Exemplo n.º 1
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    def setUp(self):
        self.nn = 100

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='a', shape=(self.nn, 4))
        ivc.add_output(name='b', shape=(self.nn, 4))

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['a', 'b'])

        self.p.model.add_subsystem(name='dot_prod_comp',
                                   subsys=DotProductComp(vec_size=self.nn, length=4))

        self.p.model.connect('a', 'dot_prod_comp.a')
        self.p.model.connect('b', 'dot_prod_comp.b')

        self.p.setup()

        self.p['a'] = np.random.rand(self.nn, 4)
        self.p['b'] = np.random.rand(self.nn, 4)

        self.p.run_model()
    def setUp(self):
        self.nn = 5

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='A', shape=(self.nn, 6, 4))
        ivc.add_output(name='x', shape=(self.nn, 4))

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['A', 'x'])

        self.p.model.add_subsystem(name='mat_vec_product_comp',
                                   subsys=MatrixVectorProductComp(vec_size=self.nn,
                                                                  A_shape=(6, 4)))

        self.p.model.connect('A', 'mat_vec_product_comp.A')
        self.p.model.connect('x', 'mat_vec_product_comp.x')

        self.p.setup(force_alloc_complex=True)

        self.p['A'] = np.random.rand(self.nn, 6, 4)
        self.p['x'] = np.random.rand(self.nn, 4)

        self.p.run_model()
Exemplo n.º 3
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    def setUp(self):
        self.nn = 10

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='a', shape=(self.nn,))
        ivc.add_output(name='b', shape=(self.nn,))

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['a', 'b'])

        demux_comp = self.p.model.add_subsystem(name='demux_comp',
                                                subsys=DemuxComp(vec_size=self.nn))

        demux_comp.add_var('a', shape=(self.nn,))
        demux_comp.add_var('b', shape=(self.nn,))

        self.p.model.connect('a', 'demux_comp.a')
        self.p.model.connect('b', 'demux_comp.b')

        self.p.setup(force_alloc_complex=True)

        self.p['a'] = np.random.rand(self.nn)
        self.p['b'] = np.random.rand(self.nn)

        self.p.run_model()
    def test_structural_weight_loads(self):
        surface = get_default_surfaces()[0]

        comp = StructureWeightLoads(surface=surface)

        group = Group()

        indep_var_comp = IndepVarComp()

        ny = surface['mesh'].shape[1]

        #carefully chosen "random" values that give non-uniform derivatives outputs that are good for testing
        nodesval = np.array([[1., 2., 4.],
                            [20., 22., 7.],
                            [8., 17., 14.],
                            [13., 14., 16.]],dtype=complex)
        element_weights_val = np.arange(ny-1)+1

        indep_var_comp.add_output('nodes', val=nodesval,units='m')
        indep_var_comp.add_output('element_weights', val=element_weights_val,units='N')

        group.add_subsystem('indep_var_comp', indep_var_comp, promotes=['*'])
        group.add_subsystem('load', comp, promotes=['*'])

        p = run_test(self, group, complex_flag=True, compact_print=True)
Exemplo n.º 5
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    def setUp(self):
        self.nn = 5

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='a', shape=(self.nn, 3))
        ivc.add_output(name='b', shape=(self.nn, 3))

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['a', 'b'])

        adder=self.p.model.add_subsystem(name='add_subtract_comp',
                                   subsys=AddSubtractComp())
        adder.add_equation('adder_output',['input_a','input_b'],vec_size=self.nn,length=3)

        self.p.model.connect('a', 'add_subtract_comp.input_a')
        self.p.model.connect('b', 'add_subtract_comp.input_b')

        self.p.setup()

        self.p['a'] = np.random.rand(self.nn, 3)
        self.p['b'] = np.random.rand(self.nn, 3)

        self.p.run_model()
Exemplo n.º 6
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    def test_const_jacobian(self):
        import numpy as np

        from openmdao.api import Problem, Group, IndepVarComp, DirectSolver, DenseJacobian
        from openmdao.jacobians.tests.test_jacobian_features import SimpleCompConst

        model = Group()
        comp = IndepVarComp()
        for name, val in (('x', 1.), ('y1', np.ones(2)), ('y2', np.ones(2)),
                          ('y3', np.ones(2)), ('z', np.ones((2, 2)))):
            comp.add_output(name, val)
        model.add_subsystem('input_comp', comp, promotes=['x', 'y1', 'y2', 'y3', 'z'])

        problem = Problem(model=model)
        model.suppress_solver_output = True
        model.linear_solver = DirectSolver()
        model.jacobian = DenseJacobian()
        model.add_subsystem('simple', SimpleCompConst(),
                            promotes=['x', 'y1', 'y2', 'y3', 'z', 'f', 'g'])
        problem.setup(check=False)
        problem.run_model()
        totals = problem.compute_totals(['f', 'g'],
                                              ['x', 'y1', 'y2', 'y3', 'z'])

        assert_rel_error(self, totals['f', 'x'], [[1.]])
        assert_rel_error(self, totals['f', 'z'], np.ones((1, 4)))
        assert_rel_error(self, totals['f', 'y1'], np.zeros((1, 2)))
        assert_rel_error(self, totals['f', 'y2'], np.zeros((1, 2)))
        assert_rel_error(self, totals['f', 'y3'], np.zeros((1, 2)))
        assert_rel_error(self, totals['g', 'x'], [[1], [0], [0], [1]])
        assert_rel_error(self, totals['g', 'z'], np.zeros((4, 4)))
        assert_rel_error(self, totals['g', 'y1'], [[1, 0], [1, 0], [0, 1], [0, 1]])
        assert_rel_error(self, totals['g', 'y2'], [[1, 0], [0, 1], [1, 0], [0, 1]])
        assert_rel_error(self, totals['g', 'y3'], [[1, 0], [1, 0], [0, 1], [0, 1]])
Exemplo n.º 7
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    def setup(self, compname, inputs, state0):
        # create instance of component type
        try:
            comp = eval('%s(NTIME)' % compname)
        except TypeError:
            try:
                comp = eval('%s()' % compname)
            except TypeError:
                comp = eval('%s(NTIME, 300)' % compname)

        # collect metadata for component inputs
        prob = Problem(comp)
        prob.setup()
        prob.final_setup()

        self.inputs_dict = {}
        for name, meta in prob.model.list_inputs(units=True, out_stream=None):
            self.inputs_dict[name.split('.')[-1]] = meta

        # create independent vars for each input, initialized with random values
        indep = IndepVarComp()
        for item in inputs + state0:
            shape = self.inputs_dict[item]['value'].shape
            units = self.inputs_dict[item]['units']
            indep.add_output(item, np.random.random(shape), units=units)

        # setup problem for test
        self.prob = Problem()
        self.prob.model.add_subsystem('indep', indep, promotes=['*'])
        self.prob.model.add_subsystem('comp', comp, promotes=['*'])

        self.prob.setup()
Exemplo n.º 8
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    def test_iimplicit(self):
        # Testing that our scale/unscale contexts leave the output vector in the correct state when
        # linearize is called on implicit components.
        prob = Problem()
        model = prob.model

        inputs_comp = IndepVarComp()
        inputs_comp.add_output('x1_u', val=1.0)

        model.add_subsystem('p', inputs_comp)
        mycomp = model.add_subsystem('comp', MyImplicitComp())

        model.connect('p.x1_u', 'comp.x2_u')

        model.linear_solver = DirectSolver()
        model.nonlinear_solver = NewtonSolver()
        model.nonlinear_solver.options['atol'] = 1e-12
        model.nonlinear_solver.options['rtol'] = 1e-12

        model.add_design_var('p.x1_u', lower=-11, upper=11)
        model.add_constraint('p.x1_u', upper=3.3)
        model.add_objective('comp.x3_u')
        model.add_objective('comp.x3_s')

        prob.setup()
        prob.run_model()

        totals = prob.check_totals(compact_print=True, out_stream=None)

        for (of, wrt) in totals:
            assert_rel_error(self, totals[of, wrt]['abs error'][0], 0.0, 1e-7)
Exemplo n.º 9
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    def setUp(self):
        self.nn = 5

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='a', shape=(self.nn, 3, 1))
        ivc.add_output(name='b', shape=(self.nn, 3, 1))

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['a', 'b'])

        self.p.model.add_subsystem(name='cross_prod_comp',
                                   subsys=CrossProductComp(vec_size=self.nn))

        self.p.model.connect('a', 'cross_prod_comp.a')
        self.p.model.connect('b', 'cross_prod_comp.b')

        self.p.setup(force_alloc_complex=True)

        self.p['a'] = np.random.rand(self.nn, 3, 1)
        self.p['b'] = np.random.rand(self.nn, 3, 1)

        self.p['a'][:, 0, 0] = 2.0
        self.p['a'][:, 1, 0] = 3.0
        self.p['a'][:, 2, 0] = 4.0

        self.p['b'][:, 0, 0] = 5.0
        self.p['b'][:, 1, 0] = 6.0
        self.p['b'][:, 2, 0] = 7.0

        self.p.run_model()
Exemplo n.º 10
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    def setup(self):
        surface = self.options['surface']
        mesh = surface['mesh']
        nx = mesh.shape[0]
        ny = mesh.shape[1]

        # Add independent variables that do not belong to a specific component
        indep_var_comp = IndepVarComp()

        # Add structural components to the surface-specific group
        self.add_subsystem('indep_vars',
                 indep_var_comp,
                 promotes=['*'])

        if 'struct' in surface['type']:
            self.add_subsystem('radius_comp',
                RadiusComp(surface=surface),
                promotes_inputs=['mesh', 't_over_c'],
                promotes_outputs=['radius'])

        if 'thickness_cp' in surface.keys():
            n_cp = len(surface['thickness_cp'])
            # Add bspline components for active bspline geometric variables.
            self.add_subsystem('thickness_bsp', BsplinesComp(
                in_name='thickness_cp', out_name='thickness', units='m',
                num_control_points=n_cp, num_points=int(ny-1),
                bspline_order=min(n_cp, 4), distribution='uniform'),
                promotes_inputs=['thickness_cp'], promotes_outputs=['thickness'])
            indep_var_comp.add_output('thickness_cp', val=surface['thickness_cp'], units='m')

        self.add_subsystem('tube',
            SectionPropertiesTube(surface=surface),
            promotes_inputs=['thickness', 'radius'],
            promotes_outputs=['A', 'Iy', 'Iz', 'J'])
Exemplo n.º 11
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    def test_speed(self):
        from openmdao.api import Problem, Group, IndepVarComp, ExecComp
        from openmdao.core.tests.test_units import SpeedComp

        comp = IndepVarComp()
        comp.add_output('distance', val=1., units='m')
        comp.add_output('time', val=1., units='s')

        prob = Problem(model=Group())
        prob.model.add_subsystem('c1', comp)
        prob.model.add_subsystem('c2', SpeedComp())
        prob.model.add_subsystem('c3', ExecComp('f=speed',speed={'units': 'm/s'}))
        prob.model.connect('c1.distance', 'c2.distance')
        prob.model.connect('c1.time', 'c2.time')
        prob.model.connect('c2.speed', 'c3.speed')

        prob.setup()
        prob.run_model()

        assert_rel_error(self, prob['c1.distance'], 1.)  # units: m
        assert_rel_error(self, prob['c2.distance'], 1.e-3)  # units: km

        assert_rel_error(self, prob['c1.time'], 1.)  # units: s
        assert_rel_error(self, prob['c2.time'], 1./3600.)  # units: h

        assert_rel_error(self, prob['c2.speed'], 3.6)  # units: km/h
        assert_rel_error(self, prob['c3.f'], 1.0)  # units: km/h
Exemplo n.º 12
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    def setUp(self):
        self.nn = 5

        self.p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='a', shape=(self.nn, 3), units='lbf')
        ivc.add_output(name='b', shape=(self.nn, 3), units='ft/s')

        self.p.model.add_subsystem(name='ivc',
                                   subsys=ivc,
                                   promotes_outputs=['a', 'b'])

        self.p.model.add_subsystem(name='dot_prod_comp',
                                   subsys=DotProductComp(vec_size=self.nn,
                                                         a_units='N', b_units='m/s',
                                                         c_units='W'))

        self.p.model.connect('a', 'dot_prod_comp.a')
        self.p.model.connect('b', 'dot_prod_comp.b')

        self.p.setup()

        self.p['a'] = np.random.rand(self.nn, 3)
        self.p['b'] = np.random.rand(self.nn, 3)

        self.p.run_model()
Exemplo n.º 13
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    def test_const_jacobian(self):
        model = Group()
        comp = IndepVarComp()
        for name, val in (('x', 1.), ('y1', np.ones(2)), ('y2', np.ones(2)),
                          ('y3', np.ones(2)), ('z', np.ones((2, 2)))):
            comp.add_output(name, val)
        model.add_subsystem('input_comp', comp, promotes=['x', 'y1', 'y2', 'y3', 'z'])

        problem = Problem(model=model)
        problem.set_solver_print(level=0)
        model.linear_solver = ScipyKrylov()
        model.jacobian = COOJacobian()
        model.add_subsystem('simple', SimpleCompConst(),
                            promotes=['x', 'y1', 'y2', 'y3', 'z', 'f', 'g'])
        problem.setup(check=False)
        problem.run_model()
        totals = problem.compute_totals(['f', 'g'],
                                              ['x', 'y1', 'y2', 'y3', 'z'])

        jacobian = {}
        jacobian['f', 'x'] = [[1.]]
        jacobian['f', 'z'] = np.ones((1, 4))
        jacobian['f', 'y1'] = np.zeros((1, 2))
        jacobian['f', 'y2'] = np.zeros((1, 2))
        jacobian['f', 'y3'] = np.zeros((1, 2))

        jacobian['g', 'y1'] = [[1, 0], [1, 0], [0, 1], [0, 1]]
        jacobian['g', 'y2'] = [[1, 0], [0, 1], [1, 0], [0, 1]]
        jacobian['g', 'y3'] = [[1, 0], [1, 0], [0, 1], [0, 1]]

        jacobian['g', 'x'] = [[1], [0], [0], [1]]
        jacobian['g', 'z'] = np.zeros((4, 4))

        assert_rel_error(self, totals, jacobian)
Exemplo n.º 14
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    def test_sparse_jacobian(self):
        import numpy as np

        from openmdao.api import Problem, Group, IndepVarComp, ExplicitComponent

        class SparsePartialComp(ExplicitComponent):
            def setup(self):
                self.add_input('x', shape=(4,))
                self.add_output('f', shape=(2,))

                self.declare_partials(of='f', wrt='x', rows=[0, 1, 1, 1], cols=[0, 1, 2, 3])

            def compute_partials(self, inputs, partials):
                # Corresponds to the [(0,0), (1,1), (1,2), (1,3)] entries.
                partials['f', 'x'] = [1., 2., 3., 4.]

        model = Group()
        comp = IndepVarComp()
        comp.add_output('x', np.ones(4))

        model.add_subsystem('input', comp)
        model.add_subsystem('example', SparsePartialComp())

        model.connect('input.x', 'example.x')

        problem = Problem(model=model)
        problem.setup(check=False)
        problem.run_model()
        totals = problem.compute_totals(['example.f'], ['input.x'])

        assert_rel_error(self, totals['example.f', 'input.x'], [[1., 0., 0., 0.], [0., 2., 3., 4.]])
Exemplo n.º 15
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    def test_raise_no_error_on_singular(self):
        prob = Problem()
        model = prob.model

        comp = IndepVarComp()
        comp.add_output('dXdt:TAS', val=1.0)
        comp.add_output('accel_target', val=2.0)
        model.add_subsystem('des_vars', comp, promotes=['*'])

        teg = model.add_subsystem('thrust_equilibrium_group', subsys=Group())
        teg.add_subsystem('dynamics', ExecComp('z = 2.0*thrust'), promotes=['*'])

        thrust_bal = BalanceComp()
        thrust_bal.add_balance(name='thrust', val=1207.1, lhs_name='dXdt:TAS',
                               rhs_name='accel_target', eq_units='m/s**2', lower=-10.0, upper=10000.0)

        teg.add_subsystem(name='thrust_bal', subsys=thrust_bal,
                          promotes_inputs=['dXdt:TAS', 'accel_target'],
                          promotes_outputs=['thrust'])

        teg.linear_solver = DirectSolver(assemble_jac=False)

        teg.nonlinear_solver = NewtonSolver()
        teg.nonlinear_solver.options['solve_subsystems'] = True
        teg.nonlinear_solver.options['max_sub_solves'] = 1
        teg.nonlinear_solver.options['atol'] = 1e-4

        prob.setup(check=False)
        prob.set_solver_print(level=0)

        teg.linear_solver.options['err_on_singular'] = False
        prob.run_model()
    def test(self):

