def test_aero_analysis_flat_side_by_side(self):
OAS_prob = OASProblem({
'type': 'aero',
'optimize': False,
'record_db': False
})
OAS_prob.add_surface({
'name': 'wing',
'span': 5.,
'num_y': 3,
'span_cos_spacing': 0.,
'symmetry': False,
'offset': np.array([0., -2.5, 0.])
})
OAS_prob.add_surface({
'name': 'tail',
'span': 5.,
'num_y': 3,
'span_cos_spacing': 0.,
'symmetry': False,
'offset': np.array([0., 2.5, 0.])
})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.46173591841167183,
places=5)
self.assertAlmostEqual(prob['tail_perf.CL'],
0.46173591841167183,
places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .005524603647, places=5)
self.assertAlmostEqual(prob['tail_perf.CD'], .005524603647, places=5)
def test_aero_analysis_flat_multiple(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
OAS_prob.add_surface({'span_cos_spacing' : 0.})
OAS_prob.add_surface({'name' : 'tail',
'span_cos_spacing' : 0.,
'offset' : np.array([0., 0., 1000000.])})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['tail_perf.CL'], .46173591841167, places=5)
def test_aerostruct_analysis_symmetry(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'symmetry': True,
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.49879098021094814,
places=5)
self.assertAlmostEqual(prob['wing_perf.failure'],
-0.4358500552830447,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 70951.02191803591, places=1)
self.assertAlmostEqual(prob['CM'][1], -0.13082531653444995, places=2)
def test_aerostruct_analysis_symmetry(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'symmetry': True,
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.69060502679333224,
places=5)
self.assertAlmostEqual(prob['wing_perf.failure'],
0.064759950520982532,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 57109.065516474155, places=1)
self.assertAlmostEqual(prob['CM'][1], -0.19380236992046351, places=2)
def test_aerostruct_analysis(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'symmetry': False
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.6587983088529461,
places=5)
self.assertAlmostEqual(prob['wing_perf.failure'],
0.13716279310143381,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 55565.087226705218, places=2)
self.assertAlmostEqual(prob['CM'][1], -0.18836163204083048, places=2)
def test_aerostruct_analysis(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'symmetry': False
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.45756166834224915,
places=5)
self.assertAlmostEqual(prob['wing_perf.failure'],
-0.41828919706776535,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 66894.86498288115, places=2)
self.assertAlmostEqual(prob['CM'][1], -0.12243137977093457, places=2)
def test_aero_analysis_flat_multiple(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
OAS_prob.add_surface({'span_cos_spacing' : 0.})
OAS_prob.add_surface({'name' : 'tail',
'span_cos_spacing' : 0.,
'offset' : np.array([0., 0., 1000000.])})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['tail_perf.CL'], .46173591841167, places=5)
def test_aero_analysis_flat(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
OAS_prob.add_surface({'span_cos_spacing' : 0})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .005524603647, places=5)
def test_aero_analysis_flat_full(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
surf_dict = {'symmetry' : False}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .45655138, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], 0.0055402121081108589, places=5)
def test_struct_analysis_symmetry(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : False,
'record_db' : False})
surf_dict = {'symmetry' : True,
't_over_c' : 0.15}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing.structural_weight'], 988.13495481063956, places=3)
def test_aero_analysis_flat_viscous_full(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False,
'with_viscous' : True})
surf_dict = {'symmetry' : False}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .45655138, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], 0.018942466133780547, places=5)
def test_aero_analysis_flat_full(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
surf_dict = {'symmetry' : False}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .45655138, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], 0.0055402121081108589, places=5)
def test_struct_analysis_symmetry(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : False,
'record_db' : False})
surf_dict = {'symmetry' : True,
't_over_c' : 0.15}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing.structural_weight'], 988.13495481063956, places=3)
def test_aero_analysis_flat(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
OAS_prob.add_surface({'span_cos_spacing' : 0})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .005524603647, places=5)
def test_aero_analysis_flat_viscous_full(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False,
