import sys
sys.path.append('/home/ng213/code/sharpy/')
# sys.path.append('/Users/Norberto/code/sharpy/')
from cases.hangar.richards_wing import Baseline
import sharpy.sharpy_main
ws = Baseline(M=4,
N=11,
Mstarfactor=5,
u_inf=28,
rho=1.02,
alpha_deg=7.7563783342984385-4,
cs_deflection_deg=-6.733360628875144*0,
thrust=10.140622253017584)
ws.set_properties()
ws.initialise()
# ws.sweep_LE = 0
ws.clean_test_files()
ws.update_mass_stiffness(sigma=0.5, sigma_mass=1.5)
ws.update_fem_prop()
ws.generate_fem_file()
ws.update_aero_properties()
ws.generate_aero_file()
ws.set_default_config_dict()
ws.config['SHARPy']['flow'] = ['BeamLoader',
'AerogridLoader',
'StaticCoupled',
# 'StaticTrim',
'Modal',
def generate_horten(u_inf, output_folder):
M = 6
N = 11
Msf = 5
rho_fact = 1.
track_body = True
payload = 0
u_inf = u_inf
output_folder = output_folder
use_euler = True
if use_euler:
orient = 'euler'
else:
orient = 'quat'
case_rmks = 'M%gN%gMsf%g_u%g' % (M, N, Msf, u_inf)
# M4N11Msf5
alpha_deg = 3.135
cs_deflection = 0.2514
thrust = 5.118
# M8N11Msf5
# alpha_deg = 4.5162
# cs_deflection = 0.2373
# thrust = 5.5129
# ROM settings
rom_settings = dict()
rom_settings['algorithm'] = 'mimo_rational_arnoldi'
rom_settings['r'] = 5
rom_settings['frequency'] = np.array([0], dtype=float)
rom_settings['single_side'] = 'observability'
case_rmks += 'rom_%g_%s' % (rom_settings['r'],
rom_settings['single_side'][:3])
ws = Baseline(
M=M,
N=N,
Mstarfactor=Msf,
u_inf=u_inf,
rho=1.02,
alpha_deg=alpha_deg, # 7.7563783342984385,
roll_deg=0,
cs_deflection_deg=cs_deflection, # -6.733360628875144,
thrust=thrust, # 10.140622253017584,
physical_time=20,
case_name='horten_s05',
case_name_format=4,
case_remarks=case_rmks)
ws.set_properties()
ws.initialise()
# ws.sweep_LE = 0*np.pi/180
# ws.n_tstep = 2
ws.clean_test_files()
ws.tolerance = 1e-6
ws.fsi_tolerance = 1e-6
# ws.update_mass_stiffness(sigma=1., sigma_mass=1.5)
ws.update_mass_stiffness(sigma=.5, sigma_mass=1.0, payload=payload)
ws.update_fem_prop()
ws.generate_fem_file()
ws.update_aero_properties()
ws.generate_aero_file()
flow = [
'BeamLoader',
'AerogridLoader',
# 'StaticUvlm',
# 'StaticCoupled',
'StaticTrim',
'BeamPlot',
'AerogridPlot',
'AeroForcesCalculator',
'DynamicCoupled',
'Modal',
'LinearAssembler',
# 'LinDynamicSim',
# 'SaveData',
'AsymptoticStability',
'FrequencyResponse',
# 'StabilityDerivatives',
# 'LinDynamicSim',
'PickleData',
'SaveParametricCase',
'SaveStateSpace'
]
settings = dict()
settings['SHARPy'] = {
'case': ws.case_name,
'route': ws.case_route,
'flow': flow,
'write_screen': 'on',
'write_log': 'on',
'log_folder': output_folder + ws.case_name + '/',
'log_file': ws.case_name + '.log'
}
settings['BeamLoader'] = {
'unsteady': 'off',
'orientation':
algebra.euler2quat(np.array([ws.roll, ws.alpha, ws.beta]))
}
settings['AerogridLoader'] = {
'unsteady': 'off',
'aligned_grid': 'on',
'mstar': int(ws.M * ws.Mstarfactor),
'freestream_dir': ['1', '0', '0'],
'control_surface_deflection': [''],
'wake_shape_generator': 'StraightWake',
'wake_shape_generator_input': {
'u_inf': u_inf,
'u_inf_direction': [1., 0., 0.],
'dt': ws.dt
},
}
if ws.horseshoe is True:
settings['AerogridLoader']['mstar'] = 1
settings['StaticCoupled'] = {
'print_info': 'off',
'structural_solver': 'NonLinearStatic',
'structural_solver_settings': {
'print_info': 'off',
'max_iterations': 200,
'num_load_steps': 1,
'delta_curved': 1e-5,
'min_delta': ws.tolerance,
'gravity_on': 'on',
'gravity': 9.81
