def write_geometry(avl_object):
# unpack inputs
aircraft = avl_object.features
geometry_file = avl_object.settings.filenames.features
# Open the geometry file after purging if it already exists
purge_files([geometry_file])
geometry = open(geometry_file, 'w')
with open(geometry_file, 'w') as geometry:
header_text = make_header_text(avl_object)
geometry.write(header_text)
for w in aircraft.wings:
avl_wing = translate_avl_wing(w)
wing_text = make_surface_text(avl_wing)
geometry.write(wing_text)
for b in aircraft.fuselages:
avl_body = translate_avl_body(b)
body_text = make_body_text(avl_body)
geometry.write(body_text)
return
def make_case_command(avl_object, case):
""" Makes commands for case execution in AVK
Assumptions:
None
Source:
None
Inputs:
case.index
case.tag
case.result_filename
Outputs:
case_command
Properties Used:
N/A
"""
base_case_command = \
'''{0}
x
{1}
{2}
'''
index = case.index
case_tag = case.tag
res_type = 'st' # This needs to change to multiple ouputs if you want to add the ability to read other types of results
results_file = case.result_filename
purge_files([results_file])
case_command = base_case_command.format(index, res_type, results_file)
return case_command
def write_geometry(avl_object):
# unpack inputs
aircraft = avl_object.features
geometry_file = avl_object.settings.filenames.features
# Open the geometry file after purging if it already exists
purge_files([geometry_file])
geometry = open(geometry_file, "w")
with open(geometry_file, "w") as geometry:
header_text = make_header_text(avl_object)
geometry.write(header_text)
for w in aircraft.wings:
avl_wing = translate_avl_wing(w)
wing_text = make_surface_text(avl_wing)
geometry.write(wing_text)
for b in aircraft.fuselages:
avl_body = translate_avl_body(b)
body_text = make_body_text(avl_body)
geometry.write(body_text)
return
def make_case_command(avl_object,case):
""" Makes commands for case execution in AVK
Assumptions:
None
Source:
None
Inputs:
case.index
case.tag
case.result_filename
Outputs:
case_command
Properties Used:
N/A
"""
base_case_command = \
'''{0}
x
{1}
{2}
'''
index = case.index
case_tag = case.tag
res_type = 'st' # This needs to change to multiple ouputs if you want to add the ability to read other types of results
results_file = case.result_filename
purge_files([results_file])
case_command = base_case_command.format(index,res_type,results_file)
return case_command
#def make_eigen_mode_case_command(avl_object,case):
#em_base_case_command = \
#'''
#MODE
#n
#w
#{0}
#'''
#em_results_file = case.eigen_result_filename
#purge_files([em_results_file])
#em_case_command = em_base_case_command.format(em_results_file)
#return em_case_command
def write_input_deck(avl_object):
""" This fucntions writes the execution steps used in the AVL call
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object
Outputs:
None
Properties Used:
N/A
"""
open_runs = \
'''CASE {}
'''
base_input = \
'''OPER
'''
# unpack
batch = avl_object.current_status.batch_file
deck_filename = avl_object.current_status.deck_file
# purge old versions and write the new input deck
avl_regression_flag = avl_object.regression_flag
if not avl_regression_flag:
purge_files([deck_filename])
with open(deck_filename,'w') as input_deck:
input_deck.write(open_runs.format(batch))
input_deck.write(base_input)
for case_name in avl_object.current_status.cases:
# write and store aerodynamic and static stability result files
case = avl_object.current_status.cases[case_name]
case_command = make_case_command(avl_object,case)
input_deck.write(case_command)
#-----------------------------------------------------------------