        # Create a dictionary to store options about the surface
        mesh_dict = {'num_y' : 7,
                     'wing_type' : 'CRM',
                     'symmetry' : True,
                     'num_twist_cp' : 5}

        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
                    'fem_model_type' : 'tube',

                    'mesh' : mesh,
                    'radius_cp' : np.ones((5)) * 0.5,

                    # Structural values are based on aluminum 7075
                    'E' : 70.e9,            # [Pa] Young's modulus of the spar
                    'G' : 30.e9,            # [Pa] shear modulus of the spar
                    'yield' : 500.e6 / 2.5, # [Pa] yield stress divided by 2.5 for limiting case
                    'mrho' : 3.e3,          # [kg/m^3] material density
                    'fem_origin' : 0.35,    # normalized chordwise location of the spar
                    't_over_c_cp' : np.array([0.15]),      # maximum airfoil thickness
                    'thickness_cp' : np.ones((3)) * .1,
                    'wing_weight_ratio' : 2.,
                    'struct_weight_relief' : False,    # True to add the weight of the structure to the loads on the structure
                    'distributed_fuel_weight' : False,
                    'exact_failure_constraint' : False,
                    }

        # Create the problem and assign the model group
        prob = Problem()

        ny = surf_dict['mesh'].shape[1]

        indep_var_comp = IndepVarComp()
        indep_var_comp.add_output('loads', val=np.ones((ny, 6)) * 2e5, units='N')
        indep_var_comp.add_output('load_factor', val=1.)

        struct_group = SpatialBeamAlone(surface=surf_dict)

        # Add indep_vars to the structural group
        struct_group.add_subsystem('indep_vars',
             indep_var_comp,
             promotes=['*'])

        prob.model.add_subsystem(surf_dict['name'], struct_group)

        # Set up the problem
        prob.setup()

        prob.run_model()

        assert_rel_error(self, prob['wing.structural_mass'][0], 117819.798089, 1e-4)
Exemplo n.º 17
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    def setup(self):
        E = self.metadata['E']
        L = self.metadata['L']
        b = self.metadata['b']
        volume = self.metadata['volume']
        num_elements = self.metadata['num_elements']
        num_nodes = num_elements + 1

        force_vector = np.zeros(2 * num_nodes)
        force_vector[-2] = -1.

        inputs_comp = IndepVarComp()
        inputs_comp.add_output('h', shape=num_elements)
        self.add_subsystem('inputs_comp', inputs_comp)

        I_comp = MomentOfInertiaComp(num_elements=num_elements, b=b)
        self.add_subsystem('I_comp', I_comp)

        comp = LocalStiffnessMatrixComp(num_elements=num_elements, E=E, L=L)
        self.add_subsystem('local_stiffness_matrix_comp', comp)

        comp = GlobalStiffnessMatrixComp(num_elements=num_elements)
        self.add_subsystem('global_stiffness_matrix_comp', comp)

        comp = StatesComp(num_elements=num_elements, force_vector=force_vector)
        self.add_subsystem('states_comp', comp)

        comp = DisplacementsComp(num_elements=num_elements)
        self.add_subsystem('displacements_comp', comp)

        comp = ComplianceComp(num_elements=num_elements, force_vector=force_vector)
        self.add_subsystem('compliance_comp', comp)

        comp = VolumeComp(num_elements=num_elements, b=b, L=L)
        self.add_subsystem('volume_comp', comp)

        self.connect('inputs_comp.h', 'I_comp.h')
        self.connect('I_comp.I', 'local_stiffness_matrix_comp.I')
        self.connect(
            'local_stiffness_matrix_comp.K_local',
            'global_stiffness_matrix_comp.K_local')
        self.connect(
            'global_stiffness_matrix_comp.K',
            'states_comp.K')
        self.connect(
            'states_comp.d',
            'displacements_comp.d')
        self.connect(
            'displacements_comp.displacements',
            'compliance_comp.displacements')
        self.connect(
            'inputs_comp.h',
            'volume_comp.h')

        self.add_design_var('inputs_comp.h', lower=1e-2, upper=10.)
        self.add_objective('compliance_comp.compliance')
        self.add_constraint('volume_comp.volume', equals=volume)
Exemplo n.º 18
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    def test_add_output(self):
        """Define two independent variables using the add_output method."""
        from openmdao.api import Problem, IndepVarComp

        comp = IndepVarComp()
        comp.add_output('indep_var_1', val=1.0, lower=0, upper=10)
        comp.add_output('indep_var_2', val=2.0, lower=1, upper=20)

        prob = Problem(comp).setup(check=False)

        assert_rel_error(self, prob['indep_var_1'], 1.0)
        assert_rel_error(self, prob['indep_var_2'], 2.0)
Exemplo n.º 19
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    def test_scalar_with_guess_func_additional_input(self):

        model = Group(assembled_jac_type='dense')

        bal = BalanceComp()
        bal.add_balance('x')
        bal.add_input('guess_x', val=0.0)

        ivc = IndepVarComp()
        ivc.add_output(name='y_tgt', val=4)
        ivc.add_output(name='guess_x', val=2.5)

        exec_comp = ExecComp('y=x**2', x={'value': 1}, y={'value': 1})

        model.add_subsystem(name='ivc', subsys=ivc, promotes_outputs=['y_tgt', 'guess_x'])
        model.add_subsystem(name='exec', subsys=exec_comp)
        model.add_subsystem(name='balance', subsys=bal)

        model.connect('guess_x', 'balance.guess_x')
        model.connect('y_tgt', 'balance.rhs:x')
        model.connect('balance.x', 'exec.x')
        model.connect('exec.y', 'balance.lhs:x')

        model.linear_solver = DirectSolver(assemble_jac=True)
        model.nonlinear_solver = NewtonSolver(maxiter=100, iprint=0)

        prob = Problem(model)
        prob.setup()

        # run problem without a guess function
        prob['balance.x'] = .5
        prob.run_model()

        assert_almost_equal(prob['balance.x'], 2.0, decimal=7)

        iters_no_guess = model.nonlinear_solver._iter_count

        # run problem with same initial value and a guess function
        def guess_function(inputs, outputs, resids):
            outputs['x'] = inputs['guess_x']

        bal.options['guess_func'] = guess_function

        prob['balance.x'] = .5
        prob.run_model()

        assert_almost_equal(prob['balance.x'], 2.0, decimal=7)

        iters_with_guess = model.nonlinear_solver._iter_count

        # verify it converges faster with the guess function
        self.assertTrue(iters_with_guess < iters_no_guess)
Exemplo n.º 20
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    def test_keys(self):
        p = Problem()
        comp = IndepVarComp()
        comp.add_output('v1', val=1.0)
        comp.add_output('v2', val=2.0)
        p.model.add_subsystem('des_vars', comp, promotes=['*'])
        p.setup()
        p.final_setup()

        keys = sorted(p.model._outputs.keys())
        expected = ['des_vars.v1', 'des_vars.v2']

        self.assertListEqual(keys, expected, msg='keys() is not returning the expected names')
Exemplo n.º 21
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    def test_iter(self):
        p = Problem()
        comp = IndepVarComp()
        comp.add_output('v1', val=1.0)
        comp.add_output('v2', val=2.0)
        p.model.add_subsystem('des_vars', comp, promotes=['*'])
        p.setup()
        p.final_setup()

        outputs = [n for n in p.model._outputs]
        expected = ['des_vars.v1', 'des_vars.v2']

        self.assertListEqual(outputs, expected, msg='Iter is not returning the expected names')
Exemplo n.º 22
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    def test_dot(self):
        p = Problem()
        comp = IndepVarComp()
        comp.add_output('v1', val=1.0)
        comp.add_output('v2', val=2.0)
        p.model.add_subsystem('des_vars', comp, promotes=['*'])
        p.setup()
        p.final_setup()

        new_vec = p.model._outputs._clone()
        new_vec.set_const(3.)

        self.assertEqual(new_vec.dot(p.model._outputs), 9.)
Exemplo n.º 23
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    def test_scalar_with_guess_func_additional_input(self):

        n = 1

        prob = Problem(model=Group())

        bal = BalanceComp()

        bal.add_balance('x', guess_func=lambda inputs, resids: inputs['guess_x'])
        bal.add_input('guess_x', val=0.0)

        ivc = IndepVarComp()
        ivc.add_output(name='y_tgt', val=4)
        ivc.add_output(name='guess_x', val=2.5)

        exec_comp = ExecComp('y=x**2', x={'value': 1}, y={'value': 1})

        prob.model.add_subsystem(name='ivc', subsys=ivc, promotes_outputs=['y_tgt', 'guess_x'])

        prob.model.add_subsystem(name='exec', subsys=exec_comp)

        prob.model.add_subsystem(name='balance', subsys=bal)

        prob.model.connect('guess_x', 'balance.guess_x')
        prob.model.connect('y_tgt', 'balance.rhs:x')
        prob.model.connect('balance.x', 'exec.x')
        prob.model.connect('exec.y', 'balance.lhs:x')

        prob.model.linear_solver = DirectSolver()

        prob.model.nonlinear_solver = NewtonSolver()
        prob.model.nonlinear_solver.options['maxiter'] = 100
        prob.model.nonlinear_solver.options['iprint'] = 0

        prob.model.jacobian = DenseJacobian()

        prob.setup()

        prob['balance.x'] = np.random.rand(n)

        prob.run_model()

        assert_almost_equal(prob['balance.x'], 2.0, decimal=7)

        np.set_printoptions(linewidth=1024)

        cpd = prob.check_partials()

        for (of, wrt) in cpd['balance']:
            assert_almost_equal(cpd['balance'][of, wrt]['abs error'], 0.0, decimal=5)
Exemplo n.º 24
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    def test_add_output_type_bug(self):
        prob = Problem()
        model = prob.model

        ivc = IndepVarComp()
        ivc.add_output('x1', val=[1, 2, 3], lower=0, upper=10)

        model.add_subsystem('p', ivc)

        prob.setup()

        prob['p.x1'][0] = 0.5
        prob.run_model()

        assert_rel_error(self, prob['p.x1'][0], 0.5)
Exemplo n.º 25
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    def test(self):
        surface = get_default_surfaces()[0]
        ny = surface['mesh'].shape[1]

        group = Group()

        ivc = IndepVarComp()
        ivc.add_output('nodes', val=np.random.random_sample((ny, 3)))

        comp = Weight(surface=surface)

        group.add_subsystem('ivc', ivc, promotes=['*'])
        group.add_subsystem('comp', comp, promotes=['*'])

        run_test(self, group, compact_print=False, complex_flag=True)
Exemplo n.º 26
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    def test(self):
        """
        An example demonstrating a trivial use case of DemuxComp
        """
        import numpy as np
        from openmdao.api import Problem, Group, IndepVarComp, DemuxComp, ExecComp
        from openmdao.utils.assert_utils import assert_rel_error

        # The number of elements to be demuxed
        n = 3

        # The size of each element to be demuxed
        m = 100

        p = Problem(model=Group())

        ivc = IndepVarComp()
        ivc.add_output(name='pos_ecef', shape=(m, 3), units='km')

        p.model.add_subsystem(name='ivc',
                              subsys=ivc,
                              promotes_outputs=['pos_ecef'])

        mux_comp = p.model.add_subsystem(name='demux',
                                         subsys=DemuxComp(vec_size=n))

        mux_comp.add_var('pos', shape=(m, n), axis=1, units='km')

        p.model.add_subsystem(name='longitude_comp',
                              subsys=ExecComp('long = atan(y/x)',
                                              x={'value': np.ones(m), 'units': 'km'},
                                              y={'value': np.ones(m), 'units': 'km'},
                                              long={'value': np.ones(m), 'units': 'rad'}))

        p.model.connect('demux.pos_0', 'longitude_comp.x')
        p.model.connect('demux.pos_1', 'longitude_comp.y')
        p.model.connect('pos_ecef', 'demux.pos')

        p.setup()

        p['pos_ecef'][:, 0] = 6378 * np.cos(np.linspace(0, 2*np.pi, m))
        p['pos_ecef'][:, 1] = 6378 * np.sin(np.linspace(0, 2*np.pi, m))
        p['pos_ecef'][:, 2] = 0.0

        p.run_model()

        expected = np.arctan(p['pos_ecef'][:, 1] / p['pos_ecef'][:, 0])
        assert_rel_error(self, p.get_val('longitude_comp.long'), expected)
Exemplo n.º 27
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    def test_dot_petsc(self):
        if not PETScVector:
            raise unittest.SkipTest("PETSc is not installed")

        p = Problem()
        comp = IndepVarComp()
        comp.add_output('v1', val=1.0)
        comp.add_output('v2', val=2.0)
        p.model.add_subsystem('des_vars', comp, promotes=['*'])
        p.setup()
        p.final_setup()

        new_vec = p.model._outputs._clone()
        new_vec.set_const(3.)

        self.assertEqual(new_vec.dot(p.model._outputs), 9.)
Exemplo n.º 28
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    def test_debug_after_raised_error(self):
        prob = Problem()
        model = prob.model

        comp = IndepVarComp()
        comp.add_output('dXdt:TAS', val=1.0)
        comp.add_output('accel_target', val=2.0)
        model.add_subsystem('des_vars', comp, promotes=['*'])

        teg = model.add_subsystem('thrust_equilibrium_group', subsys=Group())
        teg.add_subsystem('dynamics', ExecComp('z = 2.0*thrust'), promotes=['*'])

        thrust_bal = BalanceComp()
        thrust_bal.add_balance(name='thrust', val=1207.1, lhs_name='dXdt:TAS',
                               rhs_name='accel_target', eq_units='m/s**2', lower=-10.0, upper=10000.0)

        teg.add_subsystem(name='thrust_bal', subsys=thrust_bal,
                          promotes_inputs=['dXdt:TAS', 'accel_target'],
                          promotes_outputs=['thrust'])

        teg.linear_solver = DirectSolver()

        teg.nonlinear_solver = NewtonSolver()
        teg.nonlinear_solver.options['solve_subsystems'] = True
        teg.nonlinear_solver.options['max_sub_solves'] = 1
        teg.nonlinear_solver.options['atol'] = 1e-4
        teg.nonlinear_solver.options['debug_print'] = True

        prob.setup(check=False)
        prob.set_solver_print(level=0)

        stdout = sys.stdout
        strout = StringIO()
        sys.stdout = strout

        with self.assertRaises(RuntimeError) as cm:
            prob.run_model()

        sys.stdout = stdout

        output = strout.getvalue()
        target = "'thrust_equilibrium_group.thrust_bal.thrust'"
        self.assertTrue(target in output, msg=target + "NOT FOUND IN" + output)