'with_viscous' : True})
surf_dict = {'symmetry' : False}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .45655138, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], 0.018942466133780547, places=5)
def test_aerostruct_analysis_symmetry_deriv(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': True
})
surf_dict = {
'symmetry': True,
'num_y': 7,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
data = prob.check_partial_derivatives(out_stream=None)
new_dict = {}
for key1 in data.keys():
for key2 in data[key1].keys():
for key3 in data[key1][key2].keys():
if 'rel' in key3:
error = np.linalg.norm(data[key1][key2][key3])
new_key = key1 + '_' + key2[0] + '_' + key2[
1] + '_' + key3
new_dict.update({new_key: error})
for key in new_dict.keys():
error = new_dict[key]
if not np.isnan(error):
# The FD check is not valid for these cases
if 'assembly_forces_Iy' in key or 'assembly_forces_J' in key or \
'assembly_forces_A' in key or 'assembly_K_loads' in key or \
'assembly_forces_loads' in key or 'assembly_forces_Iz' in key or \
'assembly_forces_nodes' in key or 'CM_wing_S_ref' in key or \
'CM_rho' in key:
pass
elif 'K' in key or 'vonmises' in key:
self.assertAlmostEqual(0., error, places=0)
else:
self.assertAlmostEqual(0., error, places=2)
def test_aero_analysis_flat_side_by_side(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False,
'record_db' : False})
OAS_prob.add_surface({'name' : 'wing',
'span' : 5.,
'num_y' : 3,
'span_cos_spacing' : 0.,
'symmetry' : False,
'offset' : np.array([0., -2.5, 0.])})
OAS_prob.add_surface({'name' : 'tail',
'span' : 5.,
'num_y' : 3,
'span_cos_spacing' : 0.,
'symmetry' : False,
'offset' : np.array([0., 2.5, 0.])})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.46173591841167183, places=5)
self.assertAlmostEqual(prob['tail_perf.CL'], 0.46173591841167183, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .005524603647, places=5)
self.assertAlmostEqual(prob['tail_perf.CD'], .005524603647, places=5)
def test_aerostruct_analysis(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : False,
'record_db' : False})
surf_dict = {'num_y' : 13,
'num_x' : 2,
'wing_type' : 'CRM',
'CD0' : 0.015,
'symmetry' : False}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.6587983088529461, places=5)
self.assertAlmostEqual(prob['wing_perf.failure'], 0.13716279310143381, places=5)
self.assertAlmostEqual(prob['fuelburn'], 55565.087226705218, places=2)
self.assertAlmostEqual(prob['CM'][1], -0.18836163204083048, places=2)
def test_aerostruct_analysis_symmetry(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : False,
'record_db' : False})
surf_dict = {'symmetry' : True,
'num_y' : 13,
'num_x' : 2,
'wing_type' : 'CRM',
'CD0' : 0.015}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.69060502679333224, places=5)
self.assertAlmostEqual(prob['wing_perf.failure'], 0.064759950520982532, places=5)
self.assertAlmostEqual(prob['fuelburn'], 57109.065516474155, places=1)
self.assertAlmostEqual(prob['CM'][1], -0.19380236992046351, places=2)
def test_aerostruct_analysis(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'symmetry': False
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.53470610411546438)
self.assertAlmostEqual(prob['wing_perf.failure'],
-0.88555523062055341,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 99367.43763782426, places=2)
def test_aerostruct_analysis_symmetry(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': False,
'record_db': False
})
surf_dict = {
'symmetry': True,
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.57096081806728627)
self.assertAlmostEqual(prob['wing_perf.failure'],
-0.8969902215221538,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 105120.8601409321, places=2)
def test_aerostruct_analysis_symmetry_deriv(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : False,
'record_db' : True})
surf_dict = {'symmetry' : True,
'num_y' : 7,
'num_x' : 2,
'wing_type' : 'CRM',
'CD0' : 0.015}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
data = prob.check_partial_derivatives(out_stream=None)
new_dict = {}
for key1 in data.keys():
for key2 in data[key1].keys():
for key3 in data[key1][key2].keys():
if 'rel' in key3:
error = np.linalg.norm(data[key1][key2][key3])
new_key = key1+'_'+key2[0]+'_'+key2[1]+'_'+key3
new_dict.update({new_key : error})
for key in new_dict.keys():
error = new_dict[key]
if not np.isnan(error):
# The FD check is not valid for these cases
if 'assembly_forces_Iy' in key or 'assembly_forces_J' in key or \
'assembly_forces_A' in key or 'assembly_K_loads' in key or \
'assembly_forces_loads' in key or 'assembly_forces_Iz' in key or \
'assembly_forces_nodes' in key or 'CM_wing_S_ref' in key or \
'CM_rho' in key:
pass
elif 'K' in key or 'vonmises' in key:
self.assertAlmostEqual(0., error, places=0)
else:
self.assertAlmostEqual(0., error, places=2)
raise
# Set problem type
prob_dict = {'type' : 'aerostruct',
'with_viscous' : True,
'cg' : np.array([30., 0., 5.])