# SUAVE-AVL dynamic stability analysis under development
#
# write store dynamics stability result files
# em_case_command = make_eigen_mode_case_command(avl_object,case)
# input_deck.write(em_case_command)
#
#-----------------------------------------------------------------
input_deck.write('\n\nQUIT\n')
return
def write_input_deck(avl_object):
""" This fucntions writes the execution steps used in the AVL call
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object
Outputs:
None
Properties Used:
N/A
"""
open_runs = \
'''CASE {}
'''
base_input = \
'''OPER
'''
# unpack
batch = avl_object.current_status.batch_file
deck_filename = avl_object.current_status.deck_file
# purge old versions and write the new input deck
avl_regression_flag = avl_object.regression_flag
if not avl_regression_flag:
purge_files([deck_filename])
with open(deck_filename, 'w') as input_deck:
input_deck.write(open_runs.format(batch))
input_deck.write(base_input)
for case_name in avl_object.current_status.cases:
# write and store aerodynamic and static stability result files
case = avl_object.current_status.cases[case_name]
case_command = make_case_command(avl_object, case)
input_deck.write(case_command)
#-----------------------------------------------------------------
# SUAVE-AVL dynamic stability analysis under development
#
# write store dynamics stability result files
# em_case_command = make_eigen_mode_case_command(avl_object,case)
# input_deck.write(em_case_command)
#
#-----------------------------------------------------------------
input_deck.write('\n\nQUIT\n')
def purge_directory(path, purge_subdirectories=False):
""" Deletes the contents of a directory, then the directory itself.
If purge_subdirectories is True, subdirectories of the directory will also
be purged, recursively. In this case, the directory specified in the 'path'
argument will always be removed at the end of this function.
However, if purge_subdirectories is False, files in 'path' will be deleted,
but subdirectories and their contents will be left untouched. In this case,
the directory ('path' argument) will only be removed if it contains no
subdirectories.
Assumptions:
None
Source:
None
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
contents = os.listdir(path)
subdir = []
print contents
for item in contents:
print os.path.abspath(os.path.join(path, item))
if os.path.isdir(os.path.abspath(os.path.join(path, item))):
subdir.append(item)
contents.remove(item)
print subdir, contents
purge_files(contents, path)
if purge_subdirectories:
for sub in subdir:
purge_directory(os.path.join(path, sub), True)
contents = os.listdir(path)
if contents:
print "Directory contains subdirectories which were not specified for deletion. Directory not fully deleted."
else:
os.rmdir(path)
return
def make_case_command(avl_object,case):
base_case_command = \
'''{0}
x
{1}
{2}
'''
index = case.index
case_tag = case.tag
res_type = 'st' # This needs to change to multiple ouputs if you want to add the ability to read other types of results
results_file = case.result_filename
purge_files([results_file])
case_command = base_case_command.format(index,res_type,results_file)
return case_command
def make_case_command(avl_object,case):
base_case_command = \
'''{0}
x
{1}
{2}
'''
index = case.index
case_tag = case.tag
res_type = 'st' # This needs to change to multiple ouputs if you want to add the ability to read other types of results
results_file = case.result_filename
purge_files([results_file])
case_command = base_case_command.format(index,res_type,results_file)
return case_command
def write_geometry(avl_object, spanwise_vortices_per_meter):
"""This function writes the translated aircraft geometry into text file read
by AVL when it is called
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object
Outputs:
None
Properties Used:
N/A
"""
# unpack inputs
aircraft = avl_object.geometry
