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xbeam/sharpy load ramping in nonlinearstatic solver #191

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xbeam/sharpy load ramping in nonlinearstatic solver #191

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a40ecab
added minguet test case for xbeam validation
ACea15 Feb 13, 2022
5b58772
copied models_generator from dev_rhea
ACea15 Feb 13, 2022
e6c9fa9
copied /routines & /utils/stochastic from dev_rhea_linear
ACea15 Feb 13, 2022
0fdeb35
update gen_main to take the new routines framework based on classes
ACea15 Feb 10, 2022
a818ca0
rename minguet generation file so it doesnt run with tests
ACea15 Feb 14, 2022
3e019d3
adding labels to results plot
ACea15 Feb 14, 2022
32e305b
updated nonlinearstatic and dependencies to accept optional load ramp…
kccwing Apr 27, 2022
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128 changes: 128 additions & 0 deletions cases/models_generator/examples/#goland_wing.py#
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import numpy as np
import os
import sys
import importlib
import cases.models_generator.gen_main as gm
import sharpy.utils.algebra as algebra
importlib.reload(gm)
from functools import partial

#############################
# Read goland wing from docs #
#############################
split_path = [sys.path[i].split('/') for i in [0,1,2]]
for i in range(len(split_path)):
if 'sharpy' in split_path[i]:
ind = i
break

sharpy_dir = sys.path[ind]
# path2goland = sharpy_dir + '/docs/source/content/example_notebooks/cases'
# goland_files = os.listdir(path2goland)
# for i in goland_files:
# if 'goland' in i and 'sharpy' in i:
# goland_sharpy = i
# elif 'goland' in i and 'fem' in i:
# goland_fem = i
# elif 'goland' in i and 'aero' in i:
# goland_aero = i

# goland = gm.Sharpy_data(['read_structure','read_aero','simulation'])
# goland.read_structure(path2goland+'/'+goland_fem)
# goland.read_aero(path2goland+'/'+goland_aero)
# goland.read_sim(path2goland+'/'+goland_sharpy)

# aeroelasticity parameters
main_ea = 0.33
main_cg = 0.43
sigma = 1
c_ref = 1.8288
ea, ga = 1e9, 1e9
gj = 0.987581e6
eiy = 9.77221e6
eiz = 1e2 * eiy
base_stiffness = np.diag([ea, ga, ga, sigma * gj, sigma * eiy, eiz])
stiffness = np.zeros((1, 6, 6))
stiffness[0] = base_stiffness
m_unit = 35.71
j_tors = 8.64
pos_cg_b = np.array([0., c_ref * (main_cg - main_ea), 0.])
m_chi_cg = algebra.skew(m_unit * pos_cg_b)
mass = np.zeros((1, 6, 6))
mass[0, :, :] = np.diag([m_unit, m_unit, m_unit,
j_tors, .1 * j_tors, .9 * j_tors])
mass[0, :3, 3:] = m_chi_cg
mass[0, 3:, :3] = -m_chi_cg
# goland.fem['stiffness_db'] = stiffness
# goland.fem['mass_db'] = mass
# goland.aero['elastic_axis']
# .
# .
# .

g1c = dict()
g1c['workflow'] = ['create_structure','create_aero']
g1c['geometry'] = {'length':6.096,
'num_node':9,
'direction':None,
'node0':[0., 0., 0.],
'sweep':0.,
'dihedral':0.}
g1c['fem'] = {'stiffness_db':stiffness,
'mass_db':mass,
'frame_of_reference_delta':[-1.,0.,0.]}
g1c['aero'] = {'chord':c_ref,
'elastic_axis':main_ea,
'surface_m':8}

