def test_brachistochrone_forward_shooting_path_constrained_time(self):
import openmdao.api as om
from openmdao.utils.assert_utils import assert_near_equal
import dymos as dm
from dymos.examples.brachistochrone.brachistochrone_ode import BrachistochroneODE
p = om.Problem(model=om.Group())
p.driver = om.ScipyOptimizeDriver()
phase = dm.Phase(ode_class=BrachistochroneODE,
transcription=dm.RungeKutta(num_segments=20))
p.model.add_subsystem('phase0', phase)
phase.set_time_options(initial_bounds=(0, 0),
duration_bounds=(0.5, 2.0))
phase.add_state(
'x',
rate_source=BrachistochroneODE.states['x']['rate_source'],
units=BrachistochroneODE.states['x']['units'],
fix_initial=True,
fix_final=False,
solve_segments=False)
phase.add_state(
'y',
rate_source=BrachistochroneODE.states['y']['rate_source'],
units=BrachistochroneODE.states['y']['units'],
fix_initial=True,
fix_final=False,
solve_segments=False)
phase.add_state(
'v',
rate_source=BrachistochroneODE.states['v']['rate_source'],
targets=BrachistochroneODE.states['v']['targets'],
units=BrachistochroneODE.states['v']['units'],
fix_initial=True,
fix_final=False,
solve_segments=False)
phase.add_control(
'theta',
targets=BrachistochroneODE.parameters['theta']['targets'],
continuity=True,
rate_continuity=True,
units='deg',
lower=0.01,
upper=179.9)
phase.add_parameter(
'g',
targets=BrachistochroneODE.parameters['g']['targets'],
units='m/s**2',
opt=False,
val=9.80665)
# Final state values can't be controlled with simple bounds in ExplicitPhase,
# so use nonlinear boundary constraints instead.
phase.add_boundary_constraint('x', loc='final', equals=10)
phase.add_boundary_constraint('y', loc='final', equals=5)
phase.add_path_constraint('time', lower=0.0, upper=2.0)
phase.add_path_constraint('time_phase', lower=0.0, upper=2.0)
# Minimize time at the end of the phase
phase.add_objective('time_phase', loc='final', scaler=10)
p.model.linear_solver = om.DirectSolver()
p.setup(check=True)
p['phase0.t_initial'] = 0.0
p['phase0.t_duration'] = 2.0
p['phase0.states:x'] = 0
p['phase0.states:y'] = 10
p['phase0.states:v'] = 0
p['phase0.controls:theta'] = phase.interpolate(ys=[5, 100.5],
nodes='control_input')
# Solve for the optimal trajectory
p.run_driver()
# Test the results
assert_near_equal(p['phase0.time'][-1], 1.8016, tolerance=1.0E-3)
# Generate the explicitly simulated trajectory
exp_out = phase.simulate()
assert_near_equal(exp_out.get_val('phase0.timeseries.states:x')[-1, 0],
10,
tolerance=1.0E-3)
assert_near_equal(exp_out.get_val('phase0.timeseries.states:y')[-1, 0],
5,
tolerance=1.0E-3)
def test_list_inputs_outputs(self):
prob = om.Problem()
model = prob.model
indep = model.add_subsystem('indep', om.IndepVarComp())
indep.add_discrete_output('x', 11)
model.add_subsystem('expl', ModCompEx(3))
model.add_subsystem('impl', ModCompIm(3))
model.connect('indep.x', ['expl.x', 'impl.x'])
prob.setup()
prob.run_model()
#
# list inputs, not hierarchical
#
stream = StringIO()
prob.model.list_inputs(values=True,
hierarchical=False,
out_stream=stream)
text = stream.getvalue()
self.assertEqual(1, text.count("3 Input(s) in 'model'"))
# make sure they are in the correct order
self.assertTrue(
text.find('expl.a') < text.find('expl.x') < text.find('impl.x'))
#
# list inputs, hierarchical
#
stream = StringIO()
prob.model.list_inputs(values=True,
hierarchical=True,
out_stream=stream)
text = stream.getvalue()
self.assertEqual(1, text.count("3 Input(s) in 'model'"))
self.assertEqual(1, text.count('top'))
self.assertEqual(1, text.count(' expl'))
self.assertEqual(1, text.count(' a'))
self.assertEqual(1, text.count(' impl'))
self.assertEqual(2, text.count(' x')) # both implicit & explicit
#
# list outputs, not hierarchical
#
stream = StringIO()
prob.model.list_outputs(values=True,
residuals=True,
hierarchical=False,
out_stream=stream)
text = stream.getvalue()
self.assertEqual(text.count('3 Explicit Output'), 1)
self.assertEqual(text.count('1 Implicit Output'), 1)
# make sure they are in the correct order
self.assertTrue(
text.find('indep.x') < text.find('expl.b') < text.find('expl.y') <
text.find('impl.y'))
#
# list outputs, hierarchical
#
stream = StringIO()
prob.model.list_outputs(values=True,
residuals=True,
hierarchical=True,
out_stream=stream)
text = stream.getvalue()
self.assertEqual(text.count('top'), 2) # both implicit & explicit
self.assertEqual(text.count(' indep'), 1)
self.assertEqual(text.count(' x'), 1)
self.assertEqual(text.count(' expl'), 1)
self.assertEqual(text.count(' b'), 1)
self.assertEqual(text.count(' impl'), 1)
self.assertEqual(text.count(' y'), 2) # both implicit & explicit
def make_problem(self,
transcription='radau-ps',
num_segments=5,
transcription_order=3,
compressed=True):
self.p = p = om.Problem(model=om.Group())
p.driver = om.ScipyOptimizeDriver()
p.driver.declare_coloring()
if transcription == 'gauss-lobatto':
t = dm.GaussLobatto(num_segments=num_segments,
order=transcription_order,
compressed=compressed)
elif transcription == 'radau-ps':
t = dm.Radau(num_segments=num_segments,
order=transcription_order,
compressed=compressed)
elif transcription == 'runge-kutta':
t = dm.RungeKutta(num_segments=num_segments,
order=transcription_order,
compressed=compressed)
traj = dm.Trajectory()
phase = dm.Phase(ode_class=BrachistochroneODE, transcription=t)
phase.set_refine_options(refine=True, tol=1.0E-6)
traj.add_phase('phase0', phase)
p.model.add_subsystem('traj0', traj)
phase.set_time_options(fix_initial=True, duration_bounds=(.5, 10))
phase.add_state('x', fix_initial=True, fix_final=False)
phase.add_state('y', fix_initial=True, fix_final=False)
phase.add_state('v', fix_initial=True, fix_final=False)
phase.add_control('theta',
continuity=True,
rate_continuity=True,
units='deg',
lower=0.01,
upper=179.9)
phase.add_parameter('g', units='m/s**2', val=9.80665)
phase.add_boundary_constraint('x', loc='final', equals=10)
phase.add_boundary_constraint('y', loc='final', equals=5)
# Minimize time at the end of the phase
phase.add_objective('time_phase', loc='final', scaler=10)
p.model.linear_solver = om.DirectSolver()
p.setup(check=['unconnected_inputs'])
p['traj0.phase0.t_initial'] = 0.0
p['traj0.phase0.t_duration'] = 2.0
p['traj0.phase0.states:x'] = phase.interpolate(ys=[0, 10],
nodes='state_input')
p['traj0.phase0.states:y'] = phase.interpolate(ys=[10, 5],
nodes='state_input')
p['traj0.phase0.states:v'] = phase.interpolate(ys=[0, 9.9],
nodes='state_input')
p['traj0.phase0.controls:theta'] = phase.interpolate(
ys=[5, 100], nodes='control_input')
p['traj0.phase0.parameters:g'] = 9.80665
return p
def test_static_params(self):
prob = om.Problem(model=om.Group())
traj = prob.model.add_subsystem('traj', dm.Trajectory())
# First phase: normal operation.
# NOTE: using RK4 integration here
P_DEMAND = 2.0
phase0 = dm.Phase(ode_class=BatteryODE,
transcription=dm.RungeKutta(num_segments=200))
phase0.set_time_options(fix_initial=True, fix_duration=True)
phase0.add_state('state_of_charge',
fix_initial=True,
fix_final=False,
targets=['SOC'],
rate_source='dXdt:SOC')
phase0.add_timeseries_output('battery.V_oc', output_name='V_oc')
phase0.add_timeseries_output('battery.V_pack', output_name='V_pack')
phase0.add_timeseries_output('pwr_balance.I_Li', output_name='I_Li')
traj.add_phase('phase0', phase0)
# Second phase: normal operation.
transcription = dm.Radau(num_segments=5, order=5, compressed=True)
phase1 = dm.Phase(ode_class=BatteryODE, transcription=transcription)
phase1.set_time_options(fix_initial=False, fix_duration=True)
phase1.add_state('state_of_charge',
fix_initial=False,
fix_final=False,
solve_segments=True,
targets=['SOC'],
rate_source='dXdt:SOC')
phase1.add_timeseries_output('battery.V_oc', output_name='V_oc')
phase1.add_timeseries_output('battery.V_pack', output_name='V_pack')
phase1.add_timeseries_output('pwr_balance.I_Li', output_name='I_Li')
traj.add_phase('phase1', phase1)
# Second phase, but with battery failure.
phase1_bfail = dm.Phase(ode_class=BatteryODE,
ode_init_kwargs={'num_battery': 2},
transcription=transcription)
phase1_bfail.set_time_options(fix_initial=False, fix_duration=True)
phase1_bfail.add_state('state_of_charge',
fix_initial=False,
fix_final=False,
solve_segments=True,
targets=['SOC'],
rate_source='dXdt:SOC')
phase1_bfail.add_timeseries_output('battery.V_oc', output_name='V_oc')
phase1_bfail.add_timeseries_output('battery.V_pack',
output_name='V_pack')
phase1_bfail.add_timeseries_output('pwr_balance.I_Li',
output_name='I_Li')
traj.add_phase('phase1_bfail', phase1_bfail)
# Second phase, but with motor failure.
phase1_mfail = dm.Phase(ode_class=BatteryODE,
ode_init_kwargs={'num_motor': 2},
transcription=transcription)
phase1_mfail.set_time_options(fix_initial=False, fix_duration=True)
phase1_mfail.add_state('state_of_charge',
fix_initial=False,
fix_final=False,
solve_segments=True,
targets=['SOC'],
rate_source='dXdt:SOC')
phase1_mfail.add_timeseries_output('battery.V_oc', output_name='V_oc')
phase1_mfail.add_timeseries_output('battery.V_pack',
output_name='V_pack')
phase1_mfail.add_timeseries_output('pwr_balance.I_Li',
output_name='I_Li')
traj.add_phase('phase1_mfail', phase1_mfail)
traj.link_phases(phases=['phase0', 'phase1'],
vars=['state_of_charge', 'time'],
connected=True)
traj.link_phases(phases=['phase0', 'phase1_bfail'],
vars=['state_of_charge', 'time'],
connected=True)
traj.link_phases(phases=['phase0', 'phase1_mfail'],
vars=['state_of_charge', 'time'],
connected=True)
# prob.model.linear_solver = om.DirectSolver(assemble_jac=True)
prob.setup()
prob.final_setup()
prob['traj.phases.phase0.time_extents.t_initial'] = 0
prob['traj.phases.phase0.time_extents.t_duration'] = 1.0 * 3600
# prob['traj.phases.phase1.time_extents.t_initial'] = 1.0*3600
prob['traj.phases.phase1.time_extents.t_duration'] = 1.0 * 3600
# prob['traj.phases.phase1_bfail.time_extents.t_initial'] = 1.0*3600
prob['traj.phases.phase1_bfail.time_extents.t_duration'] = 1.0 * 3600
# prob['traj.phases.phase1_mfail.time_extents.t_initial'] = 1.0*3600
prob['traj.phases.phase1_mfail.time_extents.t_duration'] = 1.0 * 3600
prob.set_solver_print(level=0)
prob.run_model()
plot = True
if plot:
import matplotlib
matplotlib.use('Agg')
import matplotlib.pyplot as plt
t0 = prob['traj.phase0.timeseries.time']
t1 = prob['traj.phase1.timeseries.time']
t1b = prob['traj.phase1_bfail.timeseries.time']
t1m = prob['traj.phase1_mfail.timeseries.time']
soc0 = prob['traj.phase0.timeseries.states:state_of_charge']
soc1 = prob['traj.phase1.timeseries.states:state_of_charge']
soc1b = prob['traj.phase1_bfail.timeseries.states:state_of_charge']
soc1m = prob['traj.phase1_mfail.timeseries.states:state_of_charge']
plt.subplot(2, 2, 1)
plt.plot(t0, soc0, 'b')
plt.plot(t1, soc1, 'b')
plt.plot(t1b, soc1b, 'r')
plt.plot(t1m, soc1m, 'c')
plt.xlabel('Time (hour)')
plt.ylabel('State of Charge (percent)')
V_oc0 = prob['traj.phase0.timeseries.V_oc']
V_oc1 = prob['traj.phase1.timeseries.V_oc']
V_oc1b = prob['traj.phase1_bfail.timeseries.V_oc']
V_oc1m = prob['traj.phase1_mfail.timeseries.V_oc']
plt.subplot(2, 2, 2)
plt.plot(t0, V_oc0, 'b')
plt.plot(t1, V_oc1, 'b')
plt.plot(t1b, V_oc1b, 'r')
plt.plot(t1m, V_oc1m, 'c')
plt.xlabel('Time (hour)')
plt.ylabel('Open Circuit Voltage (V)')
V_pack0 = prob['traj.phase0.timeseries.V_pack']
V_pack1 = prob['traj.phase1.timeseries.V_pack']
V_pack1b = prob['traj.phase1_bfail.timeseries.V_pack']
V_pack1m = prob['traj.phase1_mfail.timeseries.V_pack']
plt.subplot(2, 2, 3)
plt.plot(t0, V_pack0, 'b')
plt.plot(t1, V_pack1, 'b')
plt.plot(t1b, V_pack1b, 'r')
plt.plot(t1m, V_pack1m, 'c')
plt.xlabel('Time (hour)')
plt.ylabel('Terminal Voltage (V)')
I_Li0 = prob['traj.phase0.timeseries.I_Li']
I_Li1 = prob['traj.phase1.timeseries.I_Li']
I_Li1b = prob['traj.phase1_bfail.timeseries.I_Li']
I_Li1m = prob['traj.phase1_mfail.timeseries.I_Li']
plt.subplot(2, 2, 4)
plt.plot(t0, I_Li0, 'b')
plt.plot(t1, I_Li1, 'b')
plt.plot(t1b, I_Li1b, 'r')
plt.plot(t1m, I_Li1m, 'c')
plt.xlabel('Time (hour)')
plt.ylabel('Line Current (A)')
plt.show()
ar = np.arange(nn, dtype=int)
self.declare_partials(of='y_dot', wrt='vy', rows=ar, cols=ar, val=1.0)
def compute(self,
inputs,
outputs,
discrete_inputs=None,
discrete_outputs=None):
vy = inputs['vy']
outputs['y_dot'] = vy
outputs['vy_dot'] = -9.80665
# Instantiate an OpenMDAO Problem instance.
prob = om.Problem()
prob.driver = om.ScipyOptimizeDriver()
prob.driver.add_recorder(om.SqliteRecorder('collocation_figures.db'))
prob.driver.recording_options['includes'] = [
'*dstau*', '*rhs_col*', '*staterate*', '*timeseries*', '*timeseries2*',
'*rhs_disc*'
]
# Instantiate a Dymos Trajectory and add it to the Problem model.
traj = dm.Trajectory()
prob.model.add_subsystem('traj', traj)
# Instantiate a Phase and add it to the Trajectory.
phase = dm.Phase(ode_class=FallEOM,
transcription=dm.GaussLobatto(num_segments=NUM_SEG,
def _make_problem(self, transcription, num_seg, transcription_order=3):
p = om.Problem(model=om.Group())
p.driver = om.ScipyOptimizeDriver()
# Compute sparsity/coloring when run_driver is called
p.driver.declare_coloring()
t = {
'gauss-lobatto':
dm.GaussLobatto(num_segments=num_seg, order=transcription_order),
'radau-ps':
dm.Radau(num_segments=num_seg, order=transcription_order),
'runge-kutta':
dm.RungeKutta(num_segments=num_seg)
}
phase = dm.Phase(ode_class=_BrachistochroneTestODE,
transcription=t[transcription])
p.model.add_subsystem('phase0', phase)
phase.set_time_options(initial_bounds=(1, 1),
duration_bounds=(.5, 10),
units='s',
time_phase_targets=['time_phase'],
t_duration_targets=['t_duration'],
t_initial_targets=['t_initial'],
targets=['time'])
phase.add_state('x', fix_initial=True, rate_source='xdot', units='m')
phase.add_state('y', fix_initial=True, rate_source='ydot', units='m')
phase.add_state('v',
fix_initial=True,
rate_source='vdot',
targets=['v'],
units='m/s')
phase.add_control('theta',
units='deg',
rate_continuity=True,
lower=0.01,
upper=179.9,
targets=['theta'])
phase.add_parameter('g',
units='m/s**2',
opt=False,
val=9.80665,
targets=['g'])
phase.add_boundary_constraint('x', loc='final', equals=10)
phase.add_boundary_constraint('y', loc='final', equals=5)
# Minimize time at the end of the phase
phase.add_objective('time', loc='final', scaler=10)
p.model.linear_solver = om.DirectSolver()
p.setup(check=True)
p['phase0.t_initial'] = 1.0
p['phase0.t_duration'] = 3.0
p['phase0.states:x'] = phase.interpolate(ys=[0, 10],
nodes='state_input')
p['phase0.states:y'] = phase.interpolate(ys=[10, 5],
nodes='state_input')
p['phase0.states:v'] = phase.interpolate(ys=[0, 9.9],
nodes='state_input')
p['phase0.controls:theta'] = phase.interpolate(ys=[5, 100.5],
nodes='control_input')
return p
def test_ccblade_loads(self):
prob = om.Problem()
# Load in airfoil and blade shape inputs for NREL 5MW
npzfile = np.load(os.path.dirname(os.path.abspath(__file__)) + os.path.sep + 'smaller_dataset.npz', allow_pickle=True)
n_span = npzfile['r'].size
n_aoa = npzfile['aoa'].size
n_Re = npzfile['Re'].size
modeling_options = {}
modeling_options['blade'] = {}
modeling_options['blade']['n_span'] = n_span
modeling_options['blade']['n_aoa'] = n_aoa
modeling_options['blade']['n_Re'] = n_Re
modeling_options['blade']['n_tab'] = 1
n_span, n_aoa, n_Re, n_tab = np.moveaxis(npzfile['cl'][:,:,:,np.newaxis], 0, 1).shape
modeling_options['airfoils'] = {}
modeling_options['airfoils']['n_aoa'] = n_aoa
modeling_options['airfoils']['n_Re'] = n_Re
modeling_options['airfoils']['n_tab'] = n_tab
comp = CCBladeLoads(modeling_options=modeling_options)
prob.model.add_subsystem('comp', comp, promotes=['*'])
prob.setup(force_alloc_complex=True)
# Add some arbitrary inputs
prob.set_val('airfoils_aoa', npzfile['aoa'], units='deg')
prob.set_val('airfoils_Re', npzfile['Re'])
prob.set_val('airfoils_cl', np.moveaxis(npzfile['cl'][:,:,:,np.newaxis], 0, 1))
prob.set_val('airfoils_cd', np.moveaxis(npzfile['cd'][:,:,:,np.newaxis], 0, 1))
prob.set_val('airfoils_cm', np.moveaxis(npzfile['cm'][:,:,:,np.newaxis], 0, 1))
prob.set_val('r', npzfile['r'], units='m')
prob.set_val('chord', npzfile['chord'], units='m')
prob.set_val('theta', npzfile['theta'], units='deg')
# parameters
prob.set_val('V_load', 12., units='m/s')
prob.set_val('Omega_load', 7.0, units='rpm')
prob.set_val('pitch_load', 2.0, units='deg')
prob.set_val('azimuth_load', 3.0, units='deg')
prob.set_val('Rhub', 1., units='m')
prob.set_val('Rtip', 70., units='m')
prob.set_val('hub_height', 100., units='m')
prob.set_val('precone', 0., units='deg')
prob.set_val('tilt', 0., units='deg')
prob.set_val('yaw', 0., units='deg')
prob.set_val('precurve', np.zeros(n_span), units='m')
prob.set_val('precurveTip', 0., units='m')
prob.set_val('rho', 1.225, units='kg/m**3')
prob.set_val('mu', 1.81206e-5, units='kg/(m*s)')
prob.set_val('shearExp', 0.25)
prob.set_val('nBlades', 3)
prob.set_val('nSector', 4)
prob.set_val('tiploss', True)
prob.set_val('hubloss', True)
prob.set_val('wakerotation', True)
prob.set_val('usecd', True)
prob.run_model()
check = prob.check_partials(out_stream=None, compact_print=True)