}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize' : False})
else: # perform optimization
prob_dict.update({'optimize' : True})
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface
surf_dict = {'num_y' : 7,
'num_x' : 2,
'wing_type' : 'CRM',
'CD0' : 0.015,
'symmetry' : True,
'num_twist_cp' : 2,
'num_thickness_cp' : 2}
# Add the specified wing surface to the problem
OAS_prob.add_surface(surf_dict)
# Add design variables, constraint, and objective on the problem
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
def test_aero_optimization_fd(self):
# Need to use SLSQP here because SNOPT finds a different optimum
OAS_prob = OASProblem({
'type': 'aero',
'optimize': True,
'record_db': False,
'optimizer': 'SLSQP',
'force_fd': True
})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('wing.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('wing.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('wing.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'],
0.0038513637269919619,
places=5)
raise
# Set problem type
prob_dict = {
'type': 'aerostruct',
'with_viscous': True,
'cg': np.array([30., 0., 5.])
}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize': False})
else: # perform optimization
prob_dict.update({'optimize': True})
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface
surf_dict = {
'num_y': 5,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'symmetry': True,
'num_twist_cp': 3,
'num_thickness_cp': 3
}
# Add the specified wing surface to the problem
OAS_prob.add_surface(surf_dict)
def test_aerostruct_optimization_symmetry_multiple(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': True,
'with_viscous': True,
'record_db': False
})
surf_dict = {
'name': 'wing',
'symmetry': True,
'num_y': 5,
'num_x': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'num_twist_cp': 2,
'num_thickness_cp': 2
}
OAS_prob.add_surface(surf_dict)
surf_dict.update({
'name': 'tail',
'offset': np.array([10., 0., 10.])
})
OAS_prob.add_surface(surf_dict)
# Add design variables and constraints for both the wing and tail
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.01,
upper=0.5,
scaler=1e2)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_constraint('wing_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('tail.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('tail.thickness_cp',
lower=0.01,
upper=0.5,
scaler=1e2)
OAS_prob.add_constraint('tail_perf.failure', upper=0.)
OAS_prob.add_constraint('tail_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('L_equals_W', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-5)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'],
171166.87568490615,
places=1)
self.assertAlmostEqual(prob['wing_perf.failure'], 0, places=5)
def test_struct_optimization_symmetry_exact(self):
OAS_prob = OASProblem({
'type': 'struct',
'optimize': True,
'record_db': False
})
OAS_prob.add_surface({
'exact_failure_constraint': True,
't_over_c': 0.15
})
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.001,
upper=0.25,
scaler=1e2)
OAS_prob.add_constraint('wing.failure', upper=0.)
OAS_prob.add_constraint('wing.thickness_intersects', upper=0.)
OAS_prob.add_objective('wing.structural_weight', scaler=1e-3)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing.structural_weight'],
1132.0650209475402,
places=2)
def test_aero_optimization_fd(self):
# Need to use SLSQP here because SNOPT finds a different optimum
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True,
'record_db' : False,
'optimizer' : 'SLSQP',
'force_fd' : True})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('wing.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('wing.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('wing.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'], 0.0038513637269919619, places=5)
def test_aero_viscous_optimization(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True,
'record_db' : False,
'with_viscous' : True})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('wing.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('wing.dihedral', lower=-10., upper=20.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'], 0.019234984422361764, places=5)
def test_aero_viscous_chord_optimization(self):
# Need to use SLSQP here because SNOPT finds a different optimum
OAS_prob = OASProblem({
'type': 'aero',
'optimize': True,
'record_db': False,
'optimizer': 'SLSQP',
'with_viscous': True
})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.chord_cp', lower=0.1, upper=3.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_constraint('wing.S_ref', equals=20)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'],
0.023570021288019886,
places=5)
def test_aero_multiple_opt(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True,
'record_db' : False})
surf_dict = { 'name' : 'wing',
'span' : 5.,
'num_y' : 3,
'span_cos_spacing' : 0.}
OAS_prob.add_surface(surf_dict)
surf_dict.update({'name' : 'tail',
'offset' : np.array([0., 0., 10.])})
OAS_prob.add_surface(surf_dict)
OAS_prob.add_desvar('tail.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('tail.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('tail.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('tail.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('tail_perf.CL', equals=0.5)
