def __init__(self, tag, geom_type='Broken', n_sect=20):
"""
Constructor: set main attributes
"""
self.__tag = tag
self.__geom_type = None
self.__n_sect = None
self.__PCADModel = None
self.__BC_manager = None
self.__distrib_type = 'cos_law'
self.set_geom_type(geom_type)
self.set_n_sect(n_sect)
self.__BC_manager = BCManager()
self.__ndv = 0
self.__thetaY = None
self.__AoA_id = 'AoA'
self.__init_discrete_attributes()
self.__init_airfoils_attributes()
def __init__(self, tag, geom_type='Broken', n_sect=20):
"""
Constructor: set main attributes
"""
self.__tag = tag
self.__geom_type = None
self.__n_sect = None
self.__PCADModel = None
self.__BC_manager = None
self.__distrib_type = 'cos_law'
self.set_geom_type(geom_type)
self.set_n_sect(n_sect)
self.__BC_manager = BCManager()
self.__ndv = 0
self.__thetaY = None
self.__AoA_id = 'AoA'
self.__init_discrete_attributes()
self.__init_airfoils_attributes()
def __init__(self, tag, n_sect=20, grad_active=True):
"""
Constructor: set main attributes
"""
DLLM_Geom.__init__(self, tag, n_sect=n_sect, grad_active=grad_active)
self.BC_manager = BCManager()
self.__AoA_id = 'AoA'
self.__common_OC = None
class Wing_param():
ERROR_MSG = 'ERROR in Wing_param.'
POSSIBLE_GEOM_TYPES = ["Rectangular", "Elliptic", "Broken"]
POS_DISTRIB = ['linear', 'cos_law']
def __init__(self, tag, geom_type='Broken', n_sect=20):
"""
Constructor: set main attributes
"""
self.__tag = tag
self.__geom_type = None
self.__n_sect = None
self.__PCADModel = None
self.__BC_manager = None
self.__distrib_type = 'cos_law'
self.set_geom_type(geom_type)
self.set_n_sect(n_sect)
self.__BC_manager = BCManager()
self.__ndv = 0
self.__thetaY = None
self.__AoA_id = 'AoA'
self.__init_discrete_attributes()
self.__init_airfoils_attributes()
def __init_discrete_attributes(self):
# -- OC design variable
self.__AoA = None
self.__AoA_grad = None
# -- discrete attributes
self.__span = None
self.__span_grad = None
self.__r_list_y = None
self.__r_list_eta = None
self.__sweep = None
self.__sweep_grad = None
self.__break_percent = None
self.__break_percent_grad = None
self.__root_chord = None
self.__root_chord_grad = None
self.__break_chord = None
self.__break_chord_grad = None
self.__tip_chord = None
self.__tip_chord_grad = None
self.__root_height = None
self.__root_height_grad = None
self.__break_height = None
self.__break_height_grad = None
self.__tip_height = None
self.__tip_height_grad = None
self.__twist = None
self.__twist_grad = None
self.__chords = None
self.__chords_grad = None
self.__heights = None
self.__heights_grad = None
self.__rel_thicks = None
self.__rel_thicks_grad = None
self.__XYZ = None
self.__XYZ_grad = None
self.__eta = None
self.__eta_grad = None
self.__Lref = None
self.__Lref_grad = None
self.__Sref = None
self.__Sref_grad = None
self.__root_ToC = None
self.__root_ToC_grad = None
self.__break_ToC = None
self.__break_ToC_grad = None
self.__tip_ToC = None
self.__tip_ToC_grad = None
self.__AR = None
self.__AR_grad = None
self.__fuel = None
self.__fuel_grad = None
def __init_airfoils_attributes(self):
self.__airfoil_type = None
self.__ref_airfoil = None # reference airfoil, only used if the same airfoil is put for all sections
self.__airfoils = None # Airfoil list for each section
self.__linked_airfoils = None # Airfoil scaled to the the planform
# -- Accessors
def get_n_sect(self):
return self.__n_sect
def get_ndv(self):
return self.__ndv
def get_eta(self):
return self.__eta
def get_eta_grad(self):
return self.__eta_grad
def get_XYZ(self):
return self.__XYZ
def get_XYZ_grad(self):
return self.__XYZ_grad
def get_twist(self):
return self.__twist
def get_twist_grad(self):
return self.__twist_grad
def get_chords(self):
return self.__chords
def get_chords_grad(self):
return self.__chords_grad
def get_rel_thicks(self):
return self.__rel_thicks
def get_rel_thicks_grad(self):
return self.__rel_thicks_grad
def get_thetaY(self):
return self.__thetaY
def get_AoA(self):
return self.__AoA
def get_AoA_grad(self):
return self.__AoA_grad
def get_span(self):
return self.__span
def get_span_grad(self):
return self.__span_grad
def get_sweep(self):
return self.__sweep
def get_sweep_grad(self):
return self.__sweep_grad
def get_Lref(self):
return self.__Lref
def get_Lref_grad(self):
return self.__Lref_grad
def get_Sref(self):
return self.__Sref
def get_Sref_grad(self):
return self.__Sref_grad
def get_root_ToC(self):
return self.__root_ToC
def get_root_ToC_grad(self):
return self.__root_ToC_grad
def get_break_ToC(self):
return self.__break_ToC
def get_break_ToC_grad(self):
return self.__break_ToC_grad
def get_tip_ToC(self):
return self.__tip_ToC
def get_tip_ToC_grad(self):
return self.__tip_ToC_grad
def get_AR(self):
return self.__AR
def get_AR_grad(self):
return self.__AR_grad
def get_fuel(self):
return self.__fuel
def get_fuel_grad(self):
return self.__fuel_grad
# -- Setters
def set_AoA_id(self, AoA_id):
self.__AoA_id = AoA_id
def set_geom_type(self, geom_type):
"""
@param wing_geometry_type : Rectangular or Elliptic planforms
@param type wing_geometry_type : String
"""
if not geom_type in self.POSSIBLE_GEOM_TYPES:
raise Exception, "geom_type :" + str(
geom_type) + " not in possible types : " + str(
self.POSSIBLE_GEOM_TYPES)
self.__geom_type = geom_type
def set_n_sect(self, n_sect):
ERROR_MSG = self.ERROR_MSG + '.set_n_sect: ' + str(self.__tag) + ': '
if n_sect % 2 != 0:
raise Exception, ERROR_MSG + 'The total number of elements in the wing must be even.'
self.__n_sect = n_sect
def set_distrib_type(self, distrib_type):
if not distrib_type in self.POS_DISTRIB:
raise Exception, "distrib_type :" + str(
distrib_type) + " not in possible types : " + str(
self.POS_DISTRIB)
self.__distrib_type = distrib_type
def set_value(self, Id, val):
pt = self.__BC_manager.get_pt(Id)
pt.set_value(val)
def set_thetaY(self, thetaY):
self.__thetaY = thetaY
# -- controller management
def convert_to_variable(self, Id):
self.__BC_manager.convert_to_variable(Id)
def convert_to_design_variable(self, Id, bounds):
self.__BC_manager.convert_to_design_variable(Id, bounds)
def convert_to_parameter(self, Id, fexpr):
self.__BC_manager.convert_to_parameter(Id, fexpr)
def add_AoA_design_variable(self, val, bounds):
self.__BC_manager.create_design_variable(self.__AoA_id, val, bounds)
def __update_AoA(self):
Id = self.__AoA_id
if Id in self.get_dv_id_list():
pt = self.__BC_manager.get_pt(Id)
deg_to_rad = pi / 180.
self.__AoA = pt.get_value() * deg_to_rad
self.__AoA_grad = pt.get_gradient() * deg_to_rad
def get_dv_array(self):
return self.__BC_manager.get_dv_array()
def get_dv_id_list(self):
return self.__BC_manager.get_dv_id_list()
def get_bounds_array(self):
return self.__BC_manager.get_bounds_array()
def build_wing(self):
self.__BC_manager.clean()
self.__BC_manager.create_variable('span', 0.)