# Manually filter some entries out of the assert_check_partials call.
# Will want to add this functionality to OpenMDAO itself at some point.
new_check = {}
for comp_name in check:
new_check[comp_name] = {}
for (output_name, input_name) in check[comp_name]:
if 'airfoil' not in input_name and 'rho' not in input_name and 'mu' not in input_name and 'shearExp' not in input_name:
new_check[comp_name][(output_name, input_name)] = check[comp_name][(output_name, input_name)]
assert_check_partials(new_check, rtol=5e-5, atol=1e-4)
n_xsecs = degen_obj.surf.num_secs
points = np.empty((npts * n_xsecs, 3))
points[:, 0] = list(itertools.chain.from_iterable(degen_obj.surf.x))
points[:, 1] = list(itertools.chain.from_iterable(degen_obj.surf.y))
points[:, 2] = list(itertools.chain.from_iterable(degen_obj.surf.z))
return points
if __name__ == "__main__":
from openmdao.api import DirectSolver, NewtonSolver, BoundsEnforceLS
vsp_comp = VSPeCRM(horiz_tail_name="Tail", vert_tail_name="VerticalTail", wing_name="Wing")
p = om.Problem()
model = p.model
#newton = model.nonlinear_solver = NewtonSolver()
#newton.options['iprint'] = 2
#newton.options['maxiter'] = 100
#newton.options['solve_subsystems'] = True
#newton.options['atol'] = 1e-7
#newton.options['rtol'] = 1e-15
#newton.options['err_on_non_converge'] = True
#model.linear_solver = DirectSolver()
#ls = newton.linesearch = BoundsEnforceLS()
#ls.options['iprint'] = 2
#ls.options['print_bound_enforce'] = True
#ls.options['bound_enforcement'] = 'scalar'
def test_two_phase_cannonball_for_docs(self):
import openmdao.api as om
from openmdao.utils.assert_utils import assert_near_equal
import dymos as dm
from dymos.examples.cannonball.size_comp import CannonballSizeComp
from dymos.examples.cannonball.cannonball_phase import CannonballPhase
p = om.Problem(model=om.Group())
p.driver = om.pyOptSparseDriver()
p.driver.options['optimizer'] = 'SLSQP'
p.driver.declare_coloring()
external_params = p.model.add_subsystem('external_params', om.IndepVarComp())
external_params.add_output('radius', val=0.10, units='m')
external_params.add_output('dens', val=7.87, units='g/cm**3')
external_params.add_design_var('radius', lower=0.01, upper=0.10, ref0=0.01, ref=0.10)
p.model.add_subsystem('size_comp', CannonballSizeComp())
traj = p.model.add_subsystem('traj', dm.Trajectory())
transcription = dm.Radau(num_segments=5, order=3, compressed=True)
ascent = CannonballPhase(transcription=transcription)
ascent = traj.add_phase('ascent', ascent)
# All initial states except flight path angle are fixed
# Final flight path angle is fixed (we will set it to zero so that the phase ends at apogee)
ascent.set_time_options(fix_initial=True, duration_bounds=(1, 100), duration_ref=100, units='s')
ascent.set_state_options('r', fix_initial=True, fix_final=False)
ascent.set_state_options('h', fix_initial=True, fix_final=False)
ascent.set_state_options('gam', fix_initial=False, fix_final=True)
ascent.set_state_options('v', fix_initial=False, fix_final=False)
ascent.add_parameter('S', targets=['aero.S'], units='m**2')
ascent.add_parameter('mass', targets=['eom.m', 'kinetic_energy.m'], units='kg')
# Limit the muzzle energy
ascent.add_boundary_constraint('kinetic_energy.ke', loc='initial', units='J',
upper=400000, lower=0, ref=100000, shape=(1,))
# Second Phase (descent)
transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True)
descent = CannonballPhase(transcription=transcription)
traj.add_phase('descent', descent)
# All initial states and time are free (they will be linked to the final states of ascent.
# Final altitude is fixed (we will set it to zero so that the phase ends at ground impact)
descent.set_time_options(initial_bounds=(.5, 100), duration_bounds=(.5, 100),
duration_ref=100, units='s')
descent.add_state('r', )
descent.add_state('h', fix_initial=False, fix_final=True)
descent.add_state('gam', fix_initial=False, fix_final=False)
descent.add_state('v', fix_initial=False, fix_final=False)
descent.add_parameter('S', targets=['aero.S'], units='m**2')
descent.add_parameter('mass', targets=['eom.m', 'kinetic_energy.m'], units='kg')
descent.add_objective('r', loc='final', scaler=-1.0)
# Add internally-managed design parameters to the trajectory.
traj.add_parameter('CD',
targets={'ascent': ['aero.CD'], 'descent': ['aero.CD']},
val=0.5, units=None, opt=False)
traj.add_parameter('CL',
targets={'ascent': ['aero.CL'], 'descent': ['aero.CL']},
val=0.0, units=None, opt=False)
traj.add_parameter('T',
targets={'ascent': ['eom.T'], 'descent': ['eom.T']},
val=0.0, units='N', opt=False)
traj.add_parameter('alpha',
targets={'ascent': ['eom.alpha'], 'descent': ['eom.alpha']},
val=0.0, units='deg', opt=False)
# Add externally-provided design parameters to the trajectory.
# In this case, we connect 'm' to pre-existing input parameters named 'mass' in each phase.
traj.add_parameter('m', units='kg', val=1.0,
targets={'ascent': 'mass', 'descent': 'mass'})
# In this case, by omitting targets, we're connecting these parameters to parameters
# with the same name in each phase.
traj.add_parameter('S', units='m**2', val=0.005)
# Link Phases (link time and all state variables)
traj.link_phases(phases=['ascent', 'descent'], vars=['*'])
# Issue Connections
p.model.connect('external_params.radius', 'size_comp.radius')
p.model.connect('external_params.dens', 'size_comp.dens')
p.model.connect('size_comp.mass', 'traj.parameters:m')
p.model.connect('size_comp.S', 'traj.parameters:S')
# A linear solver at the top level can improve performance.
p.model.linear_solver = om.DirectSolver()
# Finish Problem Setup
p.setup()
# Set Initial Guesses
p.set_val('external_params.radius', 0.05, units='m')
p.set_val('external_params.dens', 7.87, units='g/cm**3')
p.set_val('traj.parameters:CD', 0.5)
p.set_val('traj.parameters:CL', 0.0)
p.set_val('traj.parameters:T', 0.0)
p.set_val('traj.ascent.t_initial', 0.0)
p.set_val('traj.ascent.t_duration', 10.0)
p.set_val('traj.ascent.states:r', ascent.interpolate(ys=[0, 100], nodes='state_input'))
p.set_val('traj.ascent.states:h', ascent.interpolate(ys=[0, 100], nodes='state_input'))
p.set_val('traj.ascent.states:v', ascent.interpolate(ys=[200, 150], nodes='state_input'))
p.set_val('traj.ascent.states:gam', ascent.interpolate(ys=[25, 0], nodes='state_input'),
units='deg')
p.set_val('traj.descent.t_initial', 10.0)
p.set_val('traj.descent.t_duration', 10.0)
p.set_val('traj.descent.states:r', descent.interpolate(ys=[100, 200], nodes='state_input'))
p.set_val('traj.descent.states:h', descent.interpolate(ys=[100, 0], nodes='state_input'))
p.set_val('traj.descent.states:v', descent.interpolate(ys=[150, 200], nodes='state_input'))
p.set_val('traj.descent.states:gam', descent.interpolate(ys=[0, -45], nodes='state_input'),
units='deg')
dm.run_problem(p)
assert_near_equal(p.get_val('traj.descent.states:r')[-1],
3183.25, tolerance=1.0E-2)
exp_out = traj.simulate()
print('optimal radius: {0:6.4f} m '.format(p.get_val('external_params.radius',
units='m')[0]))
print('cannonball mass: {0:6.4f} kg '.format(p.get_val('size_comp.mass',
units='kg')[0]))
print('launch angle: {0:6.4f} '
'deg '.format(p.get_val('traj.ascent.timeseries.states:gam', units='deg')[0, 0]))
print('maximum range: {0:6.4f} '
'm '.format(p.get_val('traj.descent.timeseries.states:r')[-1, 0]))
fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6))
time_imp = {'ascent': p.get_val('traj.ascent.timeseries.time'),
'descent': p.get_val('traj.descent.timeseries.time')}
time_exp = {'ascent': exp_out.get_val('traj.ascent.timeseries.time'),
'descent': exp_out.get_val('traj.descent.timeseries.time')}
r_imp = {'ascent': p.get_val('traj.ascent.timeseries.states:r'),
'descent': p.get_val('traj.descent.timeseries.states:r')}
r_exp = {'ascent': exp_out.get_val('traj.ascent.timeseries.states:r'),
'descent': exp_out.get_val('traj.descent.timeseries.states:r')}
h_imp = {'ascent': p.get_val('traj.ascent.timeseries.states:h'),
'descent': p.get_val('traj.descent.timeseries.states:h')}
h_exp = {'ascent': exp_out.get_val('traj.ascent.timeseries.states:h'),
'descent': exp_out.get_val('traj.descent.timeseries.states:h')}
axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo')
axes.plot(r_imp['descent'], h_imp['descent'], 'ro')
axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--')
axes.plot(r_exp['descent'], h_exp['descent'], 'r--')
axes.set_xlabel('range (m)')
axes.set_ylabel('altitude (m)')
fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6))
states = ['r', 'h', 'v', 'gam']
for i, state in enumerate(states):
x_imp = {'ascent': p.get_val('traj.ascent.timeseries.states:{0}'.format(state)),
'descent': p.get_val('traj.descent.timeseries.states:{0}'.format(state))}
x_exp = {'ascent': exp_out.get_val('traj.ascent.timeseries.states:{0}'.format(state)),
'descent': exp_out.get_val('traj.descent.timeseries.states:{0}'.format(state))}
axes[i].set_ylabel(state)
axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo')
axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro')
axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--')
axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--')
params = ['CL', 'CD', 'T', 'alpha', 'mass', 'S']
fig, axes = plt.subplots(nrows=6, ncols=1, figsize=(12, 6))
for i, param in enumerate(params):
p_imp = {
'ascent': p.get_val('traj.ascent.timeseries.parameters:{0}'.format(param)),
'descent': p.get_val('traj.descent.timeseries.parameters:{0}'.format(param))}
p_exp = {'ascent': exp_out.get_val('traj.ascent.timeseries.'
'parameters:{0}'.format(param)),
'descent': exp_out.get_val('traj.descent.timeseries.'
'parameters:{0}'.format(param))}
axes[i].set_ylabel(param)
axes[i].plot(time_imp['ascent'], p_imp['ascent'], 'bo')
axes[i].plot(time_imp['descent'], p_imp['descent'], 'ro')
axes[i].plot(time_exp['ascent'], p_exp['ascent'], 'b--')
axes[i].plot(time_exp['descent'], p_exp['descent'], 'r--')
plt.show()
def test_finite_burn_orbit_raise(self):
import numpy as np
import matplotlib.pyplot as plt
import openmdao.api as om
from openmdao.utils.assert_utils import assert_near_equal
import dymos as dm
from dymos.examples.finite_burn_orbit_raise.finite_burn_eom import FiniteBurnODE
p = om.Problem(model=om.Group())
p.driver = om.pyOptSparseDriver()
p.driver.options['optimizer'] = 'IPOPT'
p.driver.declare_coloring()
traj = dm.Trajectory()
traj.add_parameter('c', opt=False, val=1.5, units='DU/TU',
targets={'burn1': ['c'], 'coast': ['c'], 'burn2': ['c']})
# First Phase (burn)
burn1 = dm.Phase(ode_class=FiniteBurnODE,
transcription=dm.GaussLobatto(num_segments=5, order=3, compressed=False))
burn1 = traj.add_phase('burn1', burn1)
burn1.set_time_options(fix_initial=True, duration_bounds=(.5, 10), units='TU')
burn1.add_state('r', fix_initial=True, fix_final=False, defect_scaler=100.0,
rate_source='r_dot', units='DU')
burn1.add_state('theta', fix_initial=True, fix_final=False, defect_scaler=100.0,
rate_source='theta_dot', units='rad')
burn1.add_state('vr', fix_initial=True, fix_final=False, defect_scaler=100.0,
rate_source='vr_dot', units='DU/TU')
burn1.add_state('vt', fix_initial=True, fix_final=False, defect_scaler=100.0,
rate_source='vt_dot', units='DU/TU')
burn1.add_state('accel', fix_initial=True, fix_final=False,
rate_source='at_dot', units='DU/TU**2')
burn1.add_state('deltav', fix_initial=True, fix_final=False,
rate_source='deltav_dot', units='DU/TU')
burn1.add_control('u1', rate_continuity=True, rate2_continuity=True, units='deg',
scaler=0.01, rate_continuity_scaler=0.001, rate2_continuity_scaler=0.001,
lower=-30, upper=30)
# Second Phase (Coast)
coast = dm.Phase(ode_class=FiniteBurnODE,
transcription=dm.GaussLobatto(num_segments=5, order=3, compressed=False))
coast.set_time_options(initial_bounds=(0.5, 20), duration_bounds=(.5, 50), duration_ref=50,
units='TU')
coast.add_state('r', fix_initial=False, fix_final=False, defect_scaler=100.0,
rate_source='r_dot', targets=['r'], units='DU')
coast.add_state('theta', fix_initial=False, fix_final=False, defect_scaler=100.0,
rate_source='theta_dot', targets=['theta'], units='rad')
coast.add_state('vr', fix_initial=False, fix_final=False, defect_scaler=100.0,
rate_source='vr_dot', targets=['vr'], units='DU/TU')
coast.add_state('vt', fix_initial=False, fix_final=False, defect_scaler=100.0,
rate_source='vt_dot', targets=['vt'], units='DU/TU')
coast.add_state('accel', fix_initial=True, fix_final=True,
rate_source='at_dot', targets=['accel'], units='DU/TU**2')
coast.add_state('deltav', fix_initial=False, fix_final=False,
rate_source='deltav_dot', units='DU/TU')
coast.add_parameter('u1', opt=False, val=0.0, units='deg', targets=['u1'])
# Third Phase (burn)
burn2 = dm.Phase(ode_class=FiniteBurnODE,
transcription=dm.GaussLobatto(num_segments=5, order=3, compressed=False))
traj.add_phase('coast', coast)
traj.add_phase('burn2', burn2)
burn2.set_time_options(initial_bounds=(0.5, 50), duration_bounds=(.5, 10), initial_ref=10,
units='TU')
burn2.add_state('r', fix_initial=False, fix_final=True, defect_scaler=100.0,
rate_source='r_dot', units='DU')
burn2.add_state('theta', fix_initial=False, fix_final=False, defect_scaler=100.0,
rate_source='theta_dot', units='rad')
burn2.add_state('vr', fix_initial=False, fix_final=True, defect_scaler=1000.0,
rate_source='vr_dot', units='DU/TU')
burn2.add_state('vt', fix_initial=False, fix_final=True, defect_scaler=1000.0,
rate_source='vt_dot', units='DU/TU')
burn2.add_state('accel', fix_initial=False, fix_final=False, defect_scaler=1.0,
rate_source='at_dot', units='DU/TU**2')
burn2.add_state('deltav', fix_initial=False, fix_final=False, defect_scaler=1.0,
rate_source='deltav_dot', units='DU/TU')
burn2.add_objective('deltav', loc='final', scaler=100.0)
burn2.add_control('u1', rate_continuity=True, rate2_continuity=True, units='deg',
scaler=0.01, lower=-90, upper=90)
burn1.add_timeseries_output('pos_x')
coast.add_timeseries_output('pos_x')
burn2.add_timeseries_output('pos_x')
burn1.add_timeseries_output('pos_y')
coast.add_timeseries_output('pos_y')
burn2.add_timeseries_output('pos_y')
# Link Phases
traj.link_phases(phases=['burn1', 'coast', 'burn2'],
vars=['time', 'r', 'theta', 'vr', 'vt', 'deltav'])
traj.link_phases(phases=['burn1', 'burn2'], vars=['accel'])
p.model.add_subsystem('traj', subsys=traj)
# Finish Problem Setup
# Needed to move the direct solver down into the phases for use with MPI.
# - After moving down, used fewer iterations (about 30 less)
p.driver.add_recorder(om.SqliteRecorder('two_burn_orbit_raise_example.db'))
p.setup(check=True, mode='fwd')
# Set Initial Guesses
p.set_val('traj.parameters:c', value=1.5, units='DU/TU')
burn1 = p.model.traj.phases.burn1
burn2 = p.model.traj.phases.burn2
coast = p.model.traj.phases.coast
p.set_val('traj.burn1.t_initial', value=0.0)
p.set_val('traj.burn1.t_duration', value=2.25)
p.set_val('traj.burn1.states:r', value=burn1.interp('r', [1, 1.5]))
p.set_val('traj.burn1.states:theta', value=burn1.interp('theta', [0, 1.7]))
p.set_val('traj.burn1.states:vr', value=burn1.interp('vr', [0, 0]))
p.set_val('traj.burn1.states:vt', value=burn1.interp('vt', [1, 1]))
p.set_val('traj.burn1.states:accel', value=burn1.interp('accel', [0.1, 0]))
p.set_val('traj.burn1.states:deltav', value=burn1.interp('deltav', [0, 0.1]))
p.set_val('traj.burn1.controls:u1', value=burn1.interp('u1', [-3.5, 13.0]))
p.set_val('traj.coast.t_initial', value=2.25)
p.set_val('traj.coast.t_duration', value=3.0)
p.set_val('traj.coast.states:r', value=coast.interp('r', [1.3, 1.5]))
p.set_val('traj.coast.states:theta', value=coast.interp('theta', [2.1767, 1.7]))
p.set_val('traj.coast.states:vr', value=coast.interp('vr', [0.3285, 0]))
p.set_val('traj.coast.states:vt', value=coast.interp('vt', [0.97, 1]))
p.set_val('traj.coast.states:accel', value=coast.interp('accel', [0, 0]))
p.set_val('traj.burn2.t_initial', value=5.25)
p.set_val('traj.burn2.t_duration', value=1.75)
p.set_val('traj.burn2.states:r', value=burn2.interp('r', [1, 3.]))