        # Make sure exception is unchanged.
        expected_msg = "Singular entry found in 'thrust_equilibrium_group' for row associated with state/residual 'thrust'."
        self.assertEqual(expected_msg, str(cm.exception))
Exemplo n.º 29
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    def test(self):
        surfaces = get_default_surfaces()

        group = Group()

        comp = VLMGeometry(surface=surfaces[0])

        indep_var_comp = IndepVarComp()

        indep_var_comp.add_output('def_mesh', val=surfaces[0]['mesh'], units='m')

        group.add_subsystem('geom', comp)
        group.add_subsystem('indep_var_comp', indep_var_comp)

        group.connect('indep_var_comp.def_mesh', 'geom.def_mesh')

        run_test(self, group)
    def test2(self):
        surfaces = get_default_surfaces()

        group = Group()

        comp = MomentCoefficient(surfaces=surfaces)

        indep_var_comp = IndepVarComp()

        indep_var_comp.add_output('S_ref_total', val=1e4, units='m**2')

        group.add_subsystem('moment_calc', comp)
        group.add_subsystem('indep_var_comp', indep_var_comp)

        group.connect('indep_var_comp.S_ref_total', 'moment_calc.S_ref_total')

        run_test(self, group)
Exemplo n.º 31
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    def test_group_assembled_jac_with_ext_mat(self):
        class TwoSellarDis1(ExplicitComponent):
            """
            Component containing Discipline 1 -- no derivatives version.
            """
            def setup(self):
                self.add_input('z', val=np.zeros(2))
                self.add_input('x', val=np.zeros(2))
                self.add_input('y2', val=np.ones(2))
                self.add_output('y1', val=np.ones(2))

                self.declare_partials(of='*', wrt='*')

            def compute(self, inputs, outputs):
                z1 = inputs['z'][0]
                z2 = inputs['z'][1]
                x1 = inputs['x']
                y2 = inputs['y2']

                outputs['y1'][0] = z1**2 + z2 + x1[0] - 0.2 * y2[0]
                outputs['y1'][1] = z1**2 + z2 + x1[0] - 0.2 * y2[0]

            def compute_partials(self, inputs, partials):
                """
                Jacobian for Sellar discipline 1.
                """
                partials['y1', 'y2'] = np.array([[-0.2, 0.], [0., -0.2]])
                partials['y1', 'z'] = np.array([[2.0 * inputs['z'][0], 1.0],
                                                [2.0 * inputs['z'][0], 1.0]])
                partials['y1', 'x'] = np.eye(2)

        class TwoSellarDis2(ExplicitComponent):
            def setup(self):
                self.add_input('z', val=np.zeros(2))
                self.add_input('y1', val=np.ones(2))
                self.add_output('y2', val=np.ones(2))

                self.declare_partials('*', '*', method='fd')

            def compute(self, inputs, outputs):

                z1 = inputs['z'][0]
                z2 = inputs['z'][1]
                y1 = inputs['y1']

                # Note: this may cause some issues. However, y1 is constrained to be
                # above 3.16, so lets just let it converge, and the optimizer will
                # throw it out
                if y1[0].real < 0.0:
                    y1[0] *= -1
                if y1[1].real < 0.0:
                    y1[1] *= -1

                outputs['y2'][0] = y1[0]**.5 + z1 + z2
                outputs['y2'][1] = y1[1]**.5 + z1 + z2

            def compute_partials(self, inputs, J):
                y1 = inputs['y1']
                if y1[0].real < 0.0:
                    y1[0] *= -1
                if y1[1].real < 0.0:
                    y1[1] *= -1

                J['y2', 'y1'] = np.array([[.5 * y1[0]**-.5, 0.],
                                          [0., .5 * y1[1]**-.5]])
                J['y2', 'z'] = np.array([[1.0, 1.0], [1.0, 1.0]])

        prob = Problem()
        model = prob.model

        model.add_subsystem('px',
                            IndepVarComp('x', np.array([1.0, 1.0])),
                            promotes=['x'])
        model.add_subsystem('pz',
                            IndepVarComp('z', np.array([5.0, 2.0])),
                            promotes=['z'])
        sup = model.add_subsystem('sup', Group(), promotes=['*'])

        sub1 = sup.add_subsystem('sub1', Group(), promotes=['*'])
        sub2 = sup.add_subsystem('sub2', Group(), promotes=['*'])

        d1 = sub1.add_subsystem('d1',
                                TwoSellarDis1(),
                                promotes=['x', 'z', 'y1', 'y2'])
        sub2.add_subsystem('d2', TwoSellarDis2(), promotes=['z', 'y1', 'y2'])

        model.add_subsystem('con_cmp1',
                            ExecComp('con1 = 3.16 - y1[0] - y1[1]',
                                     y1=np.array([0.0, 0.0])),
                            promotes=['con1', 'y1'])
        model.add_subsystem('con_cmp2',
                            ExecComp('con2 = y2[0] + y2[1] - 24.0',
                                     y2=np.array([0.0, 0.0])),
                            promotes=['con2', 'y2'])

        model.linear_solver = LinearBlockGS()
        sup.linear_solver = LinearBlockGS()

        sub1.linear_solver = DirectSolver(assemble_jac=True)
        sub2.linear_solver = DirectSolver(assemble_jac=True)
        prob.set_solver_print(level=0)

        prob.setup(check=False, mode='rev')
        prob.run_model()

        of = ['con1', 'con2']
        wrt = ['x', 'z']

        # Make sure we don't get a size mismatch.
        derivs = prob.compute_totals(of=of, wrt=wrt)
Exemplo n.º 32
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    def test_model_path_and_recursion(self):

        from openmdao.api import Problem, IndepVarComp

        p = Problem()
        model = p.model

        group = model.add_subsystem('G1', Group(), promotes=['*'])
        group2 = model.add_subsystem('G2', Group())
        group.add_subsystem('ground', IndepVarComp('V', 0., units='V'))
        group.add_subsystem('source', IndepVarComp('I', 0.1, units='A'))
        group2.add_subsystem('source2', IndepVarComp('I', 0.1, units='A'))
        group.add_subsystem('circuit', Circuit())

        group.connect('source.I', 'circuit.I_in')
        group.connect('ground.V', 'circuit.Vg')

        model.add_design_var('ground.V')
        model.add_design_var('source.I')
        model.add_objective('circuit.D1.I')

        p.setup(check=False)

        # set some initial guesses
        p['circuit.n1.V'] = 10.
        p['circuit.n2.V'] = 1.

        p.run_model()

        # No model path, no recursion
        write_xdsm(p,
                   'xdsm_circuit',
                   out_format=PYXDSM_OUT,
                   quiet=QUIET,
                   show_browser=SHOW,
                   recurse=False)
        self.assertTrue(os.path.isfile('.'.join(['xdsm_circuit', PYXDSM_OUT])))

        # Model path given + recursion
        write_xdsm(p,
                   'xdsm_circuit2',
                   out_format=PYXDSM_OUT,
                   quiet=QUIET,
                   show_browser=SHOW,
                   recurse=True,
                   model_path='G2',
                   include_external_outputs=False)
        self.assertTrue(os.path.isfile('.'.join(['xdsm_circuit2',
                                                 PYXDSM_OUT])))

        # Model path given + no recursion
        write_xdsm(p,
                   'xdsm_circuit3',
                   out_format=PYXDSM_OUT,
                   quiet=QUIET,
                   show_browser=SHOW,
                   recurse=False,
                   model_path='G1')
        self.assertTrue(os.path.isfile('.'.join(['xdsm_circuit3',
                                                 PYXDSM_OUT])))

        # Invalid model path, should raise error
        with self.assertRaises(ValueError):
            write_xdsm(p,
                       'xdsm_circuit4',
                       out_format='tex',
                       quiet=QUIET,
                       show_browser=SHOW,
                       recurse=False,
                       model_path='G3')
Exemplo n.º 33
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    def test_csc_masking(self):
        class CCBladeResidualComp(ImplicitComponent):
            def initialize(self):
                self.options.declare('num_nodes', types=int)
                self.options.declare('num_radial', types=int)

            def setup(self):
                num_nodes = self.options['num_nodes']
                num_radial = self.options['num_radial']

                self.add_input('chord', shape=(1, num_radial))
                self.add_input('theta', shape=(1, num_radial))

                self.add_output('phi',
                                lower=-0.5 * np.pi,
                                upper=0.0,
                                shape=(num_nodes, num_radial))
                self.add_output('Tp', shape=(num_nodes, num_radial))

                of_names = ('phi', 'Tp')
                row_col = np.arange(num_radial)

                for name in of_names:
                    self.declare_partials(name,
                                          'chord',
                                          rows=row_col,
                                          cols=row_col)
                    self.declare_partials(name,
                                          'theta',
                                          rows=row_col,
                                          cols=row_col,
                                          val=0.0)
                    self.declare_partials(name,
                                          'phi',
                                          rows=row_col,
                                          cols=row_col)

                self.declare_partials('Tp',
                                      'Tp',
                                      rows=row_col,
                                      cols=row_col,
                                      val=1.)

            def linearize(self, inputs, outputs, partials):

                partials['phi', 'chord'] = np.array([1., 2, 3, 4])
                partials['phi', 'phi'] = np.array([5., 6, 7, 8])

                partials['Tp', 'chord'] = np.array([9., 10, 11, 12])
                partials['Tp', 'phi'] = np.array([13., 14, 15, 16])

        prob = Problem()
        model = prob.model

        comp = IndepVarComp()
        comp.add_output('chord', val=np.ones((4, )))
        model.add_subsystem('indep_var_comp', comp, promotes=['*'])

        comp = CCBladeResidualComp(num_nodes=1,
                                   num_radial=4,
                                   assembled_jac_type='csc')

        comp.linear_solver = DirectSolver(assemble_jac=True)
        model.add_subsystem('ccblade_comp',
                            comp,
                            promotes_inputs=['chord'],
                            promotes_outputs=['Tp'])

        prob.setup(mode='fwd')
        prob.run_model()
        totals = prob.compute_totals(of=['Tp'],
                                     wrt=['chord'],
                                     return_format='array')

        expected = np.array([[-6.4, 0., 0., 0.], [0., -5.33333333, 0., 0.],
                             [0., 0., -4.57142857, 0.], [0., 0., 0., -4.]])

        np.testing.assert_allclose(totals, expected)
    apoints_coord = aero_problem_params.apoints_coord
    
    geom_propts = GeometricalProperties(Ln,Vn,tn,an,sn,t_0,l_0,s_0_tot,Ix_0_tot,Iy_0_tot)
    
    t = geom_propts.t
    a = geom_propts.a
    s = geom_propts.s
    Ix = geom_propts.Ix
    Iy = geom_propts.Iy
        
    top = Problem()
    top.root = root = Group()

    #Add independent variables
    root.add('wing_area', IndepVarComp('Sw', Sw), promotes=['*'])
    root.add('airspeed', IndepVarComp('V', V), promotes=['*'])
    root.add('air_density', IndepVarComp('rho_a', rho_a), promotes=['*'])
    root.add('Mach_number', IndepVarComp('Mach', Mach), promotes=['*'])
    root.add('angle_of_attack', IndepVarComp('alpha', alpha), promotes=['*'])
    root.add('wing_span', IndepVarComp('b', b), promotes=['*'])
    root.add('wing_chord', IndepVarComp('c', c), promotes=['*'])
    root.add('s_coord', IndepVarComp('node_coord', node_coord), promotes=['*'])
    root.add('s_coord_all', IndepVarComp('node_coord_all', node_coord_all), promotes=['*'])
    root.add('a_coord', IndepVarComp('apoints_coord', apoints_coord), promotes=['*'])
    root.add('load_factor', IndepVarComp('n', n), promotes=['*'])
    
    root.add('thicknesses', IndepVarComp('t', t), promotes=['*'])
    if an > 0:
        root.add('rod_sections', IndepVarComp('a', a), promotes=['*'])   
    root.add('bar_sections', IndepVarComp('s', s), promotes=['*'])
Exemplo n.º 35
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        Length = L1 + L2
        Width = W1 + W2
        Height = H1 + H2
        Volume = Length * Width * Height
        Mass = L1 * W1 * H1 * D1 + L2 * W2 * H2 * D2
        return (Length, Width, Height, Volume, Mass)


if __name__ == "__main__":

    top = Problem()

    root = top.root = Group()

    # TODO: Add reasonable input values for testing purposes
    root.add('L1', IndepVarComp('y', 1.0))
    root.add('W1', IndepVarComp('y', 2.0))
    root.add('H1', IndepVarComp('y', 3.0))
    root.add('L2', IndepVarComp('y', 4.0))
    root.add('W2', IndepVarComp('y', 5.0))
    root.add('H2', IndepVarComp('y', 6.0))

    root.add('Optimize_Container', Optimize_Container())

    root.connect('L1.y', 'Optimize_Container.L1')
    root.connect('W1.y', 'Optimize_Container.W1')
    root.connect('H1.y', 'Optimize_Container.H1')
    root.connect('L2.y', 'Optimize_Container.L2')
    root.connect('W2.y', 'Optimize_Container.W2')
    root.connect('H2.y', 'Optimize_Container.H2')
Exemplo n.º 36
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    def compute_partials(self, inputs, partials):
        x = inputs['x']
        derivs = partials['y', 'x'].reshape((num_nodes, 2))
        derivs[:, 0] = np.cos(x[:, 0])
        derivs[:, 1] = -np.sin(x[:, 1])


if __name__ == '__main__':
    from openmdao.api import Problem, IndepVarComp
    
    num_nodes = 5

    prob = Problem()

    comp = IndepVarComp()
    comp.add_output('x', val=np.random.random((num_nodes, 2)))
    prob.model.add_subsystem('ivc', comp, promotes=['*'])
                    
    comp = CosComp(num_nodes=num_nodes)
    prob.model.add_subsystem('cos_comp', comp, promotes=['*'])
    
    prob.setup()
                    
    prob.run_model()

    print(prob['x'])
    print(prob['y'])

    prob.check_partials(compact_print=True)
Exemplo n.º 37
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        self.connect('D1.I', 'n2.I_out:0')

        self.nonlinear_solver = NewtonSolver()
        self.nonlinear_solver.options['iprint'] = 2
        self.nonlinear_solver.options['maxiter'] = 20
        self.linear_solver = DirectSolver()


if __name__ == "__main__":
    from openmdao.api import ArmijoGoldsteinLS, Problem, IndepVarComp, BalanceComp, ExecComp
    from openmdao.api import NewtonSolver, DirectSolver, NonlinearRunOnce, LinearRunOnce

    p = Problem()
    model = p.model

    model.add_subsystem('ground', IndepVarComp('V', 0., units='V'))

    # replacing the fixed current source with a BalanceComp to represent a fixed Voltage source
    # model.add_subsystem('source', IndepVarComp('I', 0.1, units='A'))
    model.add_subsystem('batt', IndepVarComp('V', 1.5, units='V'))
    bal = model.add_subsystem('batt_balance', BalanceComp())
    bal.add_balance('I', units='A', eq_units='V')

    model.add_subsystem('circuit', Circuit())
    model.add_subsystem('batt_deltaV', ExecComp('dV = V1 - V2', V1={'units':'V'}, V2={'units':'V'}, dV={'units':'V'}))

