_error(self, p['circuit.R1.I'], 0.09908303, 1e-5)
assert_rel_error(self, p['circuit.R2.I'], 0.00091697, 1e-5)
assert_rel_error(self, p['circuit.D1.I'], 0.00091697, 1e-5)
# sanity check: should sum to .1 Amps
assert_rel_error(self, p['circuit.R1.I'] + p['circuit.D1.I'], .1, 1e-6)
def test_circuit_voltage_source(self):
from openmdao.api import ArmijoGoldsteinLS, Problem, IndepVarComp, BalanceComp, ExecComp
from openmdao.api import NewtonSolver, DirectSolver, NonlinearRunOnce, LinearRunOnce
from openmdao.test_suite.scripts.circuit_analysis import Circuit
p = Problem()
model = p.model
model.add_subsystem('ground', IndepVarComp('V', 0., units='V'))
# replacing the fixed current source with a BalanceComp to represent a fixed Voltage source
# model.add_subsystem('source', IndepVarComp('I', 0.1, units='A'))
model.add_subsystem('batt', IndepVarComp('V', 1.5, units='V'))
bal = model.add_subsystem('batt_balance', BalanceComp())
bal.add_balance('I', units='A', eq_units='V')
model.add_subsystem('circuit', Circuit())
model.add_subsystem(
'batt_deltaV',
ExecComp('dV = V1 - V2',
V1={'units': 'V'},
V2={'units': 'V'},
dV={'units': 'V'}))
# current into the circuit is now the output state from the batt_balance comp
model.connect('batt_balance.I', 'circuit.I_in')
model.connect('ground.V', ['circuit.Vg', 'batt_deltaV.V2'])
model.connect('circuit.n1.V', 'batt_deltaV.V1')
# set the lhs and rhs for the battery residual
model.connect('batt.V', 'batt_balance.rhs:I')
model.connect('batt_deltaV.dV', 'batt_balance.lhs:I')
p.setup()
###################
# Solver Setup
###################
# change the circuit solver to RunOnce because we're
# going to converge at the top level of the model with newton instead
p.model.circuit.nonlinear_solver = NonlinearRunOnce()
p.model.circuit.linear_solver = LinearRunOnce()
# Put Newton at the top so it can also converge the new BalanceComp residual
newton = p.model.nonlinear_solver = NewtonSolver()
p.model.linear_solver = DirectSolver()
newton.options['iprint'] = 2
newton.options['maxiter'] = 20
newton.options['solve_subsystems'] = True
newton.linesearch = ArmijoGoldsteinLS()
newton.linesearch.options['maxiter'] = 10
newton.linesearch.options['iprint'] = 2
# set initial guesses from the current source problem
p['circuit.n1.V'] = 9.8
p['circuit.n2.V'] = .7
p.run_model()
assert_rel_error(self, p['circuit.n1.V'], 1.5, 1e-5)
assert_rel_error(self, p['circuit.n2.V'], 0.676232, 1e-5)
assert_rel_error(self, p['circuit.R1.I'], 0.015, 1e-5)
assert_rel_error(self, p['circuit.R2.I'], 8.23767999e-05, 1e-5)
assert_rel_error(self, p['circuit.D1.I'], 8.23767999e-05, 1e-5)
def setup(self):
thermo_spec = species_data.janaf
design = self.options['design']
statics = self.options['statics']
self.add_subsystem('fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX))
self.add_subsystem('inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX))
self.add_subsystem('fan', Compressor(map_data=FanMap, design=design, thermo_data=thermo_spec, elements=AIR_MIX,
bleed_names=[], statics=statics, map_extrap=True), promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('splitter', Splitter(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics))
self.add_subsystem('duct4', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics))
self.add_subsystem('lpc', Compressor(map_data=LPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX,
statics=statics, map_extrap=True),promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('duct6', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics))
