def setup(self):
surface = self.options['surface']
ny = surface['num_y']
if 'spar_thickness_cp' in surface.keys(
) or 'skin_thickness_cp' in surface.keys():
# 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 'spar_thickness_cp' in surface.keys():
n_cp = len(surface['spar_thickness_cp'])
# Add bspline components for active bspline geometric variables.
self.add_subsystem('spar_thickness_bsp',
BsplinesComp(in_name='spar_thickness_cp',
out_name='spar_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['spar_thickness_cp'],
promotes_outputs=['spar_thickness'])
indep_var_comp.add_output('spar_thickness_cp',
val=surface['spar_thickness_cp'],
units='m')
if 'skin_thickness_cp' in surface.keys():
n_cp = len(surface['skin_thickness_cp'])
# Add bspline components for active bspline geometric variables.
self.add_subsystem('skin_thickness_bsp',
BsplinesComp(in_name='skin_thickness_cp',
out_name='skin_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['skin_thickness_cp'],
promotes_outputs=['skin_thickness'])
indep_var_comp.add_output('skin_thickness_cp',
val=surface['skin_thickness_cp'],
units='m')
self.add_subsystem(
'wingbox_geometry',
WingboxGeometry(surface=surface),
promotes_inputs=['mesh'],
promotes_outputs=['fem_chords', 'fem_twists', 'streamwise_chords'])
self.add_subsystem('wingbox',
SectionPropertiesWingbox(surface=surface),
promotes_inputs=[
'spar_thickness', 'skin_thickness', 't_over_c',
'fem_chords', 'fem_twists', 'streamwise_chords'
],
promotes_outputs=[
'A', 'Iy', 'Qz', 'Iz', 'J', 'A_enc', 'A_int',
'htop', 'hbottom', 'hfront', 'hrear'
])
def test(self):
"""
This is for checking the partials.
"""
surface = get_default_surfaces()[0]
# turn down some of these properties, so the absolute deriv error isn't magnified
surface['E'] = 7
surface['G'] = 3
surface['yield'] = .02
surface['data_x_upper'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_x_lower'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_y_upper'] = np.array([
0.0447, 0.046, 0.0472, 0.0484, 0.0495, 0.0505, 0.0514, 0.0523,
0.0531, 0.0538, 0.0545, 0.0551, 0.0557, 0.0563, 0.0568, 0.0573,
0.0577, 0.0581, 0.0585, 0.0588, 0.0591, 0.0593, 0.0595, 0.0597,
0.0599, 0.06, 0.0601, 0.0602, 0.0602, 0.0602, 0.0602, 0.0602,
0.0601, 0.06, 0.0599, 0.0598, 0.0596, 0.0594, 0.0592, 0.0589,
0.0586, 0.0583, 0.058, 0.0576, 0.0572, 0.0568, 0.0563, 0.0558,
0.0553, 0.0547, 0.0541
],
dtype='complex128')
surface['data_y_lower'] = np.array([
-0.0447, -0.046, -0.0473, -0.0485, -0.0496, -0.0506, -0.0515,
-0.0524, -0.0532, -0.054, -0.0547, -0.0554, -0.056, -0.0565,
-0.057, -0.0575, -0.0579, -0.0583, -0.0586, -0.0589, -0.0592,
-0.0594, -0.0595, -0.0596, -0.0597, -0.0598, -0.0598, -0.0598,
-0.0598, -0.0597, -0.0596, -0.0594, -0.0592, -0.0589, -0.0586,
-0.0582, -0.0578, -0.0573, -0.0567, -0.0561, -0.0554, -0.0546,
-0.0538, -0.0529, -0.0519, -0.0509, -0.0497, -0.0485, -0.0472,
-0.0458, -0.0444
],
dtype='complex128')
surface['original_wingbox_airfoil_t_over_c'] = 0.1
comp = SectionPropertiesWingbox(surface=surface)
run_test(self, comp, complex_flag=True, method='cs', step=1e-40)
def test(self):
surface = get_default_surfaces()[0]
surface['data_x_upper'] = np.array([0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2, 0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31, 0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42, 0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53, 0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6], dtype = 'complex128')
