root.add('specific_fuel_consumption', IndepVarComp('SFC', SFC), promotes=['*'])
root.add('design_range', IndepVarComp('R', R), promotes=['*'])
# Independent variables that are optimization design variables
root.add('thicknesses', IndepVarComp('t', t_0), promotes=['*'])
root.add('local_chords', IndepVarComp('chords', chords_0), promotes=['*'])
root.add('local_sweep_angles', IndepVarComp('sweep', sweep_0), promotes=['*'])
root.add('wing_span', IndepVarComp('b', b_0), promotes=['*'])
root.add('wing_twist', IndepVarComp('theta', theta_0), promotes=['*'])
root.add('angle_of_attack', IndepVarComp('alpha', alpha_0), promotes=['*'])
root.add('airfoil_tc_ratio', IndepVarComp('tc', tc_0), promotes=['*'])
root.add('minimum_cabin_height', IndepVarComp('h_min', h_min), promotes=['*'])
root.add('minimum_cabin_area', IndepVarComp('area_min', area_min), promotes=['*'])
#Interpolation Components
root.add('interp_struct_morph', Interpolation(ns_all, na_unique_h, function = function_type, bias = bias_morph))
#Geometry and meshing Components
root.add('aerodynamic_mesher', PanairMesher(n_sec, na, na_unique, network_info, ref_airfoil_files), promotes=['camc','chords','tc','theta','x_le','y_le','z_le'])
root.add('aerodynamic_mesher_h', PanairMesher(n_sec, na_h, na_unique_h, network_info_h, ref_airfoil_files), promotes=['camc','chords','tc','theta','x_le','y_le','z_le','apoints_coord','apoints_coord_unique'])
root.add('structure_mesher', StructureMesher(na_unique_h, node_id, node_id_all), promotes=['*'])
root.add('x_leading_edge', XLeadingEdge(n_sec), promotes=['*'])
root.add('y_leading_edge', ExecComp(
'y_le = b/b_baseline*y_le_baseline', y_le=np.zeros(len(y_le_baseline), dtype=float), y_le_baseline=np.zeros(len(y_le_baseline), dtype=float)), promotes=['*'])
#Planform area
root.add('reference_surface',
ExecComp('Sw = 2.*area_segment.sum()', area_segment=np.zeros(n_sec-1, dtype=float)), promotes=['*'])
#Total wet surface
root.add('wing_span', IndepVarComp('b', b), promotes=['*'])
root.add('t_max', IndepVarComp('t_i_max', t_i_max), promotes=['*'])
root.add('t_min', IndepVarComp('t_i_min', t_i_min), promotes=['*'])
root.add('wing_chord', IndepVarComp('c', c), promotes=['*'])
root.add('s_coord', IndepVarComp('node_coord', node_coord), promotes=['*'])
root.add('s_coord_all',
IndepVarComp('node_coord_all', node_coord_all),
promotes=['*'])
root.add('thicknesses', IndepVarComp('t', t), promotes=['*'])
# root.add('masses', IndepVarComp('m', m), promotes=['*'])
root.add('a_coord',
IndepVarComp('apoints_coord', apoints_coord),
promotes=['*'])
root.add('inter',
Interpolation(na, ns, function=function_type, bias=bias),
promotes=['*'])
# root.add('agrr', Aggregation(n_stress,p,function), promotes=['*'])
mda = Group()
#Add disciplines to the group
mda.add('displacement_transfer',
DisplacementTransfer(na, ns),
promotes=['*'])
mda.add('aerodynamics', Panair(na, network_info), promotes=['*'])
mda.add('load_transfer', LoadTransfer(na, ns), promotes=['*'])
mda.add('structures',
NastranStatic(node_id, node_id_all, n_stress, tn, mn),
promotes=['*'])
#Add disciplines to the high-fidelity group CHECK INPUTS
mda_h.add('mult_filter', Filter(ns, fidelity))
mda_h.add('displacement_transfer_h', DisplacementTransfer(na_h, ns))
mda_h.add(
'aerodynamics_h',
Panair(na_h,
network_info_h,
case_name_h,
aero_template_h,
sym_plane_index=sym_plane_index))
mda_h.add('load_transfer_h', LoadTransfer(na_h, ns))
mda_h.add(
'structures_h',
NastranStatic(node_id, node_id_all, n_stress, tn, mn, sn, case_name_h))
mda_l.add('inter', Interpolation(na, ns, function=function_type,
bias=bias))
mda_h.add('inter_h',
Interpolation(na_h, ns, function=function_type, bias=bias))
#Define solver type and tolerance for MDA Lo-Fi
mda_l.nl_solver = NLGaussSeidel()
#The solver execution limit is used to control fidelity levels
if fidelity == 'high':
mda_l.nl_solver.options['maxiter'] = 0 #No Lo-Fi iterations
elif fidelity == 'multi':
mda_l.nl_solver.options[
'maxiter'] = it_l #Adds the limit for the execution of the MDA Solver
mda_l.nl_solver.options['rutol'] = 1.e-2
mda_l.nl_solver.options['use_aitken'] = True
mda_l.nl_solver.options['aitken_alpha_min'] = 0.1
root.add('root_chord', IndepVarComp('cr', cr), promotes=['*'])