self.add_subsystem('hpc', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX,
bleed_names=['cool1','cool2','cust'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('bld3', BleedOut(design=design, statics=statics, bleed_names=['cool3','cool4']))
self.add_subsystem('burner', Combustor(design=design,thermo_data=thermo_spec,
inflow_elements=AIR_MIX,
air_fuel_elements=AIR_FUEL_MIX,
fuel_type='Jet-A(g)', statics=statics))
self.add_subsystem('hpt', Turbine(map_data=HPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX,
bleed_names=['cool3','cool4'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('duct11', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics))
self.add_subsystem('lpt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX,
bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('duct13', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics))
self.add_subsystem('core_nozz', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX))
self.add_subsystem('byp_bld', BleedOut(design=design, statics=statics, bleed_names=['bypBld']))
self.add_subsystem('duct15', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics))
self.add_subsystem('byp_nozz', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_MIX))
self.add_subsystem('lp_shaft', Shaft(num_ports=3),promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('hp_shaft', Shaft(num_ports=2),promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('perf', Performance(num_nozzles=2, num_burners=1))
self.connect('inlet.Fl_O:tot:P', 'perf.Pt2')
self.connect('hpc.Fl_O:tot:P', 'perf.Pt3')
self.connect('burner.Wfuel', 'perf.Wfuel_0')
self.connect('inlet.F_ram', 'perf.ram_drag')
self.connect('core_nozz.Fg', 'perf.Fg_0')
self.connect('byp_nozz.Fg', 'perf.Fg_1')
self.connect('fan.trq', 'lp_shaft.trq_0')
self.connect('lpc.trq', 'lp_shaft.trq_1')
self.connect('lpt.trq', 'lp_shaft.trq_2')
self.connect('hpc.trq', 'hp_shaft.trq_0')
self.connect('hpt.trq', 'hp_shaft.trq_1')
self.connect('fc.Fl_O:stat:P', 'core_nozz.Ps_exhaust')
self.connect('fc.Fl_O:stat:P', 'byp_nozz.Ps_exhaust')
balance = self.add_subsystem('balance', BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
self.connect('balance.W', 'inlet.Fl_I:stat:W')
self.connect('perf.Fn', 'balance.lhs:W')
balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
balance.add_balance('lpt_PR', val=1.5, lower=1.001, upper=8,
eq_units='hp', use_mult=True, mult_val=-1)
self.connect('balance.lpt_PR', 'lpt.PR')
self.connect('lp_shaft.pwr_in_real', 'balance.lhs:lpt_PR')
self.connect('lp_shaft.pwr_out_real', 'balance.rhs:lpt_PR')
balance.add_balance('hpt_PR', val=1.5, lower=1.001, upper=8,
eq_units='hp', use_mult=True, mult_val=-1)
self.connect('balance.hpt_PR', 'hpt.PR')
self.connect('hp_shaft.pwr_in_real', 'balance.lhs:hpt_PR')
self.connect('hp_shaft.pwr_out_real', 'balance.rhs:hpt_PR')
else:
balance.add_balance('FAR', val=0.017, lower=1e-4, eq_units='lbf')
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.lhs:FAR')
balance.add_balance('W', units='lbm/s', lower=10., upper=1000., eq_units='inch**2')
self.connect('balance.W', 'inlet.Fl_I:stat:W')
self.connect('core_nozz.Throat:stat:area', 'balance.lhs:W')
balance.add_balance('BPR', lower=2., upper=10., eq_units='inch**2')
self.connect('balance.BPR', 'splitter.BPR')
self.connect('byp_nozz.Throat:stat:area', 'balance.lhs:BPR')
balance.add_balance('lp_Nmech', val=1.5, units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1)
self.connect('balance.lp_Nmech', 'LP_Nmech')
self.connect('lp_shaft.pwr_in_real', 'balance.lhs:lp_Nmech')