OAS_prob.add_objective('tail_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], 0.41532382375677429, places=4)
self.assertAlmostEqual(prob['tail_perf.CL'], .5, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .0075400306289957033, places=5)
self.assertAlmostEqual(prob['tail_perf.CD'], 0.008087914662238814, places=5)
def test_aero_viscous_chord_optimization(self):
# Need to use SLSQP here because SNOPT finds a different optimum
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True,
'record_db' : False,
'optimizer' : 'SLSQP',
'with_viscous' : True})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.chord_cp', lower=0.1, upper=3.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_constraint('wing.S_ref', equals=20)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'], 0.023570021288019886, places=5)
def test_aerostruct_optimization_symmetry_multiple(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : True,
'with_viscous' : True,
'record_db' : False})
surf_dict = {'name' : 'wing',
'symmetry' : True,
'num_y' : 5,
'num_x' : 2,
'wing_type' : 'CRM',
'CD0' : 0.015,
'num_twist_cp' : 2,
'num_thickness_cp' : 2}
OAS_prob.add_surface(surf_dict)
surf_dict.update({'name' : 'tail',
'offset':np.array([10., 0., 10.])})
OAS_prob.add_surface(surf_dict)
# Add design variables and constraints for both the wing and tail
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp', lower=0.01, upper=0.5, scaler=1e2)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_constraint('wing_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('tail.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('tail.thickness_cp', lower=0.01, upper=0.5, scaler=1e2)
OAS_prob.add_constraint('tail_perf.failure', upper=0.)
OAS_prob.add_constraint('tail_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('L_equals_W', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-5)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'], 171166.87568490615, places=1)
self.assertAlmostEqual(prob['wing_perf.failure'], 0, places=5)
def test_aerostruct_optimization_symmetry(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : True,
'with_viscous' : True,
'record_db' : False})
surf_dict = {'symmetry' : True,
'num_y' : 7,
'num_x' : 3,
'wing_type' : 'CRM',
'CD0' : 0.015,
'num_twist_cp' : 2,
'num_thickness_cp' : 2}
OAS_prob.add_surface(surf_dict)
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp', lower=0.01, upper=0.5, scaler=1e2)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_constraint('wing_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('L_equals_W', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'], 96077.224922178371, places=0)
self.assertAlmostEqual(prob['wing_perf.failure'], 0, places=5)
def OAS_setup(user_prob_dict={}, user_surf_list=[]):
# default prob_dict and surf_dict's from run_aerostruct.py
default_prob_dict = _get_default_prob_dict()
default_prob_dict.update(user_prob_dict)
prob_dict = default_prob_dict
# remove 'des_vars', 'contraints', and 'objectives' entries from prob_dict
# so it doesn't potentially conflict with OASProblem object
des_vars = prob_dict.pop('des_vars', [])
constraints = prob_dict.pop('constraints', [])
objectives = prob_dict.pop('objectives', [])
if user_surf_list:
# replace default_surf_list if user supplied one
surf_list = user_surf_list
else:
surf_list = _get_default_surf_list()
# when wrapping from Matlab, an array of a single value will always be
# converted to a float in Python and not an iterable, which causes problems.
iterable_vars = [
'chord_cp', 'thickness_cp', 'radius_cp', 'twist_cp', 'xshear_cp',
'yshear_cp', 'zshear_cp'
]
for surf in surf_list:
for key, val in iteritems(surf):
if (key in iterable_vars) and (not hasattr(val, '__iter__')):
surf[key] = np.array([val]) # make an ndarray from list
# Create OASProblem object
OASprob = OASProblem(prob_dict)
# Add surfaces to OASProblem
for surf in surf_list:
OASprob.add_surface(surf)
# Add design variables to OASProblem
for var_tuple in des_vars:
OASprob.add_desvar(var_tuple[0], **var_tuple[1])
# Add constraints to OASProblem
for var_tuple in constraints:
OASprob.add_constraint(var_tuple[0], **var_tuple[1])
# Add objectives to OASProblem
for var_tuple in objectives:
OASprob.add_objective(var_tuple[0], **var_tuple[1])
# setup OpenMDAO components in OASProblem
OASprob.setup()
return OASprob
def test_aero_optimization_chord_monotonic_no_sym(self):
OAS_prob = OASProblem({
'type': 'aero',
'optimize': True,
'record_db': False,
'symmetry': False,
'with_viscous': False
})
OAS_prob.add_surface({
'chord_cp': np.random.random(5),
'num_y': 11,
'monotonic_con': ['chord'],
'span_cos_spacing': 0.,
})
OAS_prob.add_desvar('wing.chord_cp', lower=0.1, upper=5.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.1)
OAS_prob.add_constraint('wing.S_ref', equals=20)
OAS_prob.add_constraint('wing.monotonic_chord', upper=0.)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'],
0.00057432581266351113,
places=5)
self.assertAlmostEqual(prob['wing.monotonic_chord'][0],
-1.710374671671999,
places=2)
from os import sys, path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from OpenAeroStruct import OASProblem
from time import time
import numpy as np
# Set problem type
prob_dict = {
'type': 'aerostruct',
'optimize': False, # Don't optimize, only perform analysis
'record_db': True,
}
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface.