    # current into the circuit is now the output state from the batt_balance comp
    model.connect('batt_balance.I', 'circuit.I_in')
    model.connect('ground.V', ['circuit.Vg','batt_deltaV.V2'])
    model.connect('circuit.n1.V', 'batt_deltaV.V1')
Exemplo n.º 38
0
        sum([j * j for j in xrange(10000000)])  # dummy delay (busy loop)
        unknowns['y'] = params['c'] * params['x']


if __name__ == "__main__":

    if MPI:  # pragma: no cover
        # if you called this script with 'mpirun', then use the petsc data passing
        from openmdao.core.petsc_impl import PetscImpl as impl
    else:
        # if you didn't use `mpirun`, then use the numpy data passing
        from openmdao.api import BasicImpl as impl

    problem = Problem(impl=impl)
    root = problem.root = Group()
    root.add('indep_var', IndepVarComp('x', val=7.0))
    root.add('const', IndepVarComp('c', val=3.0, pass_by_obj=False))
    root.add('dut', DUT())

    root.connect('indep_var.x', 'dut.x')
    root.connect('const.c', 'dut.c')

    problem.driver = UniformDriver(num_samples=10, num_par_doe=5)
    problem.driver.add_desvar('indep_var.x', low=4410.0, high=4450.0)
    problem.driver.add_objective('dut.y')

    recorder = DumpRecorder()
    problem.driver.add_recorder(recorder)

    problem.setup()
    problem.run()
Exemplo n.º 39
0
    # Define Parameters
    params = (('m_pod', 3000.0, {
        'units': 'kg'
    }), ('l_pod', 22.0, {
        'units': 'm'
    }), ('d_pod', 1.0, {
        'units': 'm'
    }), ('vel_b', 23.0, {
        'units': 'm/s'
    }), ('h_lev', 0.01, {
        'unit': 'm'
    }), ('vel', 350.0, {
        'units': 'm/s'
    }))

    prob.root.add('input_vars', IndepVarComp(params))

    # Constraint Equation
    #root.add('con1', ExecComp('c1 = (fyu - m_pod * g)/1e5'))

    # Connect
    #prob.root.connect('lev.Drag.fyu', 'con1.fyu')
    #prob.root.connect('lev.Drag.g', 'con1.g')

    prob.root.connect('input_vars.m_pod', 'lev.m_pod')
    #prob.root.connect('lev.m_pod', 'con1.m_pod')
    prob.root.connect('input_vars.l_pod', 'lev.l_pod')
    prob.root.connect('input_vars.d_pod', 'lev.d_pod')
    prob.root.connect('input_vars.vel_b', 'lev.vel_b')
    prob.root.connect('input_vars.h_lev', 'lev.h_lev')
    prob.root.connect('input_vars.vel', 'lev.vel')
Exemplo n.º 40
0
    def test_case1(self):

        prob = Problem()
        model = prob.model = Cycle()
        model.options['thermo_method'] = 'CEA'
        model.options['thermo_data'] = species_data.janaf

        model.add_subsystem(
            'ivc',
            IndepVarComp('in_composition', [
                3.23319235e-04, 1.10132233e-05, 5.39157698e-02, 1.44860137e-02
            ]))

        model.add_subsystem('flow_start', FlowStart())
        model.add_subsystem('combustor', Combustor())

        model.pyc_connect_flow('flow_start.Fl_O', 'combustor.Fl_I')

        # model.set_input_defaults('Fl_I:tot:P', 100.0, units='lbf/inch**2')
        # model.set_input_defaults('Fl_I:tot:h', 100.0, units='Btu/lbm')
        # model.set_input_defaults('Fl_I:stat:W', 100.0, units='lbm/s')
        model.set_input_defaults('combustor.Fl_I:FAR', 0.0)
        model.set_input_defaults('combustor.MN', 0.5)

        # needed because composition is sized by connection
        # model.connect('ivc.in_composition', ['Fl_I:tot:composition', 'Fl_I:stat:composition', ])

        prob.set_solver_print(level=2)
        prob.setup(check=False, force_alloc_complex=True)

        # 6 cases to check against
        for i, data in enumerate(ref_data):

            # input flowstation
            # prob['Fl_I:tot:P'] = data[h_map['Fl_I.Pt']]
            # prob['Fl_I:tot:h'] = data[h_map['Fl_I.ht']]
            # prob['Fl_I:stat:W'] = data[h_map['Fl_I.W']]
            # prob['Fl_I:FAR'] = data[h_map['FAR']]
            prob.set_val('flow_start.P', data[h_map['Fl_I.Pt']], units='psi')
            prob.set_val('flow_start.T', data[h_map['Fl_I.Tt']], units='degR')
            prob.set_val('flow_start.W', data[h_map['Fl_I.W']], units='lbm/s')
            prob['combustor.Fl_I:FAR'] = data[h_map['FAR']]
            prob['combustor.MN'] = data[h_map['Fl_O.MN']]

            prob.run_model()

            # prob.model.combustor.mix_fuel.list_inputs(print_arrays=True)
            # prob.model.combustor.mix_fuel.list_outputs(print_arrays=True)
            # print(prob['combustor.Fl_I:tot:composition'])
            # print(prob['combustor.Fl_I:tot:n'])
            print(prob['combustor.Fl_I:tot:h'])
            print(prob['combustor.Fl_I:tot:P'])
            # exit()

            # check outputs
            tol = 1.0e-2

            npss = data[h_map['Fl_O.Pt']]
            pyc = prob['combustor.Fl_O:tot:P']
            rel_err = abs(npss - pyc) / npss
            print('Pt out:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            npss = data[h_map['Fl_O.Tt']]
            pyc = prob['combustor.Fl_O:tot:T']
            rel_err = abs(npss - pyc) / npss
            print('Tt out:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            npss = data[h_map['Fl_O.ht']]
            pyc = prob['combustor.Fl_O:tot:h']
            rel_err = abs(npss - pyc) / npss
            print('ht out:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            npss = data[h_map['Fl_O.Ps']]
            pyc = prob['combustor.Fl_O:stat:P']
            rel_err = abs(npss - pyc) / npss
            print('Ps out:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            npss = data[h_map['Fl_O.Ts']]
            pyc = prob['combustor.Fl_O:stat:T']
            rel_err = abs(npss - pyc) / npss
            print('Ts out:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            npss = data[h_map['Wfuel']]
            pyc = prob['combustor.Fl_I:stat:W'] * (prob['combustor.Fl_I:FAR'])
            rel_err = abs(npss - pyc) / npss
            print('Wfuel:', npss, pyc, rel_err)
            self.assertLessEqual(rel_err, tol)

            print('')

            partial_data = prob.check_partials(out_stream=None,
                                               method='cs',
                                               includes=[
                                                   'combustor.*',
                                               ],
                                               excludes=[
                                                   '*.base_thermo.*',
                                               ])
            assert_check_partials(partial_data, atol=1e-8, rtol=1e-8)
Exemplo n.º 41
0
    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':
            True,
            # 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 = Problem()

        # Add problem information as an independent variables component
        indep_var_comp = 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')
        indep_var_comp.add_output('fuel_mass', val=10000., units='kg')

        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:

                prob.model.connect('load_factor', name + '.load_factor')
                prob.model.connect('load_factor',
                                   point_name + '.coupled.load_factor')

                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_weights',
                    point_name + '.coupled.' + name + '.element_weights')

                # 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_weight', point_name + '.' +
                    'total_perf.' + name + '_structural_weight')

                # 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.model.connect(
                'wing.struct_setup.fuel_vols',
                'AS_point_0.coupled.wing.struct_states.fuel_vols')
            prob.model.connect(
                'fuel_mass', 'AS_point_0.coupled.wing.struct_states.fuel_mass')

            comp = ExecComp('fuel_diff = (fuel_mass - fuelburn) / fuelburn',
                            fuel_mass={
                                'value': 1.0,
                                'units': 'kg'
                            },
                            fuelburn={
                                'value': 1.0,
                                'units': 'kg'
                            })
            prob.model.add_subsystem('fuel_diff',
                                     comp,
                                     promotes_inputs=['fuel_mass'],
                                     promotes_outputs=['fuel_diff'])
            prob.model.connect('AS_point_0.fuelburn', 'fuel_diff.fuelburn')
            #=======================================================================================
            #=======================================================================================

        from openmdao.api import ScipyOptimizeDriver
        prob.driver = ScipyOptimizeDriver()
        prob.driver.options['tol'] = 1e-9
        prob.driver.options['maxiter'] = 2

        # from openmdao.api import pyOptSparseDriver
        # prob.driver = pyOptSparseDriver()
        # prob.driver.add_recorder(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_design_var('fuel_mass',
                                  lower=0.,
                                  upper=2e5,
                                  scaler=1e-5)

        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.)
        prob.model.add_constraint('fuel_diff', equals=0.)
        #=======================================================================================
        #=======================================================================================

        # Set up the problem
        prob.setup()

        # from openmdao.api import view_model
        # view_model(prob)

        prob.run_model()

        # Check the partials at the initial point in the design space,
        # only care about relative error
        data = prob.check_partials(compact_print=True,
                                   out_stream=None,
                                   method='cs',
                                   step=1e-40)

        assert_check_partials(data, atol=1e20, rtol=1e-6)

        # Run the optimizer for 2 iterations
        prob.run_driver()

        # Check the partials at this point in the design space
        data = prob.check_partials(compact_print=True,
                                   out_stream=None,
                                   method='cs',
                                   step=1e-40)
        assert_check_partials(data, atol=1e20, rtol=1e-6)
Exemplo n.º 42
0
    def test_opt_over_doe_uq(self):
        np.random.seed(42)

        prob = Problem(impl=impl, root=Group())
        prob.root.deriv_options['type'] = 'fd'

        subprob = Problem(impl=impl, root=SellarDerivatives())
        subprob.root.deriv_options['type'] = 'fd'

        if MPI:
            npardoe = self.N_PROCS
        else:
            npardoe = 1

        subprob.driver = UQTestDriver(nsamples=100, num_par_doe=npardoe)
        subprob.driver.add_desvar('z', std_dev=1e-2)
        subprob.driver.add_desvar('x', std_dev=1e-2)
        subprob.driver.add_response('obj')
        subprob.driver.add_response('con1')
        subprob.driver.add_response('con2')

        #subprob.driver.recorders.append(SqliteRecorder("subsellar.db"))

        prob.root.add("indeps",
                      IndepVarComp([('x', 1.0), ('z', np.array([5.0, 2.0]))]),
                      promotes=['x', 'z'])
        prob.root.add(
            "sub",
            SubProblem(subprob,
                       params=['z', 'x'],
                       unknowns=['obj', 'con1', 'con2']))

        prob.root.connect('x', 'sub.x')
        prob.root.connect('z', 'sub.z')

        # top level driver setup
        prob.driver = ScipyOptimizer()
        prob.driver.options['optimizer'] = 'SLSQP'
        prob.driver.options['tol'] = 1.0e-8
        prob.driver.options['maxiter'] = 50
        prob.driver.options['disp'] = False

        prob.driver.add_desvar('z',
                               lower=np.array([-10.0, 0.0]),
                               upper=np.array([10.0, 10.0]))
        prob.driver.add_desvar('x', lower=0.0, upper=10.0)

        prob.driver.add_objective('sub.obj')
        prob.driver.add_constraint('sub.con1', upper=0.0)
        prob.driver.add_constraint('sub.con2', upper=0.0)

        #prob.driver.recorders.append(SqliteRecorder("sellar.db"))

        prob.setup(check=False)

        prob.run()

        tol = 1.e-3
        assert_rel_error(self, prob['sub.obj'], 3.1833940, tol)
        assert_rel_error(self, prob['z'][0], 1.977639, tol)
        assert_rel_error(self, prob['z'][1], 0.0, tol)
        assert_rel_error(self, prob['x'], 0.0, tol)
    def test(self):

        # 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' : 5}

        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' : 'tube',

                    'twist_cp' : twist_cp,
                    'mesh' : mesh,

                    # 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' : 0.015,            # 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([0.15]),      # thickness over chord ratio (NACA0015)
                    'c_max_t' : .303,       # chordwise location of maximum (NACA0015)
                                            # thickness
                    'with_viscous' : True,  # if true, compute viscous drag
                    'with_wave' : False,     # if true, compute wave drag
                    }

        # Create a dictionary to store options about the surface
        mesh_dict = {'num_y' : 7,
                     'num_x' : 2,
                     'wing_type' : 'rect',
                     'symmetry' : True,
                     'offset' : np.array([50, 0., 0.])}

        mesh = generate_mesh(mesh_dict)

        surf_dict2 = {
                    # Wing definition
                    'name' : 'tail',        # 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'

                    'twist_cp' : twist_cp,
                    'mesh' : mesh,

                    # 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' : 0.0,            # CD of the surface at alpha=0

                    'fem_origin' : 0.35,

                    # 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([0.15]),      # thickness over chord ratio (NACA0015)
                    'c_max_t' : .303,       # chordwise location of maximum (NACA0015)
                                            # thickness
                    'with_viscous' : True,  # if true, compute viscous drag
                    'with_wave' : False,     # if true, compute wave drag
                    }

        surfaces = [surf_dict, surf_dict2]

        # Create the problem and the model group
        prob = Problem()

        indep_var_comp = IndepVarComp()
        indep_var_comp.add_output('v', val=248.136, units='m/s')
        indep_var_comp.add_output('alpha', val=5., units='deg')
        indep_var_comp.add_output('Mach_number', val=0.84)
        indep_var_comp.add_output('re', val=1.e6, units='1/m')
        indep_var_comp.add_output('rho', val=0.38, units='kg/m**3')
        indep_var_comp.add_output('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:

            geom_group = Geometry(surface=surface)

            # Add tmp_group to the problem as the name of the surface.
            # Note that is a group and performance group for each
            # individual surface.
            prob.model.add_subsystem(surface['name'], geom_group)

        # Loop through and add a certain number of aero points
        for i in range(1):

            # Create the aero point group and add it to the model
            aero_group = AeroPoint(surfaces=surfaces)
            point_name = 'aero_point_{}'.format(i)
            prob.model.add_subsystem(point_name, aero_group)

            # 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('cg', point_name + '.cg')

            # Connect the parameters within the model for each aero point
            for surface in surfaces:

                name = surface['name']

                # Connect the mesh from the geometry component to the analysis point
                prob.model.connect(name + '.mesh', point_name + '.' + name + '.def_mesh')

                # Perform the connections with the modified names within the
                # 'aero_states' group.
                prob.model.connect(name + '.mesh', point_name + '.aero_states.' + name + '_def_mesh')

                prob.model.connect(name + '.t_over_c', point_name + '.' + name + '_perf.' + 't_over_c')

        # Set up the problem
        prob.setup()

        prob.run_model()

        assert_rel_error(self, prob['aero_point_0.wing_perf.CD'][0], 0.037210478659832125, 1e-6)
        assert_rel_error(self, prob['aero_point_0.wing_perf.CL'][0], 0.5124736932248048, 1e-6)
        assert_rel_error(self, prob['aero_point_0.CM'][1], -1.7028233361964462, 1e-6)
Exemplo n.º 44
0
    def test_fan_out_grouped(self):

        prob = Problem(impl=impl)
        prob.root = root = Group()

        root.add('p', IndepVarComp('x', 1.0))
        root.add('comp1', ExecComp(['y=3.0*x']))

        sub = root.add('sub', ParallelGroup())
        sub.add('comp2', ExecComp(['y=-2.0*x']))
        sub.add('comp3', ExecComp(['y=5.0*x']))

        root.add('c2', ExecComp(['y=-x']))
        root.add('c3', ExecComp(['y=3.0*x']))
        root.connect('sub.comp2.y', 'c2.x')
        root.connect('sub.comp3.y', 'c3.x')

        root.connect("comp1.y", "sub.comp2.x")
        root.connect("comp1.y", "sub.comp3.x")
        root.connect("p.x", "comp1.x")

        prob.root.ln_solver = LinearGaussSeidel()
        prob.root.sub.ln_solver = LinearGaussSeidel()

        prob.setup(check=False)
        prob.run()

        param = 'p.x'
        unknown_list = ['sub.comp2.y', "sub.comp3.y"]

        J = prob.calc_gradient([param],
                               unknown_list,
                               mode='fwd',
                               return_format='dict')

        assert_rel_error(self, J[unknown_list[0]][param][0][0], -6.0, 1e-6)
        assert_rel_error(self, J[unknown_list[1]][param][0][0], 15.0, 1e-6)

