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_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_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_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_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'],
0.45756166834224915,
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_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_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_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)
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'], 96074.934265520889, places=0)
self.assertAlmostEqual(prob['wing_perf.failure'], 0, 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_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_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)
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_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_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_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_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_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_struct_optimization_symmetry(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : True,
'record_db' : False})
OAS_prob.add_surface({'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'], 1144.8503583047038, 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)
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_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_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_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'})
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'], 0.0049392534859265614, 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_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_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_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_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_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 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
# Add additional lifting surface
surf_dict = {'name' : 'tail',
'num_y' : 7,
'num_x' : 2,
'span' : 20.,
'root_chord' : 5.,
'wing_type' : 'rect',
'offset' : np.array([50., 0., 5.]),
'twist_cp' : np.array([-9.5])}
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.)
# Setup problem
OAS_prob.setup()
st = time()
# Actually run the problem
OAS_prob.run()
print("\nFuelburn:", OAS_prob.prob['fuelburn'])
print("Time elapsed: {} secs".format(time() - st))
OAS_prob.add_objective('wing_perf.CD', scaler=1e3)
else:
# Add design variables, constraint, and objective on the problem
# OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('L_equals_W', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=0.1)
# Setup problem and add design variables, constraint, and objective
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.0001,
upper=0.5,
scaler=1e3)
OAS_prob.add_desvar('wing.sweep', lower=-60., upper=60., scaler=1e-1)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_constraint('wing_perf.thickness_intersects', upper=0.)
OAS_prob.add_constraint('CM', equals=0.)
OAS_prob.setup()
st = time()
# Actually run the problem
OAS_prob.run()
print("\nWing CL:", OAS_prob.prob['wing_perf.CL'])
print("Wing CD:", OAS_prob.prob['wing_perf.CD'])
print("Time elapsed: {} secs".format(time() - st))
