def vlm_geometry(def_mesh, comp):
""" Compute various geometric properties for VLM analysis.
Parameters
----------
def_mesh[nx, ny, 3] : numpy array
Array defining the nodal coordinates of the lifting surface.
comp : Either OpenAeroStruct component object (better), or surface dict.
Returns
-------
b_pts[nx-1, ny, 3] : numpy array
Bound points for the horseshoe vortices, found along the 1/4 chord.
c_pts[nx-1, ny-1, 3] : numpy array
Collocation points on the 3/4 chord line where the flow tangency
condition is satisfed. Used to set up the linear system.
widths[nx-1, ny-1] : numpy array
The spanwise widths of each individual panel.
lengths[ny] : numpy array
The chordwise length of the entire airfoil following the camber line.
normals[nx-1, ny-1, 3] : numpy array
The normal vector for each panel, computed as the cross of the two
diagonals from the mesh points.
S_ref : float
The reference area of the lifting surface.
"""
if not isinstance(comp, Component):
surface = comp
comp = VLMGeometry(surface)
params = {
'def_mesh': def_mesh
}
unknowns = {
'b_pts': np.zeros((comp.nx-1, comp.ny, 3), dtype=data_type),
'c_pts': np.zeros((comp.nx-1, comp.ny-1, 3)),
'widths': np.zeros((comp.ny-1)),
'cos_sweep': np.zeros((comp.ny-1)),
'lengths': np.zeros((comp.ny)),
'normals': np.zeros((comp.nx-1, comp.ny-1, 3)),
'S_ref': 0.
}
resids=None
comp.solve_nonlinear(params, unknowns, resids)
b_pts=unknowns.get('b_pts')
c_pts=unknowns.get('c_pts')
widths=unknowns.get('widths')
cos_sweep=unknowns.get('cos_sweep')
lengths=unknowns.get('lengths')
normals=unknowns.get('normals')
S_ref=unknowns.get('S_ref')
return b_pts, c_pts, widths, cos_sweep, lengths, normals, S_ref
def vlm_geometry(def_mesh, comp):
""" Compute various geometric properties for VLM analysis.
Parameters
----------
def_mesh[nx, ny, 3] : numpy array
Array defining the nodal coordinates of the lifting surface.
comp : Either OpenAeroStruct component object (better), or surface dict.
Returns
-------
b_pts[nx-1, ny, 3] : numpy array
Bound points for the horseshoe vortices, found along the 1/4 chord.
c_pts[nx-1, ny-1, 3] : numpy array
Collocation points on the 3/4 chord line where the flow tangency
condition is satisfed. Used to set up the linear system.
widths[nx-1, ny-1] : numpy array
The spanwise widths of each individual panel.
lengths[ny] : numpy array
The chordwise length of the entire airfoil following the camber line.
normals[nx-1, ny-1, 3] : numpy array
The normal vector for each panel, computed as the cross of the two
diagonals from the mesh points.
S_ref : float
The reference area of the lifting surface.
"""
if not isinstance(comp, Component):
surface = comp
comp = VLMGeometry(surface)
params = {'def_mesh': def_mesh}
unknowns = {
'b_pts': np.zeros((comp.nx - 1, comp.ny, 3), dtype=data_type),
'c_pts': np.zeros((comp.nx - 1, comp.ny - 1, 3)),
'widths': np.zeros((comp.ny - 1)),
'cos_sweep': np.zeros((comp.ny - 1)),
'lengths': np.zeros((comp.ny)),
'normals': np.zeros((comp.nx - 1, comp.ny - 1, 3)),
'S_ref': 0.
}
resids = None
comp.solve_nonlinear(params, unknowns, resids)
b_pts = unknowns.get('b_pts')
c_pts = unknowns.get('c_pts')
widths = unknowns.get('widths')
cos_sweep = unknowns.get('cos_sweep')
lengths = unknowns.get('lengths')
normals = unknowns.get('normals')
S_ref = unknowns.get('S_ref')
return b_pts, c_pts, widths, cos_sweep, lengths, normals, S_ref
('rho', prob_dict['rho']),
('r', r),
('M', prob_dict['M']),
('Re', prob_dict['Re']),
]