if self.__geom_type not in ['Elliptic']:
self.__BC_manager.create_variable('sweep', 0.)
if self.__geom_type in ['Rectangular', 'Elliptic']:
self.__BC_manager.create_variable('root_chord', 0.)
self.__BC_manager.create_variable('root_height', 0.)
self.__BC_manager.create_variable('tip_height', 0.)
elif self.__geom_type == 'Broken':
self.__BC_manager.create_variable('break_percent', 0.33)
self.__BC_manager.create_variable('root_chord', 0.)
self.__BC_manager.create_variable('break_chord', 0.)
self.__BC_manager.create_variable('tip_chord', 0.)
self.__BC_manager.create_variable('root_height', 0.)
self.__BC_manager.create_variable('break_height', 0.)
self.__BC_manager.create_variable('tip_height', 0.)
for i in xrange(self.__n_sect / 2):
self.__BC_manager.create_design_variable('rtwist' + str(i), 0.,
(-10., 10.))
for i in xrange(self.__n_sect / 2):
# print self.__tag+'.twist'+str(i),self.__tag+'.twist'+str(self.__n_sect/2+i),self.__tag+'.rtwist'+str(self.__n_sect/2-1-i),self.__tag+'.rtwist'+str(i)
self.__BC_manager.create_parameter(
'twist' + str(i), 'rtwist' + str(self.__n_sect / 2 - 1 - i))
self.__BC_manager.create_parameter(
'twist' + str(self.__n_sect / 2 + i), 'rtwist' + str(i))
# for i in xrange(self.__n_sect):
# self.__BC_manager.create_design_variable(self.__tag+'.twist'+str(i),-25.,0.,25.)
def config_from_dict(self, OC, config_dict):
self.build_wing()
self.__config_airfoils(OC, config_dict)
self.__config_desc(config_dict)
self.update()
def __config_airfoils(self, OC, config_dict):
in_keys_list = config_dict.keys()
airfoil_type_key = self.__tag + '.airfoil.type'
if airfoil_type_key in in_keys_list:
airfoil_type = config_dict[airfoil_type_key]
else:
airfoil_type = 'simple'
if airfoil_type == 'simple':
AoA0_key = self.__tag + '.airfoil.AoA0'
if AoA0_key in in_keys_list:
AoA0 = config_dict[AoA0_key]
else:
AoA0 = 0.
Cm0_key = self.__tag + '.airfoil.Cm0'
if Cm0_key in in_keys_list:
Cm0 = config_dict[Cm0_key]
else:
Cm0 = 0.
self.build_linear_airfoil(OC, AoA0=AoA0, Cm0=Cm0, set_as_ref=True)
elif airfoil_type == 'meta':
surrogate_model_key = self.__tag + '.airfoil.surrogate_model'
if surrogate_model_key in in_keys_list:
surrogate_model = config_dict[surrogate_model_key]
else:
surrogate_model = None
self.build_meta_airfoil(OC, surrogate_model, set_as_ref=True)
self.build_airfoils_from_ref()
def __config_desc(self, config_dict):
in_keys_list = sorted(config_dict.keys())
existing_keys = deepcopy(self.__BC_manager.get_list_id())
# Add user defined DesignVariable, Variable and Parameter
added_list = []
for in_key in in_keys_list:
words = in_key.split('.')
if len(words) >= 4:
test = string.join(words[:-2], '.')
if test == self.__tag + '.desc':
name = words[-2]
Id = name
Id_in = self.__tag + '.desc.' + name
type = config_dict[Id_in + '.type']
if Id not in existing_keys and Id not in added_list:
if type == 'DesignVariable':
bounds = config_dict[Id_in + '.bounds']
value = config_dict[Id_in + '.value']
self.__BC_manager.create_design_variable(
Id, value, (bounds[0], bounds[1]))
elif type == 'Variable':
value = config_dict[Id_in + '.value']
self.__BC_manager.create_variable(Id, value)
elif type == 'Parameter':
fexpr = config_dict[Id_in + '.fexpr']
self.__BC_manager.create_parameter(Id, fexpr)
added_list.append(Id)
# Convert pre-defined parameters
for existing_id in existing_keys:
ex_words = existing_id.split('.')
name = ex_words[-1]
Id_in = self.__tag + '.desc.' + name
Id = name
if Id_in + '.type' in in_keys_list:
type = config_dict[Id_in + '.type']
if type == 'DesignVariable':
bounds = config_dict[Id_in + '.bounds']
value = config_dict[Id_in + '.value']
self.set_value(Id, value)
self.convert_to_design_variable(Id, bounds)
elif type == 'Variable':
value = config_dict[Id_in + '.value']
self.set_value(Id, value)
self.convert_to_variable(Id)
elif type == 'Parameter':
fexpr = config_dict[Id_in + '.fexpr']
self.convert_to_parameter(Id, fexpr)
def update(self):
self.__BC_manager.update()
self.__ndv = self.__BC_manager.get_ndv()
self.__update_AoA()
self.__check_thetaY()
self.__build_discretization()
self.__check_airfoils_inputs()
self.__link_airfoils_to_geom()
self.__compute_Sref_Lref_ToC_AR_fuel()
def update_from_x_list(self, x):
#print 'update wing_param with x=',x
self.__BC_manager.update_dv_from_x_list(x)
self.update()
def __repr__(self):
info_string = '\n*** Wing param information ***'
info_string += '\n geom_type : ' + str(self.__geom_type)
info_string += '\n n_sect : ' + str(self.__n_sect)
info_string += '\n ndv : ' + str(self.__ndv)
info_string += '\n airfoil_type : ' + str(self.__airfoil_type)
info_string += '\n -- parameters information section --\n'
for Id in self.__BC_manager.get_list_id():
pt = self.__BC_manager.get_pt(Id)
BC_Type = pt.get_BCType()
if BC_Type == 'Variable':
value = pt.get_value()
info_string += "%30s" % Id + "%20s" % BC_Type + " %24.16e" % value + "\n"
if BC_Type == 'DesignVariable':
value = pt.get_value()
bounds = pt.get_bounds()
info_string += "%30s" % Id + "%20s" % BC_Type + " %24.16e" % value + " %24s" % str(
bounds) + "\n"
if BC_Type == 'Parameter':
expr = pt.get_expr()
info_string += "%30s" % Id + "%20s" % BC_Type + " %24s" % expr + "\n"
info_string += ' -- end of parameters information section --\n'
return info_string
# -- Structural displacement methods
def __check_thetaY(self):
# 6 dimensions for structural displacement: dx,dy,dz,dthetax,dthetay,dthetaz at each section
if self.__thetaY is None:
self.__thetaY = zeros(self.__n_sect)
# -- discretization methods
def __build_discretization(self):
self.__build_planform()
self.__build_r_lists()
self.__build_chords()
self.__build_heights_rel_thicks()
self.__build_XYZ_eta()
def __build_planform(self):
deg_to_rad = pi / 180.
