def setup(self):
surface = self.options['surface']
self.add_subsystem(
'aero_funcs',
VLMFunctionals(surface=surface),
promotes_inputs=[
'v', 'alpha', 'Mach_number', 're', 'rho', 'widths',
'cos_sweep', 'lengths', 'S_ref', 'sec_forces', 't_over_c'
],
promotes_outputs=['CDv', 'L', 'D', 'CL1', 'CDi', 'CD', 'CL'])
if surface['fem_model_type'] == 'tube':
self.add_subsystem(
'struct_funcs',
SpatialBeamFunctionals(surface=surface),
promotes_inputs=['thickness', 'radius', 'nodes', 'disp'],
promotes_outputs=[
'thickness_intersects', 'vonmises', 'failure'
])
elif surface['fem_model_type'] == 'wingbox':
self.add_subsystem('struct_funcs',
SpatialBeamFunctionals(surface=surface),
promotes_inputs=[
'Qz', 'Iz', 'J', 'A_enc', 'spar_thickness',
'skin_thickness', 'htop', 'hbottom',
'hfront', 'hrear', 'nodes', 'disp'
],
promotes_outputs=['vonmises', 'failure'])
else:
raise NameError(
'Please select a valid `fem_model_type` from either `tube` or `wingbox`.'
)
def setup(self):
surfaces = self.options['surfaces']
for surface in surfaces:
name = surface['name']
self.connect(name + '.normals', 'aero_states.' + name + '_normals')
# self.connect(name + '.b_pts', 'aero_states.' + name + '_b_pts')
# self.connect(name + '.c_pts', 'aero_states.' + name + '_c_pts')
# self.connect(name + '.cos_sweep', 'aero_states.' + name + '_cos_sweep')
# self.connect(name + '.widths', 'aero_states.' + name + '_widths')
# Connect the results from 'aero_states' to the performance groups
self.connect('aero_states.' + name + '_sec_forces', name + '_perf' + '.sec_forces')
# Connect S_ref for performance calcs
self.connect(name + '.S_ref', name + '_perf.S_ref')
self.connect(name + '.widths', name + '_perf.widths')
self.connect(name + '.chords', name + '_perf.chords')
self.connect(name + '.lengths', name + '_perf.lengths')
self.connect(name + '.cos_sweep', name + '_perf.cos_sweep')
# Connect S_ref for performance calcs
self.connect(name + '.S_ref', 'total_perf.' + name + '_S_ref')
self.connect(name + '.widths', 'total_perf.' + name + '_widths')
self.connect(name + '.chords', 'total_perf.' + name + '_chords')
self.connect(name + '.b_pts', 'total_perf.' + name + '_b_pts')
self.connect(name + '_perf' + '.CL', 'total_perf.' + name + '_CL')
self.connect(name + '_perf' + '.CD', 'total_perf.' + name + '_CD')
self.connect('aero_states.' + name + '_sec_forces', 'total_perf.' + name + '_sec_forces')
self.add_subsystem(name, VLMGeometry(surface=surface))
# Add a single 'aero_states' component that solves for the circulations
# and forces from all the surfaces.
# While other components only depends on a single surface,
# this component requires information from all surfaces because
# each surface interacts with the others.
aero_states = VLMStates(surfaces=surfaces)
aero_states.linear_solver = LinearRunOnce()
self.add_subsystem('aero_states',
aero_states,
promotes_inputs=['v', 'alpha', 'rho'],
promotes_outputs=['circulations'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
# This is necessary because the VLMStates component requires information
# from each surface, but this information is stored within each
# surface's group.
for surface in surfaces:
self.add_subsystem(surface['name'] +'_perf', VLMFunctionals(surface=surface),
promotes_inputs=["v", "alpha", "M", "re", "rho"])
self.add_subsystem('total_perf',
TotalAeroPerformance(surfaces=surfaces),
promotes_inputs=['v', 'rho', 'cg', 'S_ref_total'],
promotes_outputs=['CM', 'CL', 'CD'])
def setup(self):
surfaces = self.options['surfaces']
rotational = self.options['rotational']
# Loop through each surface and connect relevant parameters
for surface in surfaces:
name = surface['name']
self.connect(name + '.normals', 'aero_states.' + name + '_normals')
# Connect the results from 'aero_states' to the performance groups
self.connect('aero_states.' + name + '_sec_forces',
name + '_perf' + '.sec_forces')
# Connect S_ref for performance calcs
self.connect(name + '.S_ref', name + '_perf.S_ref')
self.connect(name + '.widths', name + '_perf.widths')
self.connect(name + '.chords', name + '_perf.chords')
self.connect(name + '.lengths', name + '_perf.lengths')
self.connect(name + '.cos_sweep', name + '_perf.cos_sweep')
# Connect S_ref for performance calcs
self.connect(name + '.S_ref', 'total_perf.' + name + '_S_ref')
self.connect(name + '.widths', 'total_perf.' + name + '_widths')
self.connect(name + '.chords', 'total_perf.' + name + '_chords')
self.connect(name + '.b_pts', 'total_perf.' + name + '_b_pts')
self.connect(name + '_perf' + '.CL', 'total_perf.' + name + '_CL')
self.connect(name + '_perf' + '.CD', 'total_perf.' + name + '_CD')
self.connect('aero_states.' + name + '_sec_forces',
'total_perf.' + name + '_sec_forces')
self.add_subsystem(name, VLMGeometry(surface=surface))
# Add a single 'aero_states' component that solves for the circulations
# and forces from all the surfaces.
# While other components only depends on a single surface,
# this component requires information from all surfaces because
# each surface interacts with the others.
if self.options['compressible'] == True:
aero_states = CompressibleVLMStates(surfaces=surfaces,
rotational=rotational)
prom_in = ['v', 'alpha', 'beta', 'rho', 'Mach_number']
else:
aero_states = VLMStates(surfaces=surfaces, rotational=rotational)
prom_in = ['v', 'alpha', 'beta', 'rho']
aero_states.linear_solver = om.LinearRunOnce()
if rotational:
prom_in.extend(['omega', 'cg'])
self.add_subsystem('aero_states',
aero_states,
promotes_inputs=prom_in,
promotes_outputs=['circulations'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
# This is necessary because the VLMStates component requires information
# from each surface, but this information is stored within each
# surface's group.
for surface in surfaces:
self.add_subsystem(surface['name'] + '_perf',
VLMFunctionals(surface=surface),
promotes_inputs=[
'v', 'alpha', 'beta', 'Mach_number', 're',
'rho'
])
# Add the total aero performance group to compute the CL, CD, and CM
# of the total aircraft. This accounts for all lifting surfaces.
self.add_subsystem(
'total_perf',
TotalAeroPerformance(
surfaces=surfaces,
user_specified_Sref=self.options['user_specified_Sref']),
promotes_inputs=['v', 'rho', 'cg', 'S_ref_total'],
promotes_outputs=['CM', 'CL', 'CD'])
def test(self):
surfaces = get_default_surfaces()
comp = VLMFunctionals(surface=surfaces[0])
run_test(self, comp)
def test(self):
surfaces = get_default_surfaces()
comp = VLMFunctionals(surface=surfaces[0])
run_test(self, comp, complex_flag=True, step=1e-8)