###############################################################
# Problem 2a:
# These are your components. Here we simply create the objects.
###############################################################
indep_vars_comp = IndepVarComp(indep_vars)
tube_comp = MaterialsTube(surface)
mesh_comp = GeometryMesh(surface)
geom_comp = VLMGeometry(surface)
spatialbeamstates_comp = SpatialBeamStates(surface)
def_mesh_comp = TransferDisplacements(surface)
vlmstates_comp = VLMStates(OAS_prob.surfaces, OAS_prob.prob_dict)
loads_comp = TransferLoads(surface)
vlmfuncs_comp = VLMFunctionals(surface)
spatialbeamfuncs_comp = SpatialBeamFunctionals(surface)
fuelburn_comp = FunctionalBreguetRange(OAS_prob.surfaces,
OAS_prob.prob_dict)
eq_con_comp = FunctionalEquilibrium(OAS_prob.surfaces, OAS_prob.prob_dict)
#################################################################
# Problem 2a:
# Now add the components you created above to the correct groups.
# indep_vars_comp, tube_comp, and vlm_funcs have been
def setup_aerostruct(self):
"""
Specific method to add the necessary components to the problem for an
aerostructural problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aerostruct'
# Create the base root-level group
root = Group()
coupled = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [
('twist_cp', numpy.zeros(surface['num_twist'])),
('thickness_cp', numpy.ones(surface['num_thickness']) *
numpy.max(surface['t'])), ('r', surface['r']),
('dihedral', surface['dihedral']), ('sweep', surface['sweep']),
('span', surface['span']), ('taper', surface['taper'])
]
# Obtain the Jacobians to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
jac_thickness = get_bspline_mtx(surface['num_thickness'],
surface['num_y'] - 1)
# Add components to include in the surface's group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline('twist_cp', 'twist', jac_twist),
promotes=['*'])
tmp_group.add('thickness_bsp',
Bspline('thickness_cp', 'thickness', jac_thickness),
promotes=['*'])
tmp_group.add('tube', MaterialsTube(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface.
name_orig = name
name = name[:-1]
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=[])')
# Add components to the 'coupled' group for each surface.
# The 'coupled' group must contain all components and parameters
# needed to converge the aerostructural system.
tmp_group = Group()
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('aero_geom', VLMGeometry(surface), promotes=['*'])
tmp_group.add('struct_states',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.struct_states.ln_solver = LinearGaussSeidel()
name = name_orig
exec(name + ' = tmp_group')
exec('coupled.add("' + name[:-1] + '", ' + name + ', promotes=[])')
# Add a loads component to the coupled group
exec('coupled.add("' + name_orig + 'loads' + '", ' +
'TransferLoads(surface)' + ', promotes=[])')
# Add a performance group which evaluates the data after solving
# the coupled system
tmp_group = Group()
tmp_group.add('struct_funcs',
SpatialBeamFunctionals(surface),
promotes=['*'])
tmp_group.add('aero_funcs',
VLMFunctionals(surface),
promotes=['*'])
name = name_orig + 'perf'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name +
', promotes=["rho", "v", "alpha", "Re", "M"])')
# Add a single 'aero_states' component for the whole system within the
# coupled group.
coupled.add('aero_states',
VLMStates(self.surfaces, self.prob_dict),
promotes=['v', 'alpha', 'rho'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
for surface in self.surfaces:
name = surface['name']
# Perform the connections with the modified names within the
# 'aero_states' group.
root.connect('coupled.' + name[:-1] + '.def_mesh',
'coupled.aero_states.' + name + 'def_mesh')
root.connect('coupled.' + name[:-1] + '.b_pts',
'coupled.aero_states.' + name + 'b_pts')
root.connect('coupled.' + name[:-1] + '.c_pts',
'coupled.aero_states.' + name + 'c_pts')
root.connect('coupled.' + name[:-1] + '.normals',
'coupled.aero_states.' + name + 'normals')
# Connect the results from 'aero_states' to the performance groups
root.connect('coupled.aero_states.' + name + 'sec_forces',
name + 'perf' + '.sec_forces')
# Connect the results from 'coupled' to the performance groups
root.connect('coupled.' + name[:-1] + '.def_mesh',
'coupled.' + name + 'loads.def_mesh')
root.connect('coupled.aero_states.' + name + 'sec_forces',
'coupled.' + name + 'loads.sec_forces')
root.connect('coupled.' + name + 'loads.loads',
name + 'perf.loads')