self.connect('lp_shaft.pwr_out_real', 'balance.rhs:lp_Nmech')
balance.add_balance('hp_Nmech', val=1.5, units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1)
self.connect('balance.hp_Nmech', 'HP_Nmech')
self.connect('hp_shaft.pwr_in_real', 'balance.lhs:hp_Nmech')
self.connect('hp_shaft.pwr_out_real', 'balance.rhs:hp_Nmech')
self.set_order(['balance', 'fc', 'inlet', 'fan', 'splitter', 'duct4', 'lpc', 'duct6', 'hpc', 'bld3', 'burner', 'hpt', 'duct11',
'lpt', 'duct13', 'core_nozz', 'byp_bld', 'duct15', 'byp_nozz', 'lp_shaft', 'hp_shaft', 'perf'])
connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False)
connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I')
connect_flow(self, 'fan.Fl_O', 'splitter.Fl_I')
connect_flow(self, 'splitter.Fl_O1', 'duct4.Fl_I')
connect_flow(self, 'duct4.Fl_O', 'lpc.Fl_I')
connect_flow(self, 'lpc.Fl_O', 'duct6.Fl_I')
connect_flow(self, 'duct6.Fl_O', 'hpc.Fl_I')
connect_flow(self, 'hpc.Fl_O', 'bld3.Fl_I')
connect_flow(self, 'bld3.Fl_O', 'burner.Fl_I')
connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I')
connect_flow(self, 'hpt.Fl_O', 'duct11.Fl_I')
connect_flow(self, 'duct11.Fl_O', 'lpt.Fl_I')
connect_flow(self, 'lpt.Fl_O', 'duct13.Fl_I')
connect_flow(self, 'duct13.Fl_O','core_nozz.Fl_I')
connect_flow(self, 'splitter.Fl_O2', 'byp_bld.Fl_I')
connect_flow(self, 'byp_bld.Fl_O', 'duct15.Fl_I')
connect_flow(self, 'duct15.Fl_O', 'byp_nozz.Fl_I')
connect_flow(self, 'hpc.cool1', 'lpt.cool1', connect_stat=False)
connect_flow(self, 'hpc.cool2', 'lpt.cool2', connect_stat=False)
connect_flow(self, 'bld3.cool3', 'hpt.cool3', connect_stat=False)
connect_flow(self, 'bld3.cool4', 'hpt.cool4', connect_stat=False)
newton = self.nonlinear_solver = NewtonSolver()
newton.options['atol'] = 1e-8
newton.options['rtol'] = 1e-8
newton.options['iprint'] = 2
newton.options['maxiter'] = 50
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
# ls = newton.linesearch = BoundsEnforceLS()
ls = newton.linesearch = ArmijoGoldsteinLS()
ls.options['maxiter'] = 3
ls.options['bound_enforcement'] = 'scalar'
# ls.options['print_bound_enforce'] = True
self.linear_solver = DirectSolver(assemble_jac=True)
# set the lhs and rhs for the battery residual
model.connect('batt.V', 'batt_balance.rhs:I')
model.connect('batt_deltaV.dV', 'batt_balance.lhs:I')
p.setup()
###################
# Solver Setup
###################
# change the circuit solver to RunOnce because we're
# going to converge at the top level of the model with newton instead
p.model.circuit.nonlinear_solver = NonlinearRunOnce()
p.model.circuit.linear_solver = LinearRunOnce()
# Put Newton at the top so it can also converge the new BalanceComp residual
newton = p.model.nonlinear_solver = NewtonSolver()
p.model.linear_solver = DirectSolver()
newton.options['iprint'] = 2
newton.options['maxiter'] = 20
newton.options['solve_subsystems'] = True
newton.linesearch = ArmijoGoldsteinLS()
newton.linesearch.options['maxiter'] = 10
newton.linesearch.options['iprint'] = 2
# set initial guesses from the current source problem
p['circuit.n1.V'] = 9.8
p['circuit.n2.V'] = .7
p.run_model()
def setup(self):
newton = self.nonlinear_solver = NewtonSolver()
newton.options['maxiter'] = 100
newton.options['iprint'] = 2
newton.options['atol'] = 1e-10
newton.options['rtol'] = 1e-10
self.options['assembled_jac_type'] = 'dense'
self.linear_solver = DirectSolver(assemble_jac=True)
# ln_bt = newton.linesearch = BoundsEnforceLS()
ln_bt = newton.linesearch = ArmijoGoldsteinLS()
ln_bt.options['maxiter'] = 2
ln_bt.options['bound_enforcement'] = 'scalar'