geometry_file = avl_object.settings.filenames.features
# Open the geometry file after purging if it already exists
purge_files([geometry_file])
geometry = open(geometry_file, 'w')
with open(geometry_file, 'w') as geometry:
header_text = make_header_text(avl_object)
geometry.write(header_text)
for w in aircraft.wings:
avl_wing = translate_avl_wing(w)
wing_text = make_surface_text(avl_wing,
spanwise_vortices_per_meter)
geometry.write(wing_text)
for b in aircraft.fuselages:
if b.tag == 'fuselage':
avl_body = translate_avl_body(b)
body_text = make_body_text(avl_body)
geometry.write(body_text)
return
def write_geometry(avl_object,spanwise_vortices_per_meter):
"""This function writes the translated aircraft geometry into text file read
by AVL when it is called
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object
Outputs:
None
Properties Used:
N/A
"""
# unpack inputs
aircraft = avl_object.geometry
geometry_file = avl_object.settings.filenames.features
# Open the geometry file after purging if it already exists
purge_files([geometry_file])
geometry = open(geometry_file,'w')
with open(geometry_file,'w') as geometry:
header_text = make_header_text(avl_object)
geometry.write(header_text)
for w in aircraft.wings:
avl_wing = translate_avl_wing(w)
wing_text = make_surface_text(avl_wing,spanwise_vortices_per_meter)
geometry.write(wing_text)
for b in aircraft.fuselages:
if b.tag == 'fuselage':
avl_body = translate_avl_body(b)
body_text = make_body_text(avl_body)
geometry.write(body_text)
return
def write_input_deck(avl_object):
open_runs = \
'''CASE {}
'''
base_input = \
'''OPER
'''
# unpack
batch = avl_object.current_status.batch_file
deck_filename = avl_object.current_status.deck_file
# purge old versions and write the new input deck
purge_files([deck_filename])
with open(deck_filename,'w') as input_deck:
input_deck.write(open_runs.format(batch))
input_deck.write(base_input)
for case in avl_object.current_status.cases:
case_command = make_case_command(avl_object,case)
input_deck.write(case_command)
input_deck.write('\n\nQUIT\n')
return
def write_input_deck(avl_object):
open_runs = \
'''CASE {}
'''
base_input = \
'''OPER
'''
# unpack
batch = avl_object.current_status.batch_file
deck_filename = avl_object.current_status.deck_file
# purge old versions and write the new input deck
purge_files([deck_filename])
with open(deck_filename,'w') as input_deck:
input_deck.write(open_runs.format(batch))
input_deck.write(base_input)
for case in avl_object.current_status.cases:
case_command = make_case_command(avl_object,case)
input_deck.write(case_command)
input_deck.write('\n\nQUIT\n')
return
def purge_directory(path,purge_subdirectories=False):
"""
Deletes the contents of a directory, then the directory itself.
If purge_subdirectories is True, subdirectories of the directory will also
be purged, recursively. In this case, the directory specified in the 'path'
argument will always be removed at the end of this function.
However, if purge_subdirectories is False, files in 'path' will be deleted,
but subdirectories and their contents will be left untouched. In this case,
the directory ('path' argument) will only be removed if it contains no
subdirectories.
"""
contents = os.listdir(path)
subdir = []
print contents
for item in contents:
print os.path.abspath(os.path.join(path,item))
if os.path.isdir(os.path.abspath(os.path.join(path,item))):
subdir.append(item)
contents.remove(item)
print subdir, contents
purge_files(contents,path)
if purge_subdirectories:
for sub in subdir:
purge_directory(os.path.join(path,sub),True)
contents = os.listdir(path)
if contents:
print "Directory contains subdirectories which were not specified for deletion. Directory not fully deleted."