# Connect the output of the loads component with the FEM
# displacement parameter. This links the coupling within the coupled
# group that necessitates the subgroup solver.
root.connect('coupled.' + name + 'loads.loads',
'coupled.' + name[:-1] + '.loads')
# Connect aerodyamic design variables
root.connect(name[:-1] + '.dihedral',
'coupled.' + name[:-1] + '.dihedral')
root.connect(name[:-1] + '.span', 'coupled.' + name[:-1] + '.span')
root.connect(name[:-1] + '.sweep',
'coupled.' + name[:-1] + '.sweep')
root.connect(name[:-1] + '.taper',
'coupled.' + name[:-1] + '.taper')
root.connect(name[:-1] + '.twist',
'coupled.' + name[:-1] + '.twist')
# Connect structural design variables
root.connect(name[:-1] + '.A', 'coupled.' + name[:-1] + '.A')
root.connect(name[:-1] + '.Iy', 'coupled.' + name[:-1] + '.Iy')
root.connect(name[:-1] + '.Iz', 'coupled.' + name[:-1] + '.Iz')
root.connect(name[:-1] + '.J', 'coupled.' + name[:-1] + '.J')
# Connect performance calculation variables
root.connect(name[:-1] + '.r', name + 'perf.r')
root.connect(name[:-1] + '.A', name + 'perf.A')
# Connection performance functional variables
root.connect(name + 'perf.weight', 'fuelburn.' + name + 'weight')
root.connect(name + 'perf.weight', 'eq_con.' + name + 'weight')
root.connect(name + 'perf.L', 'eq_con.' + name + 'L')
root.connect(name + 'perf.CL', 'fuelburn.' + name + 'CL')
root.connect(name + 'perf.CD', 'fuelburn.' + name + 'CD')
# Connect paramters from the 'coupled' group to the performance
# group.
root.connect('coupled.' + name[:-1] + '.nodes',
name + 'perf.nodes')
root.connect('coupled.' + name[:-1] + '.disp', name + 'perf.disp')
root.connect('coupled.' + name[:-1] + '.S_ref',
name + 'perf.S_ref')
# Set solver properties for the coupled group
coupled.ln_solver = ScipyGMRES()
coupled.ln_solver.options['iprint'] = 1
coupled.ln_solver.preconditioner = LinearGaussSeidel()
coupled.aero_states.ln_solver = LinearGaussSeidel()
coupled.nl_solver = NLGaussSeidel()
coupled.nl_solver.options['iprint'] = 1
# Ensure that the groups are ordered correctly within the coupled group
# so that a system with multiple surfaces is solved corretly.
order_list = []
for surface in self.surfaces:
order_list.append(surface['name'][:-1])
order_list.append('aero_states')
for surface in self.surfaces:
order_list.append(surface['name'] + 'loads')
coupled.set_order(order_list)
# Add the coupled group to the root problem
root.add('coupled', coupled, promotes=['v', 'alpha', 'rho'])
# Add problem information as an independent variables component
prob_vars = [('v', self.prob_dict['v']),
('alpha', self.prob_dict['alpha']),
('M', self.prob_dict['M']), ('Re', self.prob_dict['Re']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add functionals to evaluate performance of the system.
# Note that only the interesting results are promoted here; not all
# of the parameters.
root.add('fuelburn',
FunctionalBreguetRange(self.surfaces, self.prob_dict),
promotes=['fuelburn'])
root.add('eq_con',
FunctionalEquilibrium(self.surfaces, self.prob_dict),
promotes=['eq_con', 'fuelburn'])
# Actually set up the system
self.setup_prob()
def setup_aero(self):
"""
Specific method to add the necessary components to the problem for an
aerodynamic problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aero'
# Create the base root-level group
root = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [('twist_cp', numpy.zeros(surface['num_twist'])),
('dihedral', surface['dihedral']),
('sweep', surface['sweep']),
('span', surface['span']),
('taper', surface['taper']),
('disp', numpy.zeros((surface['num_y'], 6)))]
# Obtain the Jacobian to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
# Add aero components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline('twist_cp', 'twist', jac_twist),
promotes=['*'])
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
# Add tmp_group to the problem as the name of the surface.
# Note that is a group and performance group for each
# individual surface.
name_orig = name.strip('_')
name = name_orig
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=[])')
# Add a performance group for each surface
name = name_orig + '_perf'
exec('root.add("' + name + '", ' + 'VLMFunctionals(surface)' +
', promotes=["v", "alpha", "M", "Re", "rho"])')
# Add problem information as an independent variables component
prob_vars = [('v', self.prob_dict['v']),
('alpha', self.prob_dict['alpha']),
('M', self.prob_dict['M']), ('Re', self.prob_dict['Re']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# 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.