ln_bt.options['iprint'] = -1
#ln_bt.options['maxiter'] = 1
# Once the concentration of a species reaches its minimum, we
# can essentially remove it from the problem. This switch controls
# whether to do this.
self.remove_trace_species = False
# multiply a damping function that scales down the residual for trace species
self.use_trace_damping = True
thermo = self.options['thermo']
mode = self.options['mode']
num_prod = thermo.num_prod
num_element = thermo.num_element
# Input vars
self.add_input('init_prod_amounts', val=thermo.init_prod_amounts, shape=(num_prod,),
desc="initial mass fractions of products, before equilibrating")
self.add_input('P', val=1.0, units="bar", desc="Pressure")
if mode == "T": # T is an input
self.add_input('T', val=400., units="degK", desc="Temperature")
elif mode == "h" or mode == "S": # T becomes another state variable
if mode == "h": # hP solve
self.add_input('h', val=0., units="cal/g",
desc="Enthalpy")
elif mode == "S": # SP solve
self.add_input('S', val=0., units="cal/(g*degK)",
desc="Entropy")
self.T_idx = num_prod + num_element
self.add_output('T', val=400., units="degK", desc="Temperature",
lower=1.,
res_ref=100
)
# State vars
self.n_init = np.ones(num_prod) / num_prod / 10 # initial guess for n
# for a known solution, these are the orders of magnitude of the variables.
# We'll try setting scaling to +/1 1 order around thee values
mag = np.array([3.23319258e-04, 1.00000000e-10, 1.10131241e-05, 1.00000000e-10,
1.15755853e-08, 2.95692989e-09, 1.00000000e-10, 2.69578794e-02,
1.00000000e-10, 7.23198523e-03])
#mag = np.ones(num_prod)
self.add_output('n', shape=num_prod,
val=self.n_init,
desc="mole fractions of the mixture",
lower=1e-10,
res_ref=10000.
)
self.add_output('pi', val=np.ones(num_element),
desc="modified lagrange multipliers from the Gibbs lagrangian")
# Explicit Outputs
self.add_output('b0', shape=num_element, # when converged, b0=b
desc='assigned kg-atoms of element i per total kg of reactant '
'for the initial prod amounts')
self.add_output('n_moles', lower=1e-10, val=0.034, shape=1,
desc="1/molecular weight of gas")
# allocate the newton Jacobian
self.size = size = num_prod + num_element
if mode != "T":
size += 1 # added T as a state variable
self._dRdy = np.zeros((size, size))
self._rhs = np.zeros(size) # used for solve_linear
# Cached stuff for speed
self.H0_T = None
self.S0_T = None
self.dH0_dT = None
self.dS0_dT = None
self.sum_n_H0_T = None
# self.deriv_options['check_type'] = 'cs'
# self.deriv_options['check_step_size'] = 1e-50
# self.deriv_options['type'] = 'fd'
# self.deriv_options['step_size'] = 1e-5
self.declare_partials('n', ['n', 'pi', 'P', 'T'])
self.declare_partials('pi', ['n', 'init_prod_amounts'])
self.declare_partials('b0', ['b0', 'init_prod_amounts'])
self.declare_partials('n_moles', 'n')
self.declare_partials('n_moles', 'n_moles', val=-1)
if mode == 'h':
self.declare_partials('T', ['n', 'h', 'T'])
elif mode == 'S':
self.declare_partials('T', ['n', 'S', 'T', 'P'])
def setup(self):
thermo_spec = species_data.janaf
design = self.options['design']
statics = self.options['statics']
self.add_subsystem('fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX))
self.add_subsystem('inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX))
self.add_subsystem('duct1', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics))
self.add_subsystem('comp', Compressor(map_data=AXI5, design=design, thermo_data=thermo_spec, elements=AIR_MIX,
bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=['Nmech'])
self.add_subsystem('burner', Combustor(design=design,thermo_data=thermo_spec,
inflow_elements=AIR_MIX,
air_fuel_elements=AIR_FUEL_MIX,
fuel_type='JP-7', statics=statics))
self.add_subsystem('turb', Turbine(map_data=LPT2269, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX,
bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=['Nmech'])
self.add_subsystem('ab', Combustor(design=design,thermo_data=thermo_spec,
inflow_elements=AIR_FUEL_MIX,
air_fuel_elements=AIR_FUEL_MIX,
fuel_type='JP-7', statics=statics))
self.add_subsystem('nozz', Nozzle(nozzType='CD', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX, internal_solver=True))
self.add_subsystem('shaft', Shaft(num_ports=2),promotes_inputs=['Nmech'])
self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=2))
self.connect('duct1.Fl_O:tot:P', 'perf.Pt2')
self.connect('comp.Fl_O:tot:P', 'perf.Pt3')
self.connect('burner.Wfuel', 'perf.Wfuel_0')
self.connect('ab.Wfuel', 'perf.Wfuel_1')
self.connect('inlet.F_ram', 'perf.ram_drag')
self.connect('nozz.Fg', 'perf.Fg_0')
self.connect('comp.trq', 'shaft.trq_0')
self.connect('turb.trq', 'shaft.trq_1')
# self.connect('shaft.Nmech', 'comp.Nmech')
# self.connect('shaft.Nmech', 'turb.Nmech')
self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust')
balance = self.add_subsystem('balance', BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
self.connect('balance.W', 'inlet.Fl_I:stat:W')
self.connect('perf.Fn', 'balance.lhs:W')
balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
balance.add_balance('turb_PR', val=1.5, lower=1.001, upper=8, eq_units='hp', rhs_val=0.)