        J = prob.calc_gradient([param],
                               unknown_list,
                               mode='rev',
                               return_format='dict')
        assert_rel_error(self, J[unknown_list[0]][param][0][0], -6.0, 1e-6)
        assert_rel_error(self, J[unknown_list[1]][param][0][0], 15.0, 1e-6)

        unknown_list = ['c2.y', "c3.y"]

        J = prob.calc_gradient([param],
                               unknown_list,
                               mode='fwd',
                               return_format='dict')

        assert_rel_error(self, J[unknown_list[0]][param][0][0], 6.0, 1e-6)
        assert_rel_error(self, J[unknown_list[1]][param][0][0], 45.0, 1e-6)

        J = prob.calc_gradient([param],
                               unknown_list,
                               mode='rev',
                               return_format='dict')
        assert_rel_error(self, J[unknown_list[0]][param][0][0], 6.0, 1e-6)
        assert_rel_error(self, J[unknown_list[1]][param][0][0], 45.0, 1e-6)
Exemplo n.º 45
0
 def add_subsystems(self):
     self.add_subsystem('A', IndepVarComp('x', 0.))
     self.add_subsystem('B', CompB())
     self.connect('A.x', 'B.x')
Exemplo n.º 46
0
    def test(self):

        from openaerostruct.geometry.utils import generate_mesh, write_FFD_file
        from openaerostruct.geometry.geometry_group import Geometry
        from openaerostruct.transfer.displacement_transfer import DisplacementTransfer

        from openaerostruct.aerodynamics.aero_groups import AeroPoint
        from openaerostruct.integration.multipoint_comps import MultiCD, GeomMatch

        from openmdao.api import IndepVarComp, Problem, Group, NewtonSolver, ScipyIterativeSolver, LinearBlockGS, NonlinearBlockGS, DirectSolver, LinearBlockGS, PetscKSP, ScipyOptimizeDriver, ExplicitComponent  # TODO, SqliteRecorder, CaseReader, profile

        # Create a dictionary to store options about the surface
        mesh_dict = {
            'num_y': 5,
            'num_x': 3,
            'wing_type': 'CRM',
            'symmetry': True,
            'num_twist_cp': 5,
            'span_cos_spacing': 0.
        }

        mesh, twist_cp = generate_mesh(mesh_dict)

        surf_dict = {
            # Wing definition
            'name': 'wing',  # name of the surface
            'type': 'aero',
            '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': 'tube',
            'mesh': mesh,
            'twist_cp': twist_cp,

            # 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': 0.015,  # 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([0.15]),  # thickness over chord ratio (NACA0015)
            'c_max_t': .303,  # chordwise location of maximum (NACA0015)
            # thickness
            'with_viscous': True,  # if true, compute viscous drag
            'with_wave': False,  # if true, compute wave drag
        }

        surf_dict['num_x'], surf_dict['num_y'] = surf_dict['mesh'].shape[:2]

        surfaces = [surf_dict]

        n_points = 2

        # Create the problem and the model group
        prob = Problem()

        indep_var_comp = IndepVarComp()
        indep_var_comp.add_output('v', val=248.136, units='m/s')
        indep_var_comp.add_output('alpha',
                                  val=np.ones(n_points) * 6.64,
                                  units='deg')
        indep_var_comp.add_output('M', val=0.84)
        indep_var_comp.add_output('re', val=1.e6, units='1/m')
        indep_var_comp.add_output('rho', val=0.38, units='kg/m**3')
        indep_var_comp.add_output('cg', val=np.zeros((3)), units='m')

        prob.model.add_subsystem('prob_vars', indep_var_comp, promotes=['*'])

        # Loop through and add a certain number of aero points
        for i in range(n_points):

            # Create the aero point group and add it to the model
            aero_group = AeroPoint(surfaces=surfaces)
            point_name = 'aero_point_{}'.format(i)
            prob.model.add_subsystem(point_name, aero_group)

            # Connect flow properties to the analysis point
            prob.model.connect('v', point_name + '.v')
            prob.model.connect('alpha', point_name + '.alpha', src_indices=[i])
            prob.model.connect('M', point_name + '.M')
            prob.model.connect('re', point_name + '.re')
            prob.model.connect('rho', point_name + '.rho')
            prob.model.connect('cg', point_name + '.cg')

            # Connect the parameters within the model for each aero point
            for surface in surfaces:

                geom_group = Geometry(surface=surface)

                # Add tmp_group to the problem as the name of the surface.
                # Note that is a group and performance group for each
                # individual surface.
                aero_group.add_subsystem(surface['name'] + '_geom', geom_group)

                name = surface['name']
                prob.model.connect(point_name + '.CD',
                                   'multi_CD.' + str(i) + '_CD')

                # Connect the mesh from the geometry component to the analysis point
                prob.model.connect(point_name + '.' + name + '_geom.mesh',
                                   point_name + '.' + name + '.def_mesh')

                # Perform the connections with the modified names within the
                # 'aero_states' group.
                prob.model.connect(
                    point_name + '.' + name + '_geom.mesh',
                    point_name + '.aero_states.' + name + '_def_mesh')

                prob.model.connect(
                    point_name + '.' + name + '_geom.t_over_c',
                    point_name + '.' + name + '_perf.' + 't_over_c')

        prob.model.add_subsystem('multi_CD',
                                 MultiCD(n_points=n_points),
                                 promotes_outputs=['CD'])

        from openmdao.api import ScipyOptimizeDriver
        prob.driver = ScipyOptimizeDriver()
        prob.driver.options['tol'] = 1e-9

        # # Setup problem and add design variables, constraint, and objective
        prob.model.add_design_var('alpha', lower=-15, upper=15)

        prob.model.add_design_var('aero_point_0.wing_geom.twist_cp',
                                  lower=-5,
                                  upper=8)
        prob.model.add_constraint('aero_point_0.wing_perf.CL', equals=0.45)

        prob.model.add_design_var('aero_point_1.wing_geom.twist_cp',
                                  lower=-5,
                                  upper=8)
        prob.model.add_constraint('aero_point_1.wing_perf.CL', equals=0.5)

        prob.model.add_objective('CD', scaler=1e4)

        # Set up the problem
        prob.setup()

        # print('gona check')
        # prob.run_model()
        # prob.check_partials(compact_print=True)
        # exit()
        prob.run_driver()

        assert_rel_error(self, prob['aero_point_0.wing_perf.CL'][0], 0.45,
                         1e-6)
        assert_rel_error(self, prob['aero_point_0.wing_perf.CD'][0],
                         0.03231556149303963, 1e-6)
        assert_rel_error(self, prob['aero_point_1.wing_perf.CL'][0], 0.5, 1e-6)
        assert_rel_error(self, prob['aero_point_1.wing_perf.CD'][0],
                         0.03376555561457066, 1e-6)
Exemplo n.º 47
0
    def __init__(self, RefBlade):
        super(FloatingTurbine, self).__init__()

        self.add('hub_height', IndepVarComp('hub_height', 0.0), promotes=['*'])

        # TODO:
        #Weibull/Rayleigh CDF

        # Rotor
        self.add('rotor', RotorSE(RefBlade), promotes=['*'])

        # RNA
        self.add('rna', RNA(1), promotes=['downwind'])

        # Tower and substructure
        myfloat = FloatingSE()
        self.add('sm', myfloat, promotes=['*'])

        # Turbine constraints
        self.add('tcons', TurbineConstraints(myfloat.nFullTow), promotes=['*'])

        # Turbine costs
        self.add('tcost', Turbine_CostsSE_2015(), promotes=['*'])

        # Balance of station
        self.add('wobos', WindOBOS(), promotes=['*'])

        # LCOE Calculation
        self.add('lcoe', PlantFinance(), promotes=['*'])

        # Define all input variables from all models
        self.add('offshore',
                 IndepVarComp('offshore', True, pass_by_obj=True),
                 promotes=['*'])
        self.add('crane',
                 IndepVarComp('crane', False, pass_by_obj=True),
                 promotes=['*'])

        # Turbine Costs
        # REMOVE ONCE DRIVESE AND GENERATORSE ARE CONNECTED
        self.add('bearing_number',
                 IndepVarComp('bearing_number', 0, pass_by_obj=True),
                 promotes=['*'])
        self.add('bedplate_mass',
                 IndepVarComp('bedplate_mass', 0.0),
                 promotes=['*'])
        self.add('crane_cost', IndepVarComp('crane_cost', 0.0), promotes=['*'])
        self.add('gearbox_mass',
                 IndepVarComp('gearbox_mass', 0.0),
                 promotes=['*'])
        self.add('generator_mass',
                 IndepVarComp('generator_mass', 0.0),
                 promotes=['*'])
        self.add('hss_mass', IndepVarComp('hss_mass', 0.0), promotes=['*'])
        self.add('hvac_mass', IndepVarComp('hvac_mass', 0.0), promotes=['*'])
        self.add('lss_mass', IndepVarComp('lss_mass', 0.0), promotes=['*'])
        self.add('main_bearing_mass',
                 IndepVarComp('main_bearing_mass', 0.0),
                 promotes=['*'])
        self.add('cover_mass', IndepVarComp('cover_mass', 0.0), promotes=['*'])
        self.add('platforms_mass',
                 IndepVarComp('platforms_mass', 0.0),
                 promotes=['*'])
        self.add('pitch_system_mass',
                 IndepVarComp('pitch_system_mass', 0.0),
                 promotes=['*'])
        self.add('spinner_mass',
                 IndepVarComp('spinner_mass', 0.0),
                 promotes=['*'])
        self.add('transformer_mass',
                 IndepVarComp('transformer_mass', 0.0),
                 promotes=['*'])
        self.add('vs_electronics_mass',
                 IndepVarComp('vs_electronics_mass', 0.0),
                 promotes=['*'])
        self.add('yaw_mass', IndepVarComp('yaw_mass', 0.0), promotes=['*'])

        # Tower
        #self.add('stress_standard_value',          IndepVarComp('stress_standard_value', 0.0), promotes=['*'])
        #self.add('fatigue_parameters',             IndepVarComp('fatigue_parameters', np.zeros(nDEL)), promotes=['*'])
        #self.add('fatigue_z',                      IndepVarComp('fatigue_z', np.zeros(nDEL)), promotes=['*'])
        #self.add('frame3dd_matrix_method',         IndepVarComp('frame3dd_matrix_method', 0, pass_by_obj=True), promotes=['*'])
        #self.add('compute_stiffnes',               IndepVarComp('compute_stiffnes', False, pass_by_obj=True), promotes=['*'])
        self.add('project_lifetime',
                 IndepVarComp('project_lifetime', 0.0),
                 promotes=['*'])
        #self.add('lumped_mass_matrix',             IndepVarComp('lumped_mass_matrix', 0, pass_by_obj=True), promotes=['*'])
        #self.add('slope_SN',                       IndepVarComp('slope_SN', 0, pass_by_obj=True), promotes=['*'])
        #self.add('number_of_modes',                IndepVarComp('number_of_modes', 0, pass_by_obj=True), promotes=['*'])
        #self.add('compute_shear',                  IndepVarComp('compute_shear', True, pass_by_obj=True), promotes=['*'])
        #self.add('shift_value',                    IndepVarComp('shift_value', 0.0), promotes=['*'])
        #self.add('frame3dd_convergence_tolerance', IndepVarComp('frame3dd_convergence_tolerance', 1e-9), promotes=['*'])

        # TODO: Multiple load cases
        # Environment
        self.add('air_density',
                 IndepVarComp('air_density', 0.0),
                 promotes=['*'])
        self.add('air_viscosity',
                 IndepVarComp('air_viscosity', 0.0),
                 promotes=['*'])
        self.add('wind_reference_speed',
                 IndepVarComp('wind_reference_speed', 0.0),
                 promotes=['*'])
        self.add('wind_reference_height',
                 IndepVarComp('wind_reference_height', 0.0),
                 promotes=['*'])
        self.add('shearExp', IndepVarComp('shearExp', 0.0), promotes=['*'])
        self.add('wind_bottom_height',
                 IndepVarComp('wind_bottom_height', 0.0),
                 promotes=['*'])
        self.add('wind_beta', IndepVarComp('wind_beta', 0.0), promotes=['*'])
        self.add('cd_usr', IndepVarComp('cd_usr', np.inf), promotes=['*'])

        # Environment
        self.add('water_depth',
                 IndepVarComp('water_depth', 0.0),
                 promotes=['*'])
        self.add('water_density',
                 IndepVarComp('water_density', 0.0),
                 promotes=['*'])
        self.add('water_viscosity',
                 IndepVarComp('water_viscosity', 0.0),
                 promotes=['*'])
        self.add('wave_height',
                 IndepVarComp('wave_height', 0.0),
                 promotes=['*'])
        self.add('wave_period',
                 IndepVarComp('wave_period', 0.0),
                 promotes=['*'])
        self.add('mean_current_speed',
                 IndepVarComp('mean_current_speed', 0.0),
                 promotes=['*'])
        #self.add('wave_beta',                  IndepVarComp('wave_beta', 0.0), promotes=['*'])
        #self.add('wave_velocity_z0',           IndepVarComp('wave_velocity_z0', 0.0), promotes=['*'])
        #self.add('wave_acceleration_z0',       IndepVarComp('wave_acceleration_z0', 0.0), promotes=['*'])

        # Design standards
        self.add('gamma_freq', IndepVarComp('gamma_freq', 0.0), promotes=['*'])
        self.add('gamma_f', IndepVarComp('gamma_f', 0.0), promotes=['*'])
        self.add('gamma_m', IndepVarComp('gamma_m', 0.0), promotes=['*'])
        self.add('gamma_b', IndepVarComp('gamma_b', 0.0), promotes=['*'])
        self.add('gamma_fatigue',
                 IndepVarComp('gamma_fatigue', 0.0),
                 promotes=['*'])
        self.add('gamma_n', IndepVarComp('gamma_n', 0.0), promotes=['*'])

        # RNA
        self.add('dummy_mass', IndepVarComp('dummy_mass', 0.0), promotes=['*'])
        self.add('hub_mass', IndepVarComp('hub_mass', 0.0), promotes=['*'])
        self.add('nac_mass', IndepVarComp('nac_mass', 0.0), promotes=['*'])
        self.add('hub_cm',
                 IndepVarComp('hub_cm', np.zeros((3, ))),
                 promotes=['*'])
        self.add('nac_cm',
                 IndepVarComp('nac_cm', np.zeros((3, ))),
                 promotes=['*'])
        self.add('hub_I', IndepVarComp('hub_I', np.zeros(6)), promotes=['*'])
        self.add('nac_I', IndepVarComp('nac_I', np.zeros(6)), promotes=['*'])
        self.add('rna_weightM',
                 IndepVarComp('rna_weightM', True, pass_by_obj=True),
                 promotes=['*'])

        # Column
        self.add('morison_mass_coefficient',
                 IndepVarComp('morison_mass_coefficient', 0.0),
                 promotes=['*'])
        self.add('material_density',
                 IndepVarComp('material_density', 0.0),
                 promotes=['*'])
        self.add('E', IndepVarComp('E', 0.0), promotes=['*'])
        self.add('nu', IndepVarComp('nu', 0.0), promotes=['*'])
        self.add('yield_stress',
                 IndepVarComp('yield_stress', 0.0),
                 promotes=['*'])

        # Pontoons
        self.add('G', IndepVarComp('G', 0.0), promotes=['*'])

        # LCOE
        self.add('number_of_turbines',
                 IndepVarComp('number_of_turbines', 0, pass_by_obj=True),
                 promotes=['*'])
        self.add('annual_opex',
                 IndepVarComp('annual_opex', 0.0),
                 promotes=['*'])  # TODO: Replace with output connection
        self.add('fixed_charge_rate',
                 IndepVarComp('fixed_charge_rate', 0.0),
                 promotes=['*'])
        self.add('discount_rate',
                 IndepVarComp('discount_rate', 0.0),
                 promotes=['*'])