# -- span
Id = 'span'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__span = val
self.__span_grad = grad
if self.__geom_type not in ['Elliptic']:
# -- sweep
Id = 'sweep'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__sweep = val * deg_to_rad
self.__sweep_grad = grad * deg_to_rad
else:
self.__sweep = 0.
self.__sweep_grad = zeros(self.get_ndv())
if self.__geom_type in ['Rectangular', 'Elliptic']:
Id = 'root_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_chord = val
self.__root_chord_grad = grad
Id = 'root_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_height = val
self.__root_height_grad = grad
Id = 'tip_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_height = val
self.__tip_height_grad = grad
elif self.__geom_type == 'Broken':
Id = 'break_percent'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_percent = val
self.__break_percent_grad = grad
Id = 'root_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_chord = val
self.__root_chord_grad = grad
Id = 'break_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_chord = val
self.__break_chord_grad = grad
Id = 'tip_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_chord = val
self.__tip_chord_grad = grad
Id = 'root_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_height = val
self.__root_height_grad = grad
Id = 'break_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_height = val
self.__break_height_grad = grad
Id = 'tip_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_height = val
self.__tip_height_grad = grad
self.__twist = zeros((self.__n_sect))
self.__twist_grad = zeros((self.__n_sect, self.__ndv))
for i in xrange(self.__n_sect):
Id = 'twist' + str(i)
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__twist[i] = val * deg_to_rad
self.__twist_grad[i, :] = grad * deg_to_rad
def __build_r_lists(self):
N = self.__n_sect
if self.__distrib_type == 'linear':
self.__r_list_eta = numpy.linspace(-0.5, 0.5, N + 1)
else:
theta_list = numpy.linspace(0., numpy.pi, N + 1)
self.__r_list_eta = -0.5 + 0.5 * (1. - numpy.cos(theta_list))
self.__r_list_y = 0.5 * (self.__r_list_eta[:-1] +
self.__r_list_eta[1:])
def __build_chords(self):
self.__chords = zeros((self.__n_sect))
self.__chords_grad = zeros((self.__n_sect, self.__ndv))
self.__chords_eta = zeros((self.__n_sect + 1))
self.__chords_grad_eta = zeros((self.__n_sect + 1, self.__ndv))
if self.__geom_type == 'Elliptic':
for i, r in enumerate(self.__r_list_y):
self.__chords[i] = self.__root_chord * sqrt(1. - (2. * r)**2)
self.__chords_grad[
i, :] = self.__root_chord_grad[:] * sqrt(1. - (2. * r)**2)
for i, r in enumerate(self.__r_list_eta):
self.__chords_eta[i] = self.__root_chord * sqrt(1. -
(2. * r)**2)
self.__chords_grad_eta[
i, :] = self.__root_chord_grad[:] * sqrt(1. - (2. * r)**2)
elif self.__geom_type == 'Rectangular':
for i in xrange(self.__n_sect):
self.__chords[i] = self.__root_chord
self.__chords_grad[i, :] = self.__root_chord_grad[:]
for i in xrange(self.__n_sect + 1):
self.__chords_eta[i] = self.__root_chord
self.__chords_grad_eta[i, :] = self.__root_chord_grad[:]
elif self.__geom_type == 'Broken':
p = self.__break_percent / 100.
p_grad = self.__break_percent_grad / 100.
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__chords[i] = (self.__break_chord - self.__root_chord
) * coeff + self.__root_chord
self.__chords_grad[i,:] = (self.__break_chord_grad[:] - self.__root_chord_grad[:])*coeff \
+ (self.__break_chord - self.__root_chord)*dcoeff \
+ self.__root_chord_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__chords[i] = (self.__tip_chord - self.__break_chord
) * coeff + self.__break_chord
self.__chords_grad[i,:] = (self.__tip_chord_grad[:] - self.__break_chord_grad[:])*coeff \
+ (self.__tip_chord - self.__break_chord)*dcoeff \
+ self.__break_chord_grad[:]
for i, r in enumerate(self.__r_list_eta):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__chords_eta[i] = (
self.__break_chord -
self.__root_chord) * coeff + self.__root_chord
self.__chords_grad_eta[i,:] = (self.__break_chord_grad[:] - self.__root_chord_grad[:])*coeff \
+ (self.__break_chord - self.__root_chord)*dcoeff \
+ self.__root_chord_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__chords_eta[i] = (
self.__tip_chord -
self.__break_chord) * coeff + self.__break_chord
self.__chords_grad_eta[i,:] = (self.__tip_chord_grad[:] - self.__break_chord_grad[:])*coeff \
+ (self.__tip_chord - self.__break_chord)*dcoeff \
+ self.__break_chord_grad[:]
def __build_heights_rel_thicks(self):
self.__heights = zeros((self.__n_sect))
self.__heights_grad = zeros((self.__n_sect, self.__ndv))
self.__rel_thicks = zeros((self.__n_sect))
self.__rel_thicks_grad = zeros((self.__n_sect, self.__ndv))
if self.__geom_type == 'Broken':
p = self.__break_percent / 100.
p_grad = self.__break_percent_grad / 100.
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__heights[i] = (
(self.__break_height - self.__root_height) * coeff +
self.__root_height)
self.__heights_grad[i,:] = (self.__break_height_grad[:] - self.__root_height_grad[:])*coeff \
+ (self.__break_height - self.__root_height)*dcoeff \
+ self.__root_height_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__heights[i] = (
(self.__tip_height - self.__break_height) * coeff +
self.__break_height)
self.__heights_grad[i,:] = (self.__tip_height_grad[:] - self.__break_height_grad[:])*coeff \
+ (self.__tip_height- self.__break_height)*dcoeff \
+ self.__break_height_grad[:]
else:
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
self.__heights[i] = (
(self.__tip_height - self.__root_height) * r +
self.__root_height)
self.__heights_grad[i, :] = (
(self.__tip_height_grad[:] - self.__root_height_grad[:]) *
r + self.__root_height_grad[:])
#-- build rel_thiks
for i in xrange(self.__n_sect):
self.__rel_thicks[i] = self.__heights[i] / self.__chords[i]
self.__rel_thicks_grad[
i, :] = (self.__heights_grad[i, :] * self.__chords[i] -
self.__heights[i] * self.__chords_grad[i, :]) / (
self.__chords[i])**2
def __build_XYZ_eta(self):
self.__XYZ = zeros((3, self.__n_sect))
self.__XYZ_grad = zeros((3, self.__n_sect, self.__ndv))
self.__eta = zeros((3, self.__n_sect + 1))
self.__eta_grad = zeros((3, self.__n_sect + 1, self.__ndv))
#print 'sweep=',self.__sweep,'sin sweep',sin(self.__sweep)
for i, r in enumerate(self.__r_list_y):
abs_r = abs(r)
#self.__XYZ[0,i] = 0.25*self.__chords[i] + abs_r*self.__span*sin(self.__sweep)
self.__XYZ[0, i] = abs_r * self.__span * sin(self.__sweep)
#self.__XYZ_grad[0,i,:] = 0.25*self.__chords_grad[i] + abs_r*self.__span_grad[:]*sin(self.__sweep)+abs_r*self.__span*cos(self.__sweep)*self.__sweep_grad[:]
self.__XYZ_grad[0, i, :] = abs_r * self.__span_grad[:] * sin(
self.__sweep) + abs_r * self.__span * cos(
self.__sweep) * self.__sweep_grad[:]
self.__XYZ[1, i] = r * self.__span
self.__XYZ_grad[1, i, :] = r * self.__span_grad[:]
for i, r in enumerate(self.__r_list_eta):
abs_r = abs(r)
#self.__eta[0,i] = 0.25*self.__chords_eta[i] + abs_r*self.__span*sin(self.__sweep)
self.__eta[0, i] = abs_r * self.__span * sin(self.__sweep)
#self.__eta_grad[0,i,:] = 0.25*self.__chords_grad_eta[i] + abs_r*self.__span_grad[:]*sin(self.__sweep)+abs_r*self.__span*cos(self.__sweep)*self.__sweep_grad[:]
self.__eta_grad[0, i, :] = abs_r * self.__span_grad[:] * sin(
self.__sweep) + abs_r * self.__span * cos(
self.__sweep) * self.__sweep_grad[:]
self.__eta[1, i] = r * self.__span
self.__eta_grad[1, i, :] = r * self.__span_grad[:]
# -- Airfoils methods
def get_linked_airfoils(self):
return self.__linked_airfoils
def set_ref_aifoil(self, ref_airfoil):
self.__ref_airfoil = ref_airfoil
def set_airfoils(self, airfoils):
ERROR_MSG = self.ERROR_MSG + 'set_airfoils: '
if len(airfoils) != self.__n_sect:
print ERROR_MSG + 'number of airfoils is different than the number of sections. attribute not set'
self.__airfoils = None
else:
self.__airfoils = airfoils
def build_linear_airfoil(self,
OC,
AoA0=0.,
Cm0=0.,
Sref=1.,
Lref=1.,
rel_thick=0.,
sweep=0.,
Ka=0.95,
set_as_ref=True):
self.__airfoil_type = 'simple'
degToRad = pi / 180.