},
'aero_solver': 'StaticUvlm',
'aero_solver_settings': {
'print_info': 'off',
'horseshoe': ws.horseshoe,
'num_cores': 4,
'n_rollup': int(0),
'vortex_radius': 1e-6,
'rollup_dt': ws.dt,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {
'u_inf': ws.u_inf,
'u_inf_direction': [1., 0, 0]
},
'rho': ws.rho
},
'max_iter': 200,
'n_load_steps': 2,
'tolerance': ws.tolerance,
'relaxation_factor': 0.1
}
settings['StaticTrim'] = {
'solver': 'StaticCoupled',
'solver_settings': settings['StaticCoupled'],
'thrust_nodes': ws.thrust_nodes,
'initial_alpha': ws.alpha,
'initial_deflection': ws.cs_deflection,
'initial_thrust': ws.thrust,
'max_iter': 50,
'fz_tolerance': 1e-2,
'fx_tolerance': 1e-2,
'm_tolerance': 1e-2,
'save_info': 'off',
'folder': output_folder
}
settings['AerogridPlot'] = {
'folder': output_folder,
'include_rbm': 'off',
'include_applied_forces': 'on',
'minus_m_star': 0,
'u_inf': ws.u_inf
}
settings['AeroForcesCalculator'] = {
'folder': output_folder,
'write_text_file': 'on',
'text_file_name': 'aeroforces.csv',
'screen_output': 'on',
'unsteady': 'off',
'coefficients': True,
'q_ref': 0.5 * ws.rho * ws.u_inf**2,
'S_ref': 12.809,
}
settings['BeamPlot'] = {
'folder': output_folder,
'include_rbm': 'on',
'include_applied_forces': 'on',
'include_FoR': 'on'
}
struct_solver_settings = {
'print_info': 'off',
'initial_velocity_direction': [-1., 0., 0.],
'max_iterations': 950,
'delta_curved': 1e-6,
'min_delta': ws.tolerance,
'newmark_damp': 5e-3,
'gravity_on': True,
'gravity': 9.81,
'num_steps': ws.n_tstep,
'dt': ws.dt,
'initial_velocity': ws.u_inf * 1
}
step_uvlm_settings = {
'print_info': 'on',
'horseshoe': ws.horseshoe,
'num_cores': 4,
'n_rollup': 1,
'convection_scheme': ws.wake_type,
'rollup_dt': ws.dt,
'vortex_radius': 1e-6,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {
'u_inf': ws.u_inf * 0,
'u_inf_direction': [1., 0., 0.]
},
'rho': ws.rho,
'n_time_steps': ws.n_tstep,
'dt': ws.dt,
'gamma_dot_filtering': 3
}
settings['DynamicCoupled'] = {
'print_info': 'on',
# 'structural_substeps': 1,
# 'dynamic_relaxation': 'on',
# 'clean_up_previous_solution': 'on',
'structural_solver': 'NonLinearDynamicCoupledStep',
'structural_solver_settings': struct_solver_settings,
'aero_solver': 'StepUvlm',
'aero_solver_settings': step_uvlm_settings,
'fsi_substeps': 200,
'fsi_tolerance': ws.fsi_tolerance,
'relaxation_factor': ws.relaxation_factor,
'minimum_steps': 1,
'relaxation_steps': 150,
'final_relaxation_factor': 0.5,
'n_time_steps': 1, # ws.n_tstep,
'dt': ws.dt,
'include_unsteady_force_contribution': 'off',
'postprocessors': ['BeamPlot', 'AerogridPlot', 'WriteVariablesTime'],
'postprocessors_settings': {
'BeamLoads': {
'folder': output_folder,
'csv_output': 'off'
},
'BeamPlot': {
'folder': output_folder,
'include_rbm': 'on',
'include_applied_forces': 'on'
},
'AerogridPlot': {
'u_inf': ws.u_inf,
'folder': output_folder,
'include_rbm': 'on',
'include_applied_forces': 'on',
'minus_m_star': 0
},
'WriteVariablesTime': {
'folder':
output_folder,
'cleanup_old_solution':
'on',
'delimiter':
',',
'FoR_variables':
['total_forces', 'total_gravity_forces', 'for_pos', 'quat'],
}
}
}
settings['Modal'] = {
'print_info': True,
'use_undamped_modes': True,
'NumLambda': 30,
'rigid_body_modes': True,
'write_modes_vtk': 'on',
'print_matrices': 'on',
'write_data': 'on',
'continuous_eigenvalues': 'off',
'dt': ws.dt,
'plot_eigenvalues': False,
'rigid_modes_cg': 'off',
'folder': output_folder
}
settings['LinearAssembler'] = {
