def generate_forces(alpha=0.,
elevator=0.,
thrust=0.,
dt=0.1,
case_name='hale_forces',
case_route='./',
**kwargs):
output_route = kwargs.get('output_route', './output/')
m = kwargs.get('M', 4)
rho = kwargs.get('rho', 1.225)
tolerance = kwargs.get('tolerance', 1e-5)
hale = aircraft.Hale(case_name, case_route, output_route)
hale.clean()
hale.init_structure(**kwargs)
hale.init_aero(m)
hale.set_flight_controls(thrust=thrust, elevator=elevator)
hale.generate()
settings = dict()
u_inf = kwargs.get('u_inf', 10)
settings['SHARPy'] = {
'case': case_name,
'route': case_route,
'flow': kwargs.get('flow', []),
'write_screen': 'on',
'write_log': 'on',
'log_folder': './output/',
'log_file': case_name + '.log'
}
settings['BeamLoader'] = {
'unsteady': 'on',
'orientation': algebra.euler2quat(np.array([0., alpha, 0.]))
}
settings['AerogridLoader'] = {
'unsteady': 'off',
'aligned_grid': 'on',
'mstar': int(kwargs.get('wake_length', 10) * m),
'control_surface_deflection': ['', ''],
'control_surface_deflection_generator_settings': {
'0': {},
'1': {}
},
'wake_shape_generator': 'StraightWake',
'wake_shape_generator_input': {
'u_inf': u_inf,
'u_inf_direction': [1., 0., 0.],
'dt': dt,
},
}
settings['NonLinearStatic'] = {
'print_info': 'off',
'max_iterations': 150,
'num_load_steps': 1,
'delta_curved': 1e-1,
'min_delta': tolerance,
'gravity_on': kwargs.get('gravity', 'on'),
'gravity': 10.6235,
'initial_position': [0., 0., 0.]
}
settings['StaticUvlm'] = {
'print_info': 'on',
'horseshoe': kwargs.get('horseshoe', 'off'),
'num_cores': 4,
'n_rollup': 0,
'rollup_dt': dt,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {
'u_inf': u_inf,
'u_inf_direction': [1., 0, 0]
},
'rho': rho
}
settings['StaticCoupled'] = {
'print_info': 'off',
'structural_solver': 'NonLinearStatic',
'structural_solver_settings': settings['NonLinearStatic'],
'aero_solver': 'StaticUvlm',
'aero_solver_settings': settings['StaticUvlm'],
'max_iter': 100,
'n_load_steps': kwargs.get('n_load_steps', 1),
'tolerance': kwargs.get('fsi_tolerance', 1e-5),
'relaxation_factor': kwargs.get('relaxation_factor', 0.2)
}
settings['StaticTrim'] = {
'solver': 'StaticCoupled',
'solver_settings': settings['StaticCoupled'],
'initial_alpha': alpha,
'initial_deflection': elevator,
'initial_thrust': thrust,
'fz_tolerance': 0.1,
'fx_tolerance': 0.1,
'm_tolerance': 0.1,
'save_info': 'on',
}
settings['BeamPlot'] = {'include_FoR': 'on'}
settings['AerogridPlot'] = {
'include_rbm': 'off',
'include_applied_forces': 'on',
'minus_m_star': 0,
'u_inf': u_inf
}
settings['AeroForcesCalculator'] = {
'write_text_file': 'on',
'text_file_name': 'aeroforces.txt',
'screen_output': 'on',
'coefficients': True,
'q_ref': 0.5 * rho * u_inf**2,
'S_ref': 2 * hale.structure.span_main * hale.aero.chord_main,
'b_ref': 2 * hale.structure.span_main
}
settings['SaveParametricCase'] = {
'save_case': 'off',
'parameters': {
'alpha': alpha
}
}
hale.create_settings(settings)
hale.run()
def generate_derivatives(alpha=0., elevator=0., thrust=0., dt=0.1, case_name='hale_static', case_route='./', **kwargs):
output_route = kwargs.get('output_route', './output/')
m = kwargs.get('M', 4)
rho = kwargs.get('rho', 1.225)
tolerance = kwargs.get('tolerance', 1e-5)
hale = aircraft.Hale(case_name, case_route, output_route)
hale.clean()
hale.init_structure(**kwargs)
hale.init_aero(m)
hale.set_flight_controls(thrust=thrust, elevator=elevator)
hale.generate()
settings = dict()
u_inf = kwargs.get('u_inf', 10)
settings['SHARPy'] = {'case': case_name,
'route': case_route,
'flow': kwargs.get('flow', []),
'write_screen': 'on',
'write_log': 'on',
'log_folder': './output/',
'log_file': case_name + '.log'}
settings['BeamLoader'] = {'unsteady': 'on',
'orientation': algebra.euler2quat(np.array([0.,
alpha,
0.]))}
settings['AerogridLoader'] = {'unsteady': 'on',
'aligned_grid': 'on',
'mstar': int(kwargs.get('wake_length', 10) * m),
'control_surface_deflection': ['', ''],
'control_surface_deflection_generator_settings':
{'0': {},
'1': {}},
'wake_shape_generator': 'StraightWake',
'wake_shape_generator_input': {
'u_inf': u_inf,
'u_inf_direction': [1., 0., 0.],
'dt': dt,
},
}
settings['NonLinearStatic'] = {'print_info': 'off',
'max_iterations': 150,
'num_load_steps': 1,
'delta_curved': 1e-1,
'min_delta': tolerance,
'gravity_on': kwargs.get('gravity', 'on'),
'gravity': 10.6235,
'initial_position': [0., 0., 0.]}
settings['StaticUvlm'] = {'print_info': 'on',
'horseshoe': kwargs.get('horseshoe', 'off'),
'num_cores': 4,