comp1 = gm.Components('wing1','sharpy',['sharpy'],g1c)
g1cm = {'wing1':g1c}
g1mm = {'model_name':'goland_b',
'model_route':'/mnt/work/Programs/runs/goland_wing',#sharpy_dir+'/cases/models_generator/examples/goland_wing',
'iterate_type': 'Full_Factorial',
'iterate_vars': {'wing1*geometry-sweep':np.linspace(15.5*np.pi/180,19.5*np.pi/180,5), #np.linspace(15*np.pi/180,20*np.pi/180,6)
'wing1*geometry-length':6.096*np.linspace(1.025,1.275,6), #6.096*np.linspace(1,1.3,7)
'wing1*aero-chord':c_ref*np.array([np.linspace(1.,1.,2),np.linspace(0.9,0.95,2)]).T},
#c_ref*np.array([np.linspace(1.,1.,3),np.linspace(0.85,1.,3)]).T}
'iterate_labels': {'label_type':'number',
'print_name_var':0}}

g1sm = {'sharpy': {'simulation_input':None,
'default_module':'sharpy.routines.flutter',
'default_solution':'sol_145',
'default_solution_vars': {'panels_wake':8*5,
'num_modes':5,
'rho':1.02,
'u_inf':0.01,
'c_ref':1.8288,
'folder':'./runs',
'velocity_analysis':[70,220,150],
'rom_algorithm':'mimo_rational_arnoldi',
'rom_size':6,
'flow':['BeamLoader',
'AerogridLoader',
'StaticCoupled',
'AerogridPlot',
'Modal',
'LinearAssembler',
'AsymptoticStability',
'PickleData'],
'AerogridPlot':{'folder':'./runs',
'include_rbm': 'off',
'include_applied_forces': 'off',
'minus_m_star': 0},
'PickleData': {'folder':'./runs'},
'LinearAssembler':{'linear_system_settings':{'aero_settings':{'use_sparse':False,
'rom_method':[],
'rom_method_settings':{'Balanced':{'algorithm':'FrequencyLimited'}}},
'beam_settings':{'modal_projection': 'off',
'inout_coords': 'nodes'}},
'inout_coordinates':'nodes'}},
'default_sharpy':{},
'model_route':None}}

g1 = gm.Model('sharpy',['sharpy'], model_dict=g1mm, components_dict=g1cm,
simulation_dict=g1sm)

g1.run()

130 changes: 130 additions & 0 deletions cases/models_generator/examples/a320wing.py
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import numpy as np
import os
import sys
import pdb
import importlib
import cases.models_generator.gen_main as gm
from cases.models_generator.gen_utils import node2aero, get_chord
import sharpy.utils.algebra as algebra
importlib.reload(gm)

split_path = [sys.path[i].split('/') for i in range(len(sys.path))]
for i in range(len(split_path)):
if 'sharpy' in split_path[i]:
ind = i
break
sharpy_dir = sys.path[ind]
# aeroelasticity parameters
main_ea = 0.33
main_cg = 0.43
sigma = 1

# other
c_ref = 1.8288

ea, ga = 1e9, 1e9
gj = 0.987581e6
eiy = 9.77221e6
eiz = 1e2 * eiy
base_stiffness = np.diag([ea, ga, ga, sigma * gj, sigma * eiy, eiz])
stiffness1 = np.zeros((1, 6, 6))
stiffness1[0] = base_stiffness
m_unit = 35.71
j_tors = 8.64
pos_cg_b = np.array([0., c_ref * (main_cg - main_ea), 0.])
m_chi_cg = algebra.skew(m_unit * pos_cg_b)
mass1 = np.zeros((1, 6, 6))
mass1[0, :, :] = np.diag([m_unit, m_unit, m_unit,
j_tors, .1 * j_tors, .9 * j_tors])
mass1[0, :3, 3:] = m_chi_cg
mass1[0, 3:, :3] = -m_chi_cg

stiffness2 = stiffness1*0.9
mass2 = mass1*0.9

chord01 = 6.5
ea01 = 0.4
sweep1 = np.pi/180*20
num_node1 = 7
lenght1 = 6.
dl1 = lenght1/num_node1
ledge01 = np.array([-chord01*ea01,0.,0.])
ledge1 = [np.array([dl1*i*np.sin(sweep1), dl1*i*np.cos(sweep1), 0.]) for i in range(num_node1)]
ledge1 = np.array(ledge1) + ledge01
beam1 = [np.array([dl1*i*np.sin(sweep1), dl1*i*np.cos(sweep1), 0.]) for i in range(num_node1)]
beam1 = np.array(beam1)
tedge1 = [np.array([(1.-ea01)*chord01, dl1*i*np.cos(sweep1), 0.]) for i in range(num_node1)]
tedge1 = np.array(tedge1)
ea1, chord1 = get_chord(ledge1, tedge1, beam1)
ea1, chord1 = node2aero(ea1,chord1)
g1c = dict()