root.add('aero_states',
VLMStates(self.surfaces, self.prob_dict),
promotes=['circulations', 'v', 'alpha', 'rho'])
# 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 self.surfaces:
name = surface['name']
# Perform the connections with the modified names within the
# 'aero_states' group.
root.connect(name[:-1] + '.def_mesh',
'aero_states.' + name + 'def_mesh')
root.connect(name[:-1] + '.b_pts', 'aero_states.' + name + 'b_pts')
root.connect(name[:-1] + '.c_pts', 'aero_states.' + name + 'c_pts')
root.connect(name[:-1] + '.normals',
'aero_states.' + name + 'normals')
# Connect the results from 'aero_states' to the performance groups
root.connect('aero_states.' + name + 'sec_forces',
name + 'perf' + '.sec_forces')
# Connect S_ref for performance calcs
root.connect(name[:-1] + '.S_ref', name + 'perf' + '.S_ref')
# Actually set up the problem
self.setup_prob()
def setup_aerostruct(self):
"""
Specific method to add the necessary components to the problem for an
aerostructural problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aerostruct'
# Create the base root-level group
root = Group()
coupled = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [
(name + 'twist_cp', numpy.zeros(surface['num_twist'])),
(name + 'thickness_cp', numpy.ones(surface['num_thickness']) *
numpy.max(surface['t'])), (name + 'r', surface['r']),
(name + 'dihedral', surface['dihedral']),
(name + 'sweep', surface['sweep']),
(name + 'span', surface['span']),
(name + 'taper', surface['taper'])
]
# Obtain the Jacobians to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
jac_thickness = get_bspline_mtx(surface['num_thickness'],
surface['num_y'] - 1)
# Add components to include in the '_pre_solve' group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline(name + 'twist_cp', name + 'twist',
jac_twist),
promotes=['*'])
tmp_group.add('thickness_bsp',
Bspline(name + 'thickness_cp', name + 'thickness',
jac_thickness),
promotes=['*'])
tmp_group.add('tube', MaterialsTube(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface and
# '_pre_solve' appended.
name_orig = name #.strip('_')
name = name + 'pre_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add components to the 'coupled' group for each surface
tmp_group = Group()
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
tmp_group.add('spatialbeamstates',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.spatialbeamstates.ln_solver = LinearGaussSeidel()
name = name_orig + 'group'
exec(name + ' = tmp_group')
exec('coupled.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a loads component to the coupled group
exec('coupled.add("' + name_orig + 'loads' + '", ' +
'TransferLoads(surface)' + ', promotes=["*"])')
# Add a '_post_solve' group which evaluates the data after solving
# the coupled system
tmp_group = Group()
tmp_group.add('spatialbeamfuncs',
SpatialBeamFunctionals(surface),
promotes=['*'])
tmp_group.add('vlmfuncs', VLMFunctionals(surface), promotes=['*'])
name = name_orig + 'post_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a single 'VLMStates' component for the whole system
coupled.add('vlmstates',
VLMStates(self.surfaces, self.prob_dict),
promotes=['*'])
# Set solver properties for the coupled group
coupled.ln_solver = ScipyGMRES()
coupled.ln_solver.options['iprint'] = 1
coupled.ln_solver.preconditioner = LinearGaussSeidel()
coupled.vlmstates.ln_solver = LinearGaussSeidel()
coupled.nl_solver = NLGaussSeidel()
coupled.nl_solver.options['iprint'] = 1
# Ensure that the groups are ordered correctly within the coupled group
order_list = []
for surface in self.surfaces:
order_list.append(surface['name'] + 'group')
order_list.append('vlmstates')
for surface in self.surfaces:
order_list.append(surface['name'] + 'loads')
coupled.set_order(order_list)
# Add the coupled group to the root problem
root.add('coupled', coupled, promotes=['*'])
# Add problem information as an independent variables component
prob_vars = [('v', self.prob_dict['v']),
('alpha', self.prob_dict['alpha']),
('M', self.prob_dict['M']), ('Re', self.prob_dict['Re']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add functionals to evaluate performance of the system
root.add('fuelburn',
FunctionalBreguetRange(self.surfaces, self.prob_dict),
promotes=['*'])
root.add('eq_con',
FunctionalEquilibrium(self.surfaces, self.prob_dict),
promotes=['*'])
self.setup_prob()
def setup_aero(self):
"""
Specific method to add the necessary components to the problem for an
aerodynamic problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aero'
# Create the base root-level group
root = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [(name + 'twist_cp',
numpy.zeros(surface['num_twist'])),
(name + 'dihedral', surface['dihedral']),
(name + 'sweep', surface['sweep']),
(name + 'span', surface['span']),
(name + 'taper', surface['taper']),
(name + 'disp', numpy.zeros((surface['num_y'], 6)))]
# Obtain the Jacobian to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
# Add aero components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline(name + 'twist_cp', name + 'twist',
jac_twist),
promotes=['*'])