self.connect('balance.turb_PR', 'turb.PR')
self.connect('shaft.pwr_net', 'balance.lhs:turb_PR')
# self.set_order(['fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf', 'thrust_balance', 'temp_balance', 'shaft_balance'])
self.set_order(['balance', 'fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf'])
else:
balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
balance.add_balance('Nmech', val=8000., units='rpm', lower=500., eq_units='hp', rhs_val=0.)
self.connect('balance.Nmech', 'Nmech')
self.connect('shaft.pwr_net', 'balance.lhs:Nmech')
balance.add_balance('W', val=100.0, units='lbm/s', eq_units=None, rhs_val=2.0)
self.connect('balance.W', 'inlet.Fl_I:stat:W')
self.connect('comp.map.RlineMap', 'balance.lhs:W')
self.set_order(['balance', 'fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf'])
if statics:
connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False)
connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I')
connect_flow(self, 'duct1.Fl_O', 'comp.Fl_I')
connect_flow(self, 'comp.Fl_O', 'burner.Fl_I')
connect_flow(self, 'burner.Fl_O', 'turb.Fl_I')
connect_flow(self, 'turb.Fl_O', 'ab.Fl_I')
connect_flow(self, 'ab.Fl_O', 'nozz.Fl_I')
else:
connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False)
connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I', connect_stat=False)
connect_flow(self, 'duct1.Fl_O', 'comp.Fl_I', connect_stat=False)
connect_flow(self, 'comp.Fl_O', 'burner.Fl_I', connect_stat=False)
connect_flow(self, 'burner.Fl_O', 'turb.Fl_I', connect_stat=False)
connect_flow(self, 'turb.Fl_O', 'ab.Fl_I', connect_stat=False)
connect_flow(self, 'ab.Fl_O', 'nozz.Fl_I', connect_stat=False)
connect_flow(self, 'comp.cool1', 'turb.cool1', connect_stat=False)
connect_flow(self, 'comp.cool2', 'turb.cool2', connect_stat=False)
newton = self.nonlinear_solver = NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 15
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
# newton.linesearch = BoundsEnforceLS()
newton.linesearch = ArmijoGoldsteinLS()
# newton.linesearch.options['c'] = .0001
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = DirectSolver(assemble_jac=True)
def run_a320_analysis():
# Set up OpenMDAO to analyze the airplane
num_nodes = 9
prob = Problem()
prob.model = A320AnalysisGroup()
prob.model.nonlinear_solver = NewtonSolver(iprint=2)
# prob.model.nonlinear_solver = NonlinearBlockGS(iprint=2)
prob.model.options['assembled_jac_type'] = 'csc'
prob.model.linear_solver = DirectSolver(assemble_jac=True)
prob.model.nonlinear_solver.options['solve_subsystems'] = True
prob.model.nonlinear_solver.options['maxiter'] = 50
prob.model.nonlinear_solver.options['atol'] = 1e-7
prob.model.nonlinear_solver.options['rtol'] = 1e-7
prob.model.nonlinear_solver.linesearch = ArmijoGoldsteinLS(bound_enforcement='vector', maxiter=5, print_bound_enforce=False)
prob.setup(check=True, mode='fwd')
