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
'type' : 'structural',
'symmetry' : True, # if true, model one half of wing
# reflected across the plane y = 0
'fem_model_type' : 'tube',
'mesh' : mesh,
'num_x' : mesh.shape[0],
'num_y' : mesh.shape[1],
# 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' : 0.15, # maximum airfoil thickness
'thickness_cp' : np.ones((3)) * .1,
'wing_weight_ratio' : 2.,
'exact_failure_constraint' : False,
}
# Create the problem and assign the model group
prob = Problem()
ny = surf_dict['num_y']
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=2.)
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_weight'][0], 2437385.6547349701, 1e-4)
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)
def test(self):
import numpy as np
from openaerostruct.geometry.utils import generate_mesh
from openaerostruct.geometry.geometry_group import Geometry
from openaerostruct.transfer.displacement_transfer import DisplacementTransfer
from openaerostruct.structures.struct_groups import SpatialBeamAlone
from openmdao.api import IndepVarComp, Problem, Group, SqliteRecorder
# 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
'type': 'structural',
'symmetry': True, # if true, model one half of wing
# reflected across the plane y = 0
'fem_model_type': 'tube',
'mesh': mesh,
'num_x': mesh.shape[0],
'num_y': mesh.shape[1],
# 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': 0.15, # maximum airfoil thickness
'thickness_cp': np.ones((3)) * .1,
'wing_weight_ratio': 2.,
'exact_failure_constraint': False,
}
# Create the problem and assign the model group
prob = Problem()
ny = surf_dict['num_y']
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)
from openmdao.api import ScipyOptimizeDriver
prob.driver = ScipyOptimizeDriver()
prob.driver.options['disp'] = True
recorder = SqliteRecorder('struct.db')
prob.driver.add_recorder(recorder)
prob.driver.recording_options['record_derivatives'] = True
# Setup problem and add design variables, constraint, and objective
prob.model.add_design_var('wing.thickness_cp',
lower=0.01,
upper=0.5,
scaler=1e2)
prob.model.add_constraint('wing.failure', upper=0.)
prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_weight', scaler=1e-5)
# Set up the problem
prob.setup()
prob.run_driver()
assert_rel_error(self, prob['wing.structural_weight'][0],
697377.8734430908, 1e-8)
def test(self):
# Create a dictionary to store options about the surface
mesh_dict = {'num_y' : 7,
'wing_type' : 'uCRM_based',
'symmetry' : True,
'num_twist_cp' : 5}
mesh, twist_cp = generate_mesh(mesh_dict)
surf_dict = {
# Wing definition
'name' : 'wing', # name of the surface
# 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',
'symmetry' : True,
'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' : False,
'distributed_fuel_weight' : True,
# Constraints
'exact_failure_constraint' : True, # 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
}
# 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.)
indep_var_comp.add_output('fuel_mass', val=10000., units='kg')
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)
if surf_dict['distributed_fuel_weight']:
prob.model.connect('wing.fuel_mass', 'wing.struct_states.fuel_mass')
prob.model.connect('wing.struct_setup.fuel_vols', 'wing.struct_states.fuel_vols')
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('wing.spar_thickness_cp', lower=0.01, upper=0.5, ref=1e-1)
prob.model.add_design_var('wing.skin_thickness_cp', lower=0.01, upper=0.5, ref=1e-1)
prob.model.add_constraint('wing.failure', upper=0.)
#prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_mass', scaler=1e-5)
# Set up the problem
prob.setup(force_alloc_complex=False)
prob.run_model()
data = prob.check_partials(compact_print=True, out_stream=None, method='fd')
assert_check_partials(data, atol=1e20, rtol=1e-6)
prob.run_driver()
assert_rel_error(self, prob['wing.structural_mass'], 16704.07393593, 1e-6)
def test(self):
# Create a dictionary to store options about the surface
mesh_dict = {
'num_y': 5,
'num_x': 3,
'wing_type': 'rect',
'symmetry': True,
'span_cos_spacing': 1.,
'span': 10,
'chord': 1
}
mesh = 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,
# 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)) * .0075,
'wing_weight_ratio': 1.,
'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]
loads = np.zeros((ny, 6))
loads[0, 2] = 1e4
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('loads', val=loads, 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)
from openmdao.api import ScipyOptimizeDriver
prob.driver = ScipyOptimizeDriver()
prob.driver.options['disp'] = True
# Setup problem and add design variables, constraint, and objective
prob.model.add_design_var('wing.thickness_cp',
lower=0.001,
upper=0.25,
scaler=1e2)
prob.model.add_constraint('wing.failure', upper=0.)
prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_weight', scaler=1e-5)
# Set up the problem
prob.setup()
# from openmdao.api import view_model
# view_model(prob)
prob.run_driver()
assert_rel_error(self, prob['wing.structural_weight'][0],
1144.8503583047038, 1e-4)
def test(self):
# Create a dictionary to store options about the surface
mesh_dict = {
'num_y': 7,
'wing_type': 'uCRM_based',
'symmetry': True,
'num_twist_cp': 5
}
mesh, twist_cp = generate_mesh(mesh_dict)
surf_dict = {
# Wing definition
'name':
'wing', # name of the surface
# 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',
'symmetry':
True,
'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':
False,
'distributed_fuel_weight':
True,
# Constraints
'exact_failure_constraint':
True, # 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
}
# 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.)
indep_var_comp.add_output('fuel_mass', val=10000., units='kg')
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)
if surf_dict['distributed_fuel_weight']:
prob.model.connect('wing.fuel_mass',
'wing.struct_states.fuel_mass')
prob.model.connect('wing.struct_setup.fuel_vols',
'wing.struct_states.fuel_vols')
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('wing.spar_thickness_cp',
lower=0.01,
upper=0.5,
ref=1e-1)
prob.model.add_design_var('wing.skin_thickness_cp',
lower=0.01,
upper=0.5,
ref=1e-1)
prob.model.add_constraint('wing.failure', upper=0.)
#prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_mass', scaler=1e-5)
import warnings
#warnings.filterwarnings('error')
# Set up the problem
prob.setup()
prob.run_model()
data = prob.check_partials(compact_print=True,
out_stream=None,
method='cs')
assert_check_partials(data, atol=1e20, rtol=1e-6)
prob.run_driver()
assert_rel_error(self, prob['wing.structural_mass'], 16704.10113356,
1e-6)
def test_multiple_masses(self):
# Create a dictionary to store options about the surface
mesh_dict = {'num_y' : 31,
'wing_type' : 'rect',
'span' : 10,
'symmetry' : True}
mesh = generate_mesh(mesh_dict)
surface = {
# 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,
# 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' : 0.5, # 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 = om.Problem()
ny = surface['mesh'].shape[1]
surface['n_point_masses'] = 2
indep_var_comp = om.IndepVarComp()
indep_var_comp.add_output('loads', val=np.zeros((ny, 6)), units='N')
indep_var_comp.add_output('load_factor', val=1.)
point_masses = np.array([[10., 20.]])
point_mass_locations = np.array([[1., -1., 0.],
[1., -2., 0.]])