p.set_val('traj.burn2.states:theta', value=burn2.interp('theta', [0, 4.0]))
p.set_val('traj.burn2.states:vr', value=burn2.interp('vr', [0, 0]))
p.set_val('traj.burn2.states:vt', value=burn2.interp('vt', [1, np.sqrt(1 / 3.)]))
p.set_val('traj.burn2.states:deltav', value=burn2.interp('deltav', [0.1, 0.2]))
p.set_val('traj.burn2.states:accel', value=burn2.interp('accel', [0.1, 0]))
p.set_val('traj.burn2.controls:u1', value=burn2.interp('u1', [0, 0]))
dm.run_problem(p)
assert_near_equal(p.get_val('traj.burn2.states:deltav')[-1], 0.3995,
tolerance=2.0E-3)
#
# Plot results
#
traj = p.model.traj
exp_out = traj.simulate()
fig = plt.figure(figsize=(8, 4))
fig.suptitle('Two Burn Orbit Raise Solution')
ax_u1 = plt.subplot2grid((2, 2), (0, 0))
ax_deltav = plt.subplot2grid((2, 2), (1, 0))
ax_xy = plt.subplot2grid((2, 2), (0, 1), rowspan=2)
span = np.linspace(0, 2 * np.pi, 100)
ax_xy.plot(np.cos(span), np.sin(span), 'k--', lw=1)
ax_xy.plot(3 * np.cos(span), 3 * np.sin(span), 'k--', lw=1)
ax_xy.set_xlim(-4.5, 4.5)
ax_xy.set_ylim(-4.5, 4.5)
ax_xy.set_xlabel('x ($R_e$)')
ax_xy.set_ylabel('y ($R_e$)')
ax_u1.set_xlabel('time ($TU$)')
ax_u1.set_ylabel('$u_1$ ($deg$)')
ax_u1.grid(True)
ax_deltav.set_xlabel('time ($TU$)')
ax_deltav.set_ylabel('${\Delta}v$ ($DU/TU$)')
ax_deltav.grid(True)
t_sol = dict((phs, p.get_val('traj.{0}.timeseries.time'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
x_sol = dict((phs, p.get_val('traj.{0}.timeseries.pos_x'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
y_sol = dict((phs, p.get_val('traj.{0}.timeseries.pos_y'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
dv_sol = dict((phs, p.get_val('traj.{0}.timeseries.states:deltav'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
u1_sol = dict((phs, p.get_val('traj.{0}.timeseries.controls:u1'.format(phs), units='deg'))
for phs in ['burn1', 'burn2'])
t_exp = dict((phs, exp_out.get_val('traj.{0}.timeseries.time'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
x_exp = dict((phs, exp_out.get_val('traj.{0}.timeseries.pos_x'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
y_exp = dict((phs, exp_out.get_val('traj.{0}.timeseries.pos_y'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
dv_exp = dict((phs, exp_out.get_val('traj.{0}.timeseries.states:deltav'.format(phs)))
for phs in ['burn1', 'coast', 'burn2'])
u1_exp = dict((phs, exp_out.get_val('traj.{0}.timeseries.controls:u1'.format(phs),
units='deg'))
for phs in ['burn1', 'burn2'])
for phs in ['burn1', 'coast', 'burn2']:
try:
ax_u1.plot(t_exp[phs], u1_exp[phs], '-', marker=None, color='C0')
ax_u1.plot(t_sol[phs], u1_sol[phs], 'o', mfc='C1', mec='C1', ms=3)
except KeyError:
pass
ax_deltav.plot(t_exp[phs], dv_exp[phs], '-', marker=None, color='C0')
ax_deltav.plot(t_sol[phs], dv_sol[phs], 'o', mfc='C1', mec='C1', ms=3)
ax_xy.plot(x_exp[phs], y_exp[phs], '-', marker=None, color='C0', label='explicit')
ax_xy.plot(x_sol[phs], y_sol[phs], 'o', mfc='C1', mec='C1', ms=3, label='implicit')
plt.show()
def test_connect_control_to_parameter(self):
""" Test that the final value of a control in one phase can be connected as the value
of a parameter in a subsequent phase. """
import openmdao.api as om
from openmdao.utils.assert_utils import assert_near_equal
import dymos as dm
from dymos.examples.cannonball.size_comp import CannonballSizeComp
p = om.Problem(model=om.Group())
p.driver = om.pyOptSparseDriver()
p.driver.options['optimizer'] = 'SLSQP'
p.driver.declare_coloring()
external_params = p.model.add_subsystem('external_params',
om.IndepVarComp())
external_params.add_output('radius', val=0.10, units='m')
external_params.add_output('dens', val=7.87, units='g/cm**3')
external_params.add_design_var('radius',
lower=0.01,
upper=0.10,
ref0=0.01,
ref=0.10)
p.model.add_subsystem('size_comp', CannonballSizeComp())
traj = p.model.add_subsystem('traj', dm.Trajectory())
transcription = dm.Radau(num_segments=5, order=3, compressed=True)
ascent = dm.Phase(ode_class=CannonballODEVectorCD,
transcription=transcription)
ascent = traj.add_phase('ascent', ascent)
# All initial states except flight path angle are fixed
# Final flight path angle is fixed (we will set it to zero so that the phase ends at apogee)
ascent.set_time_options(fix_initial=True,
duration_bounds=(1, 100),
duration_ref=100,
units='s')
ascent.add_state('r',
fix_initial=True,
fix_final=False,
rate_source='r_dot',
units='m')
ascent.add_state('h',
fix_initial=True,
fix_final=False,
units='m',
rate_source='h_dot')
ascent.add_state('gam',
fix_initial=False,
fix_final=True,
units='rad',
rate_source='gam_dot')
ascent.add_state('v',
fix_initial=False,
fix_final=False,
units='m/s',
rate_source='v_dot')
ascent.add_parameter('S',
targets=['S'],
units='m**2',
static_target=True)
ascent.add_parameter('mass',
targets=['m'],
units='kg',
static_target=True)
ascent.add_control('CD', targets=['CD'], opt=False, val=0.05)
# Limit the muzzle energy
ascent.add_boundary_constraint('ke',
loc='initial',
upper=400000,
lower=0,
ref=100000)
# Second Phase (descent)
transcription = dm.GaussLobatto(num_segments=5,
order=3,
compressed=True)
descent = dm.Phase(ode_class=CannonballODEVectorCD,
transcription=transcription)
traj.add_phase('descent', descent)
# All initial states and time are free (they will be linked to the final states of ascent.
# Final altitude is fixed (we will set it to zero so that the phase ends at ground impact)
descent.set_time_options(initial_bounds=(.5, 100),
duration_bounds=(.5, 100),
duration_ref=100,
units='s')
descent.add_state('r', units='m', rate_source='r_dot')
descent.add_state('h',
units='m',
rate_source='h_dot',
fix_initial=False,
fix_final=True)
descent.add_state('gam',
units='rad',
rate_source='gam_dot',
fix_initial=False,
fix_final=False)
descent.add_state('v',
units='m/s',
rate_source='v_dot',
fix_initial=False,
fix_final=False)
descent.add_parameter('S',
targets=['S'],
units='m**2',
static_target=True)
descent.add_parameter('mass',
targets=['m'],
units='kg',
static_target=True)
descent.add_parameter('CD', targets=['CD'], val=0.01)
descent.add_objective('r', loc='final', scaler=-1.0)
# Add externally-provided design parameters to the trajectory.
# In this case, we connect 'm' to pre-existing input parameters named 'mass' in each phase.
traj.add_parameter('m',
units='kg',
val=1.0,
targets={
'ascent': 'mass',
'descent': 'mass'
},
static_target=True)
# In this case, by omitting targets, we're connecting these parameters to parameters
# with the same name in each phase.
traj.add_parameter('S', units='m**2', val=0.005, static_target=True)
# Link Phases (link time and all state variables)
traj.link_phases(phases=['ascent', 'descent'], vars=['*'])
# Issue Connections
p.model.connect('external_params.radius', 'size_comp.radius')
p.model.connect('external_params.dens', 'size_comp.dens')
p.model.connect('size_comp.mass', 'traj.parameters:m')
p.model.connect('size_comp.S', 'traj.parameters:S')
traj.connect('ascent.timeseries.controls:CD',
'descent.parameters:CD',
src_indices=[-1],
flat_src_indices=True)
# A linear solver at the top level can improve performance.
p.model.linear_solver = om.DirectSolver()
# Finish Problem Setup
p.setup()
# Set Initial Guesses
p.set_val('external_params.radius', 0.05, units='m')
p.set_val('external_params.dens', 7.87, units='g/cm**3')
p.set_val('traj.ascent.controls:CD', 0.5)
p.set_val('traj.ascent.t_initial', 0.0)
p.set_val('traj.ascent.t_duration', 10.0)
p.set_val('traj.ascent.states:r', ascent.interp('r', [0, 100]))
p.set_val('traj.ascent.states:h', ascent.interp('h', [0, 100]))
p.set_val('traj.ascent.states:v', ascent.interp('v', [200, 150]))
p.set_val('traj.ascent.states:gam',
ascent.interp('gam', [25, 0]),
units='deg')
p.set_val('traj.descent.t_initial', 10.0)
p.set_val('traj.descent.t_duration', 10.0)
p.set_val('traj.descent.states:r', descent.interp('r', [100, 200]))
p.set_val('traj.descent.states:h', descent.interp('h', [100, 0]))
p.set_val('traj.descent.states:v', descent.interp('v', [150, 200]))
p.set_val('traj.descent.states:gam',
descent.interp('gam', [0, -45]),
units='deg')
dm.run_problem(p, simulate=True, make_plots=True)
assert_near_equal(p.get_val('traj.descent.states:r')[-1],
3183.25,
tolerance=1.0E-2)
assert_near_equal(
p.get_val('traj.ascent.timeseries.controls:CD')[-1],
p.get_val('traj.descent.timeseries.parameters:CD')[0])
def test_partial_deriv_plot(self):
class ArrayComp2D(om.ExplicitComponent):
"""
A fairly simple array component with an intentional error in compute_partials.
"""
def setup(self):
self.JJ = np.array([[1.0, 0.0, 0.0, 7.0],
[0.0, 2.5, 0.0, 0.0],
[-1.0, 0.0, 8.0, 0.0],
[0.0, 4.0, 0.0, 6.0]])
# Params
self.add_input('x1', np.zeros([4]))
# Unknowns
self.add_output('y1', np.zeros([4]))
self.declare_partials(of='*', wrt='*')
def compute(self, inputs, outputs):
"""
Execution.
"""
outputs['y1'] = self.JJ.dot(inputs['x1'])
def compute_partials(self, inputs, partials):
"""
Analytical derivatives.
"""
# create some error to force the diff plot to show something
error = np.zeros((4,4))
err = 1e-7
error[0][3] = err
error[1][2] = - 2.0 * err
partials[('y1', 'x1')] = self.JJ + error
prob = om.Problem()
model = prob.model
model.add_subsystem('x_param1', om.IndepVarComp('x1', np.ones((4))), promotes=['x1'])
model.add_subsystem('mycomp', ArrayComp2D(), promotes=['x1', 'y1'])
prob.setup(check=False, mode='fwd')
check_partials_data = prob.check_partials(out_stream=None)
# plot with defaults
fig, ax = om.partial_deriv_plot('y1', 'x1', check_partials_data, title="Defaults")
# Instead of seeing if the images created by matplotlib match what we expect, which
# is a fragile thing to do in testing, check a data structure inside matplotlib's
# objects. We will assume matplotlib draws the correct thing.
expected_array = np.array([[1., 0., 0., 1.],
[0., 1., 0., 0.],
[1., 0., 1., 0.],
[0., 1., 0., 1.]])
actual_array = ax[0].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 1., 0., 0., 1.],
[ 0., 1., 1., 0.],
[ 1., 0., 1., 0.],
[ 0., 1., 0., 1.]])
actual_array = ax[1].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 9.31322575e-10, 0.0, 0.0, 1.0e-07],
[ 0.0, 0.0, -2.0e-07, 0.0],
[ 0.0, 0.0, 9.31322575e-10, 0.0],
[ 0.0, 0.0, 0.0, 1.86264515e-09]])
actual_array = ax[2].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
# plot with specified jac_method
fig, ax = om.partial_deriv_plot('y1', 'x1', check_partials_data, jac_method = "J_rev",
title="specified jac_method")
expected_array = np.array([[1., 0., 0., 1.],
[0., 1., 0., 0.],
[1., 0., 1., 0.],
[0., 1., 0., 1.]])
actual_array = ax[0].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 1., 0., 0., 1.],
[ 0., 1., 1., 0.],
[ 1., 0., 1., 0.],
[ 0., 1., 0., 1.]])