        # Connect all input variables from all models
        self.connect('water_depth', ['waterD', 'sea_depth'])
        self.connect('hub_height', 'hubH')
        self.connect('tower_outer_diameter', 'towerD', src_indices=[0])

        self.connect('wind_beta', 'beta')
        self.connect('mean_current_speed', 'Uc')

        self.connect('project_lifetime', ['struc.lifetime', 'projLife'])
        #self.connect('slope_SN', 'm_SN')
        #self.connect('compute_shear', 'shear')
        #self.connect('compute_stiffnes', 'geom')
        #self.connect('frame3dd_matrix_method', 'Mmethod')
        #self.connect('shift_value', 'shift')
        # TODO:
        #self.connect('number_of_modes', ['nM', 'nF'])
        #self.connect('frame3dd_convergence_tolerance', 'tol')
        #self.connect('lumped_mass_matrix', 'lump')
        #self.connect('stress_standard_value', 'DC')

        self.connect('rna.loads.top_F', 'rna_force')
        self.connect('rna.loads.top_M', 'rna_moment')
        self.connect('rna.rna_I_TT', 'rna_I')
        self.connect('rna.rna_mass', ['rnaM', 'rna_mass'])
        self.connect('rna.rna_cm', 'rna_cg')
        self.connect('mass_all_blades', 'rna.blades_mass')
        self.connect('I_all_blades', 'rna.blades_I')
        self.connect('hub_mass', 'rna.hub_mass')
        self.connect('nac_mass', 'rna.nac_mass')
        self.connect('hub_cm', 'rna.hub_cm')
        self.connect('nac_cm', 'rna.nac_cm')
        self.connect('hub_I', 'rna.hub_I')
        self.connect('nac_I', 'rna.nac_I')
        self.connect('tilt', 'rna.tilt')
        self.connect('Fxyz_total', 'rna.loads.F')
        self.connect('Mxyz_total', 'rna.loads.M')
        self.connect('rna_weightM', 'rna.rna_weightM')

        self.connect('air_density', ['main.windLoads.rho', 'analysis.rho'])
        self.connect('air_viscosity', ['main.windLoads.mu', 'analysis.mu'])
        self.connect('water_density', 'water_density')
        self.connect('water_viscosity', 'main.waveLoads.mu')
        self.connect('wave_height', 'Hs')
        self.connect('wave_period', 'T')
        self.connect('wind_reference_speed', 'Uref')
        self.connect('wind_reference_height', ['zref', 'wind.zref'])
        self.connect('wind_bottom_height', ['z0', 'wind.z0'])
        self.connect('shearExp', 'wind.shearExp')
        self.connect('morison_mass_coefficient', 'cm')

        self.connect('ballast_cost_rate', 'ballCR')
        self.connect('mooring_cost_rate', 'moorCR')
        self.connect('mooring_cost', 'moorCost')
        self.connect('mooring_diameter', 'moorDia')
        self.connect('number_of_mooring_lines', 'moorLines')
        self.connect('material_cost_rate', 'sSteelCR')
        self.connect('main.tapered_column_cost_rate',
                     ['spStifColCR', 'spTapColCR', 'ssStifColCR'])
        self.connect('pontoon_cost_rate', 'ssTrussCR')

        self.connect('nBlades', 'blade_number')
        self.connect('mass_one_blade', 'blade_mass')
        self.connect('control_maxOmega', 'rotor_omega')
        self.connect('structural_frequencies', 'tower_freq')

        self.connect('turbine_cost_kW', 'turbCapEx')
        self.connect('machine_rating', 'turbR')
        self.connect('diameter', 'rotorD')
        self.connect('bladeLength', 'bladeL')
        self.connect('hub_diameter', 'hubD')

        # Link outputs from one model to inputs to another
        self.connect('tower_mass', 'towerM')
        self.connect('dummy_mass', 'off.stack_mass_in')

        self.connect('total_cost', 'subTotCost')
        self.connect('total_mass', 'subTotM')
        self.connect('total_bos_cost', 'bos_costs')

        self.connect('number_of_turbines', ['nTurb', 'turbine_number'])
        self.connect('annual_opex', 'avg_annual_opex')
        self.connect('AEP', 'net_aep')
        self.connect('totInstTime', 'construction_time')

        # Use complex number finite differences
        typeStr = 'fd'
        formStr = 'central'
        stepVal = 1e-5
        stepStr = 'relative'

        self.deriv_options['type'] = typeStr
        self.deriv_options['form'] = formStr
        self.deriv_options['step_size'] = stepVal
        self.deriv_options['step_calc'] = stepStr
Exemplo n.º 48
0
    def test_assembled_jacobian_unsupported_cases(self):
        class ParaboloidApply(ImplicitComponent):
            def setup(self):
                self.add_input('x', val=0.0)
                self.add_input('y', val=0.0)

                self.add_output('f_xy', val=0.0)

            def linearize(self, inputs, outputs, jacobian):
                return

            def apply_linear(self, inputs, outputs, d_inputs, d_outputs,
                             d_residuals, mode):
                d_residuals['x'] += (
                    np.exp(outputs['x']) -
                    2 * inputs['a']**2 * outputs['x']) * d_outputs['x']
                d_residuals['x'] += (-2 * inputs['a'] *
                                     outputs['x']**2) * d_inputs['a']

        # One level deep

        prob = Problem()
        model = prob.model = Group(assembled_jac_type='dense')
        model.linear_solver = DirectSolver(assemble_jac=True)

        model.add_subsystem('p1', IndepVarComp('x', val=1.0))
        model.add_subsystem('p2', IndepVarComp('y', val=1.0))
        model.add_subsystem('comp', ParaboloidApply())

        model.connect('p1.x', 'comp.x')
        model.connect('p2.y', 'comp.y')

        prob.setup()

        msg = "AssembledJacobian not supported for matrix-free subcomponent."
        with self.assertRaisesRegex(Exception, msg):
            prob.run_model()

        # Nested

        prob = Problem()
        model = prob.model = Group(assembled_jac_type='dense')
        model.linear_solver = DirectSolver(assemble_jac=True)

        sub = model.add_subsystem('sub', Group())

        model.add_subsystem('p1', IndepVarComp('x', val=1.0))
        model.add_subsystem('p2', IndepVarComp('y', val=1.0))
        sub.add_subsystem('comp', ParaboloidApply())

        model.connect('p1.x', 'sub.comp.x')
        model.connect('p2.y', 'sub.comp.y')

        prob.setup()

        msg = "AssembledJacobian not supported for matrix-free subcomponent."
        with self.assertRaisesRegex(Exception, msg):
            prob.run_model()

        # Try a component that is derived from a matrix-free one

        class FurtherDerived(ParaboloidApply):
            def do_nothing(self):
                pass

        prob = Problem()
        model = prob.model = Group(assembled_jac_type='dense')
        model.linear_solver = DirectSolver(assemble_jac=True)

        model.add_subsystem('p1', IndepVarComp('x', val=1.0))
        model.add_subsystem('p2', IndepVarComp('y', val=1.0))
        model.add_subsystem('comp', FurtherDerived())

        model.connect('p1.x', 'comp.x')
        model.connect('p2.y', 'comp.y')

        prob.setup()

        msg = "AssembledJacobian not supported for matrix-free subcomponent."
        with self.assertRaisesRegex(Exception, msg):
            prob.run_model()

        # Make sure regular comps don't give an error.

        prob = Problem()
        model = prob.model = Group(assembled_jac_type='dense')
        model.linear_solver = DirectSolver(assemble_jac=True)

        model.add_subsystem('p1', IndepVarComp('x', val=1.0))
        model.add_subsystem('p2', IndepVarComp('y', val=1.0))
        model.add_subsystem('comp', Paraboloid())

        model.connect('p1.x', 'comp.x')
        model.connect('p2.y', 'comp.y')

        prob.setup()
        prob.final_setup()

        class ParaboloidJacVec(Paraboloid):
            def linearize(self, inputs, outputs, jacobian):
                return

            def compute_jacvec_product(self, inputs, d_inputs, d_outputs,
                                       d_residuals, mode):
                d_residuals['x'] += (
                    np.exp(outputs['x']) -
                    2 * inputs['a']**2 * outputs['x']) * d_outputs['x']
                d_residuals['x'] += (-2 * inputs['a'] *
                                     outputs['x']**2) * d_inputs['a']

        # One level deep

        prob = Problem()
        model = prob.model = Group(assembled_jac_type='dense')
        model.linear_solver = DirectSolver(assemble_jac=True)

        model.add_subsystem('p1', IndepVarComp('x', val=1.0))
        model.add_subsystem('p2', IndepVarComp('y', val=1.0))
        model.add_subsystem('comp', ParaboloidJacVec())

        model.connect('p1.x', 'comp.x')
        model.connect('p2.y', 'comp.y')

        prob.setup()

        msg = "AssembledJacobian not supported for matrix-free subcomponent."
        with self.assertRaisesRegex(Exception, msg):
            prob.run_model()
Exemplo n.º 49
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    def setup(self):
        fe_model = self.options['fe_model']
        nelx = self.options['num_ele_x']
        nely = self.options['num_ele_y']
        penal = self.options['penal_factor']
        volume_fraction = self.options['volume_fraction']
        radius = self.options['filter_radius']
        max_buckling_load = self.options['max_buckling_load']
        initial_x = self.options['initial_densities']
        data_recorder = self.options['data_recorder']

        # Check FEA assembly and evaluate dimensions of the sparse matrix
        n_elements = nelx * nely
        n_dof = 2 * (nelx + 1) * (nely + 1)
        unknown_dof = fe_model.unknown_dof

        # Inside default parameters
        n_eigenvalues = 5
        eigenvalue_gap = 1.01
        #aggregation_parameter = 30.0
        minimum_x = 1e-6

        # Setup design variables ['densities']
        comp = IndepVarComp()
        comp.add_output('densities', val=initial_x, shape=n_elements)
        comp.add_design_var('densities', lower=0.0, upper=1.0)
        self.add_subsystem('input_comp', comp)
        self.connect('input_comp.densities', 'filter_comp.densities')

        # Density Filter
        comp = DensityFilterComp(num_ele_x=nelx, num_ele_y=nely, radius=radius)
        self.add_subsystem('filter_comp', comp)
        self.connect('filter_comp.densities_f', 'penalization_comp.densities')
        self.connect('filter_comp.densities_f', 'volume_comp.densities')

        # Penalization
        comp = PenalizationComp(penal=penal, n_elements=n_elements)
        self.add_subsystem('penalization_comp', comp)
        self.connect('penalization_comp.multipliers',
                     'states_comp.multipliers')

        ## STATES COMP
        comp = States_comp(number_of_elements=n_elements,
                           number_of_dof=n_dof,
                           finite_elements_model=fe_model)
        self.add_subsystem('states_comp', comp)
        self.connect('states_comp.states', 'compliance_comp.displacements')

        # Compliance
        comp = ComplianceComp(fe_model=fe_model,
                              ndof=n_dof,
                              unknown_dof=unknown_dof,
                              data_recorder=data_recorder)
        self.add_subsystem('compliance_comp', comp)

        # Volume
        comp = VolumeComp(nelements=n_elements, data_recorder=data_recorder)
        self.add_subsystem('volume_comp', comp)

        # Design variables
        self.add_design_var('input_comp.densities', upper=1)

        # Objective
        #self.add_objective('volume_comp.volume')
        self.add_objective('compliance_comp.compliance')

        # Constraints:
        self.add_constraint('volume_comp.volume',
                            upper=volume_fraction,
                            linear=True)
Exemplo n.º 50
0
    def test1(self):

        r = np.array([2.8667, 5.6000, 8.3333, 11.7500, 15.8500, 19.9500, 24.0500,
                  28.1500, 32.2500, 36.3500, 40.4500, 44.5500, 48.6500, 52.7500,
                  56.1667, 58.9000, 61.6333])
        chord = np.array([3.542, 3.854, 4.167, 4.557, 4.652, 4.458, 4.249, 4.007, 3.748,
                      3.502, 3.256, 3.010, 2.764, 2.518, 2.313, 2.086, 1.419])
        theta = np.array([13.308, 13.308, 13.308, 13.308, 11.480, 10.162, 9.011, 7.795,
                      6.544, 5.361, 4.188, 3.125, 2.319, 1.526, 0.863, 0.370, 0.106])
        Rhub = 1.5
        Rtip = 63.0
        hubHt = 80.0
        precone = 2.5
        tilt = -5.0
        yaw = 0.0
        B = 3
        rho = 1.225
        mu = 1.81206e-5
        shearExp = 0.2
        nSector = 4
        precurve = np.zeros(len(r))
        precurveTip = 0.0

        # airfoils
        basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_AFFiles/')

        # load all airfoils
        airfoil_types = [0]*8
        airfoil_types[0] = basepath + 'Cylinder1.dat'
        airfoil_types[1] = basepath + 'Cylinder2.dat'
        airfoil_types[2] = basepath + 'DU40_A17.dat'
        airfoil_types[3] = basepath + 'DU35_A17.dat'
        airfoil_types[4] = basepath + 'DU30_A17.dat'
        airfoil_types[5] = basepath + 'DU25_A17.dat'
        airfoil_types[6] = basepath + 'DU21_A17.dat'
        airfoil_types[7] = basepath + 'NACA64_A17.dat'

        # place at appropriate radial stations
        af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7]

        n = len(r)
        af = [0]*n
        for i in range(n):
            af[i] = airfoil_types[af_idx[i]]

        airfoil_files = np.array(af)

        run_case = 'power'
        Uhub = np.array([3.0, 4.15789473684, 5.31578947368, 6.47368421053, 7.63157894737, 8.78947368421, 9.94736842105, 11.1052631579, 12.2631578947, 13.4210526316, 14.5789473684, 15.7368421053, 16.8947368421, 18.0526315789, 19.2105263158, 20.3684210526, 21.5263157895, 22.6842105263, 23.8421052632, 25.0])
        Omega = np.array([3.43647024491, 4.76282718154, 6.08918411817, 7.41554105481, 8.74189799144, 10.0682549281, 11.3946118647, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0, 12.0])
        pitch = np.array([0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0])
        n2 = len(Uhub)

        prob = Problem()
        prob.root = Group()
        prob.root.add('comp', CCBlade(run_case, n, n2), promotes=['*'])
        prob.root.add('r', IndepVarComp('r', np.zeros(len(r))), promotes=['*'])
        prob.root.add('chord', IndepVarComp('chord', np.zeros(len(chord))), promotes=['*'])
        prob.root.add('theta', IndepVarComp('theta', np.zeros(len(theta))), promotes=['*'])
        prob.root.add('Rhub', IndepVarComp('Rhub', 0.0), promotes=['*'])
        prob.root.add('Rtip', IndepVarComp('Rtip', 0.0), promotes=['*'])
        prob.root.add('hubHt', IndepVarComp('hubHt', 0.0), promotes=['*'])
        prob.root.add('precone', IndepVarComp('precone', 0.0), promotes=['*'])
        prob.root.add('precurve', IndepVarComp('precurve', precurve), promotes=['*'])
        prob.root.add('precurveTip', IndepVarComp('precurveTip', 0.0), promotes=['*'])
        prob.root.add('tilt', IndepVarComp('tilt', 0.0), promotes=['*'])
        prob.root.add('yaw', IndepVarComp('yaw', 0.0), promotes=['*'])
        prob.root.add('B', IndepVarComp('B', 0), promotes=['*'])
        prob.root.add('rho', IndepVarComp('rho', 0.0), promotes=['*'])
        prob.root.add('mu', IndepVarComp('mu', 0.0), promotes=['*'])
        prob.root.add('shearExp', IndepVarComp('shearExp', 0.0, pass_by_obj=True), promotes=['*'])
        prob.root.add('nSector', IndepVarComp('nSector', nSector), promotes=['*'])
        prob.root.add('airfoil_files', IndepVarComp('airfoil_files', airfoil_files), promotes=['*'])
        prob.root.add('Uhub', IndepVarComp('Uhub', np.zeros(len(Uhub))), promotes=['*'])
        prob.root.add('Omega', IndepVarComp('Omega', np.zeros(len(Omega))), promotes=['*'])
        prob.root.add('pitch', IndepVarComp('pitch', np.zeros(len(pitch))), promotes=['*'])
        prob.setup(check=False)