g1c['wing_r1'] = {'workflow':['create_structure', 'create_aero'],
'fem': {'stiffness_db':stiffness1,
'mass_db':mass1,
'coordinates':beam1,
'frame_of_reference_delta':[-1, 0., 0.]},
'aero': {'chord':chord1,
'elastic_axis':ea1,
'surface_m':8}
}
g1c['wing_r2'] = {'workflow':['create_structure', 'create_aero'],
'geometry': {'length':14.,
'num_node':15,
'direction':None,
'node0':[0., 0., 0.],
'sweep':sweep1,
'dihedral':0.},
'fem': {'stiffness_db':stiffness2,
'mass_db':mass2,
'frame_of_reference_delta':[-1, 0., 0.]},
'aero': {'chord':[chord1[-1,1],1.6],
'elastic_axis':ea1[-1,1],
'surface_m':8}
}

g1c['wing_l1'] = {'symmetric': {'component':'wing_r1'}}
g1c['wing_l2'] = {'symmetric': {'component':'wing_r2'}}

g1mm = {'model_name':'A320mock',
'model_route':sharpy_dir+'/cases/models_generator/examples/wing_plantform',
'iterate_type': 'DoE', # Full_Factorial
'iterate_vars': {'wing_r2*geometry-sweep':np.linspace(sweep1,sweep1*1.5,2),
'wing_r2*geometry-length':np.linspace(14,18.,2)},
'iterate_labels': {'label_type':'number',
'print_name_var':0},
'assembly': {'include_aero':1,
'default_settings': 1, #beam_number and aero surface and
#surface_distribution
#selected by default one
#per component
'wing_r1':{'upstream_component':'',
'node_in_upstream':0},
'wing_r2':{'boundary_connection':0,
'upstream_component':'wing_r1',
'node_in_upstream':num_node1-1},
'wing_l1':{'upstream_component':'wing_r1',
'node_in_upstream':0},
'wing_l2':{'boundary_connection':0,
'upstream_component':'wing_l1',
'node_in_upstream':num_node1-1},
}
}

g1sm = {'sharpy': {'simulation_input':None,
'default_module':'sharpy.routines.roms',
'default_solution':'sol_500',
'default_solution_vars': {'panels_wake':8*3,
'num_modes':20,
'rho': 1.225,
'u_inf':1.,
'c_ref':3
},
'default_sharpy':{},
'model_route':None}}

g1 = gm.Model('sharpy',['sharpy'], model_dict=g1mm, components_dict=g1c,
simulation_dict=g1sm)
#g1.build()
g1.run()

127 changes: 127 additions & 0 deletions cases/models_generator/examples/goland_wing.py
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import numpy as np
import os
import sys
import importlib
import cases.models_generator.gen_main as gm
import sharpy.utils.algebra as algebra
importlib.reload(gm)
from functools import partial

#############################
# Read goland wing from docs #
#############################
split_path = [sys.path[i].split('/') for i in [0,1,2]]
for i in range(len(split_path)):
if 'sharpy' in split_path[i]:
ind = i
break

sharpy_dir = sys.path[ind]
# path2goland = sharpy_dir + '/docs/source/content/example_notebooks/cases'
# goland_files = os.listdir(path2goland)
# for i in goland_files:
# if 'goland' in i and 'sharpy' in i:
# goland_sharpy = i
# elif 'goland' in i and 'fem' in i:
# goland_fem = i
# elif 'goland' in i and 'aero' in i:
# goland_aero = i

# goland = gm.Sharpy_data(['read_structure','read_aero','simulation'])
# goland.read_structure(path2goland+'/'+goland_fem)
# goland.read_aero(path2goland+'/'+goland_aero)
# goland.read_sim(path2goland+'/'+goland_sharpy)