actual_array = ax[1].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 9.31322575e-10, 0.0, 0.0, 1.0e-07],
[ 0.0, 0.0, -2.0e-07, 0.0],
[ 0.0, 0.0, 9.31322575e-10, 0.0],
[ 0.0, 0.0, 0.0, 1.86264515e-09]])
actual_array = ax[2].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
# plot in non-binary mode
fig, ax = om.partial_deriv_plot('y1', 'x1', check_partials_data, binary = False,
title="non-binary")
expected_array = np.array([[ 1. , 0. , 0. , 7. ],
[ 0. , 2.5, 0. , 0. ],
[-1. , 0. , 8. , 0. ],
[ 0. , 4. , 0. , 6. ]])
actual_array = ax[0].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 1.0e+00, 0.0, 0.0, 7.00000010e+00],
[ 0.0, 2.5e+00, -2.0e-07, 0.0],
[ -1.0e+00, 0.0, 8.0e+00, 0.0],
[ 0.0, 4.0e+00, 0.0, 6.0e+00]])
actual_array = ax[1].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
expected_array = np.array([[ 9.31322575e-10, 0.0, 0.0, 1.0e-07],
[ 0.0, 0.0, -2.0e-07, 0.0],
[ 0.0, 0.0, 9.31322575e-10, 0.0],
[ 0.0, 0.0, 0.0, 1.86264515e-09]])
actual_array = ax[2].images[0]._A.data
assert_near_equal(expected_array, actual_array, 1e-8)
# plot with different tol values
# Not obvious how to test this other than image matching
om.partial_deriv_plot('y1', 'x1', check_partials_data, tol=1e-5,
title="tol greater than err")
om.partial_deriv_plot('y1', 'x1', check_partials_data, tol=1e-10,
title="tol less than err")
def test_doc_ssto_earth(self):
import matplotlib.pyplot as plt
import openmdao.api as om
import dymos as dm
#
# Setup and solve the optimal control problem
#
p = om.Problem(model=om.Group())
p.driver = om.pyOptSparseDriver()
p.driver.declare_coloring(tol=1.0E-12)
from dymos.examples.ssto.launch_vehicle_ode import LaunchVehicleODE
#
# Initialize our Trajectory and Phase
#
traj = dm.Trajectory()
phase = dm.Phase(ode_class=LaunchVehicleODE,
transcription=dm.GaussLobatto(num_segments=12,
order=3,
compressed=False))
traj.add_phase('phase0', phase)
p.model.add_subsystem('traj', traj)
#
# Set the options for the variables
#
phase.set_time_options(fix_initial=True, duration_bounds=(10, 500))
phase.add_state('x',
fix_initial=True,
ref=1.0E5,
defect_ref=10000.0,
rate_source='xdot')
phase.add_state('y',
fix_initial=True,
ref=1.0E5,
defect_ref=10000.0,
rate_source='ydot')
phase.add_state('vx',
fix_initial=True,
ref=1.0E3,
defect_ref=1000.0,
rate_source='vxdot')
phase.add_state('vy',
fix_initial=True,
ref=1.0E3,
defect_ref=1000.0,
rate_source='vydot')
phase.add_state('m',
fix_initial=True,
ref=1.0E3,
defect_ref=100.0,
rate_source='mdot')
phase.add_control('theta',
units='rad',
lower=-1.57,
upper=1.57,
targets=['theta'])
phase.add_parameter('thrust',
units='N',
opt=False,
val=2100000.0,
targets=['thrust'])
#
# Set the options for our constraints and objective
#
phase.add_boundary_constraint('y',
loc='final',
equals=1.85E5,
linear=True)
phase.add_boundary_constraint('vx', loc='final', equals=7796.6961)
phase.add_boundary_constraint('vy', loc='final', equals=0)
phase.add_objective('time', loc='final', scaler=0.01)
p.model.linear_solver = om.DirectSolver()
#
# Setup and set initial values
#
p.setup(check=True)
p.set_val('traj.phase0.t_initial', 0.0)
p.set_val('traj.phase0.t_duration', 150.0)
p.set_val('traj.phase0.states:x', phase.interp('x', [0, 1.15E5]))
p.set_val('traj.phase0.states:y', phase.interp('y', [0, 1.85E5]))
p.set_val('traj.phase0.states:vy', phase.interp('vx', [1.0E-6, 0]))
p.set_val('traj.phase0.states:m', phase.interp('vy', [117000, 1163]))
p.set_val('traj.phase0.controls:theta',
phase.interp('theta', [1.5, -0.76]))
p.set_val('traj.phase0.parameters:thrust', 2.1, units='MN')
#
# Solve the Problem
#
dm.run_problem(p)
assert_near_equal(p.get_val('traj.phase0.timeseries.time')[-1],
143,
tolerance=0.05)
assert_near_equal(
p.get_val('traj.phase0.timeseries.states:y')[-1], 1.85E5, 1e-4)
assert_near_equal(
p.get_val('traj.phase0.timeseries.states:vx')[-1], 7796.6961, 1e-4)
assert_near_equal(
p.get_val('traj.phase0.timeseries.states:vy')[-1], 0, 1e-4)
#
# Get the explicitly simulated results
#
exp_out = traj.simulate()
#
# Plot the results
#
fig, axes = plt.subplots(nrows=2, ncols=1, figsize=(10, 8))
axes[0].plot(p.get_val('traj.phase0.timeseries.states:x'),
p.get_val('traj.phase0.timeseries.states:y'),
marker='o',
ms=4,
linestyle='None',
label='solution')
axes[0].plot(exp_out.get_val('traj.phase0.timeseries.states:x'),
exp_out.get_val('traj.phase0.timeseries.states:y'),
marker=None,
linestyle='-',
label='simulation')
axes[0].set_xlabel('range (m)')
axes[0].set_ylabel('altitude (m)')
axes[0].set_aspect('equal')
axes[1].plot(p.get_val('traj.phase0.timeseries.time'),
p.get_val('traj.phase0.timeseries.controls:theta'),
marker='o',
ms=4,
linestyle='None')
axes[1].plot(exp_out.get_val('traj.phase0.timeseries.time'),
exp_out.get_val('traj.phase0.timeseries.controls:theta'),
linestyle='-',
marker=None)
axes[1].set_xlabel('time (s)')
axes[1].set_ylabel('theta (deg)')
plt.suptitle(
'Single Stage to Orbit Solution Using Linear Tangent Guidance')
fig.legend(loc='lower center', ncol=2)
plt.show()
def test_brachistochrone_external_control(self):
import numpy as np
import openmdao.api as om
import dymos as dm
from dymos.examples.brachistochrone.brachistochrone_ode import BrachistochroneODE
import matplotlib
matplotlib.use('Agg')
import matplotlib.pyplot as plt
#
# Define the OpenMDAO problem
#
p = om.Problem(model=om.Group())
# Instantiate the transcription so we can get the number of nodes from it while
# building the problem.
tx = dm.GaussLobatto(num_segments=10, order=3)
# Add an indep var comp to provide the external control values
ivc = p.model.add_subsystem('control_ivc', om.IndepVarComp(), promotes_outputs=['*'])
# Add the output to provide the values of theta at the control input nodes of the transcription.
ivc.add_output('theta', shape=(tx.grid_data.subset_num_nodes['control_input']), units='rad')
# Add this external control as a design variable
# Note the lower bound to avoid the singularity in the ODE when theta = 0
p.model.add_design_var('theta', units='rad', lower=1.0E-4, upper=np.pi)
# Connect this to controls:theta in the appropriate phase.
# connect calls are cached, so we can do this before we actually add the trajectory to the problem.
p.model.connect('theta', 'traj.phase0.controls:theta')
#
# Define a Trajectory object
#
traj = dm.Trajectory()
p.model.add_subsystem('traj', subsys=traj)
#
# Define a Dymos Phase object with GaussLobatto Transcription
#
phase = dm.Phase(ode_class=BrachistochroneODE,
transcription=tx)
traj.add_phase(name='phase0', phase=phase)
#
# Set the time options
# Time has no targets in our ODE.
# We fix the initial time so that the it is not a design variable in the optimization.
# The duration of the phase is allowed to be optimized, but is bounded on [0.5, 10].
#
phase.set_time_options(fix_initial=True, duration_bounds=(0.5, 10.0), units='s')
#
# Set the time options
# Initial values of positions and velocity are all fixed.
# The final value of position are fixed, but the final velocity is a free variable.
# The equations of motion are not functions of position, so 'x' and 'y' have no targets.
# The rate source points to the output in the ODE which provides the time derivative of the
# given state.
phase.add_state('x', fix_initial=True, fix_final=True, rate_source='xdot')
phase.add_state('y', fix_initial=True, fix_final=True, rate_source='ydot')
phase.add_state('v', fix_initial=True, fix_final=False, rate_source='vdot')
# Define theta as a control.
# Use opt=False to allow it to be connected to an external source.
# Arguments lower and upper are no longer valid for an input control.
phase.add_control(name='theta', units='rad', targets=['theta'], opt=False)
# Minimize final time.
phase.add_objective('time', loc='final')
# Set the driver.
p.driver = om.ScipyOptimizeDriver()
# Allow OpenMDAO to automatically determine our sparsity pattern.
# Doing so can significant speed up the execution of Dymos.
p.driver.declare_coloring()
# Setup the problem
p.setup(check=True)
# Now that the OpenMDAO problem is setup, we can set the values of the states.
p.set_val('traj.phase0.states:x',
phase.interpolate(ys=[0, 10], nodes='state_input'),
units='m')
p.set_val('traj.phase0.states:y',
phase.interpolate(ys=[10, 5], nodes='state_input'),
units='m')
p.set_val('traj.phase0.states:v',
phase.interpolate(ys=[0, 5], nodes='state_input'),
units='m/s')
p.set_val('traj.phase0.controls:theta',
phase.interpolate(ys=[90, 90], nodes='control_input'),
units='deg')
# Run the driver to solve the problem
p.run_driver()
# Check the validity of our results by using scipy.integrate.solve_ivp to
# integrate the solution.
sim_out = traj.simulate()
# Plot the results
fig, axes = plt.subplots(nrows=1, ncols=2, figsize=(12, 4.5))
axes[0].plot(p.get_val('traj.phase0.timeseries.states:x'),
p.get_val('traj.phase0.timeseries.states:y'),
'ro', label='solution')
axes[0].plot(sim_out.get_val('traj.phase0.timeseries.states:x'),
sim_out.get_val('traj.phase0.timeseries.states:y'),
'b-', label='simulation')
axes[0].set_xlabel('x (m)')
axes[0].set_ylabel('y (m/s)')
axes[0].legend()
axes[0].grid()
axes[1].plot(p.get_val('traj.phase0.timeseries.time'),
p.get_val('traj.phase0.timeseries.controls:theta', units='deg'),
'ro', label='solution')
axes[1].plot(sim_out.get_val('traj.phase0.timeseries.time'),
sim_out.get_val('traj.phase0.timeseries.controls:theta', units='deg'),
'b-', label='simulation')
axes[1].set_xlabel('time (s)')
axes[1].set_ylabel(r'$\theta$ (deg)')
axes[1].legend()
axes[1].grid()
plt.show()
def test_units_with_scaling(self):
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units='degF')
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_subsystem('comp2',
om.ExecComp('y2 = 3.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y2={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y2'])
model.add_design_var('x',
units='degC',
lower=0.0,
upper=100.0,
scaler=3.5,
adder=77.0)
model.add_constraint('y1',
units='degC',
lower=0.0,
upper=100.0,
scaler=3.5,
adder=77.0)
model.add_objective('y2', units='degC', scaler=3.5, adder=77.0)
recorder = om.SqliteRecorder('cases.sql')
prob.driver.add_recorder(recorder)
prob.driver.recording_options['record_objectives'] = True
prob.driver.recording_options['record_constraints'] = True
prob.driver.recording_options['record_desvars'] = True
prob.setup()
prob.run_driver()
dv = prob.driver.get_design_var_values()
assert_near_equal(dv['p.x'][0], ((3.0 * 5 / 9) + 77.0) * 3.5, 1e-8)
obj = prob.driver.get_objective_values(driver_scaling=True)
assert_near_equal(obj['comp2.y2'][0], ((73.0 * 5 / 9) + 77.0) * 3.5,
1e-8)
con = prob.driver.get_constraint_values(driver_scaling=True)
assert_near_equal(con['comp1.y1'][0], ((38.0 * 5 / 9) + 77.0) * 3.5,
1e-8)
meta = model.get_design_vars()
assert_near_equal(meta['p.x']['lower'], ((0.0) + 77.0) * 3.5, 1e-7)
assert_near_equal(meta['p.x']['upper'], ((100.0) + 77.0) * 3.5, 1e-7)
meta = model.get_constraints()
assert_near_equal(meta['comp1.y1']['lower'], ((0.0) + 77.0) * 3.5,
1e-7)
assert_near_equal(meta['comp1.y1']['upper'], ((100.0) + 77.0) * 3.5,
1e-7)
stdout = sys.stdout
strout = StringIO()
sys.stdout = strout
try:
prob.list_problem_vars(desvar_opts=['units'],
objs_opts=['units'],
cons_opts=['units'])
finally:
sys.stdout = stdout
output = strout.getvalue().split('\n')
self.assertTrue('275.33' in output[5])
self.assertTrue('343.3888' in output[12])
self.assertTrue('411.444' in output[19])
self.assertTrue('degC' in output[5])
self.assertTrue('degC' in output[12])
self.assertTrue('degC' in output[19])
totals = prob.check_totals(out_stream=None, driver_scaling=True)
for key, val in totals.items():
assert_near_equal(val['rel error'][0], 0.0, 1e-6)
cr = om.CaseReader("cases.sql")
cases = cr.list_cases('driver')
case = cr.get_case(cases[0])
dv = case.get_design_vars()
assert_near_equal(dv['p.x'][0], ((3.0 * 5 / 9) + 77.0) * 3.5, 1e-8)
obj = case.get_objectives()
assert_near_equal(obj['comp2.y2'][0], ((73.0 * 5 / 9) + 77.0) * 3.5,
1e-8)
con = case.get_constraints()
assert_near_equal(con['comp1.y1'][0], ((38.0 * 5 / 9) + 77.0) * 3.5,
1e-8)
def test_steady_aircraft_for_docs(self):
import matplotlib.pyplot as plt
import openmdao.api as om
from openmdao.utils.assert_utils import assert_near_equal
import dymos as dm
from dymos.examples.aircraft_steady_flight.aircraft_ode import AircraftODE
from dymos.examples.plotting import plot_results
from dymos.utils.lgl import lgl
p = om.Problem(model=om.Group())
p.driver = om.pyOptSparseDriver()
p.driver.options['optimizer'] = 'SLSQP'
p.driver.declare_coloring()
num_seg = 15
seg_ends, _ = lgl(num_seg + 1)
traj = p.model.add_subsystem('traj', dm.Trajectory())
phase = traj.add_phase(
'phase0',
dm.Phase(ode_class=AircraftODE,
transcription=dm.Radau(num_segments=num_seg,
segment_ends=seg_ends,
order=3,
compressed=False)))
# Pass Reference Area from an external source
assumptions = p.model.add_subsystem('assumptions', om.IndepVarComp())
assumptions.add_output('S', val=427.8, units='m**2')
assumptions.add_output('mass_empty', val=1.0, units='kg')
assumptions.add_output('mass_payload', val=1.0, units='kg')
phase.set_time_options(fix_initial=True,
duration_bounds=(300, 10000),
duration_ref=5600)
phase.add_state('range',
units='NM',
rate_source='range_rate_comp.dXdt:range',
fix_initial=True,
fix_final=False,
ref=1e-3,
defect_ref=1e-3,
lower=0,
upper=2000)
phase.add_state('mass_fuel',
units='lbm',
rate_source='propulsion.dXdt:mass_fuel',
fix_initial=True,
fix_final=True,
upper=1.5E5,
lower=0.0,
ref=1e2,
defect_ref=1e2)
phase.add_state('alt',
units='kft',
rate_source='climb_rate',
fix_initial=True,
fix_final=True,
lower=0.0,
upper=60,
ref=1e-3,
defect_ref=1e-3)
phase.add_control('climb_rate',
units='ft/min',
opt=True,
lower=-3000,
upper=3000,
targets=['gam_comp.climb_rate'],
rate_continuity=True,
rate2_continuity=False)
phase.add_control('mach',
targets=['tas_comp.mach', 'aero.mach'],
units=None,
opt=False)
phase.add_parameter(
'S',
targets=['aero.S', 'flight_equilibrium.S', 'propulsion.S'],
units='m**2')
phase.add_parameter('mass_empty',
targets=['mass_comp.mass_empty'],
units='kg')
phase.add_parameter('mass_payload',
targets=['mass_comp.mass_payload'],
units='kg')
phase.add_path_constraint('propulsion.tau', lower=0.01, upper=2.0)
p.model.connect('assumptions.S', 'traj.phase0.parameters:S')
p.model.connect('assumptions.mass_empty',
'traj.phase0.parameters:mass_empty')
p.model.connect('assumptions.mass_payload',
'traj.phase0.parameters:mass_payload')
phase.add_objective('range', loc='final', ref=-1.0e-4)
phase.add_timeseries_output('aero.CL')
phase.add_timeseries_output('aero.CD')
p.setup()
p['traj.phase0.t_initial'] = 0.0
p['traj.phase0.t_duration'] = 3600.0
p['traj.phase0.states:range'][:] = phase.interpolate(
ys=(0, 724.0), nodes='state_input')
p['traj.phase0.states:mass_fuel'][:] = phase.interpolate(
ys=(30000, 1e-3), nodes='state_input')
p['traj.phase0.states:alt'][:] = 10.0
p['traj.phase0.controls:mach'][:] = 0.8
p['assumptions.S'] = 427.8
p['assumptions.mass_empty'] = 0.15E6
p['assumptions.mass_payload'] = 84.02869 * 400
dm.run_problem(p)
assert_near_equal(p.get_val('traj.phase0.timeseries.states:range',
units='NM')[-1],
726.85,
tolerance=1.0E-2)
exp_out = traj.simulate()
assert_near_equal(p.get_val('traj.phase0.timeseries.CL')[0],
exp_out.get_val('traj.phase0.timeseries.CL')[0],
tolerance=1.0E-9)
assert_near_equal(p.get_val('traj.phase0.timeseries.CD')[0],
exp_out.get_val('traj.phase0.timeseries.CD')[0],
tolerance=1.0E-9)
plot_results(
[('traj.phase0.timeseries.states:range',
'traj.phase0.timeseries.states:alt', 'range (NM)',
'altitude (kft)'),
('traj.phase0.timeseries.time',
'traj.phase0.timeseries.states:mass_fuel', 'time (s)',
'fuel mass (lbm)'),
('traj.phase0.timeseries.time', 'traj.phase0.timeseries.CL',
'time (s)', 'lift coefficient'),
('traj.phase0.timeseries.time', 'traj.phase0.timeseries.CD',
'time (s)', 'drag coefficient')],
title='Commercial Aircraft Optimization',
p_sol=p,
p_sim=exp_out)
plt.show()
def test_units_error_messages(self):
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units='degF')
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_design_var('x',
units='ft',
lower=0.0,
upper=100.0,
scaler=3.5,
adder=77.0)
prob.setup()
with self.assertRaises(RuntimeError) as context:
prob.final_setup()
msg = "<model> <class Group>: Target for design variable x has 'degF' units, but 'ft' units were specified."
self.assertEqual(str(context.exception), msg)
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units='degF')
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_constraint('x', units='ft', lower=0.0, upper=100.0)
prob.setup()
with self.assertRaises(RuntimeError) as context:
prob.final_setup()
msg = "<model> <class Group>: Target for constraint x has 'degF' units, but 'ft' units were specified."
self.assertEqual(str(context.exception), msg)
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units=None)
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={'value': 2.0},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_design_var('x',
units='ft',
lower=0.0,
upper=100.0,
scaler=3.5,
adder=77.0)
prob.setup()
with self.assertRaises(RuntimeError) as context:
prob.final_setup()
msg = "<model> <class Group>: Target for design variable x has no units, but 'ft' units were specified."
self.assertEqual(str(context.exception), msg)
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units=None)
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={'value': 2.0},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_constraint('x', units='ft', lower=0.0, upper=100.0)
prob.setup()
with self.assertRaises(RuntimeError) as context:
prob.final_setup()
msg = "<model> <class Group>: Target for constraint x has no units, but 'ft' units were specified."
self.assertEqual(str(context.exception), msg)
def test_zero_shape(self):
raise unittest.SkipTest("zero shapes not fully supported yet")
class MultComp(ExplicitComponent):
def __init__(self, mult):
self.mult = mult
super().__init__()
def setup(self):
if self.comm.rank == 0:
self.add_input('x', shape=1)
self.add_output('y', shape=1)
else:
self.add_input('x', shape=0)
self.add_output('y', shape=0)
def compute(self, inputs, outputs):
outputs['y'] = inputs['x'] * self.mult
def compute_partials(self, inputs, partials):
partials['y', 'x'] = np.array([self.mult])
prob = om.Problem()
model = prob.model
model.add_subsystem('iv', om.IndepVarComp('x', 1.0))
model.add_subsystem('c1', MultComp(3.0))
model.sub = model.add_subsystem('sub', om.ParallelGroup())
model.sub.add_subsystem('c2', MultComp(-2.0))
model.sub.add_subsystem('c3', MultComp(5.0))
model.add_subsystem('c2', MultComp(1.0))
model.add_subsystem('c3', MultComp(1.0))
model.connect('iv.x', 'c1.x')
model.connect('c1.y', 'sub.c2.x')
model.connect('c1.y', 'sub.c3.x')
model.connect('sub.c2.y', 'c2.x')
model.connect('sub.c3.y', 'c3.x')
of = ['c2.y', "c3.y"]
wrt = ['iv.x']
prob.setup(check=False, mode='fwd')
prob.set_solver_print(level=0)
prob.run_model()
J = prob.compute_totals(of=['c2.y', "c3.y"], wrt=['iv.x'])
assert_near_equal(J['c2.y', 'iv.x'][0][0], -6.0, 1e-6)
assert_near_equal(J['c3.y', 'iv.x'][0][0], 15.0, 1e-6)
assert_near_equal(prob['c2.y'], -6.0, 1e-6)
assert_near_equal(prob['c3.y'], 15.0, 1e-6)
prob.setup(check=False, mode='rev')
prob.run_model()
J = prob.compute_totals(of=['c2.y', "c3.y"], wrt=['iv.x'])
assert_near_equal(J['c2.y', 'iv.x'][0][0], -6.0, 1e-6)
assert_near_equal(J['c3.y', 'iv.x'][0][0], 15.0, 1e-6)
assert_near_equal(prob['c2.y'], -6.0, 1e-6)
assert_near_equal(prob['c3.y'], 15.0, 1e-6)
def test_ccblade_twist(self):
"""
Right now this just compares fd to fd so it is not a meaningful test.