        prob['r'] = r
        prob['chord'] = chord
        prob['theta'] = theta
        prob['Rhub'] = Rhub
        prob['Rtip'] = Rtip
        prob['hubHt'] = hubHt
        prob['precone'] = precone
        prob['tilt'] = tilt
        prob['yaw'] = yaw
        prob['B'] = B
        prob['rho'] = rho
        prob['mu'] = mu
        prob['shearExp'] = shearExp
        prob['nSector'] = nSector
        prob['airfoil_files'] = airfoil_files
        prob['Uhub'] = Uhub
        prob['Omega'] = Omega
        prob['pitch'] = pitch
        prob['precurve'] = precurve
        prob['precurveTip'] = precurveTip

        check_gradient_unit_test(self, prob, tol=1e-3, display=True)
Exemplo n.º 51
0
	def __init__(self):
		super(EESG_Opt, self).__init__()
		
		self.add('machine_rating', IndepVarComp('machine_rating',0.0),promotes=['*'])
		self.add('Torque',IndepVarComp('Torque', val=0.0),promotes=['*'])
		self.add('n_nom', IndepVarComp('n_nom', val=0.0),promotes=['*'])
		
		self.add('main_shaft_cm', IndepVarComp('main_shaft_cm',val=np.array([0.0, 0.0, 0.0])),promotes=['*'])
		self.add('main_shaft_length',IndepVarComp('main_shaft_length',val=0.0),promotes=['*'])
		
		self.add('r_s',IndepVarComp('r_s',0.0),promotes=['*'])
		self.add('l_s',IndepVarComp('l_s',0.0),promotes=['*'])
		self.add('h_s',IndepVarComp('h_s',0.0),promotes=['*'])
		self.add('tau_p',IndepVarComp('tau_p',0.0),promotes=['*'])
		self.add('I_f',IndepVarComp('I_f',0.0),promotes=['*'])
		self.add('N_f',IndepVarComp('N_f',0.0),promotes=['*'])
		
		self.add('h_ys',IndepVarComp('h_ys',0.0),promotes=['*'])
		self.add('h_yr',IndepVarComp('h_yr',0.0),promotes=['*'])
		self.add('n_s',IndepVarComp('n_s',0.0),promotes=['*'])
		self.add('b_st',IndepVarComp('b_st',0.0),promotes=['*'])
		self.add('n_r',IndepVarComp('n_r',0.0),promotes=['*'])
		self.add('b_r',IndepVarComp('b_r',0.0),promotes=['*'])
		self.add('d_r',IndepVarComp('d_r',0.0),promotes=['*'])
		self.add('d_s',IndepVarComp('d_s',0.0),promotes=['*'])
		self.add('t_wr',IndepVarComp('t_wr',0.0),promotes=['*'])
		self.add('t_ws',IndepVarComp('t_ws',0.0),promotes=['*'])
		self.add('R_o',IndepVarComp('R_o',0.0),promotes=['*'])
		
		self.add('rho_Fes',IndepVarComp('rho_Fes',0.0),promotes=['*'])
		self.add('rho_Fe',IndepVarComp('rho_Fe',0.0),promotes=['*'])
		self.add('rho_Copper',IndepVarComp('rho_Copper',0.0),promotes=['*'])
		
		# add EESG component, create constraint equations
		
		self.add('EESG',EESG(),promotes=['*'])
		self.add('con_uAs', ExecComp('con_uAs =u_all_s-u_As'),promotes=['*'])
		self.add('con_zAs', ExecComp('con_zAs =z_all_s-z_A_s'),promotes=['*'])
		self.add('con_yAs', ExecComp('con_yAs =y_all-y_As'),promotes=['*'])
		self.add('con_bst', ExecComp('con_bst =b_all_s-b_st'),promotes=['*'])
		self.add('con_uAr', ExecComp('con_uAr =u_all_r-u_Ar'),promotes=['*'])
		self.add('con_zAr', ExecComp('con_zAr =z_all_r-z_A_r'),promotes=['*'])
		self.add('con_yAr', ExecComp('con_yAr =y_all-y_Ar'),promotes=['*'])
		self.add('con_br', ExecComp('con_br =b_all_r-b_r'),promotes=['*'])
		self.add('con_TC2', ExecComp('con_TC2 =TC2-TC1'),promotes=['*'])
		self.add('con_TC3', ExecComp('con_TC3 =TC3-TC1'),promotes=['*'])
		
		# add EESG_Cost component
		self.add('EESG_Cost',EESG_Cost(),promotes=['*'])
		self.add('C_Cu',IndepVarComp('C_Cu',val=0.0),promotes=['*'])
		self.add('C_Fe',IndepVarComp('C_Fe',val=0.0),promotes=['*'])
		self.add('C_Fes',IndepVarComp('C_Fes',val=0.0),promotes=['*'])
Exemplo n.º 52
0
    500.e6 / 2.5,  # [Pa] yield stress divided by 2.5 for limiting case
    'mrho': 3.e3,  # [kg/m^3] material density
    'fem_origin': 0.35,  # normalized chordwise location of the spar
    'wing_weight_ratio': 2.,
    'struct_weight_relief':
    False,  # True to add the weight of the structure to the loads on the structure
    'distributed_fuel_weight': False,
    # Constraints
    'exact_failure_constraint': False,  # if false, use KS function
}

# Create the problem and assign the model group
prob = Problem()

# Add problem information as an independent variables component
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('v', val=248.136, units='m/s')
indep_var_comp.add_output('alpha', val=5., units='deg')
indep_var_comp.add_output('Mach_number', val=0.84)
indep_var_comp.add_output('re', val=1.e6, units='1/m')
indep_var_comp.add_output('rho', val=0.38, units='kg/m**3')
indep_var_comp.add_output('CT', val=grav_constant * 17.e-6, units='1/s')
indep_var_comp.add_output('R', val=11.165e6, units='m')
indep_var_comp.add_output('W0', val=0.4 * 3e5, units='kg')
indep_var_comp.add_output('speed_of_sound', val=295.4, 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=['*'])

aerostruct_group = AerostructGeometry(surface=surface)
Exemplo n.º 53
0
    def setup_helper(self, NozzType, LossType):

        self.prob = Problem()
        self.prob.model = Group()

        des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*'])
        des_vars.add_output('Pt', 17.0, units='psi')
        des_vars.add_output('Tt', 500.0, units='degR')
        des_vars.add_output('W', 0.0, units='lbm/s')
        des_vars.add_output('MN', 0.2)
        des_vars.add_output('Ps_exhaust', 17.0, units='psi')
        des_vars.add_output('Cv', 0.99)
        des_vars.add_output('Cfg', 0.99)

        self.prob.model.add_subsystem('flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX))
        self.prob.model.add_subsystem('nozzle', Nozzle(nozzType=NozzType, lossCoef=LossType,
                                                       thermo_data=janaf, elements=AIR_MIX,
                                                       internal_solver=True))

        connect_flow(self.prob.model, "flow_start.Fl_O", "nozzle.Fl_I")

        self.prob.model.connect("Pt", "flow_start.P")
        self.prob.model.connect("Tt", "flow_start.T")
        self.prob.model.connect("W", "flow_start.W")
        self.prob.model.connect("MN", "flow_start.MN")
        self.prob.model.connect("Ps_exhaust", "nozzle.Ps_exhaust")

        if LossType == 'Cv':
            self.prob.model.connect("Cv", "nozzle.Cv")
        elif LossType == 'Cfg':
            self.prob.model.connect("Cfg", "nozzle.Cfg")

        # self.prob.model.connect("area_targ", "compressor.area")

        self.prob.set_solver_print(level=2)
        self.prob.setup(check=False)

        header = [
            'Cfg',
            'Cv',
            'PsExh',
            'Fl_I.W',
            'Fl_I.MN',
            'Fl_I.s',
            'Fl_I.Pt',
            'Fl_I.Tt',
            'Fl_I.ht',
            'Fl_I.rhot',
            'Fl_I.gamt',
            'Fl_O.MN',
            'Fl_O.s',
            'Fl_O.Pt',
            'Fl_O.Tt',
            'Fl_O.ht',
            'Fl_O.rhot',
            'Fl_O.gamt',
            'Fl_O.Ps',
            'Fl_Th.MN',
            'Fl_Th.s',
            'Fl_Th.Pt',
            'Fl_Th.Tt',
            'Fl_Th.ht',
            'Fl_Th.rhot',
            'Fl_Th.gamt',
            'Fl_Th.Ps',
            'Fl_Th.Aphy',
            'Fg',
            'FgIdeal',
            'Vactual',
            'AthCold',
            'AR',
            'PR']

        self.h_map = dict(((v_name, i) for i, v_name in enumerate(header)))
        self.fpath = os.path.dirname(os.path.realpath(__file__))
Exemplo n.º 54
0
    def setup(self):
        num_times = self.options['num_times']
        num_cp = self.options['num_cp']
        step_size = self.options['step_size']
        cubesat = self.options['cubesat']
        mtx = self.options['mtx']
        Ground_station = self.options['Ground_station']

        times = np.linspace(0., step_size * (num_times - 1), num_times)

        comp = IndepVarComp()

        comp.add_output('times', units='s', val=times)
        comp.add_output('Initial_Data', val=np.zeros((1, )))
        self.add_subsystem('inputs_comp', comp, promotes=['*'])

        group = AttitudeGroup(
            num_times=num_times,
            num_cp=num_cp,
            cubesat=cubesat,
            mtx=mtx,
        )
        self.add_subsystem('attitude_group', group, promotes=['*'])

        group = PropulsionGroup(
            num_times=num_times,
            num_cp=num_cp,
            step_size=step_size,
            cubesat=cubesat,
            mtx=mtx,
        )
        self.add_subsystem('propulsion_group', group, promotes=['*'])

        group = AerodynamicsGroup(
            num_times=num_times,
            num_cp=num_cp,
            step_size=step_size,
            cubesat=cubesat,
            mtx=mtx,
        )
        self.add_subsystem('aerodynamics_group', group, promotes=['*'])

        group = OrbitGroup(
            num_times=num_times,
            num_cp=num_cp,
            step_size=step_size,
            cubesat=cubesat,
            mtx=mtx,
        )
        self.add_subsystem('orbit_group', group, promotes=['*'])

        for Ground_station in cubesat.children:
            name = Ground_station['name']

            group = CommGroup(
                num_times=num_times,
                num_cp=num_cp,
                step_size=step_size,
                Ground_station=Ground_station,
                mtx=mtx,
            )

            # self.connect('times', '{}_comm_group.times'.format(name))

            self.add_subsystem('{}_comm_group'.format(name), group)

        # name = cubesat['name']
        shape = (1, num_times)
        rho = 100.

        # cubesat_name = cubesat['name']

        comp = ElementwiseMaxComp(shape=shape,
                                  in_names=[
                                      'UCSD_comm_group_Download_rate',
                                      'UIUC_comm_group_Download_rate',
                                      'Georgia_comm_group_Download_rate',
                                      'Montana_comm_group_Download_rate',
                                  ],
                                  out_name='KS_Download_rate',
                                  rho=rho)
        self.add_subsystem('KS_Download_rate_comp', comp, promotes=['*'])

        for Ground_station in cubesat.children:
            Ground_station_name = Ground_station['name']

            self.connect(
                '{}_comm_group.Download_rate'.format(Ground_station_name),
                '{}_comm_group_Download_rate'.format(Ground_station_name),
            )

            # self.connect(
            #     '{}_comm_group.Download_rate'.format(Ground_station_name),
            #     '{}_comm_group_Download_rate'.format(Ground_station_name),
            # )

        comp = DataDownloadComp(
            num_times=num_times,
            step_size=step_size,
        )
        self.add_subsystem('Data_download_rk4_comp', comp, promotes=['*'])

        comp = ExecComp(
            'total_Data = Data[-1] - Data[0]',
            Data=np.empty(num_times),
        )
        self.add_subsystem('KS_total_Data_comp', comp, promotes=['*'])
Exemplo n.º 55
0
    def test2(self):

        r = np.array([2.8667, 5.6000, 8.3333, 11.7500, 15.8500, 19.9500, 24.0500,
                  28.1500, 32.2500, 36.3500, 40.4500, 44.5500, 48.6500, 52.7500,
                  56.1667, 58.9000, 61.6333])
        chord = np.array([3.542, 3.854, 4.167, 4.557, 4.652, 4.458, 4.249, 4.007, 3.748,
                      3.502, 3.256, 3.010, 2.764, 2.518, 2.313, 2.086, 1.419])
        theta = np.array([13.308, 13.308, 13.308, 13.308, 11.480, 10.162, 9.011, 7.795,
                      6.544, 5.361, 4.188, 3.125, 2.319, 1.526, 0.863, 0.370, 0.106])
        Rhub = 1.5
        Rtip = 63.0
        hubHt = 80.0
        precone = 2.5
        tilt = -5.0
        yaw = 0.0
        B = 3
        rho = 1.225
        mu = 1.81206e-5
        shearExp = 0.2
        nSector = 4
        precurve = np.zeros(len(r))

        # airfoils
        basepath = os.path.join(os.path.dirname(os.path.realpath(__file__)), '5MW_AFFiles/')

        # load all airfoils
        airfoil_types = [0]*8
        airfoil_types[0] = basepath + 'Cylinder1.dat'
        airfoil_types[1] = basepath + 'Cylinder2.dat'
        airfoil_types[2] = basepath + 'DU40_A17.dat'
        airfoil_types[3] = basepath + 'DU35_A17.dat'
        airfoil_types[4] = basepath + 'DU30_A17.dat'
        airfoil_types[5] = basepath + 'DU25_A17.dat'
        airfoil_types[6] = basepath + 'DU21_A17.dat'
        airfoil_types[7] = basepath + 'NACA64_A17.dat'