airfoil = AnalyticAirfoil(OC,
AoA0=degToRad * AoA0,
Cm0=Cm0,
Sref=Sref,
Lref=Lref,
rel_thick=rel_thick,
sweep=sweep,
Ka=Ka)
if set_as_ref:
self.set_ref_aifoil(airfoil)
return airfoil
# def build_polar_airoil(self, OC, database, Sref=1., Lref=1., interpolator='2DSpline', set_as_ref=True):
# # Why relative thickness usage ? The extraction from a polar should give us more freedom.
# airfoil = AirfoilPolar(OC, database,rel_thick=0.15, interpolator=interpolator, Sref=Sref, Lref=Lref)
# if set_as_ref:
# self.set_ref_aifoil(airfoil)
# return airfoil
def build_meta_airfoil(self,
OC,
surrogate_model,
relative_thickness=.12,
camber=0.,
Sref=1.,
Lref=1.,
sweep=.0,
set_as_ref=True):
self.__airfoil_type = 'meta'
airfoil = MetaAirfoil(OC,
surrogate_model,
relative_thickness=relative_thickness,
camber=camber,
Sref=Sref,
Lref=Lref,
sweep=sweep)
if set_as_ref:
self.set_ref_aifoil(airfoil)
return airfoil
def build_airfoils_from_ref(self):
ERROR_MSG = self.ERROR_MSG + 'build_airfoils_from_ref: '
if self.__ref_airfoil is None:
print ERROR_MSG + 'cannot build airfoils if reference airfoil is not defined.'
else:
airfoils = []
for n in xrange(self.__n_sect):
airfoils.append(self.__ref_airfoil.get_scaled_copy())
self.set_airfoils(airfoils)
def __link_airfoils_to_geom(self):
self.__linked_airfoils = []
for i in range(self.__n_sect):
LLoc, LLoc_grad, SLoc, SLoc_grad = self.__compute_local_info(i)
linked_af = self.__airfoils[i].get_scaled_copy(Sref=SLoc,
Lref=LLoc)
linked_af.set_Sref_grad(SLoc_grad)
linked_af.set_Lref_grad(LLoc_grad)
linked_af.set_rel_thick_grad(self.__rel_thicks_grad[i])
linked_af.set_rel_thick(self.__rel_thicks[i])
linked_af.set_sweep(self.__sweep)
linked_af.set_sweep_grad(self.__sweep_grad)
self.__linked_airfoils.append(linked_af)
def __compute_local_info(self, i):
LLoc = self.__chords[i]
LLoc_grad = self.__chords_grad[i]
SLoc = LLoc * (self.__eta[1, i + 1] - self.__eta[1, i])
SLoc_grad = LLoc_grad * (self.__eta[1, i + 1] - self.__eta[1, i]
) + LLoc * (self.__eta_grad[1, i + 1, :] -
self.__eta_grad[1, i, :])
# SLoc = self.__span * LLoc / float(self.__n_sect)
# SLoc_grad = (self.__span_grad * LLoc + self.__span * LLoc_grad) / float(self.__n_sect)
return LLoc, LLoc_grad, SLoc, SLoc_grad
def __compute_Sref_Lref_ToC_AR_fuel(self):
"""
Compute Lref and Sref from airfoils information, ToC and AR
"""
N = self.__n_sect
self.__Sref = 0.
self.__Lref = 0.
self.__fuel = 0.
self.__Sref_grad = zeros(self.__ndv)
self.__Lref_grad = zeros(self.__ndv)
self.__fuel_grad = zeros(self.__ndv)
for i, af in enumerate(self.__linked_airfoils):
self.__Sref += af.get_Sref()
self.__Lref += af.get_Lref()
self.__fuel += self.__rel_thicks[i] * self.__chords[
i] * af.get_Sref() * 0.5
self.__Sref_grad += af.get_Sref_grad()
self.__Lref_grad += af.get_Lref_grad()
self.__fuel_grad+=self.__rel_thicks_grad[i]*self.__chords[i]*af.get_Sref()*0.5\
+ self.__rel_thicks[i]*self.__chords_grad[i]*af.get_Sref()*0.5\
+ self.__rel_thicks[i]*self.__chords[i]*af.get_Sref_grad()*0.5\
self.__Lref /= N
self.__Lref_grad /= N
self.__root_ToC = self.__root_height / self.__root_chord
self.__root_ToC_grad = (
self.__root_height_grad * self.__root_chord -
self.__root_height * self.__root_chord_grad) / self.__root_chord**2
if self.__break_chord is not None:
self.__break_ToC = self.__break_height / self.__break_chord
self.__break_ToC_grad = (
self.__break_height_grad * self.__break_chord -
self.__break_height *
self.__break_chord_grad) / self.__break_chord**2
if self.__tip_chord is not None:
self.__tip_ToC = self.__tip_height / self.__tip_chord
self.__tip_ToC_grad = (self.__tip_height_grad * self.__tip_chord -
self.__tip_height *
self.__tip_chord_grad) / self.__tip_chord**2
self.__AR = self.__span**2 / self.__Sref
self.__AR_grad = (2. * self.__span * self.__span_grad * self.__Sref -
self.__span**2 * self.__Sref_grad) / self.__Sref**2
def __check_airfoils_inputs(self):
ERROR_MSG = self.ERROR_MSG + '__check_airfoils_inputs: ' + str(
self.__tag) + ': '
checked = True
if self.__airfoils is None:
checked = False
print ERROR_MSG + 'airfoils attribute undefined. please set airfoils attribute.'
elif len(self.__airfoils) != self.__n_sect:
checked = False
print ERROR_MSG + 'number of airfoils must equal to the number of geometrical sections.'
if not checked:
sys.exit(1)
class DLLM_param(DLLM_Geom):
ERROR_MSG = 'ERROR in DLLM_param.'
def __init__(self, tag, n_sect=20, grad_active=True):
"""
Constructor: set main attributes
"""
DLLM_Geom.__init__(self, tag, n_sect=n_sect, grad_active=grad_active)
self.BC_manager = BCManager()
self.__AoA_id = 'AoA'
self.__common_OC = None
#-- Accessors
def get_dv_array(self):
return self.BC_manager.get_dv_array()
def get_dv_id_list(self):
return self.BC_manager.get_dv_id_list()
def get_dv_info_list(self):
return self.BC_manager.get_dv_info_list()
def get_bounds_array(self):
return self.BC_manager.get_bounds_array()
#-- Setters
def set_AoA_id(self, AoA_id):
self.__AoA_id = AoA_id
def set_value(self, Id, val):
pt = self.__BC_manager.get_pt(Id)
pt.set_value(val)
def set_common_OC(self, OC):
self.__common_OC = OC
#-- Methods
def import_BC_from_file(self, filename):
self.BC_manager.import_from_file(filename)
self.BC_manager.update()
def config_from_dict(self, config_dict):
config_dict_keys = config_dict.keys()
#-- Import BCManager from filename defined in config_dict
BC_filename_key=self.get_tag()+'.BCfilename'
if BC_filename_key in config_dict_keys:
BC_filename = config_dict[BC_filename_key]
self.import_BC_from_file(BC_filename)
#TBC: to be update with new way of working
#-- Config airfoils
airfoil_type_key = self.get_tag() + '.airfoil.type'
if airfoil_type_key in config_dict_keys:
airfoil_type = config_dict[airfoil_type_key]
else:
airfoil_type = 'simple'
self.set_airfoil_type(airfoil_type)
if airfoil_type == 'simple':
AoA0_key = self.get_tag() + '.airfoil.AoA0'
if AoA0_key in config_dict_keys:
AoA0 = config_dict[AoA0_key]
else:
AoA0 = 0.
self.build_linear_airfoil(self.__common_OC, AoA0=AoA0, set_as_ref=True)
elif airfoil_type == 'meta':
surrogate_model_key = self.__tag + '.airfoil.surrogate_model'
if surrogate_model_key in config_dict_keys:
surrogate_model = config_dict[surrogate_model_key]
else:
surrogate_model = None
self.build_meta_airfoil(self.__common_OC, surrogate_model, set_as_ref=True)
self.build_airfoils_from_ref()
self.update()
def update_from_x_list(self, x):
# print 'update wing_param with x=',x
self.BC_manager.update_dv_from_x_list(x)
self.update()
def update(self):
#-- Design variables update
self.BC_manager.update()
ndv = self.BC_manager.get_ndv()
self.set_ndv(ndv)
self.__update_AoA()
#-- Update necessary information
self.build_r_lists()
#-- Build discretization
self.build_discretization()
DLLM_Geom.update(self)
def build_discretization(self):
print 'WARNING: build_discretization method has to be overloaded in child classes...'