'linear_system': 'LinearAeroelastic',
'linear_system_settings': {
'beam_settings': {
'modal_projection': 'on',
'inout_coords': 'modes',
'discrete_time': True,
'newmark_damp': 0.5e-3,
'discr_method': 'newmark',
'dt': ws.dt,
'proj_modes': 'undamped',
'use_euler': use_euler,
'num_modes': 20,
'print_info': 'on',
'gravity': 'on',
'remove_dofs': []
},
'aero_settings': {
'dt': ws.dt,
# 'ScalingDict': {'length': ws.c_root,
# 'speed': ws.u_inf,
# 'density': ws.rho},
'integr_order': 2,
'density': ws.rho * rho_fact,
'remove_predictor': False,
'use_sparse': False,
'rigid_body_motion': True,
'use_euler': use_euler,
'vortex_radius': 1e-6,
'remove_inputs': ['u_gust'],
'rom_method': ['Krylov'],
'rom_method_settings': {
'Krylov': rom_settings
}
},
'rigid_body_motion': True,
'track_body': track_body,
'use_euler': use_euler,
'linearisation_tstep': -1
}
}
settings['AsymptoticStability'] = {
'print_info': 'on',
'modes_to_plot': [],
# 'velocity_analysis': [27, 29, 3],
'display_root_locus': 'off',
'frequency_cutoff': 0,
'export_eigenvalues': 'on',
'num_evals': 1000,
'target_system': ['aeroelastic', 'aerodynamic', 'structural'],
'folder': output_folder
}
settings['FrequencyResponse'] = {
'print_info': 'on',
'folder': output_folder,
'compute_fom': 'on',
'frequency_bounds': [0.1, 100],
'frequency_spacing': 'log',
'target_system': ['aeroelastic', 'aerodynamic', 'structural'],
'num_freqs': 200,
'compute_hinf': 'on'
}
settings['LinDynamicSim'] = {
'dt': ws.dt,
'n_tsteps': ws.n_tstep,
'sys_id': 'LinearAeroelastic',
# 'reference_velocity': ws.u_inf,
'write_dat': ['x', 'y', 't', 'u'],
# 'write_dat': 'on',
'postprocessors': ['BeamPlot', 'AerogridPlot'],
'postprocessors_settings': {
'AerogridPlot': {
'u_inf': ws.u_inf,
'folder': './output',
'include_rbm': 'on',
'include_applied_forces': 'on',
'minus_m_star': 0
},
'BeamPlot': {
'folder': output_folder,
'include_rbm': 'on',
'include_applied_forces': 'on'
}
}
}
settings['StabilityDerivatives'] = {
'u_inf': ws.u_inf,
'S_ref': 12.809,
'b_ref': ws.span,
'c_ref': 0.719
}
settings['SaveData'] = {
'folder': output_folder,
'save_aero': 'off',
'save_struct': 'off',
'save_linear': 'on',
'save_linear_uvlm': 'on'
}
settings['PickleData'] = {'folder': output_folder + ws.case_name + '/'}
settings['SaveParametricCase'] = {
'folder': output_folder + ws.case_name + '/',
'parameters': {
'u_inf': u_inf
}
}
settings['SaveStateSpace'] = {
'folder': output_folder,
'target_system': ['aeroelastic', 'aerodynamic', 'structural']
}
config = configobj.ConfigObj()
file_name = ws.case_route + '/' + ws.case_name + '.solver.txt'
config.filename = file_name
for k, v in settings.items():
config[k] = v
config.write()
delta = np.zeros((ws.n_tstep, 1))
delta_dot = np.zeros_like(delta)
d_elev = 1 * np.pi / 180 * 0.01
t_init = 1.0
t_ramp = 2.0
t_final = 5.0
delta[int(t_init // ws.dt):(int(t_ramp // ws.dt)),
0] = np.linspace(0, d_elev,
(int(t_ramp // ws.dt)) - int(t_init // ws.dt))
delta[int(t_ramp // ws.dt):(int(t_final // ws.dt)), 0] = d_elev
delta[int(t_final // ws.dt):(int((t_final + 1.0) // ws.dt)),
0] = np.linspace(d_elev, 0, (int(
(t_final + 1) // ws.dt)) - int(t_final // ws.dt))
delta_dot[int(t_init // ws.dt):int(t_ramp // ws.dt),
0] = d_elev / (t_ramp - t_init) * 1
delta_dot[int(t_final // ws.dt):(int((t_final + 1.0) // ws.dt)),
0] = -d_elev / 1. * 1
ws.create_linear_simulation(delta, delta_dot)
data = sharpy.sharpy_main.main(
['', ws.case_route + '/' + ws.case_name + '.solver.txt'])