else:
os.rmdir(path)
return
def write_run_cases(avl_object):
# imports
from SUAVE.Methods.Aerodynamics.AVL.write_run_cases import make_controls_case_text
# unpack avl_inputs
batch_filename = avl_object.current_status.batch_file
aircraft = avl_object.features
base_case_text = \
'''
---------------------------------------------
Run case {0}: {1}
alpha -> alpha = {2}
beta -> beta = {3}
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
rb/2V -> rb/2V = 0.00000
{4}
alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
rb/2V = 0.00000
CL = 0.00000
CDo = 0.00000
bank = 0.00000 deg
elevation = 0.00000 deg
heading = 0.00000 deg
Mach = {5}
velocity = {6} m/s
density = {7} kg/m^3
grav.acc. = {8} m/s^2
turn_rad. = 0.00000 m
load_fac. = 0.00000
X_cg = {9} m
Y_cg = {10} m
Z_cg = {11} m
mass = {12} kg
Ixx = {13} kg-m^2
Iyy = {14} kg-m^2
Izz = {15} kg-m^2
Ixy = {16} kg-m^2
Iyz = {17} kg-m^2
Izx = {18} kg-m^2
visc CL_a = 0.00000
visc CL_u = 0.00000
visc CM_a = 0.00000
visc CM_u = 0.00000
'''#{4} is a set of control surface inputs that will vary depending on the control surface configuration
# Open the geometry file after purging if it already exists
purge_files([batch_filename])
with open(batch_filename, 'w') as runcases:
x_cg = avl_object.features.mass_properties.center_of_gravity[0]
y_cg = avl_object.features.mass_properties.center_of_gravity[1]
z_cg = avl_object.features.mass_properties.center_of_gravity[2]
mass = 0 #avl_object.default_case.mass TODO: FIGURE OUT WHAT TO DEFAULT MASS TO, AND WHERE TO STORE IT BEFORE ANALYSIS.
moments_of_inertia = aircraft.mass_properties.moments_of_inertia.tensor
Ixx = moments_of_inertia[0][0]
Iyy = moments_of_inertia[1][1]
Izz = moments_of_inertia[2][2]
Ixy = moments_of_inertia[0][1]
Iyz = moments_of_inertia[1][2]
Izx = moments_of_inertia[2][0]
for case in avl_object.current_status.cases:
index = case.index
name = case.tag
alpha = case.conditions.aerodynamics.angle_of_attack
beta = case.conditions.aerodynamics.side_slip_angle
mach = case.conditions.freestream.mach
v = case.conditions.freestream.velocity
rho = case.conditions.freestream.density
g = case.conditions.freestream.gravitational_acceleration
# form controls text
controls = []
if case.stability_and_control.control_deflections:
for cs in case.stability_and_control.control_deflections:
cs_text = make_controls_case_text(cs)
controls.append(cs_text)
controls_text = ''.join(controls)
case_text = base_case_text.format(index, name, alpha, beta,
controls_text, mach, v, rho, g,
x_cg, y_cg, z_cg, mass, Ixx, Iyy,
Izz, Ixy, Iyz, Izx)
runcases.write(case_text)
def write_run_cases(avl_object):
""" This function writes the run cases used in the AVL batch analysis
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object.current_status.batch_file [-]
avl_object.geometry.mass_properties.center_of_gravity [meters]
Outputs:
None
Properties Used:
N/A
"""
# unpack avl_inputs
batch_filename = avl_object.current_status.batch_file
aircraft = avl_object.geometry
base_case_text = \
'''
---------------------------------------------
Run case {0}: {1}
alpha -> alpha = {2}
beta -> beta = {3}
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
rb/2V -> rb/2V = 0.00000
{4}
alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
rb/2V = 0.00000
CL = 0.00000
CDo = 0.00000
bank = 0.00000 deg
elevation = 0.00000 deg
heading = 0.00000 deg
Mach = {5}
velocity = 0.0000 m/s
