def df2(x):
wing_param.update_from_x_list(x)
DLLM = DLLMTargetLift('Simple', wing_param, OC)
DLLM.set_target_Lift(769200.)
DLLM.set_F_list_names(F_list_names)
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
func_grad = array(DLLM.get_dF_list_dchi())
return func_grad
def df(x):
wing_param.update_from_x_list(x)
DLLM = DLLMTargetLift('Simple',wing_param,OC)
DLLM.set_target_Lift(769200.)
DLLM.set_F_list_names(F_list_names)
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
func_grad=numpy.array(DLLM.get_dF_list_dchi())
return func_grad
def df2(x):
wing_param.update_from_x_list(x)
DLLM = DLLMTargetLift('Simple',wing_param,OC)
DLLM.set_target_Lift(769200.)
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
func_grad=np.array(DLLM.get_dF_list_dchi())
N = func_grad.shape[0]
ndv = func_grad.shape[1]
out_grad = np.zeros((N,ndv))
for i in xrange(N):
out_grad[i,:] = func_grad[i,:]/Ref_list[i]
return out_grad
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
wing_param.convert_to_design_variable('tip_chord', (1., 2.))
wing_param.convert_to_design_variable('root_height', (1., 1.5))
wing_param.convert_to_design_variable('break_height', (0.8, 1.2))
wing_param.convert_to_design_variable('tip_height', (0.2, 0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
DLLM = DLLMTargetLift('TLift', wing_param, OC)
DLLM.set_target_Lift(769200.)
#DLLM.set_method('scipy')
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
dF_list_dchi = DLLM.get_dF_list_dchi()
# for i,name in enumerate(DLLM.get_F_list_names()):
# print 'gradients for '+name+' = ',dF_list_dchi[i]
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
wing_param.convert_to_design_variable('tip_chord',(1.,2.))
wing_param.convert_to_design_variable('root_height',(1.,1.5))
wing_param.convert_to_design_variable('break_height',(0.8,1.2))
wing_param.convert_to_design_variable('tip_height',(0.2,0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
DLLM = DLLMTargetLift('TLift',wing_param,OC)
DLLM.set_target_Lift(769200.)
#DLLM.set_method('scipy')
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
dF_list_dchi=DLLM.get_dF_list_dchi()
# for i,name in enumerate(DLLM.get_F_list_names()):
# print 'gradients for '+name+' = ',dF_list_dchi[i]
class DLLMOpenMDAOComponent(Component):
# set up interface to the framework
# pylint: disable-msg=E1101
# Outputs of lifting line problem
"""OpenMDAO component for DLLM implementation
"""
Lift = Float(iotype='out', desc='Lift')
Drag = Float(iotype='out', desc='Drag')
Drag_Pressure = Float(iotype='out', desc='Drag_Pressure')
Drag_Induced = Float(iotype='out', desc='Drag_Induced')
Drag_Wave = Float(iotype='out', desc='Drag_Wave')
Drag_Friction = Float(iotype='out', desc='Drag_Friction')
Cd = Float(iotype='out', desc='Cd')
Cdp = Float(iotype='out', desc='Cdp')
Cdi = Float(iotype='out', desc='Cdi')
Cdw = Float(iotype='out', desc='Cdw')
Cdf = Float(iotype='out', desc='Cdf')
Cl = Float(iotype='out', desc='Cl')
LoD = Float(iotype='out', desc='LoD')
Sref = Float(iotype='out', desc='Sref')
# Design variables of lifting line problem
rtwist = Array([], desc='rtwist', iotype="in")
span = Float(desc='span', default_value=34., iotype="in")
sweep = Float(desc='sweep', default_value=34., iotype="in")
break_percent = Float(desc='break_percent', default_value=33., iotype="in")
root_chord = Float(desc='root_chord', default_value=6.1, iotype="in")
break_chord = Float(desc='break_chord', default_value=4.6, iotype="in")
tip_chord = Float(desc='tip_chord', default_value=1.5, iotype="in")
root_height = Float(desc='root_height', default_value=1.28, iotype="in")
break_height = Float(desc='break_height', default_value=0.97, iotype="in")
tip_height = Float(desc='tip_height', default_value=0.33, iotype="in")
# Operating conditions variables
Mach = Float(iotype='in', default_value=0.7, desc='Mach')
altitude = Float(iotype='in', default_value=10000., desc='Altitude')
T0 = Float(iotype='in',default_value=OperatingCondition.T0,
desc='Ground ISA ref Temperature')
P0 = Float(iotype='in',default_value=OperatingCondition.P0,
desc='Ground ISA ref Pressure')
def __init__(self,Target_Lift, N = 10, verbose=0):
"""Initialization of DLLM component.