# set some (required) mission parameters. Each phase needs a vertical and air-speed
# the entire mission needs a cruise altitude and range
# U_EAS = equivalent air speed
# VS = vertical speed = Rate of Climb
ones_nn = np.ones((num_nodes,))
#"""
# climb 1: initial climb to 5000 ft
prob.set_val('climb1.fltcond|vs', 2500*ones_nn, units='ft/min')
prob.set_val('climb1.fltcond|Ueas', 175*ones_nn, units='kn')
# climb 2: 5000 to 15000 ft
prob.set_val('climb2|h0', 5000, units='ft')
prob.set_val('climb2.fltcond|vs', 2000*ones_nn, units='ft/min')
prob.set_val('climb2.fltcond|Ueas', 290*ones_nn, units='kn')
# climb 3: 15000 to 24000 ft
prob.set_val('climb3|h0', 15000, units='ft')
prob.set_val('climb3.fltcond|vs', 1400*ones_nn, units='ft/min')
prob.set_val('climb3.fltcond|Ueas', 290*ones_nn, units='kn')
# climb 4 (Mach climb): 24000 ft to cruise
prob.set_val('climb4|h0', 24000, units='ft')
prob.set_val('climb4.fltcond|vs', 1000*ones_nn, units='ft/min')
prob.set_val('climb4.fltcond|Ueas', 240*ones_nn, units='kn')
# cruise. M=0.78 at 37000 ft. U_tas = 450 kn, U_eas = 240 kn
prob.set_val('cruise|h0', 37000, units='ft')
prob.set_val('cruise.fltcond|vs', 0.1*ones_nn, units='ft/min') # horizontal cruise
prob.set_val('cruise.fltcond|Ueas', 240*ones_nn, units='kn')
# descent 1: initial descent to 24000 ft
prob.set_val('descent1.fltcond|vs', -500*ones_nn, units='ft/min') # 1000
prob.set_val('descent1.fltcond|Ueas', 240*ones_nn, units='kn')
# descent 2: 24000 to 10000 ft
prob.set_val('descent2|h0', 24000, units='ft')
prob.set_val('descent2.fltcond|vs', -1000*ones_nn, units='ft/min') # 3500 too steep?
prob.set_val('descent2.fltcond|Ueas', 290*ones_nn, units='kn')
# descent 3: approach
prob.set_val('descent3|h0', 10000, units='ft')
prob.set_val('descent3.fltcond|vs', -500*ones_nn, units='ft/min') # 1500
prob.set_val('descent3.fltcond|Ueas', 250*ones_nn, units='kn')
"""
prob.set_val('climb1.fltcond|vs', 1000*ones_nn, units='ft/min')
prob.set_val('climb1.fltcond|Ueas', 70*ones_nn, units='kn')
# cruise. M=0.78 at 37000 ft. U_tas = 450 kn, U_eas = 240 kn
prob.set_val('cruise|h0', 20000, units='ft')
prob.set_val('cruise.fltcond|vs', 0.1*ones_nn, units='ft/min') # horizontal cruise
prob.set_val('cruise.fltcond|Ueas', 150*ones_nn, units='kn')
# descent 1: initial descent to 24000 ft
prob.set_val('descent1.fltcond|vs', -800*ones_nn, units='ft/min') # 1000
prob.set_val('descent1.fltcond|Ueas', 100*ones_nn, units='kn')
"""
prob.set_val('mission_range', 2200, units='NM') # see Airbus AC-A320 pp 143 for payload-range chart
# (optional) guesses for takeoff speeds may help with convergence
prob.set_val('v0v1.fltcond|Utrue',np.ones((num_nodes))*150,units='kn')
prob.set_val('v1vr.fltcond|Utrue',np.ones((num_nodes))*150,units='kn')
prob.set_val('v1v0.fltcond|Utrue',np.ones((num_nodes))*150,units='kn')
# set some airplane-specific values. The throttle edits are to derate the takeoff power of the PT6A
prob['v0v1.throttle'] = np.ones((num_nodes))
prob['v1vr.throttle'] = np.ones((num_nodes))
prob['rotate.throttle'] = np.ones((num_nodes))
prob.run_model()
return prob