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface and
# '_pre_solve' appended.
# Note that is a '_pre_solve' and '_post_solve' group for each
# individual surface.
name_orig = name.strip('_')
name = name_orig + '_pre_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a '_post_solve' group
name = name_orig + '_post_solve'
exec('root.add("' + name + '", ' + 'VLMFunctionals(surface)' +
', promotes=["*"])')
# Add problem information as an independent variables component
prob_vars = [('v', self.prob_dict['v']),
('alpha', self.prob_dict['alpha']),
('M', self.prob_dict['M']), ('Re', self.prob_dict['Re']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add a single 'VLMStates' 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.
root.add('vlmstates',
VLMStates(self.surfaces, self.prob_dict),
promotes=['*'])
self.setup_prob()
def setup(prob_dict={}, surfaces=[{}]):
''' Setup the aerostruct mesh
Default wing mesh (single lifting surface):
-------------------------------------------
name = 'wing' # name of the surface
num_x = 3 # number of chordwise points
num_y = 5 # number of spanwise points
root_chord = 1. # root chord
span_cos_spacing = 1 # 0 for uniform spanwise panels
# 1 for cosine-spaced panels
# any value between 0 and 1 for a mixed spacing
chord_cos_spacing = 0. # 0 for uniform chordwise panels
# 1 for cosine-spaced panels
# any value between 0 and 1 for a mixed spacing
wing_type = 'rect' # initial shape of the wing either 'CRM' or 'rect'
# 'CRM' can have different options after it, such as 'CRM:alpha_2.75' for the CRM shape at alpha=2.75
offset = np.array([0., 0., 0.]) # coordinates to offset the surface from its default location
symmetry = True # if true, model one half of wing reflected across the plane y = 0
S_ref_type = 'wetted' # 'wetted' or 'projected'
# Simple Geometric Variables
span = 10. # full wingspan
dihedral = 0. # wing dihedral angle in degrees positive is upward
sweep = 0. # wing sweep angle in degrees positive sweeps back
taper = 1. # taper ratio; 1. is uniform chord
# B-spline Geometric Variables. The number of control points for each of these variables can be specified in surf_dict
# by adding the prefix "num" to the variable (e.g. num_twist)
twist_cp = None
chord_cp = None
xshear_cp = None
zshear_cp = None
thickness_cp = None
Default wing parameters:
------------------------
Zero-lift aerodynamic performance
CL0 = 0.0 # CL value at AoA (alpha) = 0
CD0 = 0.0 # CD value at AoA (alpha) = 0
Airfoil properties for viscous drag calculation
k_lam = 0.05 # percentage of chord with laminar flow, used for viscous drag
t_over_c = 0.12 # thickness over chord ratio (NACA0012)
c_max_t = .303 # chordwise location of maximum (NACA0012) thickness
Structural values are based on aluminum
E = 70.e9 # [Pa] Young's modulus of the spar
G = 30.e9 # [Pa] shear modulus of the spar
stress = 20.e6 # [Pa] yield stress
mrho = 3.e3 # [kg/m^3] material density
fem_origin = 0.35 # chordwise location of the spar
Other
W0 = 0.4 * 3e5 # [kg] MTOW of B777 is 3e5 kg with fuel
Default problem parameters:
---------------------------
Re = 1e6 # Reynolds number
reynolds_length = 1.0 # characteristic Reynolds length
alpha = 5. # angle of attack
CT = 9.80665 * 17.e-6 # [1/s] (9.81 N/kg * 17e-6 kg/N/s)
R = 14.3e6 # [m] maximum range
M = 0.84 # Mach number at cruise
rho = 0.38 # [kg/m^3] air density at 35,000 ft
a = 295.4 # [m/s] speed of sound at 35,000 ft
with_viscous = False # if true, compute viscous drag
'''
# Use steps in run_aerostruct.py to add wing surface to problem
# Set problem type
prob_dict.update({
'type': 'aerostruct'
}) # this doesn't really matter since we aren't calling OASProblem.setup()
# Instantiate problem
OAS_prob = OASProblem(prob_dict)
for surface in surfaces:
# Add SpatialBeamFEM size
FEMsize = 6 * surface['num_y'] + 6
surface.update({'FEMsize': FEMsize})