#-- Private methods
def __update_AoA(self):
Id = self.__AoA_id
if Id in self.get_dv_id_list():
pt = self.BC_manager.get_pt(Id)
deg_to_rad = np.pi / 180.
AoA = pt.get_value() * deg_to_rad
AoA_grad = pt.get_gradient() * deg_to_rad
else:
AoA = None
AoA_grad = None
self.set_AoA(AoA)
self.set_AoA_grad(AoA_grad)
def __repr__(self):
DLLM_Geom.__repr__(self)
info_string = '\n*** Wing param information ***'
info_string += '\n n_sect : ' + str(self.get_n_sect())
info_string += '\n ndv : ' + str(self.get_ndv())
info_string += '\n airfoil_type : ' + str(self.get_airfoil_type())
info_string += '\n -- parameters information section --\n'
for Id in self.BC_manager.get_list_id():
pt = self.BC_manager.get_pt(Id)
BC_Type = pt.get_BCType()
if BC_Type == 'Variable':
value = pt.get_value()
info_string += "%30s" % Id + \
"%20s" % BC_Type + " %24.16e" % value + "\n"
if BC_Type == 'DesignVariable':
value = pt.get_value()
bounds = pt.get_bounds()
info_string += "%30s" % Id + "%20s" % BC_Type + \
" %24.16e" % value + " %24s" % str(bounds) + "\n"
if BC_Type == 'Parameter':
expr = pt.get_expr()
info_string += "%30s" % Id + \
"%20s" % BC_Type + " %24s" % expr + "\n"
info_string += ' -- end of parameters information section --\n'
return info_string
class Wing_param():
ERROR_MSG = 'ERROR in Wing_param.'
POSSIBLE_GEOM_TYPES = ["Rectangular", "Elliptic", "Broken"]
POS_DISTRIB = ['linear', 'cos_law']
DISCRETE_ATTRIBUTES_LIST = [
'span',
'sweep',
'break_percent',
'root_chord',
'break_chord',
'tip_chord',
'root_height',
'break_height',
'tip_height']
def __init__(self, tag, geom_type='Broken', n_sect=20):
"""
Constructor: set main attributes
"""
self.__tag = tag
self.__geom_type = None
self.__n_sect = None
self.__PCADModel = None
self.__BC_manager = None
self.__distrib_type = 'cos_law'
self.set_geom_type(geom_type)
self.set_n_sect(n_sect)
self.__BC_manager = BCManager()
self.__ndv = 0
self.__thetaY = None
self.__AoA_id = 'AoA'
self.__init_discrete_attributes()
self.__init_airfoils_attributes()
def __init_discrete_attributes(self):
# -- OC design variable
self.__AoA = None
self.__AoA_grad = None
# -- discrete attributes
self.__span = None
self.__span_grad = None
self.__r_list_y = None
self.__r_list_eta = None
self.__sweep = None
self.__sweep_grad = None
self.__break_percent = None
self.__break_percent_grad = None
self.__root_chord = None
self.__root_chord_grad = None
self.__break_chord = None
self.__break_chord_grad = None
self.__tip_chord = None
self.__tip_chord_grad = None
self.__root_height = None
self.__root_height_grad = None
self.__break_height = None
self.__break_height_grad = None
self.__tip_height = None
self.__tip_height_grad = None
self.__twist = None
self.__twist_grad = None
self.__chords = None
self.__chords_grad = None
self.__heights = None
self.__heights_grad = None
self.__rel_thicks = None
self.__rel_thicks_grad = None
self.__XYZ = None
self.__XYZ_grad = None
self.__eta = None
self.__eta_grad = None
self.__Lref = None
self.__Lref_grad = None
self.__Sref = None
self.__Sref_grad = None
self.__root_ToC = None
self.__root_ToC_grad = None
self.__break_ToC = None
self.__break_ToC_grad = None
self.__tip_ToC = None
self.__tip_ToC_grad = None
self.__AR = None
self.__AR_grad = None
self.__fuel = None
self.__fuel_grad = None
def __init_airfoils_attributes(self):
self.__airfoil_type = None
# reference airfoil, only used if the same airfoil is put for all
# sections
self.__ref_airfoil = None
self.__airfoils = None # Airfoil list for each section
self.__linked_airfoils = None # Airfoil scaled to the the planform
# -- Accessors
def get_n_sect(self):
return self.__n_sect
def get_ndv(self):
return self.__ndv
def get_eta(self):
return self.__eta
def get_eta_grad(self):
return self.__eta_grad
def get_XYZ(self):
return self.__XYZ
def get_XYZ_grad(self):
return self.__XYZ_grad
def get_twist(self):
return self.__twist
def get_twist_grad(self):
return self.__twist_grad
def get_chords(self):
return self.__chords
def get_chords_grad(self):
return self.__chords_grad
def get_rel_thicks(self):
return self.__rel_thicks
def get_rel_thicks_grad(self):
return self.__rel_thicks_grad
def get_thetaY(self):
return self.__thetaY
def get_BC_manager(self):
return self.__BC_manager
def get_AoA(self):
return self.__AoA
def get_AoA_grad(self):
return self.__AoA_grad
def get_span(self):
return self.__span
def get_span_grad(self):
return self.__span_grad
def get_sweep(self):
return self.__sweep
def get_sweep_grad(self):
return self.__sweep_grad
def get_Lref(self):
return self.__Lref
def get_Lref_grad(self):
return self.__Lref_grad
def get_Sref(self):
return self.__Sref
def get_Sref_grad(self):
return self.__Sref_grad
def get_root_ToC(self):
return self.__root_ToC
def get_root_ToC_grad(self):
return self.__root_ToC_grad
def get_break_ToC(self):
return self.__break_ToC
def get_break_ToC_grad(self):
return self.__break_ToC_grad
def get_tip_ToC(self):
return self.__tip_ToC
def get_tip_ToC_grad(self):
return self.__tip_ToC_grad
def get_AR(self):
return self.__AR
def get_AR_grad(self):
return self.__AR_grad
def get_fuel(self):
return self.__fuel
def get_fuel_grad(self):
return self.__fuel_grad
# -- Setters
def set_AoA_id(self, AoA_id):
self.__AoA_id = AoA_id
def set_geom_type(self, geom_type):
"""
@param wing_geometry_type : Rectangular or Elliptic planforms
@param type wing_geometry_type : String
"""
if not geom_type in self.POSSIBLE_GEOM_TYPES:
raise Exception("geom_type :" +
str(geom_type) +
" not in possible types : " +
str(self.POSSIBLE_GEOM_TYPES))
self.__geom_type = geom_type
def set_n_sect(self, n_sect):
ERROR_MSG = self.ERROR_MSG + '.set_n_sect: ' + str(self.__tag) + ': '
if n_sect % 2 != 0:
raise Exception(
ERROR_MSG +
'The total number of elements in the wing must be even.')