surface['data_x_lower'] = np.array([0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2, 0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31, 0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42, 0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53, 0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6], dtype = 'complex128')
surface['data_y_upper'] = np.array([ 0.0447, 0.046, 0.0472, 0.0484, 0.0495, 0.0505, 0.0514, 0.0523, 0.0531, 0.0538, 0.0545, 0.0551, 0.0557, 0.0563, 0.0568, 0.0573, 0.0577, 0.0581, 0.0585, 0.0588, 0.0591, 0.0593, 0.0595, 0.0597, 0.0599, 0.06, 0.0601, 0.0602, 0.0602, 0.0602, 0.0602, 0.0602, 0.0601, 0.06, 0.0599, 0.0598, 0.0596, 0.0594, 0.0592, 0.0589, 0.0586, 0.0583, 0.058, 0.0576, 0.0572, 0.0568, 0.0563, 0.0558, 0.0553, 0.0547, 0.0541], dtype = 'complex128')
surface['data_y_lower'] = np.array([-0.0447, -0.046, -0.0473, -0.0485, -0.0496, -0.0506, -0.0515, -0.0524, -0.0532, -0.054, -0.0547, -0.0554, -0.056, -0.0565, -0.057, -0.0575, -0.0579, -0.0583, -0.0586, -0.0589, -0.0592, -0.0594, -0.0595, -0.0596, -0.0597, -0.0598, -0.0598, -0.0598, -0.0598, -0.0597, -0.0596, -0.0594, -0.0592, -0.0589, -0.0586, -0.0582, -0.0578, -0.0573, -0.0567, -0.0561, -0.0554, -0.0546, -0.0538, -0.0529, -0.0519, -0.0509, -0.0497, -0.0485, -0.0472, -0.0458, -0.0444], dtype = 'complex128')
surface['original_wingbox_airfoil_t_over_c'] = 0.1
comp = SectionPropertiesWingbox(surface=surface)
run_test(self, comp, complex_flag=True)
def setup(self):
surface = self.options['surface']
ny = surface['mesh'].shape[1]
if 'spar_thickness_cp' in surface.keys() or 'skin_thickness_cp' in surface.keys():
# Add independent variables that do not belong to a specific component
indep_var_comp = om.IndepVarComp()
# Add structural components to the surface-specific group
self.add_subsystem('indep_vars',
indep_var_comp,
promotes=['*'])
if 'spar_thickness_cp' in surface.keys():
n_cp = len(surface['spar_thickness_cp'])
# Add bspline components for active bspline geometric variables.
x_interp = np.linspace(0., 1., int(ny-1))
comp = self.add_subsystem('spar_thickness_bsp', om.SplineComp(
method='bsplines', x_interp_val=x_interp,
num_cp=n_cp,
interp_options={'order' : min(n_cp, 4)}),
promotes_inputs=['spar_thickness_cp'], promotes_outputs=['spar_thickness'])
comp.add_spline(y_cp_name='spar_thickness_cp', y_interp_name='spar_thickness',
y_units='m')
indep_var_comp.add_output('spar_thickness_cp', val=surface['spar_thickness_cp'], units='m')
if 'skin_thickness_cp' in surface.keys():
n_cp = len(surface['skin_thickness_cp'])
# Add bspline components for active bspline geometric variables.
x_interp = np.linspace(0., 1., int(ny-1))
comp = self.add_subsystem('skin_thickness_bsp', om.SplineComp(
method='bsplines', x_interp_val=x_interp,
num_cp=n_cp,
interp_options={'order' : min(n_cp, 4)}),
promotes_inputs=['skin_thickness_cp'], promotes_outputs=['skin_thickness'])
comp.add_spline(y_cp_name='skin_thickness_cp', y_interp_name='skin_thickness',
y_units='m')
indep_var_comp.add_output('skin_thickness_cp', val=surface['skin_thickness_cp'], units='m')
self.add_subsystem('wingbox_geometry',
WingboxGeometry(surface=surface),
promotes_inputs=['mesh'],
promotes_outputs=['fem_chords', 'fem_twists', 'streamwise_chords'])
self.add_subsystem('wingbox',
SectionPropertiesWingbox(surface=surface),
promotes_inputs=['spar_thickness', 'skin_thickness', 't_over_c', 'fem_chords', 'fem_twists', 'streamwise_chords'],
promotes_outputs=['A', 'Iy', 'Qz', 'Iz', 'J', 'A_enc', 'A_int', 'htop', 'hbottom', 'hfront', 'hrear'])
def test2(self):
"""
This is for checking the computation.