# Here we have 3 twist control points and 3 thickness control points.
# We also set the discretization, span, and panel spacing.
surf_dict = {
'name': 'wing',
'symmetry': True,
'num_y': 7,
'num_x': 2,
'num_twist_cp': 3,
'num_thickness_cp': 3,
'num_chord_cp': 2,
'wing_type': 'CRM',
'CD0': 0.015,
'span_cos_spacing': 0.,
def test_aero_viscous_optimization(self):
OAS_prob = OASProblem({
'type': 'aero',
'optimize': True,
'record_db': False,
'with_viscous': True
})
OAS_prob.add_surface()
OAS_prob.add_desvar('wing.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('wing.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('wing.dihedral', lower=-10., upper=20.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'],
0.019234984422361764,
places=5)
raise
# Set problem type
prob_dict = {'type' : 'struct'}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize' : False})
else: # perform optimization
prob_dict.update({'optimize' : True})
num_y = 11
loads = np.zeros(((num_y+1)//2, 6))
loads[:, 1] = 1e5
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
OAS_prob.add_surface({'name' : 'wing',
'num_y' : 11,
'symmetry' : True,
'loads' : loads})
# Single lifting surface
if not sys.argv[1].endswith('m'):
# Setup problem and add design variables, constraint, and objective
OAS_prob.add_desvar('wing.thickness_cp', lower=0.001, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('wing.thickness_intersects', upper=0.)
OAS_prob.add_constraint('wing.failure', upper=0.)
OAS_prob.add_objective('wing.structural_weight', scaler=1e-3)
OAS_prob.setup()
def test_aero_multiple_opt(self):
OAS_prob = OASProblem({
'type': 'aero',
'optimize': True,
'record_db': False
})
surf_dict = {
'name': 'wing',
'span': 5.,
'num_y': 3,
'span_cos_spacing': 0.
}
OAS_prob.add_surface(surf_dict)
surf_dict.update({
'name': 'tail',
'offset': np.array([0., 0., 10.])
})
OAS_prob.add_surface(surf_dict)
OAS_prob.add_desvar('tail.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('tail.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('tail.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('tail.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('tail_perf.CL', equals=0.5)
OAS_prob.add_objective('tail_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
0.41532382375677429,
places=4)
self.assertAlmostEqual(prob['tail_perf.CL'], .5, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'],
.0075400306289957033,
places=5)
self.assertAlmostEqual(prob['tail_perf.CD'],
0.008087914662238814,
places=5)
)
print(
' +---------------------------------------------------------------+\n'
)
raise
# Set problem type
prob_dict = {'type': 'struct'}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize': False})
else: # perform optimization
prob_dict.update({'optimize': True})
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
OAS_prob.add_surface({'name': 'wing', 'num_y': 11, 'symmetry': True})
# Single lifting surface
if not sys.argv[1].endswith('m'):
# Setup problem and add design variables, constraint, and objective
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.001,
upper=0.25,
scaler=1e2)
OAS_prob.add_constraint('wing.thickness_intersects', upper=0.)
OAS_prob.add_constraint('wing.failure', upper=0.)