self.__n_sect = n_sect
def set_distrib_type(self, distrib_type):
if not distrib_type in self.POS_DISTRIB:
raise Exception("distrib_type :" +
str(distrib_type) +
" not in possible types : " +
str(self.POS_DISTRIB))
self.__distrib_type = distrib_type
def set_value(self, Id, val):
pt = self.__BC_manager.get_pt(Id)
pt.set_value(val)
def set_thetaY(self, thetaY):
self.__thetaY = thetaY
# -- controller management
def convert_to_variable(self, Id):
self.__BC_manager.convert_to_variable(Id)
def convert_to_design_variable(self, Id, bounds):
self.__BC_manager.convert_to_design_variable(Id, bounds)
def convert_to_parameter(self, Id, fexpr):
self.__BC_manager.convert_to_parameter(Id, fexpr)
def add_AoA_design_variable(self, val, bounds):
self.__BC_manager.create_design_variable(self.__AoA_id, val, bounds)
def __update_AoA(self):
Id = self.__AoA_id
if Id in self.get_dv_id_list():
pt = self.__BC_manager.get_pt(Id)
deg_to_rad = pi / 180.
self.__AoA = pt.get_value() * deg_to_rad
self.__AoA_grad = pt.get_gradient() * deg_to_rad
def get_dv_array(self):
return self.__BC_manager.get_dv_array()
def get_dv_id_list(self):
return self.__BC_manager.get_dv_id_list()
def get_dv_info_list(self):
return self.__BC_manager.get_dv_info_list()
def get_bounds_array(self):
return self.__BC_manager.get_bounds_array()
def build_wing(self):
self.__BC_manager.clean()
self.__BC_manager.create_variable('span', 0.)
if self.__geom_type not in ['Elliptic']:
self.__BC_manager.create_variable('sweep', 0.)
if self.__geom_type in ['Rectangular', 'Elliptic']:
self.__BC_manager.create_variable('root_chord', 0.)
self.__BC_manager.create_variable('root_height', 0.)
self.__BC_manager.create_variable('tip_height', 0.)
elif self.__geom_type == 'Broken':
self.__BC_manager.create_variable('break_percent', 0.33)
self.__BC_manager.create_variable('root_chord', 0.)
self.__BC_manager.create_variable('break_chord', 0.)
self.__BC_manager.create_variable('tip_chord', 0.)
self.__BC_manager.create_variable('root_height', 0.)
self.__BC_manager.create_variable('break_height', 0.)
self.__BC_manager.create_variable('tip_height', 0.)
for i in xrange(self.__n_sect / 2):
self.__BC_manager.create_design_variable(
'rtwist' + str(i), 0., (-10., 10.))
for i in xrange(self.__n_sect / 2):
# print
# self.__tag+'.twist'+str(i),self.__tag+'.twist'+str(self.__n_sect/2+i),self.__tag+'.rtwist'+str(self.__n_sect/2-1-i),self.__tag+'.rtwist'+str(i)
self.__BC_manager.create_parameter(
'twist' + str(i), 'rtwist' + str(self.__n_sect / 2 - 1 - i))
self.__BC_manager.create_parameter(
'twist' + str(self.__n_sect / 2 + i), 'rtwist' + str(i))
# for i in xrange(self.__n_sect):
# self.__BC_manager.create_design_variable(self.__tag+'.twist'+str(i),-25.,0.,25.)
def config_from_dict(self, OC, config_dict):
self.build_wing()
self.__config_airfoils(OC, config_dict)
self.__config_desc(config_dict)
self.update()
def __config_airfoils(self, OC, config_dict):
in_keys_list = config_dict.keys()
airfoil_type_key = self.__tag + '.airfoil.type'
if airfoil_type_key in in_keys_list:
airfoil_type = config_dict[airfoil_type_key]
else:
airfoil_type = 'simple'
if airfoil_type == 'simple':
AoA0_key = self.__tag + '.airfoil.AoA0'
if AoA0_key in in_keys_list:
AoA0 = config_dict[AoA0_key]
else:
AoA0 = 0.
Cm0_key = self.__tag + '.airfoil.Cm0'
if Cm0_key in in_keys_list:
Cm0 = config_dict[Cm0_key]
else:
Cm0 = 0.
self.build_linear_airfoil(OC, AoA0=AoA0, Cm0=Cm0, set_as_ref=True)
elif airfoil_type == 'meta':
surrogate_model_key = self.__tag + '.airfoil.surrogate_model'
if surrogate_model_key in in_keys_list:
surrogate_model = config_dict[surrogate_model_key]
else:
surrogate_model = None
self.build_meta_airfoil(OC, surrogate_model, set_as_ref=True)
self.build_airfoils_from_ref()
def __config_desc(self, config_dict):
in_keys_list=sorted(config_dict.keys())
existing_keys=deepcopy(self.__BC_manager.get_list_id())
# Add user defined DesignVariable, Variable and Parameter
added_list=[]
for in_key in in_keys_list:
words=in_key.split('.')
if len(words) >=4:
test=string.join(words[:-2],'.')
if test==self.__tag+'.desc':
name=words[-2]
Id=name
Id_in=self.__tag+'.desc.'+name
type=config_dict[Id_in+'.type']
if Id not in existing_keys and Id not in added_list:
if type == 'DesignVariable':
bounds = config_dict[Id_in+'.bounds']
value = config_dict[Id_in+'.value']
self.__BC_manager.create_design_variable(Id,value,(bounds[0],bounds[1]))
elif type == 'Variable':
value = config_dict[Id_in+'.value']
self.__BC_manager.create_variable(Id,value)
elif type == 'Parameter':
fexpr = config_dict[Id_in+'.fexpr']
self.__BC_manager.create_parameter(Id,fexpr)
added_list.append(Id)
# Convert pre-defined parameters
for existing_id in existing_keys:
ex_words=existing_id.split('.')
name=ex_words[-1]
Id_in=self.__tag+'.desc.'+name
Id=name
if Id_in+'.type' in in_keys_list:
type=config_dict[Id_in+'.type']
if type == 'DesignVariable':
bounds = config_dict[Id_in+'.bounds']
value = config_dict[Id_in+'.value']
self.set_value(Id,value)
self.convert_to_design_variable(Id,bounds)
elif type == 'Variable':
value = config_dict[Id_in+'.value']
self.set_value(Id,value)
self.convert_to_variable(Id)
elif type == 'Parameter':
fexpr = config_dict[Id_in+'.fexpr']
self.convert_to_parameter(Id,fexpr)
def update(self):
self.__BC_manager.update()
self.__ndv = self.__BC_manager.get_ndv()
self.__update_AoA()
self.__check_thetaY()
self.__build_discretization()
self.__check_airfoils_inputs()
self.__link_airfoils_to_geom()
self.__compute_Sref_Lref_ToC_AR_fuel()
def update_from_x_list(self, x):
# print 'update wing_param with x=',x
self.__BC_manager.update_dv_from_x_list(x)
self.update()
def __repr__(self):
info_string = '\n*** Wing param information ***'
info_string += '\n geom_type : ' + str(self.__geom_type)
info_string += '\n n_sect : ' + str(self.__n_sect)
info_string += '\n ndv : ' + str(self.__ndv)
info_string += '\n airfoil_type : ' + str(self.__airfoil_type)
info_string += '\n -- parameters information section --\n'
for Id in self.__BC_manager.get_list_id():
pt = self.__BC_manager.get_pt(Id)
BC_Type = pt.get_BCType()
if BC_Type == 'Variable':
value = pt.get_value()
info_string += "%30s" % Id + \
"%20s" % BC_Type + " %24.16e" % value + "\n"
if BC_Type == 'DesignVariable':
value = pt.get_value()
bounds = pt.get_bounds()
info_string += "%30s" % Id + "%20s" % BC_Type + \
" %24.16e" % value + " %24s" % str(bounds) + "\n"
if BC_Type == 'Parameter':
expr = pt.get_expr()
info_string += "%30s" % Id + \
"%20s" % BC_Type + " %24s" % expr + "\n"
info_string += ' -- end of parameters information section --\n'
return info_string
# -- Structural displacement methods
def __check_thetaY(self):
# 6 dimensions for structural displacement:
# dx,dy,dz,dthetax,dthetay,dthetaz at each section
if self.__thetaY is None:
self.__thetaY = zeros(self.__n_sect)
# -- discretization methods
def __build_discretization(self):
self.__build_planform()
self.__build_r_lists()
self.__build_chords()
self.__build_heights_rel_thicks()
self.__build_XYZ_eta()
def __build_planform(self):
deg_to_rad = pi / 180.