However, it ensures that we have the derivatives set up in the component
to actually be finite differenced.
"""
prob = om.Problem()
# Add some arbitrary inputs
# Load in airfoil and blade shape inputs for NREL 5MW
npzfile = np.load(os.path.dirname(os.path.abspath(__file__)) + os.path.sep + 'smaller_dataset.npz', allow_pickle=True)
n_span = npzfile['r'].size
n_aoa = npzfile['aoa'].size
n_Re = npzfile['Re'].size
modeling_options = {}
modeling_options['blade'] = {}
modeling_options['blade']['n_span'] = n_span
modeling_options['blade']['n_aoa'] = n_aoa
modeling_options['blade']['n_Re'] = n_Re
modeling_options['blade']['n_tab'] = 1
modeling_options['assembly'] = {}
modeling_options['assembly']['number_of_blades'] = 3
n_span, n_aoa, n_Re, n_tab = np.moveaxis(npzfile['cl'][:,:,:,np.newaxis], 0, 1).shape
modeling_options['airfoils'] = {}
modeling_options['airfoils']['n_aoa'] = n_aoa
modeling_options['airfoils']['n_Re'] = n_Re
modeling_options['airfoils']['n_tab'] = n_tab
opt_options = {}
opt_options['optimization_variables'] = {}
opt_options['optimization_variables']['blade'] = {}
opt_options['optimization_variables']['blade']['aero_shape'] = {}
opt_options['optimization_variables']['blade']['aero_shape']['chord'] = {}
opt_options['optimization_variables']['blade']['aero_shape']['chord']['n_opt'] = 8
opt_options['optimization_variables']['blade']['aero_shape']['twist'] = {}
opt_options['optimization_variables']['blade']['aero_shape']['twist']['n_opt'] = 8
opt_options['optimization_variables']['blade']['aero_shape']['twist']['inverse'] = False
opt_options['constraints'] = {}
opt_options['constraints']['blade'] = {}
opt_options['constraints']['blade']['stall'] = {}
opt_options['constraints']['blade']['stall']['margin'] = 0.05233
comp = CCBladeTwist(modeling_options=modeling_options, opt_options=opt_options)
prob.model.add_subsystem('comp', comp, promotes=['*'])
prob.setup(force_alloc_complex=True)
prob.set_val('airfoils_aoa', npzfile['aoa'], units='deg')
prob.set_val('airfoils_Re', npzfile['Re'])
prob.set_val('airfoils_cl', np.moveaxis(npzfile['cl'][:,:,:,np.newaxis], 0, 1))
prob.set_val('airfoils_cd', np.moveaxis(npzfile['cd'][:,:,:,np.newaxis], 0, 1))
prob.set_val('airfoils_cm', np.moveaxis(npzfile['cm'][:,:,:,np.newaxis], 0, 1))
prob.set_val('r', npzfile['r'], units='m')
prob.set_val('chord', npzfile['chord'], units='m')
prob.set_val('Rhub', 1., units='m')
prob.set_val('Rtip', 70., units='m')
prob.set_val('hub_height', 100., units='m')
prob.set_val('precone', 0., units='deg')
prob.set_val('tilt', 0., units='deg')
prob.set_val('yaw', 0., units='deg')
prob.set_val('precurve', np.zeros(n_span), units='m')
prob.set_val('precurveTip', 0., units='m')
prob.set_val('rho', 1.225, units='kg/m**3')
prob.set_val('mu', 1.81206e-5, units='kg/(m*s)')
prob.set_val('shearExp', 0.25)
prob.set_val('nBlades', 3)
prob.set_val('nSector', 4)
prob.set_val('tiploss', True)
prob.set_val('hubloss', True)
prob.set_val('wakerotation', True)
prob.set_val('usecd', True)
prob.run_model()
check = prob.check_partials(out_stream=None, compact_print=True)
# Manually filter some entries out of the assert_check_partials call.
# Will want to add this functionality to OpenMDAO itself at some point.
new_check = {}
for comp_name in check:
new_check[comp_name] = {}
for (output_name, input_name) in check[comp_name]:
if 'airfoil' not in input_name and 'rho' not in input_name and 'mu' not in input_name and 'shearExp' not in input_name:
new_check[comp_name][(output_name, input_name)] = check[comp_name][(output_name, input_name)]
assert_check_partials(new_check) #, rtol=5e-5, atol=1e-4)
def _make_tree_model():
p = om.Problem()
model = p.model
units1 = units2 = 'ft'
val = 1.0
g1 = model.add_subsystem("G1", om.Group(), promotes_inputs=['x'])
g2 = g1.add_subsystem("G2", om.Group(), promotes_inputs=['x'])
g2.add_subsystem("C1",
om.ExecComp("y = 2. * x",
x={
'val': val,
'units': units2
},
y={
'val': 1.0,
'units': units2
}),
promotes_inputs=['x'])
g2.add_subsystem("C2",
om.ExecComp("y = 3. * x",
x={
'val': val,
'units': units1
},
y={
'val': 1.0,
'units': units1
}),
promotes_inputs=['x'])
g3 = model.add_subsystem("G3", om.Group(), promotes_inputs=['x'])
g3.add_subsystem("C3",
om.ExecComp("y = 4. * x",
x={
'val': val,
'units': units1
},
y={
'val': 1.0,
'units': units1
}),
promotes_inputs=['x'])
g3.add_subsystem("C4",
om.ExecComp("y = 5. * x",
x={
'val': val,
'units': units2
},
y={
'val': 1.0,
'units': units2
}),
promotes_inputs=['x'])
par = model.add_subsystem("par", om.ParallelGroup(), promotes_inputs=['x'])
g4 = par.add_subsystem("G4", om.Group(), promotes_inputs=['x'])
g4.add_subsystem("C5",
om.ExecComp("y = 6. * x",
x={
'val': val,
'units': units2
},
y={
'val': 1.0,
'units': units2
}),
promotes_inputs=['x'])
g4.add_subsystem("C6",
om.ExecComp("y = 7. * x",
x={
'val': val,
'units': units1
},
y={
'val': 1.0,
'units': units1
}),
promotes_inputs=['x'])
g5 = par.add_subsystem("G5", om.Group(), promotes_inputs=['x'])
g5.add_subsystem("C7",
om.ExecComp("y = 8. * x",
x={
'val': val,
'units': units1
},
y={
'val': 1.0,
'units': units1
}),
promotes_inputs=['x'])
g5.add_subsystem("C8",
om.ExecComp("y = 9. * x",
x={
'val': val,
'units': units2
},
y={
'val': 1.0,
'units': units2
}),
promotes_inputs=['x'])
model.add_subsystem("C9",
om.ExecComp("y = 10. * x",
x={
'val': val,
'units': units2
},
y={
'val': 1.0,
'units': units2
}),
promotes_inputs=['x'])
return p
def test_length_constrained_brachistochrone(self):
import openmdao.api as om
import dymos as dm
import matplotlib.pyplot as plt
from dymos.examples.brachistochrone.brachistochrone_ode import BrachistochroneODE
from dymos.examples.length_constrained_brachistochrone.arc_length_comp import ArcLengthComp
MAX_ARCLENGTH = 11.9
OPTIMIZER = 'SLSQP'
p = om.Problem(model=om.Group())
p.add_recorder(om.SqliteRecorder('length_constrained_brach_sol.db'))
if OPTIMIZER == 'SNOPT':
p.driver = om.pyOptSparseDriver()
p.driver.options['optimizer'] = OPTIMIZER
p.driver.opt_settings['Major iterations limit'] = 1000
p.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6
p.driver.opt_settings['Major optimality tolerance'] = 1.0E-5
p.driver.opt_settings['iSumm'] = 6
p.driver.opt_settings['Verify level'] = 3
else:
p.driver = om.ScipyOptimizeDriver()
p.driver.declare_coloring()
# Create the transcription so we can get the number of nodes for the downstream analysis
tx = dm.Radau(num_segments=20, order=3, compressed=False)
traj = dm.Trajectory()
phase = dm.Phase(transcription=tx, ode_class=BrachistochroneODE)
traj.add_phase('phase0', phase)
p.model.add_subsystem('traj', traj)
phase.set_time_options(fix_initial=True, duration_bounds=(.5, 10))
phase.add_state('x', units='m', rate_source='xdot', fix_initial=True, fix_final=True)
phase.add_state('y', units='m', rate_source='ydot', fix_initial=True, fix_final=True)
phase.add_state('v', units='m/s', rate_source='vdot', fix_initial=True, fix_final=False)
phase.add_control('theta', units='deg', lower=0.01, upper=179.9,
continuity=True, rate_continuity=True)
phase.add_parameter('g', units='m/s**2', opt=False, val=9.80665)
# Minimize time at the end of the phase
phase.add_objective('time', loc='final', scaler=1)
# p.model.options['assembled_jac_type'] = top_level_jacobian.lower()
# p.model.linear_solver = DirectSolver(assemble_jac=True)
# Add the arc length component
p.model.add_subsystem('arc_length_comp',
subsys=ArcLengthComp(num_nodes=tx.grid_data.num_nodes))
p.model.connect('traj.phase0.timeseries.controls:theta', 'arc_length_comp.theta')
p.model.connect('traj.phase0.timeseries.states:x', 'arc_length_comp.x')
p.model.add_constraint('arc_length_comp.S', upper=MAX_ARCLENGTH, ref=1)
p.setup(check=True)
p.set_val('traj.phase0.t_initial', 0.0)
p.set_val('traj.phase0.t_duration', 2.0)
p.set_val('traj.phase0.states:x', phase.interpolate(ys=[0, 10], nodes='state_input'))
p.set_val('traj.phase0.states:y', phase.interpolate(ys=[10, 5], nodes='state_input'))
p.set_val('traj.phase0.states:v', phase.interpolate(ys=[0, 9.9], nodes='state_input'))
p.set_val('traj.phase0.controls:theta', phase.interpolate(ys=[5, 100], nodes='control_input'))
p.set_val('traj.phase0.parameters:g', 9.80665)
p.run_driver()
p.record(case_name='final')
# Plot results
if SHOW_PLOTS:
# Generate the explicitly simulated trajectory
exp_out = traj.simulate()
# Extract the timeseries from the implicit solution and the explicit simulation
x = p.get_val('traj.phase0.timeseries.states:x')
y = p.get_val('traj.phase0.timeseries.states:y')
t = p.get_val('traj.phase0.timeseries.time')
theta = p.get_val('traj.phase0.timeseries.controls:theta')
x_exp = exp_out.get_val('traj.phase0.timeseries.states:x')
y_exp = exp_out.get_val('traj.phase0.timeseries.states:y')
t_exp = exp_out.get_val('traj.phase0.timeseries.time')
theta_exp = exp_out.get_val('traj.phase0.timeseries.controls:theta')
fig, axes = plt.subplots(nrows=2, ncols=1)
axes[0].plot(x, y, 'o')
axes[0].plot(x_exp, y_exp, '-')
axes[0].set_xlabel('x (m)')
axes[0].set_ylabel('y (m)')
axes[1].plot(t, theta, 'o')
axes[1].plot(t_exp, theta_exp, '-')
axes[1].set_xlabel('time (s)')
axes[1].set_ylabel(r'$\theta$ (deg)')
plt.show()
return p
def run_opt(layout_number, wec_method_number, wake_model, opt_alg_number,
max_wec, nsteps):
OPENMDAO_REQUIRE_MPI = False
run_number = layout_number
model = wake_model
# set model
MODELS = ['FLORIS', 'BPA', 'JENSEN', 'LARSEN']
print(MODELS[model])
# select optimization approach/method
opt_algs = ['snopt', 'ga', 'ps']
opt_algorithm = opt_algs[opt_alg_number]
# select wec method
wec_methods = ['none', 'diam', 'angle', 'hybrid']
wec_method = wec_methods[wec_method_number]
# pop_size = 760
# save and show options
show_start = False
show_end = False
save_start = False
save_end = False
save_locations = True
save_aep = True
save_time = True
rec_func_calls = True
input_directory = "../../../input_files/"
# set options for BPA
print_ti = False
sort_turbs = True
# turbine_type = 'NREL5MW' #can be 'V80' or 'NREL5MW'
turbine_type = 'V80' # can be 'V80' or 'NREL5MW'
wake_model_version = 2016
WECH = 0
if wec_method == 'diam':
output_directory = "../output_files/%s_wec_diam_max_wec_%i_nsteps_%.3f/" % (
opt_algorithm, max_wec, nsteps)
relax = True
# expansion_factors = np.array([3, 2.75, 2.5, 2.25, 2.0, 1.75, 1.5, 1.25, 1.0, 1.0])
expansion_factors = np.linspace(1.0, max_wec, nsteps)
expansion_factors = np.append(np.flip(expansion_factors), 1.0)
conv_tols = np.array([9E-3, 9E-3, 9E-3, 9E-3, 9E-3, 9E-3, 1E-3])
elif wec_method == 'angle':
output_directory = "../output_files/%s_wec_angle_max_wec_%i_nsteps_%.3f/" % (
opt_algorithm, max_wec, nsteps)
relax = True
# expansion_factors = np.array([50, 40, 30, 20, 10, 0.0, 0.0])
expansion_factors = np.linspace(0.0, max_wec, nsteps)
expansion_factors = np.append(np.flip(expansion_factors), 0.0)
elif wec_method == 'hybrid':
expansion_factors = np.linspace(1.0, max_wec, nsteps)
expansion_factors = np.append(np.flip(expansion_factors), 1.0)
output_directory = "../output_files/%s_wec_hybrid_max_wec_%i_nsteps_%.3f/" % (
opt_algorithm, max_wec, nsteps)
relax = True
WECH = 1
elif wec_method == 'none':
relax = False
if opt_algorithm == "ps":
expansion_factors = np.array([1.0])
conv_tols = np.array([1E-4])
else:
expansion_factors = np.array([1.0, 1.0])
conv_tols = np.array([9E-3, 1E-3])
output_directory = "../output_files/%s/" % opt_algorithm
else:
raise ValueError('wec_method must be diam, angle, hybrid, or none')
# create output directory if it does not exist yet
import distutils.dir_util
distutils.dir_util.mkpath(output_directory)
differentiable = True
# for expansion_factor in np.array([5., 4., 3., 2.75, 2.5, 2.25, 2.0, 1.75, 1.5, 1.25, 1.0]):
# for expansion_factor in np.array([20., 15., 10., 5., 4., 3., 2.5, 1.25, 1.0]):
# expansion_factors = np.array([20., 10., 5., 2.5, 1.25, 1.0])
wake_combination_method = 1 # can be [0:Linear freestreem superposition,
# 1:Linear upstream velocity superposition,
# 2:Sum of squares freestream superposition,
# 3:Sum of squares upstream velocity superposition]
ti_calculation_method = 4 # can be [0:No added TI calculations,
# 1:TI by Niayifar and Porte Agel altered by Annoni and Thomas,
# 2:TI by Niayifar and Porte Agel 2016,
# 3:TI by Niayifar and Porte Agel 2016 with added soft max function,
# 4:TI by Niayifar and Porte Agel 2016 using area overlap ratio,
# 5:TI by Niayifar and Porte Agel 2016 using area overlap ratio and SM function]
if wec_method_number > 0:
ti_opt_method = 0 # can be [0:No added TI calculations,
# 1:TI by Niayifar and Porte Agel altered by Annoni and Thomas,
# 2:TI by Niayifar and Porte Agel 2016,
# 3:TI by Niayifar and Porte Agel 2016 with added soft max function,
# 4:TI by Niayifar and Porte Agel 2016 using area overlap ratio,
# 5:TI by Niayifar and Porte Agel 2016 using area overlap ratio and SM function]
else:
ti_opt_method = 0
final_ti_opt_method = 5
if opt_algorithm == 'ps':
ti_opt_method = ti_calculation_method
sm_smoothing = 700.
if ti_calculation_method == 0:
calc_k_star_calc = False
else:
calc_k_star_calc = True
if ti_opt_method == 0:
calc_k_star_opt = False
else:
calc_k_star_opt = True
nRotorPoints = 1
wind_rose_file = 'nantucket' # can be one of: 'amalia', 'nantucket', 'directional
TI = 0.108
k_calc = 0.3837 * TI + 0.003678
# k_calc = 0.022
# k_opt = 0.04
shear_exp = 0.31
# air_density = 1.1716 # kg/m^3
air_density = 1.225 # kg/m^3 (from Jen)
if turbine_type == 'V80':
# define turbine size
rotor_diameter = 80. # (m)
hub_height = 70.0
z_ref = 80.0 # m
z_0 = 0.0
# load performance characteristics
cut_in_speed = 4. # m/s
cut_out_speed = 25. # m/s
rated_wind_speed = 16. # m/s
rated_power = 2000. # kW
generator_efficiency = 0.944
ct_curve_data = np.loadtxt(input_directory +
'mfg_ct_vestas_v80_niayifar2016.txt',
delimiter=",")
ct_curve_wind_speed = ct_curve_data[:, 0]
ct_curve_ct = ct_curve_data[:, 1]
# air_density = 1.1716 # kg/m^3
Ar = 0.25 * np.pi * rotor_diameter**2
# cp_curve_wind_speed = ct_curve[:, 0]
power_data = np.loadtxt(input_directory +
'niayifar_vestas_v80_power_curve_observed.txt',
delimiter=',')
# cp_curve_cp = niayifar_power_model(cp_curve_wind_speed)/(0.5*air_density*cp_curve_wind_speed**3*Ar)
cp_curve_cp = power_data[:, 1] * (1E6) / (0.5 * air_density *
power_data[:, 0]**3 * Ar)
cp_curve_wind_speed = power_data[:, 0]
cp_curve_spline = UnivariateSpline(cp_curve_wind_speed,
cp_curve_cp,
ext='const')
cp_curve_spline.set_smoothing_factor(.0001)
elif turbine_type == 'NREL5MW':
# define turbine size
rotor_diameter = 126.4 # (m)
hub_height = 90.0
z_ref = 80.0 # m
z_0 = 0.0
# load performance characteristics
cut_in_speed = 3. # m/s
cut_out_speed = 25. # m/s
rated_wind_speed = 11.4 # m/s
rated_power = 5000. # kW
generator_efficiency = 0.944
filename = input_directory + "NREL5MWCPCT_dict.p"
# filename = "../input_files/NREL5MWCPCT_smooth_dict.p"
import pickle
data = pickle.load(open(filename, "rb"), encoding='latin1')
ct_curve = np.zeros([data['wind_speed'].size, 2])
ct_curve_wind_speed = data['wind_speed']
ct_curve_ct = data['CT']
# cp_curve_cp = data['CP']
# cp_curve_wind_speed = data['wind_speed']
loc0 = np.where(data['wind_speed'] < 11.55)
loc1 = np.where(data['wind_speed'] > 11.7)
cp_curve_cp = np.hstack([data['CP'][loc0], data['CP'][loc1]])
cp_curve_wind_speed = np.hstack(
[data['wind_speed'][loc0], data['wind_speed'][loc1]])
cp_curve_spline = UnivariateSpline(cp_curve_wind_speed,
cp_curve_cp,
ext='const')
cp_curve_spline.set_smoothing_factor(.000001)
else:
raise ValueError("Turbine type is undefined.")