OAS_prob.add_objective('wing.structural_weight', scaler=1e-3)
OAS_prob.setup()
def test_aero_optimization_chord_monotonic_no_sym(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True,
'record_db' : False,
'symmetry' : False,
'with_viscous' : False})
OAS_prob.add_surface({
'chord_cp' : np.random.random(5),
'num_y' : 11,
'monotonic_con' : ['chord'],
'span_cos_spacing' : 0.,
})
OAS_prob.add_desvar('wing.chord_cp', lower=0.1, upper=5.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.1)
OAS_prob.add_constraint('wing.S_ref', equals=20)
OAS_prob.add_constraint('wing.monotonic_chord', upper=0.)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CD'], 0.00057432581266351113, places=5)
self.assertAlmostEqual(prob['wing.monotonic_chord'][0], -1.710374671671999, places=2)
'type': prob_type,
'compute_static_margin': True,
'optimizer': 'SNOPT',
'with_viscous': True,
'W0': 14., # kg, empty weight from manufacturer
'a': 322.2, # m/s, at 15,000 ft
'rho': 0.770816, # kg/m^3, at 15,000 ft
'R': 2500e3, # estimated range based on cruise speed and flight endurance
'CT': 9.80665 * 8.6e-6, # piston-prop estimation from Raymer
'Re': 4e5,
'M': .093, # calc'd from 30 m/s cruise speed
'cg': np.array([.4, 0., 0.]), # estimated based on aircraft pictures
}
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
zshear_cp = np.zeros(10)
zshear_cp[0] = .3
xshear_cp = np.zeros(10)
xshear_cp[0] = .15
chord_cp = np.ones(10)
chord_cp[0] = .5
radius_cp = 0.02 * np.ones(10)
radius_cp[0] = 0.015
if mesh_level == 'L1':
num_y = 101
)
print(
' +---------------------------------------------------------------+\n'
)
raise
# Set problem type
prob_dict = {'type': 'aero'}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize': False})
else: # perform optimization
prob_dict.update({'optimize': True})
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface
surf_dict = {
'num_y': 7,
'num_x': 2,
'wing_type': 'rect',
'CD0': 0.015,
'symmetry': True,
'num_twist_cp': 2,
'num_thickness_cp': 2
}
# Add the specified wing surface to the problem
OAS_prob.add_surface(surf_dict)
print(' | ERROR: Please supply a correct input argument to this script. |')
print(' | Possible options are ' + print_str[:-2] + ' |')
print(' | See the docstring at the top of this file for more info. |')
print(' +---------------------------------------------------------------+\n')
raise
# Set problem type
prob_dict = {'type' : 'aero'}
if sys.argv[1].startswith('0'): # run analysis once
prob_dict.update({'optimize' : False})
else: # perform optimization
prob_dict.update({'optimize' : True})
# Instantiate problem and add default surface
OAS_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface
surf_dict = {'num_y' : 7,
'num_x' : 2,
'wing_type' : 'rect',
'CD0' : 0.015,
'symmetry' : True,
'num_twist_cp' : 2,
'num_thickness_cp' : 2}
# Add the specified wing surface to the problem
OAS_prob.add_surface(surf_dict)
# Single lifting surface
if not sys.argv[1].endswith('m'):
def test_aerostruct_optimization_symmetry(self):
OAS_prob = OASProblem({
'type': 'aerostruct',
'optimize': True,
'with_viscous': True,
'record_db': False
})
surf_dict = {
'symmetry': True,
'num_y': 7,
'num_x': 3,
'wing_type': 'CRM',
'CD0': 0.015,
'num_twist_cp': 2,
'num_thickness_cp': 2
}
OAS_prob.add_surface(surf_dict)
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.01,
upper=0.5,
scaler=1e2)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_constraint('wing_perf.thickness_intersects', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('L_equals_W', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-4)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'],
96077.224922178371,
places=0)
self.assertAlmostEqual(prob['wing_perf.failure'], 0, places=5)
def test_struct_optimization_symmetry_exact(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : True,
'record_db' : False})
OAS_prob.add_surface({'exact_failure_constraint' : True,
't_over_c': 0.15})
OAS_prob.add_desvar('wing.thickness_cp', lower=0.001, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('wing.failure', upper=0.)
OAS_prob.add_constraint('wing.thickness_intersects', upper=0.)