# aeroelasticity parameters
main_ea = 0.33
main_cg = 0.43
sigma = 1
c_ref = 1.8288
ea, ga = 1e9, 1e9
gj = 0.987581e6
eiy = 9.77221e6
eiz = 1e2 * eiy
base_stiffness = np.diag([ea, ga, ga, sigma * gj, sigma * eiy, eiz])
stiffness = np.zeros((1, 6, 6))
stiffness[0] = base_stiffness
m_unit = 35.71
j_tors = 8.64
pos_cg_b = np.array([0., c_ref * (main_cg - main_ea), 0.])
m_chi_cg = algebra.skew(m_unit * pos_cg_b)
mass = np.zeros((1, 6, 6))
mass[0, :, :] = np.diag([m_unit, m_unit, m_unit,
j_tors, .1 * j_tors, .9 * j_tors])
mass[0, :3, 3:] = m_chi_cg
mass[0, 3:, :3] = -m_chi_cg
# goland.fem['stiffness_db'] = stiffness
# goland.fem['mass_db'] = mass
# goland.aero['elastic_axis']
# .
# .
# .

g1c = dict()
g1c['workflow'] = ['create_structure','create_aero']
g1c['geometry'] = {'length':6.096,
'num_node':9,
'direction':None,
'node0':[0., 0., 0.],
'sweep':0.,
'dihedral':0.}
g1c['fem'] = {'stiffness_db':stiffness,
'mass_db':mass,
'frame_of_reference_delta':[-1.,0.,0.]}
g1c['aero'] = {'chord':c_ref,
'elastic_axis':main_ea,
'surface_m':8}

comp1 = gm.Components('wing1','sharpy',['sharpy'],g1c)
g1cm = {'wing1':g1c}
g1mm = {'model_name':'goland_b',
'model_route':'/mnt/work/Programs/runs/goland_wing',#sharpy_dir+'/cases/models_generator/examples/goland_wing',
'iterate_type': 'Full_Factorial',
'iterate_vars': {'wing1*geometry-sweep':np.linspace(15.5*np.pi/180,19.5*np.pi/180,5), #np.linspace(15*np.pi/180,20*np.pi/180,6)
'wing1*geometry-length':6.096*np.linspace(1.025,1.275,6), #6.096*np.linspace(1,1.3,7)
'wing1*aero-chord':c_ref*np.array([np.linspace(1.,1.,2),np.linspace(0.9,0.95,2)]).T},
#c_ref*np.array([np.linspace(1.,1.,3),np.linspace(0.85,1.,3)]).T}
'iterate_labels': {'label_type':'number',
'print_name_var':0}}

g1sm = {'sharpy': {'simulation_input':None,
'default_module':'sharpy.routines.flutter',
'default_solution':'sol_145',
'default_solution_vars': {'panels_wake':8*5,
'num_modes':5,
'rho':1.02,
'u_inf':0.01,
'c_ref':1.8288,
'folder':'./runs',
'velocity_analysis':[70,220,150],
'rom_algorithm':'mimo_rational_arnoldi',
'rom_size':6,
'flow':['BeamLoader',
'AerogridLoader',
'StaticCoupled',
'AerogridPlot',
'Modal',
'LinearAssembler',
'AsymptoticStability',
'PickleData'],
'AerogridPlot':{'folder':'./runs',
'include_rbm': 'off',
'include_applied_forces': 'off',
'minus_m_star': 0},
'PickleData': {'folder':'./runs'},
'LinearAssembler':{'linear_system_settings':{'aero_settings':{'use_sparse':False,
'rom_method':[],
'rom_method_settings':{'Balanced':{'algorithm':'FrequencyLimited'}}},
'beam_settings':{'modal_projection': 'off',
'inout_coords': 'nodes'}},
'inout_coordinates':'nodes'}},
'default_sharpy':{},
'model_route':None}}

g1 = gm.Model('sharpy',['sharpy'], model_dict=g1mm, components_dict=g1cm,
simulation_dict=g1sm)
g1.run()

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