# load starting locations
layout_directory = input_directory
layout_data = np.loadtxt(
layout_directory +
"layouts/round_38turbs/nTurbs38_spacing5_layout_%i.txt" %
layout_number)
# layout_data = np.loadtxt(layout_directory + "layouts/grid_16turbs/nTurbs16_spacing5_layout_%i.txt" % layout_number)
# layout_data = np.loadtxt(layout_directory+"layouts/nTurbs9_spacing5_layout_%i.txt" % layout_number)
turbineX = layout_data[:, 0] * rotor_diameter + rotor_diameter / 2.
turbineY = layout_data[:, 1] * rotor_diameter + rotor_diameter / 2.
turbineX_init = np.copy(turbineX)
turbineY_init = np.copy(turbineY)
nTurbines = turbineX.size
# create boundary specifications
boundary_radius = 0.5 * (rotor_diameter * 4000. / 126.4 - rotor_diameter
) # 1936.8
center = np.array([boundary_radius, boundary_radius]) + rotor_diameter / 2.
start_min_spacing = 5.
nVertices = 1
boundary_center_x = center[0]
boundary_center_y = center[1]
xmax = np.max(turbineX)
ymax = np.max(turbineY)
xmin = np.min(turbineX)
ymin = np.min(turbineY)
boundary_radius_plot = boundary_radius + 0.5 * rotor_diameter
plot_round_farm(turbineX,
turbineY,
rotor_diameter, [boundary_center_x, boundary_center_y],
boundary_radius,
show_start=show_start)
# quit()
# initialize input variable arrays
nTurbs = nTurbines
rotorDiameter = np.zeros(nTurbs)
hubHeight = np.zeros(nTurbs)
axialInduction = np.zeros(nTurbs)
Ct = np.zeros(nTurbs)
Cp = np.zeros(nTurbs)
generatorEfficiency = np.zeros(nTurbs)
yaw = np.zeros(nTurbs)
minSpacing = 2. # number of rotor diameters
# define initial values
for turbI in range(0, nTurbs):
rotorDiameter[turbI] = rotor_diameter # m
hubHeight[turbI] = hub_height # m
axialInduction[turbI] = 1.0 / 3.0
Ct[turbI] = 4.0 * axialInduction[turbI] * (1.0 - axialInduction[turbI])
# print(Ct)
Cp[turbI] = 4.0 * 1.0 / 3.0 * np.power((1 - 1.0 / 3.0), 2)
generatorEfficiency[turbI] = generator_efficiency
yaw[turbI] = 0. # deg.
# Define flow properties
if wind_rose_file == 'nantucket':
windRose = np.loadtxt(input_directory +
'nantucket_windrose_ave_speeds.txt')
# windRose = np.loadtxt(input_directory + 'nantucket_wind_rose_for_LES.txt')
windDirections = windRose[:, 0]
windSpeeds = windRose[:, 1]
windFrequencies = windRose[:, 2]
size = np.size(windDirections)
elif wind_rose_file == 'amalia':
windRose = np.loadtxt(
input_directory +
'windrose_amalia_directionally_averaged_speeds.txt')
windDirections = windRose[:, 0]
windSpeeds = windRose[:, 1]
windFrequencies = windRose[:, 2]
size = np.size(windDirections)
elif wind_rose_file == 'directional':
windRose = np.loadtxt(input_directory + 'directional_windrose.txt')
windDirections = windRose[:, 0]
windSpeeds = windRose[:, 1]
windFrequencies = windRose[:, 2]
size = np.size(windDirections)
elif wind_rose_file == '1d':
windDirections = np.array([270.])
windSpeeds = np.array([8.0])
windFrequencies = np.array([1.0])
size = np.size(windDirections)
else:
size = 20
windDirections = np.linspace(0, 270, size)
windFrequencies = np.ones(size) / size
wake_model_options = {
'nSamples': 0,
'nRotorPoints': nRotorPoints,
'use_ct_curve': True,
'ct_curve_ct': ct_curve_ct,
'ct_curve_wind_speed': ct_curve_wind_speed,
'interp_type': 1,
'use_rotor_components': False,
'differentiable': differentiable,
'verbose': False
}
if MODELS[model] == 'BPA':
# initialize problem
prob = om.Problem(
model=OptAEP(nTurbines=nTurbs,
nDirections=windDirections.size,
nVertices=nVertices,
minSpacing=minSpacing,
differentiable=differentiable,
use_rotor_components=False,
wake_model=gauss_wrapper,
params_IdepVar_func=add_gauss_params_IndepVarComps,
params_IdepVar_args={'nRotorPoints': nRotorPoints},
wake_model_options=wake_model_options,
cp_points=cp_curve_cp.size,
cp_curve_spline=cp_curve_spline,
record_function_calls=True,
runparallel=False))
elif MODELS[model] == 'FLORIS':
# initialize problem
prob = om.Problem(
model=OptAEP(nTurbines=nTurbs,
nDirections=windDirections.size,
nVertices=nVertices,
minSpacing=minSpacing,
differentiable=differentiable,
use_rotor_components=False,
wake_model=floris_wrapper,
params_IdepVar_func=add_floris_params_IndepVarComps,
params_IdepVar_args={},
record_function_calls=True))
# elif MODELS[model] == 'JENSEN':
# initialize problem
# prob = om.Problem(model=OptAEP(nTurbines=nTurbs, nDirections=windDirections.size, nVertices=nVertices,
# minSpacing=minSpacing, differentiable=False, use_rotor_components=False,
# wake_model=jensen_wrapper,
# params_IdepVar_func=add_jensen_params_IndepVarComps,
# params_IdepVar_args={},
# record_function_calls=True))
else:
ValueError(
'The %s model is not currently available. Please select BPA or FLORIS'
% (MODELS[model]))
# prob.model.deriv_options['type'] = 'fd'
# prob.model.deriv_options['form'] = 'central'
# prob.model.deriv_options['step_size'] = 1.0e-8
# prob.model.linear_solver = om.LinearBlockGS()
# prob.model.linear_solver.options['iprint'] = 0
# prob.model.linear_solver.options['maxiter'] = 5
#
# prob.model.nonlinear_solver = om.NonlinearBlockGS()
# prob.model.nonlinear_solver.options['iprint'] = 0
# prob.model.linear_solver = om.DirectSolver()
prob.driver = om.pyOptSparseDriver()
if opt_algorithm == 'snopt':
# set up optimizer
prob.driver.options['optimizer'] = 'SNOPT'
# prob.driver.options['gradient method'] = 'snopt_fd'
# set optimizer options
prob.driver.opt_settings['Verify level'] = -1
# set optimizer options
prob.driver.opt_settings['Major optimality tolerance'] = np.float(1e-3)
prob.driver.opt_settings[
'Print file'] = output_directory + 'SNOPT_print_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number)
prob.driver.opt_settings[
'Summary file'] = output_directory + 'SNOPT_summary_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number)
prob.model.add_constraint('sc',
lower=np.zeros(
int(((nTurbs - 1.) * nTurbs / 2.))),
scaler=1E-4) # ,
# active_tol=(2. * rotor_diameter) ** 2)
prob.model.add_constraint('boundaryDistances',
lower=(np.zeros(1 * turbineX.size)),
scaler=1E-4) # ,
# active_tol=2. * rotor_diameter)
prob.driver.options['dynamic_derivs_sparsity'] = True
elif opt_algorithm == 'ga':
prob.driver.options['optimizer'] = 'NSGA2'
prob.driver.opt_settings['PrintOut'] = 1
prob.driver.opt_settings['maxGen'] = 50000
prob.driver.opt_settings['PopSize'] = 10 * nTurbines * 2
# prob.driver.opt_settings['pMut_real'] = 0.001
prob.driver.opt_settings['xinit'] = 1
prob.driver.opt_settings['rtol'] = 1E-4
prob.driver.opt_settings['atol'] = 1E-4
prob.driver.opt_settings['min_tol_gens'] = 200
prob.driver.opt_settings['file_number'] = run_number
prob.model.add_constraint('sc',
lower=np.zeros(
int(((nTurbs - 1.) * nTurbs / 2.))),
scaler=1E-4)
prob.model.add_constraint('boundaryDistances',
lower=(np.zeros(1 * turbineX.size)),
scaler=1E-4)
elif opt_algorithm == 'ps':
prob.driver.options['optimizer'] = 'ALPSO'
prob.driver.opt_settings['fileout'] = 1
prob.driver.opt_settings[
'filename'] = output_directory + 'ALPSO_summary_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number)
prob.driver.opt_settings['maxOuterIter'] = 10000
prob.driver.opt_settings['SwarmSize'] = 25
prob.driver.opt_settings[
'xinit'] = 1 # Initial Position Flag (0 - no position, 1 - position given)
prob.driver.opt_settings[
'Scaling'] = 1 # Design Variables Scaling Flag (0 - no scaling, 1 - scaling between [-1, 1])
# prob.driver.opt_settings['rtol'] = 1E-3 # Relative Tolerance for Lagrange Multipliers
#
# prob.driver.opt_settings['atol'] = 1E-2 # Absolute Tolerance for Lagrange Function
#
prob.driver.opt_settings[
'dtol'] = 0.01 # Relative Tolerance in Distance of All Particles to Terminate (GCPSO)
#
# prob.driver.opt_settings['itol'] = 1E-3 # Absolute Tolerance for Inequality constraints
#
# prob.driver.opt_settings['dynInnerIter'] = 1 # Dynamic Number of Inner Iterations Flag
prob.model.add_constraint('sc',
lower=np.zeros(
int(((nTurbs - 1.) * nTurbs / 2.))),
scaler=1E-4)
prob.model.add_constraint('boundaryDistances',
lower=(np.zeros(1 * turbineX.size)),
scaler=1E-4)
# prob.driver.add_objective('obj', scaler=1E0)
prob.model.add_objective('obj', scaler=1E-4)
# select design variables
prob.model.add_design_var('turbineX',
scaler=1E0,
lower=np.zeros(nTurbines),
upper=np.ones(nTurbines) * 3. * boundary_radius)
prob.model.add_design_var('turbineY',
scaler=1E0,
lower=np.zeros(nTurbines),
upper=np.ones(nTurbines) * 3. * boundary_radius)
# prob.model.ln_solver.options['single_voi_relevance_reduction'] = True
# prob.model.ln_solver.options['mode'] = 'rev'
# if run_number == 0:
# # set up recorder
# recorder = SqliteRecorder(output_directory+'recorder_database_run%i' % run_number)
# recorder.options['record_params'] = True
# recorder.options['record_metadata'] = False
# recorder.options['record_unknowns'] = True
# recorder.options['record_derivs'] = False
# recorder.options['includes'] = ['turbineX', 'turbineY', 'AEP']
# prob.driver.add_recorder(recorder)
driver_recorder = om.SqliteRecorder(output_directory +
'recorded_data_driver_%s.sql' %
(run_number))
# model_recorder = om.SqliteRecorder(output_directory + 'recorded_data_model_%s.sql' %(run_number))
prob.driver.add_recorder(driver_recorder)
# prob.model.add_recorder(model_recorder)
prob.driver.recording_options['record_constraints'] = False
prob.driver.recording_options['record_derivatives'] = False
prob.driver.recording_options['record_desvars'] = True
prob.driver.recording_options['record_inputs'] = False
prob.driver.recording_options['record_model_metadata'] = True
prob.driver.recording_options['record_objectives'] = True
prob.driver.recording_options['includes'] = ['AEP']
prob.driver.recording_options['record_responses'] = False
#
# prob_recorder = om.SqliteRecorder(output_directory + 'recorded_data_prob_%s.sql' %(run_number))
# prob.add_recorder(prob_recorder)
# prob.recording_options['includes'] = []
# prob.recording_options['record_objectives'] = True
# set up profiling
# from plantenergy.GeneralWindFarmComponents import WindFarmAEP
# methods = [
# ('*', (WindFarmAEP,))
# ]
#
# iprofile.setup(methods=methods)
print("almost time for setup")
tic = time.time()
print("entering setup at time = ", tic)
prob.setup(check=True)
toc = time.time()
print("setup complete at time = ", toc)
# print the results
print(('Problem setup took %.03f sec.' % (toc - tic)))
# assign initial values to design variables
prob['turbineX'] = np.copy(turbineX)
prob['turbineY'] = np.copy(turbineY)
for direction_id in range(0, windDirections.size):
prob['yaw%i' % direction_id] = yaw
# assign values to constant inputs (not design variables)
prob['rotorDiameter'] = rotorDiameter
prob['hubHeight'] = hubHeight
prob['axialInduction'] = axialInduction
prob['generatorEfficiency'] = generatorEfficiency
prob['windSpeeds'] = windSpeeds
prob['air_density'] = air_density
prob['windDirections'] = windDirections
prob['windFrequencies'] = windFrequencies
prob['Ct_in'] = Ct
prob['Cp_in'] = Cp
prob['cp_curve_cp'] = cp_curve_cp
prob['cp_curve_wind_speed'] = cp_curve_wind_speed
cutInSpeeds = np.ones(nTurbines) * cut_in_speed
prob['cut_in_speed'] = cutInSpeeds
ratedPowers = np.ones(nTurbines) * rated_power
prob['rated_power'] = ratedPowers
# assign values to turbine states
prob['cut_in_speed'] = np.ones(nTurbines) * cut_in_speed
prob['cut_out_speed'] = np.ones(nTurbines) * cut_out_speed
prob['rated_power'] = np.ones(nTurbines) * rated_power
prob['rated_wind_speed'] = np.ones(nTurbines) * rated_wind_speed
prob['use_power_curve_definition'] = True
# assign boundary values
prob['boundary_center'] = np.array([boundary_center_x, boundary_center_y])
prob['boundary_radius'] = boundary_radius
if MODELS[model] == 'BPA':
prob['model_params:wake_combination_method'] = np.copy(
wake_combination_method)
prob['model_params:ti_calculation_method'] = np.copy(
ti_calculation_method)
prob['model_params:wake_model_version'] = np.copy(wake_model_version)
prob['model_params:wec_factor'] = 1.0
prob['model_params:wec_spreading_angle'] = 0.0
prob['model_params:calc_k_star'] = np.copy(calc_k_star_calc)
prob['model_params:sort'] = np.copy(sort_turbs)
prob['model_params:z_ref'] = np.copy(z_ref)
prob['model_params:z_0'] = np.copy(z_0)
prob['model_params:ky'] = np.copy(k_calc)
prob['model_params:kz'] = np.copy(k_calc)
prob['model_params:print_ti'] = np.copy(print_ti)
prob['model_params:shear_exp'] = np.copy(shear_exp)
prob['model_params:I'] = np.copy(TI)
prob['model_params:sm_smoothing'] = np.copy(sm_smoothing)
prob['model_params:WECH'] = WECH
if nRotorPoints > 1:
prob['model_params:RotorPointsY'], prob[
'model_params:RotorPointsZ'] = sunflower_points(nRotorPoints)
modelruns = 0
prob.run_model(case_prefix='ModelRun%i' % modelruns)
AEP_init_calc = np.copy(prob['AEP'])
print(AEP_init_calc * 1E-6)
if MODELS[model] == 'BPA':
prob['model_params:ti_calculation_method'] = np.copy(ti_opt_method)
prob['model_params:calc_k_star'] = np.copy(calc_k_star_opt)
modelruns += 1
prob.run_model(case_prefix='ModelRun%i' % modelruns)
AEP_init_opt = np.copy(prob['AEP'])
AEP_run_opt = np.copy(AEP_init_opt)
print(AEP_init_opt * 1E-6)
config.obj_func_calls_array[:] = 0.0
config.sens_func_calls_array[:] = 0.0
expansion_factor_last = 0.0
driverruns = 0
tict = time.time()
if relax:
for expansion_factor, i in zip(
expansion_factors,
np.arange(0, expansion_factors.size)): # best so far
# print("func calls: ", config.obj_func_calls_array, np.sum(config.obj_func_calls_array))
# print("grad func calls: ", config.sens_func_calls_array, np.sum(config.sens_func_calls_array))
# AEP_init_run_opt = prob['AEP']
if expansion_factor_last == expansion_factor:
ti_opt_method = np.copy(final_ti_opt_method)
calc_k_star_opt = True
print("starting run with exp. fac = ", expansion_factor)
if opt_algorithm == 'snopt':
prob.driver.opt_settings['Major optimality tolerance'] = float(
conv_tols[i])
prob.driver.opt_settings['Print file'] = output_directory + \
'SNOPT_print_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i_EF%.3f_TItype%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number,
expansion_factor, ti_opt_method)
prob.driver.opt_settings['Summary file'] = output_directory + \
'SNOPT_summary_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i_EF%.3f_TItype%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number,
expansion_factor, ti_opt_method)
elif opt_algorithm == 'ps':
prob.driver.opt_settings[
'filename'] = output_directory + 'ALPSO_summary_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model],