# -- span
Id = 'span'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__span = val
self.__span_grad = grad
if self.__geom_type not in ['Elliptic']:
# -- sweep
Id = 'sweep'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__sweep = val * deg_to_rad
self.__sweep_grad = grad * deg_to_rad
else:
self.__sweep = 0.
self.__sweep_grad = zeros(self.get_ndv())
if self.__geom_type in ['Rectangular', 'Elliptic']:
Id = 'root_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_chord = val
self.__root_chord_grad = grad
Id = 'root_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_height = val
self.__root_height_grad = grad
Id = 'tip_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_height = val
self.__tip_height_grad = grad
elif self.__geom_type == 'Broken':
Id = 'break_percent'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_percent = val
self.__break_percent_grad = grad
Id = 'root_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_chord = val
self.__root_chord_grad = grad
Id = 'break_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_chord = val
self.__break_chord_grad = grad
Id = 'tip_chord'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_chord = val
self.__tip_chord_grad = grad
Id = 'root_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__root_height = val
self.__root_height_grad = grad
Id = 'break_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__break_height = val
self.__break_height_grad = grad
Id = 'tip_height'
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__tip_height = val
self.__tip_height_grad = grad
self.__twist = zeros((self.__n_sect))
self.__twist_grad = zeros((self.__n_sect, self.__ndv))
for i in xrange(self.__n_sect):
Id = 'twist' + str(i)
pt = self.__BC_manager.get_pt(Id)
val = pt.get_value()
grad = pt.get_gradient()
self.__twist[i] = val * deg_to_rad
self.__twist_grad[i, :] = grad * deg_to_rad
def __build_r_lists(self):
N = self.__n_sect
if self.__distrib_type == 'linear':
self.__r_list_eta = numpy.linspace(-0.5, 0.5, N + 1)
else:
theta_list = numpy.linspace(0., numpy.pi, N + 1)
self.__r_list_eta = -0.5 + 0.5 * (1. - numpy.cos(theta_list))
self.__r_list_y = 0.5 * \
(self.__r_list_eta[:-1] + self.__r_list_eta[1:])
def __build_chords(self):
self.__chords = zeros((self.__n_sect))
self.__chords_grad = zeros((self.__n_sect, self.__ndv))
self.__chords_eta = zeros((self.__n_sect + 1))
self.__chords_grad_eta = zeros((self.__n_sect + 1, self.__ndv))
if self.__geom_type == 'Elliptic':
for i, r in enumerate(self.__r_list_y):
self.__chords[i] = self.__root_chord * sqrt(1. - (2. * r)**2)
self.__chords_grad[i, :] = self.__root_chord_grad[
:] * sqrt(1. - (2. * r)**2)
for i, r in enumerate(self.__r_list_eta):
self.__chords_eta[i] = self.__root_chord * \
sqrt(1. - (2. * r)**2)
self.__chords_grad_eta[i, :] = self.__root_chord_grad[:] \
* sqrt(1. - (2. * r)**2)
elif self.__geom_type == 'Rectangular':
for i in xrange(self.__n_sect):
self.__chords[i] = self.__root_chord
self.__chords_grad[i, :] = self.__root_chord_grad[:]
for i in xrange(self.__n_sect + 1):
self.__chords_eta[i] = self.__root_chord
self.__chords_grad_eta[i, :] = self.__root_chord_grad[:]
elif self.__geom_type == 'Broken':
p = self.__break_percent / 100.
p_grad = self.__break_percent_grad / 100.
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__chords[i] = (self.__break_chord - self.__root_chord) * coeff + self.__root_chord
self.__chords_grad[i, :] = (self.__break_chord_grad[:] - self.__root_chord_grad[:]) * coeff \
+ (self.__break_chord - self.__root_chord) * dcoeff + self.__root_chord_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__chords[i] = ( self.__tip_chord - self.__break_chord) * coeff + self.__break_chord
self.__chords_grad[i, :] = (self.__tip_chord_grad[:] - self.__break_chord_grad[:]) * coeff \
+ (self.__tip_chord - self.__break_chord) * dcoeff + self.__break_chord_grad[:]
for i, r in enumerate(self.__r_list_eta):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__chords_eta[i] = (
self.__break_chord - self.__root_chord) * coeff + self.__root_chord
self.__chords_grad_eta[i, :] = (self.__break_chord_grad[:] - self.__root_chord_grad[:]) * coeff \
+ (self.__break_chord - self.__root_chord) * dcoeff \
+ self.__root_chord_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__chords_eta[i] = (
self.__tip_chord - self.__break_chord) * coeff + self.__break_chord
self.__chords_grad_eta[i, :] = (self.__tip_chord_grad[:] - self.__break_chord_grad[:]) * coeff \
+ (self.__tip_chord - self.__break_chord) * dcoeff \
+ self.__break_chord_grad[:]
def __build_heights_rel_thicks(self):
self.__heights = zeros((self.__n_sect))
self.__heights_grad = zeros((self.__n_sect, self.__ndv))
self.__rel_thicks = zeros((self.__n_sect))
self.__rel_thicks_grad = zeros((self.__n_sect, self.__ndv))
if self.__geom_type == 'Broken':
p = self.__break_percent / 100.
p_grad = self.__break_percent_grad / 100.