# Add the specified wing surface to the problem.
OAS_prob.add_surface(surface)
# Add materials properties for the wing surface to the surface dict in OAS_prob
for idx, surface in enumerate(OAS_prob.surfaces):
A, Iy, Iz, J = materials_tube(surface['radius'], surface['thickness'],
surface)
OAS_prob.surfaces[idx].update({'A': A, 'Iy': Iy, 'Iz': Iz, 'J': J})
# Get total panels and save in prob_dict
tot_panels = 0
for surface in OAS_prob.surfaces:
ny = surface['num_y']
nx = surface['num_x']
tot_panels += (nx - 1) * (ny - 1)
OAS_prob.prob_dict.update({'tot_panels': tot_panels})
# Assume we are only using a single lifting surface for now
surface = OAS_prob.surfaces[0]
# Initialize the OpenAeroStruct components and save them in a component dictionary
comp_dict = {}
comp_dict['MaterialsTube'] = MaterialsTube(surface)
comp_dict['GeometryMesh'] = GeometryMesh(surface)
comp_dict['TransferDisplacements'] = TransferDisplacements(surface)
comp_dict['VLMGeometry'] = VLMGeometry(surface)
comp_dict['AssembleAIC'] = AssembleAIC([surface])
comp_dict['AeroCirculations'] = AeroCirculations(
OAS_prob.prob_dict['tot_panels'])
comp_dict['VLMForces'] = VLMForces([surface])
comp_dict['TransferLoads'] = TransferLoads(surface)
comp_dict['ComputeNodes'] = ComputeNodes(surface)
comp_dict['AssembleK'] = AssembleK(surface)
comp_dict['SpatialBeamFEM'] = SpatialBeamFEM(surface['FEMsize'])
comp_dict['SpatialBeamDisp'] = SpatialBeamDisp(surface)
OAS_prob.comp_dict = comp_dict
return OAS_prob
tot_panels = 0
for surface in OAS_prob.surfaces:
ny = surface['num_y']
nx = surface['num_x']
tot_panels += (nx - 1) * (ny - 1)
OAS_prob.prob_dict.update({'tot_panels': tot_panels})
# Assume we are only using a single lifting surface for now
surface = OAS_prob.surfaces[0]
# Initialize the OpenAeroStruct components and save them in a component dictionary
comp_dict = {}
comp_dict['MaterialsTube'] = MaterialsTube(surface)
comp_dict['GeometryMesh'] = GeometryMesh(surface)
comp_dict['TransferDisplacements'] = TransferDisplacements(surface)
comp_dict['VLMGeometry'] = VLMGeometry(surface)
comp_dict['AssembleAIC'] = AssembleAIC([surface])
comp_dict['AeroCirculations'] = AeroCirculations(OAS_prob.prob_dict['tot_panels'])
comp_dict['VLMForces'] = VLMForces([surface])
comp_dict['TransferLoads'] = TransferLoads(surface)
comp_dict['ComputeNodes'] = ComputeNodes(surface)
comp_dict['AssembleK'] = AssembleK(surface)
comp_dict['SpatialBeamFEM'] = SpatialBeamFEM(surface['FEMsize'])
comp_dict['SpatialBeamDisp'] = SpatialBeamDisp(surface)
OAS_prob.comp_dict = comp_dict
<<<<<<< HEAD
# return the surfaces list, problem dict, and component dict
surfaces = [surface]
prob_dict = OAS_prob.prob_dict
# return surfaces, prob_dict, comp_dict