run_number)
turbineX = np.copy(prob['turbineX'])
turbineY = np.copy(prob['turbineY'])
prob['turbineX'] = np.copy(turbineX)
prob['turbineY'] = np.copy(turbineY)
if MODELS[model] == 'BPA':
prob['model_params:ti_calculation_method'] = np.copy(
ti_opt_method)
prob['model_params:calc_k_star'] = np.copy(calc_k_star_opt)
if wec_method == 'diam':
prob['model_params:wec_factor'] = np.copy(expansion_factor)
elif wec_method == "hybrid":
prob['model_params:wec_factor'] = np.copy(expansion_factor)
elif wec_method == 'angle':
prob['model_params:wec_spreading_angle'] = np.copy(
expansion_factor)
# run the problem
print('start %s run' % (MODELS[model]))
tic = time.time()
# iprofile.start()
config.obj_func_calls_array[prob.comm.rank] = 0.0
config.sens_func_calls_array[prob.comm.rank] = 0.0
prob.run_driver(case_prefix='DriverRun%i' % driverruns)
driverruns += 1
# quit()
toc = time.time()
obj_calls = np.copy(config.obj_func_calls_array[0])
sens_calls = np.copy(config.sens_func_calls_array[0])
# iprofile.stop()
toc = time.time()
# print(np.sum(config.obj_func_calls_array))
# print(np.sum(config.sens_func_calls_array))
print('end %s run' % (MODELS[model]))
run_time = toc - tic
# print(run_time, expansion_factor)
AEP_run_opt = np.copy(prob['AEP'])
# print("AEP improvement = ", AEP_run_opt / AEP_init_opt)
if MODELS[model] == 'BPA':
prob['model_params:wec_factor'] = 1.0
prob['model_params:wec_spreading_angle'] = 0.0
prob['model_params:ti_calculation_method'] = np.copy(
ti_calculation_method)
prob['model_params:calc_k_star'] = np.copy(calc_k_star_calc)
modelruns += 1
prob.run_model(case_prefix='ModelRun%i' % modelruns)
AEP_run_calc = np.copy(prob['AEP'])
# print("compare: ", aep_run, prob['AEP'])
print("AEP calc improvement = ", AEP_run_calc / AEP_init_calc)
if prob.model.comm.rank == 0:
# if save_aep:
# np.savetxt(output_directory + '%s_multistart_aep_results_%iturbs_%sWindRose_%idirs_%sModel_RunID%i_EF%.3f.txt' % (
# opt_algorithm, nTurbs, wind_rose_file, size, MODELS[model], run_number, expansion_factor),
# np.c_[AEP_init, prob['AEP']],
# header="Initial AEP, Final AEP")
if save_locations:
np.savetxt(
output_directory +
'%s_multistart_locations_%iturbs_%sWindRose_%idirs_%s_run%i_EF%.3f_TItype%i.txt'
% (opt_algorithm, nTurbs, wind_rose_file, size,
MODELS[model], run_number, expansion_factor,
ti_opt_method),
np.c_[turbineX_init, turbineY_init, prob['turbineX'],
prob['turbineY']],
header=
"initial turbineX, initial turbineY, final turbineX, final turbineY"
)
# if save_time:
# np.savetxt(output_directory + '%s_multistart_time_%iturbs_%sWindRose_%idirs_%s_run%i_EF%.3f.txt' % (
# opt_algorithm, nTurbs, wind_rose_file, size, MODELS[model], run_number, expansion_factor),
# np.c_[run_time],
# header="run time")
if save_time and save_aep and rec_func_calls:
output_file = output_directory + '%s_multistart_rundata_%iturbs_%sWindRose_%idirs_%s_run%i.txt' \
% (opt_algorithm, nTurbs, wind_rose_file, size, MODELS[model], run_number)
f = open(output_file, "a")
if i == 0:
header = "run number, exp fac, ti calc, ti opt, aep init calc (kW), aep init opt (kW), " \
"aep run calc (kW), aep run opt (kW), run time (s), obj func calls, sens func calls"
else:
header = ''
np.savetxt(f,
np.c_[run_number, expansion_factor,
ti_calculation_method, ti_opt_method,
AEP_init_calc, AEP_init_opt, AEP_run_calc,
AEP_run_opt, run_time, obj_calls,
sens_calls],
header=header)
f.close()
expansion_factor_last = expansion_factor
else:
for expansion_factor, i in zip(
expansion_factors,
np.arange(0, expansion_factors.size)): # best so far
# print("func calls: ", config.obj_func_calls_array, np.sum(config.obj_func_calls_array))
# print("grad func calls: ", config.sens_func_calls_array, np.sum(config.sens_func_calls_array))
# AEP_init_run_opt = prob['AEP']
if expansion_factor_last == expansion_factor:
ti_opt_method = np.copy(final_ti_opt_method)
calc_k_star_opt = True
if opt_algorithm == 'snopt':
prob.driver.opt_settings['Major optimality tolerance'] = float(
conv_tols[i])
prob.driver.opt_settings['Print file'] = output_directory + \
'SNOPT_print_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i_TItype%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number, ti_opt_method)
prob.driver.opt_settings['Summary file'] = output_directory + \
'SNOPT_summary_multistart_%iturbs_%sWindRose_%idirs_%sModel_RunID%i_TItype%i.out' % (
nTurbs, wind_rose_file, size, MODELS[model], run_number, ti_opt_method)
print("starting run with exp. fac = ", expansion_factor)
# run the problem
print('start %s run' % (MODELS[model]))
# cProfile.run('prob.run_driver()')
if MODELS[model] == 'BPA':
# prob['model_params:wec_factor'] = 1.
prob['model_params:ti_calculation_method'] = np.copy(
ti_opt_method)
prob['model_params:calc_k_star'] = np.copy(calc_k_star_opt)
tic = time.time()
# cProfile.run('prob.run_driver()')
config.obj_func_calls_array[prob.comm.rank] = 0.0
config.sens_func_calls_array[prob.comm.rank] = 0.0
prob.run_driver(case_prefix='DriverRun%i' % driverruns)
driverruns += 1
# quit()
toc = time.time()
obj_calls = np.copy(config.obj_func_calls_array[0])
sens_calls = np.copy(config.sens_func_calls_array[0])
run_time = toc - tic
AEP_run_opt = np.copy(prob['AEP'])
# print("AEP improvement = ", AEP_run_calc / AEP_init_calc)
if MODELS[model] == 'BPA':
prob['model_params:wec_factor'] = 1.0
prob['model_params:wec_spreading_angle'] = 0.0
prob['model_params:ti_calculation_method'] = np.copy(
ti_calculation_method)
prob['model_params:calc_k_star'] = np.copy(calc_k_star_calc)
modelruns += 1
prob.run_model(case_prefix='ModelRun%i' % modelruns)
AEP_run_calc = np.copy(prob['AEP'])
if prob.model.comm.rank == 0:
if save_locations:
np.savetxt(
output_directory +
'%s_multistart_locations_%iturbs_%sWindRose_%idirs_%s_run%i_TItype%i.txt'
% (opt_algorithm, nTurbs, wind_rose_file, size,
MODELS[model], run_number, ti_opt_method),
np.c_[turbineX_init, turbineY_init, prob['turbineX'],
prob['turbineY']],
header=
"initial turbineX, initial turbineY, final turbineX, final turbineY"
)
if save_time and save_aep and rec_func_calls:
output_file = output_directory + '%s_multistart_rundata_%iturbs_%sWindRose_%idirs_%s_run%i_TItype%i.txt' \
% (opt_algorithm, nTurbs, wind_rose_file, size, MODELS[model], run_number, ti_opt_method)
f = open(output_file, "a")
header = "run number, ti calc, ti opt, aep init calc (kW), aep init opt (kW), " \
"aep run calc (kW), aep run opt (kW), run time (s), obj func calls, sens func calls"
np.savetxt(f,
np.c_[run_number, ti_calculation_method,
ti_opt_method, AEP_init_calc,
AEP_init_opt, AEP_run_calc, AEP_run_opt,
run_time, obj_calls, sens_calls],
header=header)
f.close()
expansion_factor_last = expansion_factor
turbineX_end = np.copy(prob['turbineX'])
turbineY_end = np.copy(prob['turbineY'])
toct = time.time()
total_time = toct - tict
if prob.model.comm.rank == 0:
# print the results
print(('Opt. calculation took %.03f sec.' % (toct - tict)))
for direction_id in range(0, windDirections.size):
print('yaw%i (deg) = ' % direction_id,
prob['yaw%i' % direction_id])
print('turbine X positions in wind frame (m): %s' % prob['turbineX'])
print('turbine Y positions in wind frame (m): %s' % prob['turbineY'])
print('wind farm power in each direction (kW): %s' % prob['dirPowers'])
print('Initial AEP (kWh): %s' % AEP_init_opt)
print('Final AEP (kWh): %s' % AEP_run_calc)
print('AEP improvement: %s' % (AEP_run_calc / AEP_init_calc))
if show_end:
plot_square_farm(turbineX_end,
turbineY_end,
rotor_diameter,
boundary_x,
boundary_y,
boundary_x[1] - boundary_x[0],
show_start=show_start)
prob.cleanup()
if MODELS[model] == 'BPA':
prob['model_params:wec_factor'] = 1.0
prob['model_params:wec_spreading_angle'] = 0.0
prob['model_params:ti_calculation_method'] = 4
prob['model_params:calc_k_star'] = True
cr = om.CaseReader(output_directory +
'recorded_data_driver_%s.sql' % run_number)
driver_cases = cr.list_cases('driver')
nits = len(driver_cases)
objectives = np.zeros(nits)
AEPopt = np.zeros(nits)
AEPcalc = np.zeros(nits)
calls = np.zeros(nits)
for i in np.arange(0, nits):
case = cr.get_case(driver_cases[i])
# print(case)
AEPopt[i] = case['AEP']
objectives[i] = case.get_objectives()['obj']
prob['turbineX'] = np.copy(case['turbineX'])
prob['turbineY'] = np.copy(case['turbineY'])
if opt_algorithm == "snopt":
prob.run_model(case_prefix='ProcessingRun')
AEPcalc[i] = np.copy(prob['AEP'])
else:
AEPcalc[i] = case['AEP']
calls[i] = i
# Compute the stall margins
self.add_subsystem('stall_margins',
StallCalcs(),
promotes_inputs=[('PR_actual', 'PRmap'),
('Wc_actual', 'WcMap')],
promotes_outputs=['SMN', 'SMW'])
self.connect('SMN_map.PRmap', 'stall_margins.PR_SMN')
self.connect('SMW_map.PRmap', 'stall_margins.PR_SMW')
self.connect('SMN_map.WcMap', 'stall_margins.Wc_SMN')
if __name__ == "__main__":
from pycycle.maps.ncp01 import NCP01
p1 = om.Problem()
ivc = p1.model.add_subsystem('ivc', om.IndepVarComp(), promotes=['*'])
# Design variables
ivc.add_output('alphaMap', 0.0)
ivc.add_output('PR', 2.0)
ivc.add_output('Nc', 1000.0, units='rpm')
ivc.add_output('eff', .9)
ivc.add_output('Wc', 3000., units='lbm/s')
# Off-design variables
# ivc.add_output('alphaMap', 0.0)
# ivc.add_output('Nc', 1000.0, units='rpm')
# ivc.add_output('Wc', 3000., units='lbm/s')
# ivc.add_output('s_Nc', 1.0)
# ivc.add_output('s_Wc', 1.0)
# ivc.add_output('s_PR', 1.0)
def test_debug_print_desvar_physical_with_indices(self):
prob = om.Problem()
model = prob.model
size = 3
model.add_subsystem('p1', om.IndepVarComp('x',
np.array([50.0] * size)))
model.add_subsystem('p2', om.IndepVarComp('y',
np.array([50.0] * size)))
model.add_subsystem(
'comp',
om.ExecComp('f_xy = (x-3.0)**2 + x*y + (y+4.0)**2 - 3.0',
x=np.zeros(size),
y=np.zeros(size),
f_xy=np.zeros(size)))
model.add_subsystem(
'con',
om.ExecComp('c = - x + y',
c=np.zeros(size),
x=np.zeros(size),
y=np.zeros(size)))
model.connect('p1.x', 'comp.x')
model.connect('p2.y', 'comp.y')
model.connect('p1.x', 'con.x')
model.connect('p2.y', 'con.y')
prob.set_solver_print(level=0)
prob.driver = om.ScipyOptimizeDriver()
prob.driver.options['optimizer'] = 'SLSQP'
prob.driver.options['tol'] = 1e-9
prob.driver.options['disp'] = False
model.add_design_var('p1.x',
indices=[1],
lower=-50.0,
upper=50.0,
ref=[
5.0,
])
model.add_design_var('p2.y', indices=[1], lower=-50.0, upper=50.0)
model.add_objective('comp.f_xy', index=1)
model.add_constraint('con.c', indices=[1], upper=-15.0)
prob.setup()
prob.driver.options['debug_print'] = [
'desvars',
]
stdout = sys.stdout
strout = StringIO()
sys.stdout = strout
try:
# formatting has changed in numpy 1.14 and beyond.
if LooseVersion(np.__version__) >= LooseVersion("1.14"):
with printoptions(precision=2, legacy="1.13"):
prob.run_driver()
else:
with printoptions(precision=2):
prob.run_driver()
finally:
sys.stdout = stdout
output = strout.getvalue().split('\n')
# should see unscaled (physical) and the full arrays, not just what is indicated by indices
self.assertEqual(
output[3],
"{'p1.x': array([ 50., 50., 50.]), 'p2.y': array([ 50., 50., 50.])}"
)
def test(self):
"""
This is an opt problem that tests the wingbox model with wave drag and the fuel vol constraint
"""
# Create a dictionary to store options about the surface
mesh_dict = {'num_y' : 7,
'num_x' : 2,
'wing_type' : 'CRM',
'symmetry' : True,
'num_twist_cp' : 6,
'chord_cos_spacing' : 0,
'span_cos_spacing' : 0,
}
mesh, twist_cp = generate_mesh(mesh_dict)
surf_dict = {
# Wing definition
'name' : 'wing', # name of the surface
'symmetry' : True, # if true, model one half of wing
# reflected across the plane y = 0
'S_ref_type' : 'wetted', # how we compute the wing area,
# can be 'wetted' or 'projected'
'fem_model_type' : 'wingbox',
'spar_thickness_cp' : np.array([0.004, 0.005, 0.005, 0.008, 0.008, 0.01]), # [m]
'skin_thickness_cp' : np.array([0.005, 0.01, 0.015, 0.020, 0.025, 0.026]),
'twist_cp' : np.array([4., 5., 8., 8., 8., 9.]),
'mesh' : mesh,
'data_x_upper' : upper_x,
'data_x_lower' : lower_x,
'data_y_upper' : upper_y,
'data_y_lower' : lower_y,
'strength_factor_for_upper_skin' : 1.,
# Aerodynamic performance of the lifting surface at
# an angle of attack of 0 (alpha=0).
# These CL0 and CD0 values are added to the CL and CD
# obtained from aerodynamic analysis of the surface to get
# the total CL and CD.
# These CL0 and CD0 values do not vary wrt alpha.
'CL0' : 0.0, # CL of the surface at alpha=0
'CD0' : 0.0078, # CD of the surface at alpha=0
# Airfoil properties for viscous drag calculation
'k_lam' : 0.05, # percentage of chord with laminar
# flow, used for viscous drag
't_over_c_cp' : np.array([0.08, 0.08, 0.08, 0.10, 0.10, 0.08]),
'original_wingbox_airfoil_t_over_c' : 0.12,
'c_max_t' : .38, # chordwise location of maximum thickness
'with_viscous' : True,
'with_wave' : True, # if true, compute wave drag
# Structural values are based on aluminum 7075
'E' : 73.1e9, # [Pa] Young's modulus
'G' : (73.1e9/2/1.33), # [Pa] shear modulus (calculated using E and the Poisson's ratio here)
'yield' : (420.e6 / 1.5), # [Pa] allowable yield stress
'mrho' : 2.78e3, # [kg/m^3] material density
'strength_factor_for_upper_skin' : 1.0, # the yield stress is multiplied by this factor for the upper skin
# 'fem_origin' : 0.35, # normalized chordwise location of the spar
'wing_weight_ratio' : 1.25,
'struct_weight_relief' : True,
'distributed_fuel_weight' : False,
# Constraints
'exact_failure_constraint' : False, # if false, use KS function
'fuel_density' : 803., # [kg/m^3] fuel density (only needed if the fuel-in-wing volume constraint is used)
'Wf_reserve' :15000., # [kg] reserve fuel mass
}
surfaces = [surf_dict]
# Create the problem and assign the model group
prob = om.Problem()
# Add problem information as an independent variables component
indep_var_comp = om.IndepVarComp()
indep_var_comp.add_output('v', val=.85 * 295.07, units='m/s')
indep_var_comp.add_output('alpha', val=0., units='deg')
indep_var_comp.add_output('Mach_number', val=0.85)
indep_var_comp.add_output('re', val=0.348*295.07*.85*1./(1.43*1e-5), units='1/m')
indep_var_comp.add_output('rho', val=0.348, units='kg/m**3')
indep_var_comp.add_output('CT', val=0.53/3600, units='1/s')
indep_var_comp.add_output('R', val=14.307e6, units='m')
indep_var_comp.add_output('W0', val=148000 + surf_dict['Wf_reserve'], units='kg')
indep_var_comp.add_output('speed_of_sound', val=295.07, units='m/s')
indep_var_comp.add_output('load_factor', val=1.)