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
if r <= p:
coeff = r / p
dcoeff = -r * p_grad[:] / p**2
self.__heights[i] = (
(self.__break_height -
self.__root_height) *
coeff +
self.__root_height)
self.__heights_grad[i, :] = (self.__break_height_grad[:] - self.__root_height_grad[:]) * coeff \
+ (self.__break_height - self.__root_height) * dcoeff \
+ self.__root_height_grad[:]
else:
coeff = (r - p) / (1. - p)
dcoeff = (r - 1) * p_grad[:] / (1. - p)**2
self.__heights[i] = (
(self.__tip_height -
self.__break_height) *
coeff +
self.__break_height)
self.__heights_grad[i, :] = (self.__tip_height_grad[:] - self.__break_height_grad[:]) * coeff \
+ (self.__tip_height - self.__break_height) * dcoeff \
+ self.__break_height_grad[:]
else:
for i, r in enumerate(self.__r_list_y):
r = abs(2. * r)
self.__heights[i] = (
(self.__tip_height -
self.__root_height) *
r +
self.__root_height)
self.__heights_grad[
i,
:] = (
(self.__tip_height_grad[:] -
self.__root_height_grad[:]) *
r +
self.__root_height_grad[:])
#-- build rel_thiks
for i in xrange(self.__n_sect):
self.__rel_thicks[i] = self.__heights[i] / self.__chords[i]
self.__rel_thicks_grad[i,
:] = (self.__heights_grad[i,
:] * self.__chords[i] - self.__heights[i] * self.__chords_grad[i,
:]) / (self.__chords[i])**2
def __build_XYZ_eta(self):
self.__XYZ = zeros((3, self.__n_sect))
self.__XYZ_grad = zeros((3, self.__n_sect, self.__ndv))
self.__eta = zeros((3, self.__n_sect + 1))
self.__eta_grad = zeros((3, self.__n_sect + 1, self.__ndv))
# print 'sweep=',self.__sweep,'sin sweep',sin(self.__sweep)
for i, r in enumerate(self.__r_list_y):
abs_r = abs(r)
#self.__XYZ[0,i] = 0.25*self.__chords[i] + abs_r*self.__span*sin(self.__sweep)
self.__XYZ[0, i] = abs_r * self.__span * sin(self.__sweep)
#self.__XYZ_grad[0,i,:] = 0.25*self.__chords_grad[i] + abs_r*self.__span_grad[:]*sin(self.__sweep)+abs_r*self.__span*cos(self.__sweep)*self.__sweep_grad[:]
self.__XYZ_grad[0, i, :] = abs_r * self.__span_grad[:] * sin(
self.__sweep) + abs_r * self.__span * cos(self.__sweep) * self.__sweep_grad[:]
self.__XYZ[1, i] = r * self.__span
self.__XYZ_grad[1, i, :] = r * self.__span_grad[:]
for i, r in enumerate(self.__r_list_eta):
abs_r = abs(r)
#self.__eta[0,i] = 0.25*self.__chords_eta[i] + abs_r*self.__span*sin(self.__sweep)
self.__eta[0, i] = abs_r * self.__span * sin(self.__sweep)
#self.__eta_grad[0,i,:] = 0.25*self.__chords_grad_eta[i] + abs_r*self.__span_grad[:]*sin(self.__sweep)+abs_r*self.__span*cos(self.__sweep)*self.__sweep_grad[:]
self.__eta_grad[0, i, :] = abs_r * self.__span_grad[:] * sin(
self.__sweep) + abs_r * self.__span * cos(self.__sweep) * self.__sweep_grad[:]
self.__eta[1, i] = r * self.__span
self.__eta_grad[1, i, :] = r * self.__span_grad[:]
# -- Airfoils methods
def get_linked_airfoils(self):
return self.__linked_airfoils
def set_ref_aifoil(self, ref_airfoil):
self.__ref_airfoil = ref_airfoil
def set_airfoils(self, airfoils):
ERROR_MSG = self.ERROR_MSG + 'set_airfoils: '
if len(airfoils) != self.__n_sect:
print ERROR_MSG + 'number of airfoils is different than the number of sections. attribute not set'
self.__airfoils = None
else:
self.__airfoils = airfoils
def build_linear_airfoil(self, OC, AoA0=0., Cm0=0., Sref=1.,
Lref=1., rel_thick=0., sweep=0., Ka=0.95, set_as_ref=True):
self.__airfoil_type = 'simple'
degToRad = pi / 180.
airfoil = AnalyticAirfoil(
OC,
AoA0=degToRad *
AoA0,
Cm0=Cm0,
Sref=Sref,
Lref=Lref,
rel_thick=rel_thick,
sweep=sweep,
Ka=Ka)
if set_as_ref:
self.set_ref_aifoil(airfoil)
return airfoil
# def build_polar_airoil(self, OC, database, Sref=1., Lref=1., interpolator='2DSpline', set_as_ref=True):
# # Why relative thickness usage ? The extraction from a polar should give us more freedom.
# airfoil = AirfoilPolar(OC, database,rel_thick=0.15, interpolator=interpolator, Sref=Sref, Lref=Lref)
# if set_as_ref:
# self.set_ref_aifoil(airfoil)
# return airfoil
def build_meta_airfoil(self, OC, surrogate_model, relative_thickness=.12,
camber=0., Sref=1., Lref=1., sweep=.0, set_as_ref=True):
self.__airfoil_type = 'meta'
airfoil = MetaAirfoil(OC, surrogate_model, relative_thickness=relative_thickness,
camber=camber, Sref=Sref, Lref=Lref, sweep=sweep)
if set_as_ref:
self.set_ref_aifoil(airfoil)
return airfoil
def build_airfoils_from_ref(self):
ERROR_MSG = self.ERROR_MSG + 'build_airfoils_from_ref: '
if self.__ref_airfoil is None:
print ERROR_MSG + 'cannot build airfoils if reference airfoil is not defined.'
else:
airfoils = []
for n in xrange(self.__n_sect):
airfoils.append(self.__ref_airfoil.get_scaled_copy())
self.set_airfoils(airfoils)
def __link_airfoils_to_geom(self):
self.__linked_airfoils = []
for i in range(self.__n_sect):
LLoc, LLoc_grad, SLoc, SLoc_grad = self.__compute_local_info(i)
linked_af = self.__airfoils[i].get_scaled_copy(
Sref=SLoc,
Lref=LLoc)
linked_af.set_Sref_grad(SLoc_grad)
linked_af.set_Lref_grad(LLoc_grad)
linked_af.set_rel_thick_grad(self.__rel_thicks_grad[i])
linked_af.set_rel_thick(self.__rel_thicks[i])
linked_af.set_sweep(self.__sweep)
linked_af.set_sweep_grad(self.__sweep_grad)
self.__linked_airfoils.append(linked_af)
def __compute_local_info(self, i):
LLoc = self.__chords[i]
LLoc_grad = self.__chords_grad[i]
SLoc = LLoc * (self.__eta[1, i + 1] - self.__eta[1, i])
SLoc_grad = LLoc_grad * (self.__eta[1, i + 1] - self.__eta[1, i]) + \
LLoc * (self.__eta_grad[1, i + 1, :] - self.__eta_grad[1, i, :])
# SLoc = self.__span * LLoc / float(self.__n_sect)
# SLoc_grad = (self.__span_grad * LLoc + self.__span * LLoc_grad) / float(self.__n_sect)
return LLoc, LLoc_grad, SLoc, SLoc_grad
def __compute_Sref_Lref_ToC_AR_fuel(self):
"""
Compute Lref and Sref from airfoils information, ToC and AR
"""
N = self.__n_sect
self.__Sref = 0.
self.__Lref = 0.
self.__fuel = 0.
self.__Sref_grad = zeros(self.__ndv)
self.__Lref_grad = zeros(self.__ndv)
self.__fuel_grad = zeros(self.__ndv)
for i, af in enumerate(self.__linked_airfoils):
self.__Sref += af.get_Sref()
self.__Lref += af.get_Lref()
self.__fuel += self.__rel_thicks[i] * \
self.__chords[i] * af.get_Sref() * 0.5
self.__Sref_grad += af.get_Sref_grad()
self.__Lref_grad += af.get_Lref_grad()
self.__fuel_grad += self.__rel_thicks_grad[i] * self.__chords[i] * af.get_Sref() * 0.5\
+ self.__rel_thicks[i] * self.__chords_grad[i] * af.get_Sref() * 0.5\
+ self.__rel_thicks[i] * self.__chords[i] * af.get_Sref_grad() * 0.5\
self.__Lref /= N
self.__Lref_grad /= N
self.__root_ToC = self.__root_height / self.__root_chord
self.__root_ToC_grad = (self.__root_height_grad * self.__root_chord -
self.__root_height * self.__root_chord_grad) / self.__root_chord**2
if self.__break_chord is not None:
self.__break_ToC = self.__break_height / self.__break_chord
self.__break_ToC_grad = (self.__break_height_grad * self.__break_chord -
self.__break_height * self.__break_chord_grad) / self.__break_chord**2
if self.__tip_chord is not None:
self.__tip_ToC = self.__tip_height / self.__tip_chord
self.__tip_ToC_grad = (self.__tip_height_grad * self.__tip_chord -
self.__tip_height * self.__tip_chord_grad) / self.__tip_chord**2
self.__AR = self.__span**2 / self.__Sref
self.__AR_grad = (2. * self.__span * self.__span_grad *
self.__Sref - self.__span**2 * self.__Sref_grad) / self.__Sref**2
def __check_airfoils_inputs(self):
ERROR_MSG = self.ERROR_MSG + \
'__check_airfoils_inputs: ' + str(self.__tag) + ': '
checked = True
if self.__airfoils is None:
checked = False
print ERROR_MSG + 'airfoils attribute undefined. please set airfoils attribute.'
elif len(self.__airfoils) != self.__n_sect:
checked = False
print ERROR_MSG + 'number of airfoils must equal to the number of geometrical sections.'
if not checked:
sys.exit(1)