"""
surface = get_default_surfaces()[0]
surface['t_over_c_cp'] = np.array([0.1, 0.15, 0.2])
surface['spar_thickness_cp'] = np.array([0.004, 0.008, 0.02])
surface['skin_thickness_cp'] = np.array([0.01, 0.015, 0.021])
surface['fem_chords_cp'] = np.array([2., 3., 4.])
surface['streamwise_chords_cp'] = np.array([3., 4., 5.])
surface['fem_twists_cp'] = np.array([5., 3., 2.]) / 180. * np.pi
surface['data_x_upper'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_x_lower'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_y_upper'] = np.array([
0.0447, 0.046, 0.0472, 0.0484, 0.0495, 0.0505, 0.0514, 0.0523,
0.0531, 0.0538, 0.0545, 0.0551, 0.0557, 0.0563, 0.0568, 0.0573,
0.0577, 0.0581, 0.0585, 0.0588, 0.0591, 0.0593, 0.0595, 0.0597,
0.0599, 0.06, 0.0601, 0.0602, 0.0602, 0.0602, 0.0602, 0.0602,
0.0601, 0.06, 0.0599, 0.0598, 0.0596, 0.0594, 0.0592, 0.0589,
0.0586, 0.0583, 0.058, 0.0576, 0.0572, 0.0568, 0.0563, 0.0558,
0.0553, 0.0547, 0.0541
],
dtype='complex128')
surface['data_y_lower'] = np.array([
-0.0447, -0.046, -0.0473, -0.0485, -0.0496, -0.0506, -0.0515,
-0.0524, -0.0532, -0.054, -0.0547, -0.0554, -0.056, -0.0565,
-0.057, -0.0575, -0.0579, -0.0583, -0.0586, -0.0589, -0.0592,
-0.0594, -0.0595, -0.0596, -0.0597, -0.0598, -0.0598, -0.0598,
-0.0598, -0.0597, -0.0596, -0.0594, -0.0592, -0.0589, -0.0586,
-0.0582, -0.0578, -0.0573, -0.0567, -0.0561, -0.0554, -0.0546,
-0.0538, -0.0529, -0.0519, -0.0509, -0.0497, -0.0485, -0.0472,
-0.0458, -0.0444
],
dtype='complex128')
surface['original_wingbox_airfoil_t_over_c'] = 0.1
mesh = surface['mesh']
ny = mesh.shape[1]
nx = mesh.shape[0]
n_cp = len(surface['t_over_c_cp'])
prob = Problem()
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('t_over_c_cp', val=surface['t_over_c_cp'])
indep_var_comp.add_output('spar_thickness_cp',
val=surface['spar_thickness_cp'])
indep_var_comp.add_output('skin_thickness_cp',
val=surface['skin_thickness_cp'])
indep_var_comp.add_output('fem_chords_cp',
val=surface['fem_chords_cp'])
indep_var_comp.add_output('streamwise_chords_cp',
val=surface['streamwise_chords_cp'])
indep_var_comp.add_output('fem_twists_cp',
val=surface['fem_twists_cp'])
prob.model.add_subsystem('indep_var_comp',
indep_var_comp,
promotes=['*'])
prob.model.add_subsystem('t_over_c_bsp',
BsplinesComp(in_name='t_over_c_cp',
out_name='t_over_c',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['t_over_c_cp'],
promotes_outputs=['t_over_c'])
prob.model.add_subsystem('skin_thickness_bsp',
BsplinesComp(in_name='skin_thickness_cp',
out_name='skin_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['skin_thickness_cp'],
promotes_outputs=['skin_thickness'])
prob.model.add_subsystem('spar_thickness_bsp',
BsplinesComp(in_name='spar_thickness_cp',
out_name='spar_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['spar_thickness_cp'],
promotes_outputs=['spar_thickness'])
prob.model.add_subsystem('fem_chords_bsp',
BsplinesComp(in_name='fem_chords_cp',
out_name='fem_chords',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['fem_chords_cp'],
promotes_outputs=['fem_chords'])
prob.model.add_subsystem('streamwise_chords_bsp',
BsplinesComp(in_name='streamwise_chords_cp',
out_name='streamwise_chords',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['streamwise_chords_cp'],
promotes_outputs=['streamwise_chords'])
prob.model.add_subsystem('fem_twists_bsp',
BsplinesComp(in_name='fem_twists_cp',
out_name='fem_twists',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['fem_twists_cp'],
promotes_outputs=['fem_twists'])
comp = SectionPropertiesWingbox(surface=surface)