DLLM component use target lift capability of DLLM kernel
@param Target_Lift : the targeted lift value (float)
@param N : integer. Number of discrete section on 1/2 wing
@param verbose : integer : verbosity level
"""
try :
float(Target_Lift)
except:
raise ValueError('You MUST define a float target lift value, get '+str(Target_Lift)+' instead.')
self.Target_Lift = Target_Lift
self.N = N
self.OC = None
self.rtwist = np.zeros(N)
self.__display_wing_param = True
self.__verbose = verbose
self.__wing_param = None
super(DLLMOpenMDAOComponent, self).__init__()
self.OC = OperatingCondition(tag='DLLMOC', atmospheric_model='ISA')
self.__set_OC_values()
self.__set_wing_param()
self.__DLLM = DLLMTargetLift('test', self.__wing_param,
self.OC, verbose=self.__verbose)
self.__DLLM.set_target_Lift(Target_Lift)
self.__DLLM.run_direct()
self.__DLLM.run_post()
def __set_wing_param(self, wing_param_name='test_param'):
"""Method for wing parameters setting : design variables initial values and bounds
@param wing_param_name : wing parametrization names
"""
self.__set_wing_param_values(wing_param_name=wing_param_name)
self.__set_wing_param_bounds()
self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
self.__wing_param.build_airfoils_from_ref()
self.__wing_param.update()
if self.__display_wing_param:
self.__display_wing_param = False
print self.__wing_param
def __set_wing_param_values(self, wing_param_name='test_param'):
"""Method for wing parameters variables setting
@param wing_param_name : wing parametrization names
"""
self.__wing_param = Wing_param(wing_param_name,
geom_type='Broken', n_sect=self.N * 2)
self.__wing_param.build_wing()
for i in xrange(self.N):
self.__wing_param.set_value('rtwist%s' % i, 0.)
for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
self.__wing_param.set_value(param, getattr(self, param))
def __set_wing_param_bounds(self):
"""Method for desing variables bounds settings
Values are set to inf/-inf in DLLM component and their 'real' bounds
are defined when optimization problem is set
"""
for i in xrange(self.N):
self.__wing_param.convert_to_design_variable(
'rtwist%s' % i, (-float('inf'), float('inf')))
for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
self.__wing_param.convert_to_design_variable(param, (-float('inf'), float('inf')))
return
def __set_OC_values(self):
""" Set default operating conditions"""
self.OC.set_Mach(self.Mach)
self.OC.set_altitude(self.altitude)
self.OC.set_T0(self.T0)
self.OC.set_P0(self.P0)
self.OC.set_humidity(0.)
self.OC.compute_atmosphere()
def __update_wing_parame_values(self):
for dv_id in self.__wing_param.get_dv_id_list():
if dv_id.startswith('rtwist'):
i_twist = int(dv_id.replace('rtwist', ''))
self.__wing_param.set_value(dv_id, self.rtwist[i_twist])
else:
self.__wing_param.set_value(dv_id,getattr(self,dv_id))
self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
self.__set_wing_param_bounds()
self.__wing_param.build_airfoils_from_ref()
self.__wing_param.update()
return
def execute(self):
""" Perform a DLLM computation with the """
self.__update_wing_parame_values()
self.__set_OC_values()
self.__DLLM.set_target_Lift(self.Target_Lift)
self.__DLLM.run_direct()
self.__DLLM.run_post()
output = self.__DLLM.get_F_list()
for f, f_name in zip(output, self.__DLLM.get_F_list_names()):
setattr(self, f_name, f)
def list_deriv_vars(self):
"""specify the inputs and outputs where derivatives are defined
Specific treatment for twist : defined as rtwist0, rtwist1,... in DLLM
but as an array rtwist in openmdao component"""
out_dvid = []
for dv_id in self.__wing_param.get_dv_id_list():
if dv_id.startswith('rtwist0'):
out_dvid.append('rtwist')
elif not dv_id.startswith('rtwist'):
out_dvid.append(dv_id)
return tuple(out_dvid), tuple(self.__DLLM.get_F_list_names())
def provideJ(self):
"""Calculate the Jacobian according inputs and outputs"""
self.__DLLM.run_adjoint()
return np.array(self.__DLLM.get_dF_list_dchi())
def get_F_list(self):
return self.__DLLM.get_F_list()
def get_F_list_names(self):
return self.__DLLM.get_F_list_names()
def get_dv_array(self):
return self.__wing_param.get_dv_array()
def get_dv_id_list(self):
return self.__wing_param.get_dv_id_list()
def get_dv_info_list(self):
return self.__wing_param.get_dv_info_list()
def get_dv_value(self,dv_id):
return self.get_dv_array()[self.get_dv_id_list().index(dv_id)]