root.add('break_chord', IndepVarComp('cb', cb), promotes=['*'])
root.add('tip_chord', IndepVarComp('ct', ct), promotes=['*'])
root.add('sweep_angle', IndepVarComp('sweep', sweep), promotes=['*'])
root.add('root_leading_edge_x', IndepVarComp('xr', xr), promotes=['*'])
root.add('baseline_wing_span',
IndepVarComp('b_baseline', b_baseline),
promotes=['*'])
# Independent variables that are optimization design variables
root.add('wing_span', IndepVarComp('b', b_0), promotes=['*'])
#Interpolation Components
root.add(
'interp_struct_morph',
Interpolation(ns_all,
ngeom_unique,
function=function_type,
bias=bias_morph))
root.add(
'interp_aero_hifi_morph',
Interpolation(na_h,
ngeom_unique,
function=function_type,
bias=bias_morph))
#Geometry and meshing Components
root.add('planform_geometry',
PlanformGeometry(n_sec, b_sec),
promotes=['*'])
root.add('surface_generator',
SurfaceGenerator(n_sec, ngeom, ngeom_unique, network_info_h,
ref_airfoil_file),
root.add('break_chord', IndepVarComp('cb', cb_0), promotes=['*'])
root.add('tip_chord', IndepVarComp('ct', ct_0), promotes=['*'])
root.add('sweep_angle', IndepVarComp('sweep', sweep_0), promotes=['*'])
root.add('wing_span', IndepVarComp('b', b_0), promotes=['*'])
root.add('angle_of_attack', IndepVarComp('alpha', alpha_0), promotes=['*'])
root.add('thicknesses', IndepVarComp('t', t), promotes=['*'])
if an > 0:
root.add('rod_sections', IndepVarComp('a', a), promotes=['*'])
root.add('bar_sections', IndepVarComp('s', s), promotes=['*'])
root.add('first_moment_inertia', IndepVarComp('Ix', Ix), promotes=['*'])
root.add('second_moment_inertia', IndepVarComp('Iy', Iy), promotes=['*'])
#Interpolation Components
root.add('interp_struct_morph', Interpolation(ns_all, na_unique, function = function_type, bias = bias_morph))
root.add('interp_mda', Interpolation(na, ns, function = function_type, bias = bias_inter), promotes=['*'])
#Geometry and meshing Components
root.add('planform_geometry', PlanformGeometry(n_sec, b_sec), promotes=['*'])
root.add('aerodynamic_mesher', PanairMesher(n_sec, na, na_unique, network_info, ref_airfoil_file), promotes=['*'])
root.add('structure_mesher', StructureMesher(na_unique, node_id, node_id_all), promotes=['*'])
root.add('y_leading_edge', ExecComp(
'y_le = b/b_baseline*y_le_baseline', y_le=np.zeros(len(y_le_baseline), dtype=float), y_le_baseline=np.zeros(len(y_le_baseline), dtype=float)), promotes=['*'])
root.add('tc_ratio', ExecComp(
'tc = th/chords', tc=np.zeros(n_sec, dtype=float), th=np.zeros(n_sec, dtype=float), chords=np.zeros(n_sec, dtype=float)), promotes=['*'])
#Explicit connections
root.connect('interp_struct_morph.H', 'G')
root.add('angle_of_attack', IndepVarComp('alpha', alpha), promotes=['*'])
root.add('wing_span', IndepVarComp('b', b), promotes=['*'])
root.add('wing_chord', IndepVarComp('c', c), promotes=['*'])
root.add('s_coord', IndepVarComp('node_coord', node_coord), promotes=['*'])
root.add('s_coord_all', IndepVarComp('node_coord_all', node_coord_all), promotes=['*'])
root.add('a_coord', IndepVarComp('apoints_coord', apoints_coord), promotes=['*'])
root.add('load_factor', IndepVarComp('n', n), promotes=['*'])
root.add('thicknesses', IndepVarComp('t', t), promotes=['*'])
if an > 0:
root.add('rod_sections', IndepVarComp('a', a), promotes=['*'])
root.add('bar_sections', IndepVarComp('s', s), promotes=['*'])
root.add('first_moment_inertia', IndepVarComp('Ix', Ix), promotes=['*'])
root.add('second_moment_inertia', IndepVarComp('Iy', Iy), promotes=['*'])
root.add('inter', Interpolation(na, ns, function = function_type, bias = bias), promotes=['*'])
mda = Group()
#Add disciplines to the group
mda.add('displacement_transfer', DisplacementTransfer(na, ns), promotes=['*'])
mda.add('aerodynamics', Panair(na, network_info, case_name, sym_plane_index), promotes=['*'])
mda.add('load_transfer', LoadTransfer(na, ns), promotes=['*'])
mda.add('structures', NastranStatic(node_id, node_id_all, n_stress, tn, mn, sn, an, case_name), promotes=['*'])
#Define solver type and tolerance for MDA
mda.nl_solver = NLGaussSeidel()
# mda.nl_solver.options['maxiter'] = 0
mda.nl_solver.options['rutol'] = 1.e-2 #2 origin
mda.nl_solver.options['use_aitken'] = True
mda.nl_solver.options['aitken_alpha_min'] = 0.1