        # place at appropriate radial stations
        af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7]

        n = len(r)
        af = [0]*n
        for i in range(n):
            af[i] = airfoil_types[af_idx[i]]

        airfoil_files = np.array(af)

        run_case = 'loads'
        V_load = 12.0
        Omega_load = 10.0
        pitch_load = 0.0
        azimuth_load = 180.0
        n2 = 1

        prob = Problem()
        prob.root = Group()
        prob.root.add('comp', CCBlade(run_case, n, n2), promotes=['*'])
        prob.root.add('r', IndepVarComp('r', np.zeros(len(r))), promotes=['*'])
        prob.root.add('chord', IndepVarComp('chord', np.zeros(len(chord))), promotes=['*'])
        prob.root.add('theta', IndepVarComp('theta', np.zeros(len(theta))), promotes=['*'])
        prob.root.add('Rhub', IndepVarComp('Rhub', 0.0), promotes=['*'])
        prob.root.add('Rtip', IndepVarComp('Rtip', 0.0), promotes=['*'])
        prob.root.add('hubHt', IndepVarComp('hubHt', 0.0), promotes=['*'])
        prob.root.add('precone', IndepVarComp('precone', 0.0), promotes=['*'])
        prob.root.add('tilt', IndepVarComp('tilt', 0.0), promotes=['*'])
        prob.root.add('yaw', IndepVarComp('yaw', 0.0), promotes=['*'])
        prob.root.add('B', IndepVarComp('B', 0), promotes=['*'])
        prob.root.add('rho', IndepVarComp('rho', 0.0), promotes=['*'])
        prob.root.add('mu', IndepVarComp('mu', 0.0), promotes=['*'])
        prob.root.add('shearExp', IndepVarComp('shearExp', 0.0, pass_by_obj=True), promotes=['*'])
        prob.root.add('precurve', IndepVarComp('precurve', precurve), promotes=['*'])
        prob.root.add('nSector', IndepVarComp('nSector', nSector), promotes=['*'])
        prob.root.add('airfoil_files', IndepVarComp('airfoil_files', airfoil_files), promotes=['*'])
        prob.root.add('V_load', IndepVarComp('V_load', 0.0), promotes=['*'])
        prob.root.add('Omega_load', IndepVarComp('Omega_load', 0.0), promotes=['*'])
        prob.root.add('pitch_load', IndepVarComp('pitch_load', 0.0), promotes=['*'])
        prob.root.add('azimuth_load', IndepVarComp('azimuth_load', 0.0), promotes=['*'])
        prob.setup(check=False)

        prob['r'] = r
        prob['chord'] = chord
        prob['theta'] = theta
        prob['Rhub'] = Rhub
        prob['Rtip'] = Rtip
        prob['hubHt'] = hubHt
        prob['precone'] = precone
        prob['tilt'] = tilt
        prob['yaw'] = yaw
        prob['B'] = B
        prob['rho'] = rho
        prob['mu'] = mu
        prob['shearExp'] = shearExp
        prob['nSector'] = nSector
        prob['airfoil_files'] = airfoil_files
        prob['V_load'] = V_load
        prob['Omega_load'] = Omega_load
        prob['pitch_load'] = pitch_load
        prob['azimuth_load'] = azimuth_load
        prob['precurve'] = precurve

        check_gradient_unit_test(self, prob, tol=1e-3, display=True)
Exemplo n.º 56
0
    def test_pyxdsm_pdf(self):
        """
        Makes an XDSM of the Sphere test case. It also adds a design variable, constraint and
        objective.
        """
        class Rosenbrock(ExplicitComponent):
            def __init__(self, problem):
                super(Rosenbrock, self).__init__()
                self.problem = problem
                self.counter = 0

            def setup(self):
                self.add_input('x', np.array([1.5, 1.5]))
                self.add_output('f', 0.0)
                self.declare_partials('f',
                                      'x',
                                      method='fd',
                                      form='central',
                                      step=1e-4)

            def compute(self,
                        inputs,
                        outputs,
                        discrete_inputs=None,
                        discrete_outputs=None):
                x = inputs['x']
                outputs['f'] = sum(x**2)

        x0 = np.array([1.2, 1.5])
        filename = 'xdsm2'

        prob = Problem()
        indeps = prob.model.add_subsystem('indeps',
                                          IndepVarComp(problem=prob),
                                          promotes=['*'])
        indeps.add_output('x', list(x0))

        prob.model.add_subsystem('sphere',
                                 Rosenbrock(problem=prob),
                                 promotes=['*'])
        prob.model.add_subsystem('con',
                                 ExecComp('c=sum(x)', x=np.ones(2)),
                                 promotes=['*'])
        prob.driver = ScipyOptimizeDriver()
        prob.model.add_design_var('x')
        prob.model.add_objective('f')
        prob.model.add_constraint('c', lower=1.0)

        prob.setup(check=False)
        prob.final_setup()

        # requesting 'pdf', but if 'pdflatex' is not found we will only get 'tex'
        pdflatex = find_executable('pdflatex')

        # Write output
        write_xdsm(prob,
                   filename=filename,
                   out_format='pdf',
                   show_browser=SHOW,
                   quiet=QUIET)

        # Check if file was created
        self.assertTrue(os.path.isfile('.'.join([filename, 'tex'])))
        # Check if PDF was created (only if pdflatex is installed)
        self.assertTrue(not pdflatex
                        or os.path.isfile('.'.join([filename, 'pdf'])))
Exemplo n.º 57
0
    def test_guess_nonlinear_feature(self):
        from openmdao.api import Problem, Group, ImplicitComponent, IndepVarComp, NewtonSolver, ScipyKrylov

        class ImpWithInitial(ImplicitComponent):
            def setup(self):
                self.add_input('a', val=1.)
                self.add_input('b', val=1.)
                self.add_input('c', val=1.)
                self.add_output('x', val=0.)

                self.declare_partials(of='*', wrt='*')

            def apply_nonlinear(self, inputs, outputs, residuals):
                a = inputs['a']
                b = inputs['b']
                c = inputs['c']
                x = outputs['x']
                residuals['x'] = a * x**2 + b * x + c

            def solve_nonlinear(self, inputs, outputs):
                a = inputs['a']
                b = inputs['b']
                c = inputs['c']
                outputs['x'] = (-b + (b**2 - 4 * a * c)**0.5) / 2 / a

            def linearize(self, inputs, outputs, partials):
                a = inputs['a']
                b = inputs['b']
                c = inputs['c']
                x = outputs['x']

                partials['x', 'a'] = x**2
                partials['x', 'b'] = x
                partials['x', 'c'] = 1.0
                partials['x', 'x'] = 2 * a * x + b

                self.inv_jac = 1.0 / (2 * a * x + b)

            def solve_nonlinear(self, inputs, outputs):
                """ Do nothing. """
                pass

            def guess_nonlinear(self, inputs, outputs, resids):
                # Solution at 1 and 3. Default value takes us to -1 solution. Here
                # we set it to a value that will tke us to the 3 solution.
                outputs['x'] = 5.0

        prob = Problem()
        model = prob.model = Group()

        model.add_subsystem('pa', IndepVarComp('a', 1.0))
        model.add_subsystem('pb', IndepVarComp('b', 1.0))
        model.add_subsystem('pc', IndepVarComp('c', 1.0))
        model.add_subsystem('comp2', ImpWithInitial())
        model.connect('pa.a', 'comp2.a')
        model.connect('pb.b', 'comp2.b')
        model.connect('pc.c', 'comp2.c')

        model.nonlinear_solver = NewtonSolver()
        model.nonlinear_solver.options['solve_subsystems'] = True
        model.nonlinear_solver.options['max_sub_solves'] = 1
        model.linear_solver = ScipyKrylov()

        prob.setup(check=False)

        prob['pa.a'] = 1.
        prob['pb.b'] = -4.
        prob['pc.c'] = 3.

        prob.run_model()

        assert_rel_error(self, prob['comp2.x'], 3.)
    # # Build the model
    # model = Group()
    # ivc = IndepVarComp()
    # ivc.add_output('mean_xi', 8*np.ones(3))
    # model.add_subsystem('des_vars', ivc)
    # model.add_subsystem('paraboloid', Paraboloid())
    # model.connect('des_vars.mean_xi', 'paraboloid.mean_xi')
    # prob = Problem(model)
    # prob.setup()
    # prob.run_model()
    # print(prob['paraboloid.mean_QoI'])
    # print(prob['paraboloid.mean_xi'])

    #------------ Run optimization using SNOPT
    prob = Problem()
    indeps = prob.model.add_subsystem('indeps', IndepVarComp(), promotes=['*'])
    indeps.add_output('mean_xi', 10 * np.ones(3))
    prob.model.add_subsystem('paraboloid',
                             Paraboloid(),
                             promotes_inputs=['mean_xi'])

    # Set up the Optimization
    prob.driver = pyOptSparseDriver()
    prob.driver.options['optimizer'] = 'SNOPT'
    prob.driver.opt_settings['Major optimality tolerance'] = 3e-7
    prob.driver.opt_settings['Major feasibility tolerance'] = 3e-7
    prob.driver.opt_settings['Major iterations limit'] = 1000
    prob.driver.opt_settings['Verify level'] = -1
    prob.model.add_design_var('mean_xi',
                              lower=-20 * np.ones(3),
                              upper=20 * np.ones(3))
Exemplo n.º 59
0
    def setup(self):
        swarm = self.options['swarm']
        mtx = self.options['mtx']

        num_times = swarm['num_times']
        num_cp = swarm['num_cp']
        step_size = swarm['step_size']

        shape = (3, num_times)

        times = np.linspace(0., step_size * (num_times - 1), num_times)

        comp = IndepVarComp()
        comp.add_output('times', val=times)
        self.add_subsystem('inputs_comp', comp, promotes=['*'])

        comp = SunDirectionComp(
            num_times=num_times,
            launch_date=swarm['launch_date'],
        )
        self.add_subsystem('sun_direction_comp', comp, promotes=['*'])

        # group = ConstantOrbitGroup(
        #     num_times=num_times,
        #     num_cp=num_cp,
        #     step_size=step_size,
        #     cubesat=swarm.children[0],
        # )
        # self.add_subsystem('constant_orbit_group', group, promotes=['*'])
        comp = CrossProductComp(
            shape_no_3=(num_times, ),
            out_index=0,
            in1_index=0,
            in2_index=0,
            out_name='normal_cross_vec',
            in1_name='velocity_unit_vec',
            in2_name='position_unit_vec',
        )
        self.add_subsystem('normal_cross_vec_comp', comp, promotes=['*'])

        comp = CrossProductComp(
            shape_no_3=(num_times, ),
            out_index=0,
            in1_index=0,
            in2_index=0,
            out_name='observation_cross_vec',
            in1_name='position_unit_vec',
            in2_name='sun_unit_vec',
        )
        self.add_subsystem('observation_cross_vec_comp', comp, promotes=['*'])

        group = DecomposeVectorGroup(
            num_times=num_times,
            vec_name='normal_cross_vec',
            norm_name='normal_cross_norm',
            unit_vec_name='normal_cross_unit_vec',
        )
        self.add_subsystem('normal_cross_decomposition_group',
                           group,
                           promotes=['*'])

        group = DecomposeVectorGroup(
            num_times=num_times,
            vec_name='observation_cross_vec',
            norm_name='observation_cross_norm',
            unit_vec_name='observation_cross_unit_vec',
        )
        self.add_subsystem('observation_cross_decomposition_group',
                           group,
                           promotes=['*'])

        comp = DotProductComp(vec_size=3,
                              length=num_times,
                              a_name='observation_cross_unit_vec',
                              b_name='normal_cross_unit_vec',
                              c_name='observation_dot',
                              a_units=None,
                              b_units=None,
                              c_units=None)
        self.add_subsystem('observation_dot_comp', comp, promotes=['*'])

        comp = MaskVecComp(
            num_times=num_times,
            swarm=swarm,
        )
        self.add_subsystem('mask_vec_comp', comp, promotes=['*'])

        # Separation

        separation_constraint_names = [
            ('sunshade', 'optics'),
            ('optics', 'detector'),
        ]

        for name1, name2 in [
            ('sunshade', 'optics'),
            ('sunshade', 'detector'),
            ('optics', 'detector'),
        ]:
            position_name = 'position_{}_{}_km'.format(name1, name2)
            distance_name = 'distance_{}_{}_km'.format(name1, name2)
            unit_vec_name = 'unit_vec_{}_{}_km'.format(name1, name2)

            comp = LinearCombinationComp(
                shape=(3, num_times),
                out_name=position_name,
                coeffs_dict={
                    '{}_cubesat_group_position_km'.format(name1): 1.,
                    '{}_cubesat_group_position_km'.format(name2): -1.,
                },
            )
            self.add_subsystem('{}_comp'.format(position_name),
                               comp,
                               promotes=['*'])

            group = DecomposeVectorGroup(
                num_times=num_times,
                vec_name=position_name,
                norm_name=distance_name,
                unit_vec_name=unit_vec_name,
            )
            self.add_subsystem('{}_{}_decomposition_group'.format(
                name1, name2),
                               group,
                               promotes=['*'])

        # Transverse displacement

        transverse_constraint_names = [
            ('sunshade', 'detector'),
            ('optics', 'detector'),
        ]

        for name1, name2 in transverse_constraint_names:
            position_name = 'position_{}_{}_km'.format(name1, name2)
            projected_position_name = 'projected_position_{}_{}_km'.format(
                name1, name2)
            normal_position_name = 'normal_position_{}_{}_km'.format(
                name1, name2)
            normal_distance_name = 'normal_distance_{}_{}_km'.format(
                name1, name2)
            normal_unit_vec_name = 'normal_unit_vec_{}_{}_km'.format(
                name1, name2)

            group = ProjectionGroup(
                num_times=num_times,
                in1_name='sun_unit_vec',
                in2_name=position_name,
                out_name=projected_position_name,
            )
            self.add_subsystem('{}_group'.format(projected_position_name),
                               group,
                               promotes=['*'])

            comp = LinearCombinationComp(
                shape=(3, num_times),
                out_name=normal_position_name,
                coeffs_dict={
                    position_name: 1.,
                    projected_position_name: -1.,
                },
            )
            self.add_subsystem('{}_comp'.format(normal_position_name),
                               comp,
                               promotes=['*'])

            group = DecomposeVectorGroup(
                num_times=num_times,
                vec_name=normal_position_name,
                norm_name=normal_distance_name,
                unit_vec_name=normal_unit_vec_name,
            )
            self.add_subsystem(
                '{}_decomposition_group'.format(normal_position_name),
                group,
                promotes=['*'])

        for constraint_name in [
                'normal_distance_{}_{}'.format(name1, name2)
                for name1, name2 in transverse_constraint_names
        ] + [
                'distance_{}_{}'.format(name1, name2)
                for name1, name2 in separation_constraint_names
        ]:
            comp = PowerCombinationComp(
                shape=(num_times, ),
                out_name='{}_mm'.format(constraint_name),
                coeff=1.e6,
                powers_dict={
                    '{}_km'.format(constraint_name): 1.,
                })
            self.add_subsystem('{}_mm_comp'.format(constraint_name),
                               comp,
                               promotes=['*'])

            comp = PowerCombinationComp(
                shape=(num_times, ),
                out_name='masked_{}_mm'.format(constraint_name),
                powers_dict={
                    'mask_vec': 1.,
                    '{}_mm'.format(constraint_name): 1.,
                })
            self.add_subsystem('masked_{}_mm_comp'.format(constraint_name),
                               comp,
                               promotes=['*'])

            comp = KSComp(
                in_name='masked_{}_mm'.format(constraint_name),
                out_name='ks_masked_{}_mm'.format(constraint_name),
                shape=(1, ),
                constraint_size=num_times,
                rho=100.,
            )
            self.add_subsystem('ks_masked_{}_mm_comp'.format(constraint_name),
                               comp,
                               promotes=['*'])

            comp = PowerCombinationComp(
                shape=(num_times, ),
                out_name='masked_{}_mm_sq'.format(constraint_name),
                powers_dict={
                    'masked_{}_mm'.format(constraint_name): 2.,
                })
            self.add_subsystem('masked_{}_mm_sq_comp'.format(constraint_name),
                               comp,
                               promotes=['*'])

            comp = ScalarContractionComp(
                shape=(num_times, ),
                out_name='masked_{}_mm_sq_sum'.format(constraint_name),
                in_name='masked_{}_mm_sq'.format(constraint_name),
            )
            self.add_subsystem(
                'masked_{}_mm_sq_sum_comp'.format(constraint_name),
                comp,
                promotes=['*'])
        x = params['x']
        y = params['y']
        J = {}

        J['f_xy', 'x'] = 2.0 * x - 6.0 + y
        J['f_xy', 'y'] = 2.0 * y + 8.0 + x
        return J


if __name__ == "__main__":

    top = Problem()

    root = top.root = Group()

    root.add('p1', IndepVarComp('x', 3.0))
    root.add('p2', IndepVarComp('y', -4.0))
    root.add('p', Paraboloid())

    # Constraint Equation
    root.add('con', ExecComp('c = x-y'))

    root.connect('p1.x', 'p.x')
    root.connect('p2.y', 'p.y')
    root.connect('p.x', 'con.x')
    root.connect('p.y', 'con.y')

    top.driver = ScipyOptimizer()
    top.driver.options['optimizer'] = 'SLSQP'

    top.driver.add_desvar('p1.x', lower=-50, upper=50)