prob.model.add_subsystem('sec_prop_wb', comp, promotes=['*'])
prob.setup()
#
# from openmdao.api import view_model
# view_model(prob)
prob.run_model()
# print( prob['A'] )
# print( prob['A_enc'] )
# print( prob['A_int'] )
# print( prob['Iy'] )
# print( prob['Qz'] )
# print( prob['Iz'] )
# print( prob['J'] )
# print( prob['htop'] )
# print( prob['hbottom'] )
# print( prob['hfront'] )
# print( prob['hrear'] )
assert_rel_error(self, prob['A'],
np.array([0.02203548, 0.0563726, 0.11989703]), 1e-6)
assert_rel_error(self, prob['A_enc'],
np.array([0.3243776, 0.978003, 2.17591]), 1e-6)
assert_rel_error(self, prob['A_int'],
np.array([0.3132502, 0.949491, 2.11512]), 1e-6)
assert_rel_error(self, prob['Iy'],
np.array([0.00218612, 0.01455083, 0.06342765]), 1e-6)
assert_rel_error(self, prob['Qz'],
np.array([0.00169233, 0.00820558, 0.02707493]), 1e-6)
assert_rel_error(self, prob['Iz'],
np.array([0.00055292, 0.00520911, 0.02785168]), 1e-6)
assert_rel_error(self, prob['J'],
np.array([0.00124939, 0.01241967, 0.06649673]), 1e-6)
assert_rel_error(self, prob['htop'],
np.array([0.19106873, 0.36005945, 0.5907887]), 1e-6)
assert_rel_error(self, prob['hbottom'],
np.array([0.19906584, 0.37668887, 0.61850335]), 1e-6)
assert_rel_error(self, prob['hfront'],
np.array([0.52341176, 0.78649186, 1.04902676]), 1e-6)
assert_rel_error(self, prob['hrear'],
np.array([0.47524073, 0.71429312, 0.95303545]), 1e-6)
def test3(self):
"""
This is an extreme nonphysical case (large twist angles) for checking the computation.
"""
surface = get_default_surfaces()[0]
surface['t_over_c_cp'] = np.array([0.1, 0.15, 0.2])
surface['spar_thickness_cp'] = np.array([0.004, 0.008, 0.02])
surface['skin_thickness_cp'] = np.array([0.01, 0.015, 0.021])
surface['fem_chords_cp'] = np.array([2., 3., 4.])
surface['streamwise_chords_cp'] = np.array([3., 4., 5.])
surface['fem_twists_cp'] = np.array([5., 3., 2.])
surface['data_x_upper'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_x_lower'] = np.array([
0.1, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.2,
0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29, 0.3, 0.31,
0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38, 0.39, 0.4, 0.41, 0.42,
0.43, 0.44, 0.45, 0.46, 0.47, 0.48, 0.49, 0.5, 0.51, 0.52, 0.53,
0.54, 0.55, 0.56, 0.57, 0.58, 0.59, 0.6
],
dtype='complex128')
surface['data_y_upper'] = np.array([
0.0447, 0.046, 0.0472, 0.0484, 0.0495, 0.0505, 0.0514, 0.0523,
0.0531, 0.0538, 0.0545, 0.0551, 0.0557, 0.0563, 0.0568, 0.0573,
0.0577, 0.0581, 0.0585, 0.0588, 0.0591, 0.0593, 0.0595, 0.0597,
0.0599, 0.06, 0.0601, 0.0602, 0.0602, 0.0602, 0.0602, 0.0602,
0.0601, 0.06, 0.0599, 0.0598, 0.0596, 0.0594, 0.0592, 0.0589,
0.0586, 0.0583, 0.058, 0.0576, 0.0572, 0.0568, 0.0563, 0.0558,
0.0553, 0.0547, 0.0541
],
dtype='complex128')
surface['data_y_lower'] = np.array([
-0.0447, -0.046, -0.0473, -0.0485, -0.0496, -0.0506, -0.0515,
-0.0524, -0.0532, -0.054, -0.0547, -0.0554, -0.056, -0.0565,
-0.057, -0.0575, -0.0579, -0.0583, -0.0586, -0.0589, -0.0592,
-0.0594, -0.0595, -0.0596, -0.0597, -0.0598, -0.0598, -0.0598,
-0.0598, -0.0597, -0.0596, -0.0594, -0.0592, -0.0589, -0.0586,
-0.0582, -0.0578, -0.0573, -0.0567, -0.0561, -0.0554, -0.0546,
-0.0538, -0.0529, -0.0519, -0.0509, -0.0497, -0.0485, -0.0472,
-0.0458, -0.0444
],
dtype='complex128')
surface['original_wingbox_airfoil_t_over_c'] = 0.1
mesh = surface['mesh']
ny = mesh.shape[1]
nx = mesh.shape[0]
n_cp = len(surface['t_over_c_cp'])
prob = Problem()
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('t_over_c_cp', val=surface['t_over_c_cp'])