OAS_prob.add_objective('wing.structural_weight', scaler=1e-3)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing.structural_weight'], 1132.0650209475402, places=2)
def driver(X):
assert len(
X[0]) == (2 * N_CP +
6), "Found dimension %d, expected %d" % (len(X[0]),
(2 * N_CP + 6))
# Set problem type
prob_dict = {
'type': 'aerostruct',
'optimize': False, # Don't optimize, only perform analysis
'record_db': False,
'W0':
1000., # OEW of the aircraft without fuel and the structural weight, in kg
}
# Instantiate problem and add default surface
with silence_stdout():
oas_prob = OASProblem(prob_dict)
# Create a dictionary to store options about the surface.
# Here we have 3 twist control points and 3 thickness control points.
# We also set the discretization, span, and panel spacing.
surf_dict = {
'name': 'wing',
'symmetry': True,
'num_y': 7,
'num_x': 2,
'span': 10.,
'num_twist_cp': N_CP,
'num_thickness_cp': N_CP,
'num_chord_cp': 2,
'wing_type': 'rect',
'span_cos_spacing': 0.,
}
# Add the specified wing surface to the problem
with silence_stdout():
oas_prob.add_surface(surf_dict)
# Set up the problem. Once we have this done, we can modify the internal
# unknowns and run the multidisciplinary analysis at that design point.
oas_prob.add_desvar('wing.twist_cp')
oas_prob.add_desvar('wing.thickness_cp')
oas_prob.add_desvar('wing.chord_cp')
oas_prob.setup(out_stream=null_stream)
Y = np.zeros((X.shape[0], 5))
for i, x in enumerate(tqdm(X)):
twist_cp = x[:N_CP]
thickness_cp = x[N_CP:2 * N_CP]
root_chord = x[2 * N_CP]
taper_ratio = x[2 * N_CP + 1]
alpha = x[2 * N_CP + 2]
E = x[2 * N_CP + 3]
G = x[2 * N_CP + 4]
mrho = x[2 * N_CP + 5]
oas_prob.surfaces[0]['E'] = E
oas_prob.surfaces[0]['G'] = G
oas_prob.surfaces[0]['mrho'] = mrho
with silence_stdout():
oas_prob.setup(out_stream=null_stream)
# set design variables
oas_prob.prob['alpha'] = alpha
oas_prob.prob['wing.twist_cp'] = twist_cp
oas_prob.prob['wing.thickness_cp'] = thickness_cp
oas_prob.prob['wing.chord_cp'] = np.array([taper_ratio, 1.
]) * root_chord
with silence_stdout():
oas_prob.run()
Y[i, 0] = oas_prob.prob['fuelburn']
Y[i, 1] = oas_prob.prob['wing_perf.structural_weight']
Y[i, 2] = oas_prob.prob['wing_perf.L']
Y[i, 3] = oas_prob.prob['total_weight']
Y[i, 4] = oas_prob.prob['wing_perf.failure']
return Y
def OAS_setup(user_prob_dict={}, user_surf_list=[]):
# default prob_dict and surf_dict's from run_aerostruct.py
default_prob_dict = _get_default_prob_dict()
default_prob_dict.update(user_prob_dict)
prob_dict = default_prob_dict
# remove 'des_vars', 'contraints', and 'objectives' entries from prob_dict
# so it doesn't potentially conflict with OASProblem object
des_vars = prob_dict.pop('des_vars', [])
constraints = prob_dict.pop('constraints', [])
objectives = prob_dict.pop('objectives', [])
if user_surf_list:
# replace default_surf_list if user supplied one
surf_list = user_surf_list
else:
surf_list = _get_default_surf_list()
# when wrapping from Matlab, an array of a single value will always be
# converted to a float in Python and not an iterable, which causes problems.
iterable_vars = ['chord_cp','thickness_cp','radius_cp','twist_cp',
'xshear_cp','yshear_cp','zshear_cp']
for surf in surf_list:
for key, val in iteritems(surf):
if (key in iterable_vars) and (not hasattr(val,'__iter__')):
surf[key] = np.array([val]) # make an ndarray from list
# Create OASProblem object
OASprob = OASProblem(prob_dict)
# Add surfaces to OASProblem
for surf in surf_list:
OASprob.add_surface(surf)
# Add design variables to OASProblem
for var_tuple in des_vars:
OASprob.add_desvar(var_tuple[0], **var_tuple[1])
# Add constraints to OASProblem
for var_tuple in constraints:
OASprob.add_constraint(var_tuple[0], **var_tuple[1])
# Add objectives to OASProblem
for var_tuple in objectives:
OASprob.add_objective(var_tuple[0], **var_tuple[1])
# setup OpenMDAO components in OASProblem
OASprob.setup()
return OASprob