density = {6} kg/m^3
grav.acc. = {7} m/s^2
turn_rad. = 0.00000 m
load_fac. = 0.00000
X_cg = {8} m
Y_cg = {9} m
Z_cg = {10} m
mass = {11} kg
Ixx = {12} kg-m^2
Iyy = {13} kg-m^2
Izz = {14} kg-m^2
Ixy = {15} kg-m^2
Iyz = {16} kg-m^2
Izx = {17} kg-m^2
visc CL_a = 0.00000
visc CL_u = 0.00000
visc CM_a = 0.00000
visc CM_u = 0.00000
'''#{4} is a set of control surface inputs that will vary depending on the control surface configuration
# Open the geometry file after purging if it already exists
purge_files([batch_filename])
with open(batch_filename, 'w') as runcases:
x_cg = aircraft.mass_properties.center_of_gravity[0]
y_cg = aircraft.mass_properties.center_of_gravity[1]
z_cg = aircraft.mass_properties.center_of_gravity[2]
mass = 0
moments_of_inertia = aircraft.mass_properties.moments_of_inertia.tensor
Ixx = moments_of_inertia[0][0]
Iyy = moments_of_inertia[1][1]
Izz = moments_of_inertia[2][2]
Ixy = moments_of_inertia[0][1]
Iyz = moments_of_inertia[1][2]
Izx = moments_of_inertia[2][0]
for case_name in avl_object.current_status.cases:
case = avl_object.current_status.cases[case_name]
index = case.index
name = case.tag
alpha = case.conditions.aerodynamics.angle_of_attack
beta = case.conditions.aerodynamics.side_slip_angle
mach = case.conditions.freestream.mach
rho = case.conditions.freestream.density
g = case.conditions.freestream.gravitational_acceleration
# form controls text
controls = []
if case.stability_and_control.control_deflections:
for cs in case.stability_and_control.control_deflections:
cs_text = make_controls_case_text(cs)
controls.append(cs_text)
def write_run_cases(avl_object):
""" This function writes the run cases used in the AVL batch analysis
Assumptions:
None
Source:
Drela, M. and Youngren, H., AVL, http://web.mit.edu/drela/Public/web/avl
Inputs:
avl_object.current_status.batch_file [-]
avl_object.geometry.mass_properties.center_of_gravity [meters]
Outputs:
None
Properties Used:
N/A
"""
# unpack avl_inputs
batch_filename = avl_object.current_status.batch_file
aircraft = avl_object.geometry
base_case_text = \
'''
---------------------------------------------
Run case {0}: {1}
alpha -> alpha = {2}
beta -> beta = {3}
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
rb/2V -> rb/2V = 0.00000
{4}
alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
rb/2V = 0.00000
CL = 0.00000
CDo = 0.00000
bank = 0.00000 deg
elevation = 0.00000 deg
heading = 0.00000 deg
Mach = {5}
velocity = 0.0000 m/s
density = {6} kg/m^3
grav.acc. = {7} m/s^2
turn_rad. = 0.00000 m
load_fac. = 0.00000
X_cg = {8} m
Y_cg = {9} m
Z_cg = {10} m
mass = {11} kg
Ixx = {12} kg-m^2
Iyy = {13} kg-m^2
Izz = {14} kg-m^2
Ixy = {15} kg-m^2
Iyz = {16} kg-m^2
Izx = {17} kg-m^2
visc CL_a = 0.00000
visc CL_u = 0.00000
visc CM_a = 0.00000
visc CM_u = 0.00000
'''#{4} is a set of control surface inputs that will vary depending on the control surface configuration
# Open the geometry file after purging if it already exists
purge_files([batch_filename])
with open(batch_filename,'w') as runcases:
x_cg = aircraft.mass_properties.center_of_gravity[0]
y_cg = aircraft.mass_properties.center_of_gravity[1]
z_cg = aircraft.mass_properties.center_of_gravity[2]
mass = 0
moments_of_inertia = aircraft.mass_properties.moments_of_inertia.tensor
Ixx = moments_of_inertia[0][0]
Iyy = moments_of_inertia[1][1]
Izz = moments_of_inertia[2][2]
Ixy = moments_of_inertia[0][1]
Iyz = moments_of_inertia[1][2]