indep_var_comp.add_output('point_masses', val=point_masses, units='kg')
indep_var_comp.add_output('point_mass_locations', val=point_mass_locations, units='m')
struct_group = SpatialBeamAlone(surface=surface)
# Add indep_vars to the structural group
struct_group.add_subsystem('indep_vars',
indep_var_comp,
promotes=['*'])
prob.model.add_subsystem(surface['name'], struct_group, promotes=['*'])
# Set up the problem
prob.setup()
prob.run_model()
assert_rel_error(self, prob['vonmises'][-1, 0], 1557126.5793494075, 1e-4)
'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,
}
## Part-2: Initialize your problem and add flow conditions ------------
# Create the problem and assign the model group
prob = om.Problem()
ny = surf_dict['mesh'].shape[1]
indep_var_comp = om.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)
## Part-3: Add your design variables, constraints, and objective
# Import the Scipy Optimizer and set the driver of the problem to use
# it, which defaults to an SLSQP optimization method
prob.driver = om.ScipyOptimizeDriver()
prob.driver.options['disp'] = True
prob.driver.options['tol'] = 1e-9
recorder = om.SqliteRecorder('struct.db')
prob.driver.add_recorder(recorder)
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,
# 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.zeros((ny, 6)), 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)
from openmdao.api import ScipyOptimizeDriver
prob.driver = ScipyOptimizeDriver()
# Setup problem and add design variables, constraint, and objective
prob.model.add_design_var('wing.thickness_cp', lower=0.01, upper=0.5, scaler=1e2)
prob.model.add_constraint('wing.failure', upper=0.)
prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_mass', scaler=1e-5)
# Set up the problem
prob.setup()
from openmdao.api import view_model
prob.run_driver()
assert_rel_error(self, prob['wing.structural_mass'][0], 13601.162582, 1e-4)
assert_rel_error(self, prob['wing.disp'][1, 2], 0., 1e-4)
def test(self):
import numpy as np
from openaerostruct.geometry.utils import generate_mesh
from openaerostruct.geometry.geometry_group import Geometry
from openaerostruct.transfer.displacement_transfer import DisplacementTransfer
from openaerostruct.structures.struct_groups import SpatialBeamAlone
from openmdao.api import IndepVarComp, Problem, Group, SqliteRecorder
# 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,
# 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)
from openmdao.api import ScipyOptimizeDriver
prob.driver = ScipyOptimizeDriver()
prob.driver.options['disp'] = True
prob.driver.options['tol'] = 1e-9
recorder = SqliteRecorder('struct.db')
prob.driver.add_recorder(recorder)
prob.driver.recording_options['record_derivatives'] = True
prob.driver.recording_options['includes'] = ['*']
# Setup problem and add design variables, constraint, and objective
prob.model.add_design_var('wing.thickness_cp', lower=0.01, upper=0.5, ref=1e-1)
prob.model.add_constraint('wing.failure', upper=0.)
prob.model.add_constraint('wing.thickness_intersects', upper=0.)
# Add design variables, constraisnt, and objective on the problem
prob.model.add_objective('wing.structural_mass', scaler=1e-5)
# Set up the problem
prob.setup(force_alloc_complex=False)
# prob.run_model()
# prob.check_partials(compact_print=False, method='fd')
# exit()
prob.run_driver()
assert_rel_error(self, prob['wing.structural_mass'][0], 71088.4682399, 1e-8)
def test_multiple_masses(self):
# Create a dictionary to store options about the surface
mesh_dict = {'num_y' : 31,
'wing_type' : 'rect',
'span' : 10,
'symmetry' : True}
mesh = generate_mesh(mesh_dict)
surface = {
# 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,
# 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' : 0.5, # 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 = surface['mesh'].shape[1]
surface['n_point_masses'] = 2
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('loads', val=np.zeros((ny, 6)), units='N')
indep_var_comp.add_output('load_factor', val=1.)
engine_thrusts = np.array([[10., 20.]])
point_mass_locations = np.array([[1., -1., 0.],
[1., -2., 0.]])
indep_var_comp.add_output('engine_thrusts', val=engine_thrusts, units='N')
indep_var_comp.add_output('point_mass_locations', val=point_mass_locations, units='m')
struct_group = SpatialBeamAlone(surface=surface)
# Add indep_vars to the structural group
struct_group.add_subsystem('indep_vars',
indep_var_comp,
promotes=['*'])
prob.model.add_subsystem(surface['name'], struct_group, promotes=['*'])
# Set up the problem
prob.setup()
prob.run_model()
assert_rel_error(self, prob['vonmises'][-1, 0], 137509.870021, 1e-4)