indep_var_comp.add_output('spar_thickness_cp',
val=surface['spar_thickness_cp'])
indep_var_comp.add_output('skin_thickness_cp',
val=surface['skin_thickness_cp'])
indep_var_comp.add_output('fem_chords_cp',
val=surface['fem_chords_cp'])
indep_var_comp.add_output('streamwise_chords_cp',
val=surface['streamwise_chords_cp'])
indep_var_comp.add_output('fem_twists_cp',
val=surface['fem_twists_cp'])
prob.model.add_subsystem('indep_var_comp',
indep_var_comp,
promotes=['*'])
prob.model.add_subsystem('t_over_c_bsp',
BsplinesComp(in_name='t_over_c_cp',
out_name='t_over_c',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['t_over_c_cp'],
promotes_outputs=['t_over_c'])
prob.model.add_subsystem('skin_thickness_bsp',
BsplinesComp(in_name='skin_thickness_cp',
out_name='skin_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
units='m',
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['skin_thickness_cp'],
promotes_outputs=['skin_thickness'])
prob.model.add_subsystem('spar_thickness_bsp',
BsplinesComp(in_name='spar_thickness_cp',
out_name='spar_thickness',
num_control_points=n_cp,
num_points=int(ny - 1),
units='m',
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['spar_thickness_cp'],
promotes_outputs=['spar_thickness'])
prob.model.add_subsystem('fem_chords_bsp',
BsplinesComp(in_name='fem_chords_cp',
out_name='fem_chords',
num_control_points=n_cp,
num_points=int(ny - 1),
units='m',
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['fem_chords_cp'],
promotes_outputs=['fem_chords'])
prob.model.add_subsystem('streamwise_chords_bsp',
BsplinesComp(in_name='streamwise_chords_cp',
out_name='streamwise_chords',
num_control_points=n_cp,
num_points=int(ny - 1),
units='m',
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['streamwise_chords_cp'],
promotes_outputs=['streamwise_chords'])
prob.model.add_subsystem('fem_twists_bsp',
BsplinesComp(in_name='fem_twists_cp',
out_name='fem_twists',
units='deg',
num_control_points=n_cp,
num_points=int(ny - 1),
bspline_order=min(n_cp, 4),
distribution='uniform'),
promotes_inputs=['fem_twists_cp'],
promotes_outputs=['fem_twists'])
comp = SectionPropertiesWingbox(surface=surface)
prob.model.add_subsystem('sec_prop_wb', comp, promotes=['*'])
prob.setup()
#
# from openmdao.api import view_model
# view_model(prob)
prob.run_model()
# print( prob['A'] )
# print( prob['A_enc'] )
# print( prob['A_int'] )
# print( prob['Iy'] )
# print( prob['Qz'] )
# print( prob['Iz'] )
# print( prob['J'] )
# print( prob['htop'] )
# print( prob['hbottom'] )
# print( prob['hfront'] )
# print( prob['hrear'] )
assert_rel_error(self, prob['A'],
np.array([0.0058738, -0.05739528, -0.05042289]), 1e-6)
assert_rel_error(self, prob['A_enc'],
np.array([0.3243776, 0.978003, 2.17591]), 1e-6)
assert_rel_error(self, prob['A_int'],
np.array([0.3132502, 0.949491, 2.11512]), 1e-6)
assert_rel_error(
self, prob['Iy'],
np.array([3.59803239e-05, -1.52910019e-02, -4.01035510e-03]), 1e-6)
assert_rel_error(self, prob['Qz'],
np.array([0.00129261, 0.00870662, 0.02500053]), 1e-6)
assert_rel_error(self, prob['Iz'],
np.array([0.00056586, -0.00582207, -0.02877714]),
1e-6)
assert_rel_error(self, prob['J'],
np.array([0.00124939, 0.01241967, 0.06649673]), 1e-6)
assert_rel_error(self, prob['htop'],
np.array([0.53933652, -0.23509863, 0.71255343]), 1e-6)
assert_rel_error(self, prob['hbottom'],
np.array([0.50366564, -0.19185349, 0.73525459]), 1e-6)
assert_rel_error(self, prob['hfront'],
np.array([0.13442747, -0.78514756, -0.3919784]), 1e-6)
assert_rel_error(self, prob['hrear'],
np.array([0.12219305, -0.71214916, -0.35484131]),
1e-6)