Izx = moments_of_inertia[2][0]
for case_name in avl_object.current_status.cases:
case = avl_object.current_status.cases[case_name]
index = case.index
name = case.tag
alpha = case.conditions.aerodynamics.angle_of_attack
beta = case.conditions.aerodynamics.side_slip_angle
mach = case.conditions.freestream.mach
rho = case.conditions.freestream.density
g = case.conditions.freestream.gravitational_acceleration
# form controls text
controls = []
if case.stability_and_control.control_deflections:
for cs in case.stability_and_control.control_deflections:
cs_text = make_controls_case_text(cs)
controls.append(cs_text)
controls_text = ''.join(controls)
case_text = base_case_text.format(index,name,alpha,beta,controls_text,
mach,rho,g,x_cg,y_cg,z_cg,mass,
Ixx,Iyy,Izz,Ixy,Iyz,Izx)
runcases.write(case_text)
return
def write_run_cases(avl_object):
# imports
from SUAVE.Methods.Aerodynamics.AVL.write_run_cases import make_controls_case_text
# unpack avl_inputs
batch_filename = avl_object.current_status.batch_file
aircraft = avl_object.features
base_case_text = """
---------------------------------------------
Run case {0}: {1}
alpha -> alpha = {2}
beta -> beta = {3}
pb/2V -> pb/2V = 0.00000
qc/2V -> qc/2V = 0.00000
rb/2V -> rb/2V = 0.00000
{4}
alpha = 0.00000 deg
beta = 0.00000 deg
pb/2V = 0.00000
qc/2V = 0.00000
rb/2V = 0.00000
CL = 0.00000
CDo = 0.00000
bank = 0.00000 deg
elevation = 0.00000 deg
heading = 0.00000 deg
Mach = {5}
velocity = {6} m/s
density = {7} kg/m^3
grav.acc. = {8} m/s^2
turn_rad. = 0.00000 m
load_fac. = 0.00000
X_cg = {9} m
Y_cg = {10} m
Z_cg = {11} m
mass = {12} kg
Ixx = {13} kg-m^2
Iyy = {14} kg-m^2
Izz = {15} kg-m^2
Ixy = {16} kg-m^2
Iyz = {17} kg-m^2
Izx = {18} kg-m^2
visc CL_a = 0.00000
visc CL_u = 0.00000
visc CM_a = 0.00000
visc CM_u = 0.00000
""" # {4} is a set of control surface inputs that will vary depending on the control surface configuration
# Open the geometry file after purging if it already exists
purge_files([batch_filename])
with open(batch_filename, "w") as runcases:
x_cg = avl_object.features.mass_properties.center_of_gravity[0]
y_cg = avl_object.features.mass_properties.center_of_gravity[1]
z_cg = avl_object.features.mass_properties.center_of_gravity[2]
mass = (
0
) # avl_object.default_case.mass TODO: FIGURE OUT WHAT TO DEFAULT MASS TO, AND WHERE TO STORE IT BEFORE ANALYSIS.
moments_of_inertia = aircraft.mass_properties.moments_of_inertia.tensor
Ixx = moments_of_inertia[0][0]
Iyy = moments_of_inertia[1][1]
Izz = moments_of_inertia[2][2]
Ixy = moments_of_inertia[0][1]
Iyz = moments_of_inertia[1][2]
Izx = moments_of_inertia[2][0]
for case in avl_object.current_status.cases:
index = case.index
name = case.tag
alpha = case.conditions.aerodynamics.angle_of_attack
beta = case.conditions.aerodynamics.side_slip_angle
mach = case.conditions.freestream.mach
v = case.conditions.freestream.velocity
rho = case.conditions.freestream.density
g = case.conditions.freestream.gravitational_acceleration
# form controls text
controls = []
if case.stability_and_control.control_deflections:
for cs in case.stability_and_control.control_deflections:
cs_text = make_controls_case_text(cs)
controls.append(cs_text)
controls_text = "".join(controls)
case_text = base_case_text.format(
index,
name,
alpha,
beta,
controls_text,
mach,
v,
rho,
g,
x_cg,
y_cg,
z_cg,
mass,
Ixx,
Iyy,
Izz,
Ixy,
Iyz,
Izx,
)
runcases.write(case_text)
return