indep_var_comp.add_output('empty_cg', val=np.zeros((3)), units='m')
prob.model.add_subsystem('prob_vars',
indep_var_comp,
promotes=['*'])
# Loop over each surface in the surfaces list
for surface in surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
aerostruct_group = AerostructGeometry(surface=surface)
# Add tmp_group to the problem with the name of the surface.
prob.model.add_subsystem(name, aerostruct_group)
# Loop through and add a certain number of aero points
for i in range(1):
point_name = 'AS_point_{}'.format(i)
# Connect the parameters within the model for each aero point
# Create the aero point group and add it to the model
AS_point = AerostructPoint(surfaces=surfaces)
prob.model.add_subsystem(point_name, AS_point)
# Connect flow properties to the analysis point
prob.model.connect('v', point_name + '.v')
prob.model.connect('alpha', point_name + '.alpha')
prob.model.connect('Mach_number', point_name + '.Mach_number')
prob.model.connect('re', point_name + '.re')
prob.model.connect('rho', point_name + '.rho')
prob.model.connect('CT', point_name + '.CT')
prob.model.connect('R', point_name + '.R')
prob.model.connect('W0', point_name + '.W0')
prob.model.connect('speed_of_sound', point_name + '.speed_of_sound')
prob.model.connect('empty_cg', point_name + '.empty_cg')
prob.model.connect('load_factor', point_name + '.load_factor')
for surface in surfaces:
com_name = point_name + '.' + name + '_perf.'
prob.model.connect(name + '.local_stiff_transformed', point_name + '.coupled.' + name + '.local_stiff_transformed')
prob.model.connect(name + '.nodes', point_name + '.coupled.' + name + '.nodes')
# Connect aerodyamic mesh to coupled group mesh
prob.model.connect(name + '.mesh', point_name + '.coupled.' + name + '.mesh')
prob.model.connect(name + '.element_mass', point_name + '.coupled.' + name + '.element_mass')
# Connect performance calculation variables
prob.model.connect(name + '.nodes', com_name + 'nodes')
prob.model.connect(name + '.cg_location', point_name + '.' + 'total_perf.' + name + '_cg_location')
prob.model.connect(name + '.structural_mass', point_name + '.' + 'total_perf.' + name + '_structural_mass')
# Connect wingbox properties to von Mises stress calcs
prob.model.connect(name + '.Qz', com_name + 'Qz')
prob.model.connect(name + '.J', com_name + 'J')
prob.model.connect(name + '.A_enc', com_name + 'A_enc')
prob.model.connect(name + '.htop', com_name + 'htop')
prob.model.connect(name + '.hbottom', com_name + 'hbottom')
prob.model.connect(name + '.hfront', com_name + 'hfront')
prob.model.connect(name + '.hrear', com_name + 'hrear')
prob.model.connect(name + '.spar_thickness', com_name + 'spar_thickness')
prob.model.connect(name + '.t_over_c', com_name + 't_over_c')
#=======================================================================================
# Here we add the fuel volume constraint componenet to the model
#=======================================================================================
prob.model.add_subsystem('fuel_vol_delta', WingboxFuelVolDelta(surface=surface))
prob.model.connect('AS_point_0.fuelburn', 'fuel_vol_delta.fuelburn')
prob.model.connect('wing.struct_setup.fuel_vols', 'fuel_vol_delta.fuel_vols')
#=======================================================================================
#=======================================================================================
prob.driver = om.ScipyOptimizeDriver()
prob.driver.options['tol'] = 1e-9
# prob.driver = om.pyOptSparseDriver()
# prob.driver.add_recorder(om.SqliteRecorder("cases.sql"))
# prob.driver.options['optimizer'] = "SNOPT"
# prob.driver.opt_settings['Major optimality tolerance'] = 1e-6
# prob.driver.opt_settings['Major feasibility tolerance'] = 1e-8
# prob.driver.opt_settings['Major iterations limit'] = 200
prob.model.add_objective('AS_point_0.fuelburn', scaler=1e-5)
prob.model.add_design_var('wing.twist_cp', lower=-15., upper=15., scaler=0.1)
prob.model.add_design_var('wing.spar_thickness_cp', lower=0.003, upper=0.1, scaler=1e2)
prob.model.add_design_var('wing.skin_thickness_cp', lower=0.003, upper=0.1, scaler=1e2)
prob.model.add_design_var('wing.geometry.t_over_c_cp', lower=0.07, upper=0.2, scaler=10.)
prob.model.add_constraint('AS_point_0.CL', equals=0.5)
prob.model.add_constraint('AS_point_0.wing_perf.failure', upper=0.)
#=======================================================================================
# Here we add the fuel volume constraint
#=======================================================================================
prob.model.add_constraint('fuel_vol_delta.fuel_vol_delta', lower=0.)
#=======================================================================================
#=======================================================================================
# Set up the problem
prob.setup()
# om.view_model(prob)
prob.run_driver()
# prob.check_partials(form='central', compact_print=True)
# print(prob['AS_point_0.fuelburn'][0])
# print(prob['wing.structural_mass'][0]/1.25)
assert_rel_error(self, prob['AS_point_0.fuelburn'][0], 85029.7479699, 1e-5)
assert_rel_error(self, prob['wing.structural_mass'][0]/1.25, 18927.5387802, 1e-5)
def test_driver_recording_options_deprecated(self):
prob = om.Problem()
msg = "The recording option, record_model_metadata, on Driver is deprecated. " \
"Recording of model metadata will always be done"
with assert_warning(DeprecationWarning, msg):
prob.driver.recording_options['record_model_metadata'] = True
def test_obj_pass(self):
prob = om.Problem()
model = prob.model
indep = model.add_subsystem('indep',
om.IndepVarComp(),
promotes_outputs=['x'])
indep.add_discrete_output('x', _DiscreteVal(19))
G = model.add_subsystem('G', om.ParallelGroup(), promotes_inputs=['x'])
G1 = G.add_subsystem('G1',
om.Group(),
promotes_inputs=['x'],
promotes_outputs=['y'])
G1.add_subsystem('C1_1',
ObjAdderCompEx(_DiscreteVal(5)),
promotes_inputs=['x'])
G1.add_subsystem('C1_2',
ObjAdderCompEx(_DiscreteVal(7)),
promotes_outputs=['y'])
G1.connect('C1_1.y', 'C1_2.x')
G2 = G.add_subsystem('G2', om.Group(), promotes_inputs=['x'])
G2.add_subsystem('C2_1',
ObjAdderCompEx(_DiscreteVal(1)),
promotes_inputs=['x'])
G2.add_subsystem('C2_2',
ObjAdderCompEx(_DiscreteVal(11)),
promotes_outputs=['y'])
G2.connect('C2_1.y', 'C2_2.x')
model.add_subsystem('C3', ObjAdderCompEx(_DiscreteVal(9)))
model.add_subsystem('C4', ObjAdderCompEx(_DiscreteVal(21)))
model.connect('G.y', 'C3.x')
model.connect('G.G2.y', 'C4.x')
prob.setup()
prob.run_model()
self.assertEqual(prob['C3.y'].getval(), 40)
self.assertEqual(prob['C4.y'].getval(), 52)
def _var_iter(obj):
name = obj['name']
if 'children' in obj:
for c in obj['children']:
for vname in _var_iter(c):
if name:
yield '.'.join((name, vname))
else:
yield vname
else:
yield name
# add a test to see if discrete vars show up in n2
data = _get_viewer_data(prob)
findvars = [
'indep.x',
'G.G1.C1_1.x',
'G.G1.C1_1.y',
'G.G1.C1_2.x',
'G.G1.C1_2.y',
'G.G2.C2_1.x',
'G.G2.C2_1.y',
'G.G2.C2_2.x',
'G.G2.C2_2.y',
'C3.x',
'C3.y',
'C4.x',
'C4.y',
]
vnames = list(_var_iter(data['tree']))
self.assertTrue(sorted(findvars), sorted(vnames))
def test_units_basic(self):
prob = om.Problem()
model = prob.model
ivc = om.IndepVarComp()
ivc.add_output('x', 35.0, units='degF')
model.add_subsystem('p', ivc, promotes=['x'])
model.add_subsystem('comp1',
om.ExecComp('y1 = 2.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y1={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y1'])
model.add_subsystem('comp2',
om.ExecComp('y2 = 3.0*x',
x={
'value': 2.0,
'units': 'degF'
},
y2={
'value': 2.0,
'units': 'degF'
}),
promotes=['x', 'y2'])
model.add_design_var('x', units='degC', lower=0.0, upper=100.0)
model.add_constraint('y1', units='degC', lower=0.0, upper=100.0)
model.add_objective('y2', units='degC')
prob.setup()
prob.run_driver()
dv = prob.driver.get_design_var_values()
assert_near_equal(dv['p.x'][0], 3.0 * 5 / 9, 1e-8)
obj = prob.driver.get_objective_values(driver_scaling=True)
assert_near_equal(obj['comp2.y2'][0], 73.0 * 5 / 9, 1e-8)
con = prob.driver.get_constraint_values(driver_scaling=True)
assert_near_equal(con['comp1.y1'][0], 38.0 * 5 / 9, 1e-8)
meta = model.get_design_vars()
assert_near_equal(meta['p.x']['lower'], 0.0, 1e-7)
assert_near_equal(meta['p.x']['upper'], 100.0, 1e-7)
meta = model.get_constraints()
assert_near_equal(meta['comp1.y1']['lower'], 0.0, 1e-7)
assert_near_equal(meta['comp1.y1']['upper'], 100.0, 1e-7)
stdout = sys.stdout
strout = StringIO()
sys.stdout = strout
try:
prob.list_problem_vars(desvar_opts=['units'],
objs_opts=['units'],
cons_opts=['units'])
finally:
sys.stdout = stdout
output = strout.getvalue().split('\n')
self.assertTrue('1.666' in output[5])
self.assertTrue('21.111' in output[12])
self.assertTrue('40.555' in output[19])
self.assertTrue('degC' in output[5])
self.assertTrue('degC' in output[12])
self.assertTrue('degC' in output[19])
import openmdao.api as om
import dymos as dm
from donner_sub_ode import DonnerSubODE
# Create the problem
p = om.Problem(model=om.Group())
# Add the trajectory (optional for single phase problems)
traj = dm.Trajectory()
# Create the phase
phase = dm.Phase(ode_class=DonnerSubODE,
transcription=dm.GaussLobatto(num_segments=20,
order=3,
compressed=False))
# Add the phase to the trajectory, and the trajectory to the model
traj.add_phase('phase0', phase=phase)
p.model.add_subsystem('traj', traj)
#
# Configure the phase
#
phase.set_time_options(units=None,
targets=['threat_comp.time'],
fix_initial=True,
duration_bounds=(0.1, 100))
phase.add_state('x',
rate_source='eom_comp.dx_dt',
targets=['nav_comp.x'],
def testRunAll(self):
opt = {}
opt["floating"] = {}
opt["WISDEM"] = {}
opt["WISDEM"]["FloatingSE"] = {}
opt["floating"]["members"] = {}
opt["floating"]["members"]["n_members"] = n_member = 6
opt["floating"]["members"]["n_height"] = [2]
opt["floating"]["members"]["n_bulkheads"] = [4]
opt["floating"]["members"]["n_layers"] = [1]
opt["floating"]["members"]["n_ballasts"] = [0]
opt["floating"]["members"]["n_axial_joints"] = [1]
opt["floating"]["tower"] = {}
opt["floating"]["tower"]["n_height"] = [3]
opt["floating"]["tower"]["n_bulkheads"] = [0]
opt["floating"]["tower"]["n_layers"] = [1]
opt["floating"]["tower"]["n_ballasts"] = [0]
opt["floating"]["tower"]["n_axial_joints"] = [0]
opt["WISDEM"]["FloatingSE"]["frame3dd"] = {}
opt["WISDEM"]["FloatingSE"]["frame3dd"]["shear"] = True
opt["WISDEM"]["FloatingSE"]["frame3dd"]["geom"] = True
opt["WISDEM"]["FloatingSE"]["frame3dd"]["tol"] = 1e-7
opt["WISDEM"]["FloatingSE"]["frame3dd"]["modal"] = False # True
opt["WISDEM"]["FloatingSE"]["gamma_f"] = 1.35 # Safety factor on loads
opt["WISDEM"]["FloatingSE"]["gamma_m"] = 1.3 # Safety factor on materials
opt["WISDEM"]["FloatingSE"]["gamma_n"] = 1.0 # Safety factor on consequence of failure
opt["WISDEM"]["FloatingSE"]["gamma_b"] = 1.1 # Safety factor on buckling
opt["WISDEM"]["FloatingSE"]["gamma_fatigue"] = 1.755 # Not used
opt["mooring"] = {}
opt["mooring"]["n_attach"] = 3
opt["mooring"]["n_anchors"] = 3
opt["materials"] = {}
opt["materials"]["n_mat"] = 2
prob = om.Problem()
prob.model = frame.FloatingFrame(modeling_options=opt)
prob.setup()
# Material properties
prob["rho_mat"] = np.array([7850.0, 5000.0]) # Steel, ballast slurry [kg/m^3]
prob["E_mat"] = 200e9 * np.ones((2, 3)) # Young's modulus [N/m^2]
prob["G_mat"] = 79.3e9 * np.ones((2, 3)) # Shear modulus [N/m^2]
prob["sigma_y_mat"] = 3.45e8 * np.ones(2) # Elastic yield stress [N/m^2]
prob["unit_cost_mat"] = np.array([2.0, 1.0])
prob["material_names"] = ["steel", "slurry"]
# Mass and cost scaling factors
prob["labor_cost_rate"] = 1.0 # Cost factor for labor time [$/min]
prob["painting_cost_rate"] = 14.4 # Cost factor for column surface finishing [$/m^2]
prob["member0:nodes_xyz"][:2, :] = np.array([[0, 0, 0], [1, 0, 0]])
prob["member1:nodes_xyz"][:2, :] = np.array([[1, 0, 0], [0.5, 1, 0]])
prob["member2:nodes_xyz"][:2, :] = np.array([[0.5, 1, 0], [0, 0, 0]])
prob["member3:nodes_xyz"][:2, :] = np.array([[0, 0, 0], [0, 0, 1]])
prob["member4:nodes_xyz"][:2, :] = np.array([[1, 0, 0], [0, 0, 1]])
prob["member5:nodes_xyz"][:2, :] = np.array([[0.5, 1, 0], [0, 0, 1]])
for k in range(n_member):
L = np.sqrt(np.sum(np.diff(prob["member" + str(k) + ":nodes_xyz"][:, 2], axis=0) ** 2))
prob["member" + str(k) + ":nodes_r"][:2] = 0.1 * k * np.ones(2)
prob["member" + str(k) + ":section_D"][:1] = 2.0
prob["member" + str(k) + ":section_t"][:1] = 0.1
prob["member" + str(k) + ":section_A"][:1] = 0.5 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_Asx"][:1] = 0.5 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_Asy"][:1] = 0.5 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_Ixx"][:1] = 2 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_Iyy"][:1] = 2 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_Izz"][:1] = 2 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_rho"][:1] = 1e3 / (0.5 * k * np.ones(1) + 1) / L
prob["member" + str(k) + ":section_E"][:1] = 3 * k * np.ones(1) + 1
prob["member" + str(k) + ":section_G"][:1] = 4 * k * np.ones(1) + 1
prob["member" + str(k) + ":idx_cb"] = 0
prob["member" + str(k) + ":buoyancy_force"] = 1e2
prob["member" + str(k) + ":displacement"] = 1e1
prob["member" + str(k) + ":center_of_buoyancy"] = prob["member" + str(k) + ":nodes_xyz"][:2, :].mean(axis=0)
prob["member" + str(k) + ":center_of_mass"] = prob["member" + str(k) + ":nodes_xyz"][:2, :].mean(axis=0)
prob["member" + str(k) + ":total_mass"] = 1e3
prob["member" + str(k) + ":total_cost"] = 2e3
prob["member" + str(k) + ":Awater"] = 5.0
prob["member" + str(k) + ":Iwater"] = 15.0
prob["member" + str(k) + ":added_mass"] = np.arange(6)
# Set environment to that used in OC3 testing campaign
# prob["rho_air"] = 1.226 # Density of air [kg/m^3]
# prob["mu_air"] = 1.78e-5 # Viscosity of air [kg/m/s]
prob["rho_water"] = 1025.0 # Density of water [kg/m^3]
# prob["mu_water"] = 1.08e-3 # Viscosity of water [kg/m/s]
# prob["water_depth"] = 320.0 # Distance to sea floor [m]
# prob["Hsig_wave"] = 0.0 # Significant wave height [m]
# prob["Tsig_wave"] = 1e3 # Wave period [s]
# prob["shearExp"] = 0.11 # Shear exponent in wind power law
# prob["cm"] = 2.0 # Added mass coefficient
# prob["Uc"] = 0.0 # Mean current speed
# prob["yaw"] = 0.0 # Turbine yaw angle
# prob["beta_wind"] = prob["beta_wave"] = 0.0
# prob["cd_usr"] = -1.0 # Compute drag coefficient
# prob["Uref"] = 10.0
# prob["zref"] = 100.0
# Porperties of turbine tower
nTower = prob.model.options["modeling_options"]["floating"]["tower"]["n_height"][0]
prob["hub_height"] = 85.0
prob["distance_tt_hub"] = 5.0
prob["tower.s"] = np.linspace(0.0, 1.0, nTower)
prob["tower.outer_diameter_in"] = np.linspace(6.5, 3.87, nTower)
prob["tower.layer_thickness"] = np.linspace(0.027, 0.019, nTower).reshape((1, nTower))
prob["tower.layer_materials"] = ["steel"]
prob["tower.outfitting_factor"] = 1.07
prob["mooring_neutral_load"] = np.zeros((3, 3))
prob["mooring_neutral_load"][:, 0] = [200, -100.0, -100]
prob["mooring_neutral_load"][:, 1] = [0.0, 50, -50]
prob["mooring_neutral_load"][:, 2] = -1e3
prob["mooring_fairlead_joints"] = np.array([[0.0, 0.0, 0.0], [0.5, 1.0, 0.0], [1.0, 0.0, 0.0]])
prob["rna_mass"] = 1e4
prob["rna_cg"] = np.ones(3)
prob["rna_I"] = 1e4 * np.arange(6)
prob["rna_F"] = np.array([1e2, 1e1, 0.0])
prob["rna_M"] = np.array([2e1, 2e2, 0.0])
prob["transition_piece_mass"] = 1e3
prob["transition_node"] = prob["member4:nodes_xyz"][0, :]
prob.run_model()
self.assertTrue(True)