'n_rollup': 0,
'rollup_dt': dt,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {'u_inf': u_inf,
'u_inf_direction': [1., 0, 0]},
'rho': rho}
settings['StaticCoupled'] = {'print_info': 'off',
'structural_solver': 'NonLinearStatic',
'structural_solver_settings': settings['NonLinearStatic'],
'aero_solver': 'StaticUvlm',
'aero_solver_settings': settings['StaticUvlm'],
'max_iter': 100,
'n_load_steps': kwargs.get('n_load_steps', 1),
'tolerance': kwargs.get('fsi_tolerance', 1e-5),
'relaxation_factor': kwargs.get('relaxation_factor', 0.2)}
settings['StaticTrim'] = {'solver': 'StaticCoupled',
'solver_settings': settings['StaticCoupled'],
'initial_alpha': alpha,
'initial_deflection': elevator,
'initial_thrust': thrust,
'fz_tolerance': 0.1,
'fx_tolerance': 0.1,
'm_tolerance': 0.1,
'save_info': 'on',
}
settings['BeamPlot'] = {
'include_FoR': 'on'}
settings['AerogridPlot'] = {
'include_rbm': 'off',
'include_applied_forces': 'on',
'minus_m_star': 0,
'u_inf': u_inf
}
settings['AeroForcesCalculator'] = {
'write_text_file': 'on',
'text_file_name': 'aeroforces.txt',
'screen_output': 'on',
'coefficients': True,
'q_ref': 0.5 * rho * u_inf ** 2,
'S_ref': hale.structure.span_main * hale.aero.chord_main,
}
settings['BeamPlot'] = {
'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': tolerance,
'newmark_damp': 5e-3,
'gravity_on': kwargs.get('gravity', 'on'),
'gravity': 10.6235,
'num_steps': 1,
'dt': dt,
'initial_velocity': u_inf * 1}
step_uvlm_settings = {'print_info': 'on',
'num_cores': 4,
'convection_scheme': 2, #ws.wake_type,
'vortex_radius': 1e-6,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {'u_inf': u_inf * 0,
'u_inf_direction': [1., 0., 0.]},
'rho': rho,
'n_time_steps': 1,
'dt': 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': tolerance,
'relaxation_factor': 0.3,
'minimum_steps': 1,
'relaxation_steps': 150,
'final_relaxation_factor': 0.5,
'n_time_steps': 1, # ws.n_tstep,
'dt': dt,
'include_unsteady_force_contribution': 'off'}
# 'postprocessors': ['BeamPlot', 'AerogridPlot', 'WriteVariablesTime'],
# 'postprocessors_settings': {'BeamLoads': {'folder': output_route,
# 'csv_output': 'off'},
# 'BeamPlot': {'folder': output_route,
# 'include_rbm': 'on',
# 'include_applied_forces': 'on'},
# 'AerogridPlot': {
# 'u_inf': ws.u_inf,
# 'folder': output_route,
# 'include_rbm': 'on',
# 'include_applied_forces': 'on',
# 'minus_m_star': 0},
# 'WriteVariablesTime': {
# 'folder': output_route,
# 'cleanup_old_solution': 'on',
# 'delimiter': ',',
# 'FoR_variables': ['total_forces',
# 'total_gravity_forces',
# 'for_pos', 'quat'],
# }}}
settings['StabilityDerivatives'] = {
'u_inf': u_inf,
'c_ref': hale.aero.chord_main,
'b_ref': hale.structure.span_main * 2,
'S_ref': 2 * hale.structure.span_main * hale.aero.chord_main,
}
settings['Modal'] = {'print_info': True,
'use_undamped_modes': True,
'NumLambda': 50,
'rigid_body_modes': True,
'write_modes_vtk': 'on',
'print_matrices': 'on',
'save_data': 'on',
'continuous_eigenvalues': 'off',
'dt': dt,
'plot_eigenvalues': False,
'rigid_modes_ppal_axes': 'off',
'rigid_modes_cg': 'on',
}
# ROM settings
rom_settings = dict()
rom_settings['algorithm'] = 'mimo_rational_arnoldi'
rom_settings['r'] = 4
rom_settings['frequency'] = np.array([0], dtype=float)
rom_settings['single_side'] = 'observability'
settings['LinearAssembler'] = {'linear_system': 'LinearAeroelastic',
'linear_system_settings': {
'beam_settings': {'modal_projection': 'on',
'inout_coords': 'modes',
'discrete_time': 'off',
'newmark_damp': 0.5e-3,
'discr_method': 'newmark',
'dt': dt,
'proj_modes': 'undamped',
'use_euler': 'on',
'num_modes': 20,
'print_info': 'on',
'gravity': kwargs.get('gravity', 'on'),
'remove_dofs': [],
'remove_rigid_states': 'on'},
'aero_settings': {'dt': dt,
# 'ScalingDict': {'length': hale.aero.chord_main / 2,
# 'speed': u_inf,
# 'density': rho},
'integr_order': 2,
'density': rho,
'remove_predictor': 'off',
'use_sparse': False,
'vortex_radius': 1e-7,
'remove_inputs': ['u_gust'],
'convert_to_ct': 'on',
# 'rom_method': ['Krylov'],
# 'rom_method_settings': {'Krylov': rom_settings},
},
'track_body': 'off',
}}
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_route}
settings['FrequencyResponse'] = {'target_system': ['aeroelastic', 'aerodynamic', 'structural'],
'quick_plot': 'off',
'frequency_spacing': 'log',
'frequency_unit': 'w',
'frequency_bounds': [1e-3, 1e3],
'num_freqs': 200,
'print_info': 'on'}
settings['PickleData'] = {}
hale.create_settings(settings)
return hale