def _load_from_file(self, filename):
vsp.ClearVSPModel()
vsp.ReadVSPFile(filename)
for geom_id in vsp.FindGeoms():
geom_name_raw = vsp.GetGeomName(geom_id)
geom_name, geom_idx = regex_listname.findall(geom_name_raw)[0]
if geom_name not in self:
if geom_idx:
self[geom_name] = []
else:
self[geom_name] = VspElement()
if geom_idx != '':
geom = self._update_list(self[geom_name], geom_idx)
else:
geom = self[geom_name]
geom._id = geom_id
for param_id in vsp.GetGeomParmIDs(geom_id):
group_name_raw = vsp.GetParmDisplayGroupName(param_id)
group_name, group_idx = regex_listname.findall(
group_name_raw)[0]
if group_name not in EXCLUDE_GROUPS:
if group_name not in geom:
if group_idx:
geom[group_name] = []
else:
geom[group_name] = VspElement()
if group_idx != '':
geom[group_name], group = self._update_list(
geom[group_name], group_idx)
else:
group = geom[group_name]
param = self._make_parameter(param_id)
if param['name'] in group:
raise ValueError("{} already in <{}:{}>".format(
param.name, geom_name, group_name))
group[param['name']] = param
def __init__(self,
vspFile,
comm=MPI.COMM_WORLD,
scale=1.0,
comps=[],
intersectedComps=None,
debug=False):
self.points = OrderedDict()
self.pointSets = OrderedDict()
self.updated = {}
self.vspScale = scale
self.comm = comm
self.vspFile = vspFile
self.debug = debug
self.jac = None
# Load in the VSP model
vsp.ClearVSPModel()
vsp.ReadVSPFile(vspFile)
# Setup the export group set (0) with just the sets we want.
self.exportSet = 9
# List of all componets returned from VSP. Note that this
# order is important...it is the order the comps will be
# written out in plot3d format.
allComps = vsp.FindGeoms()
# If we were not given comps, use all of them
if comps == []:
for c in allComps:
comps.append(vsp.GetContainerName(c))
# First set the export flag for exportSet to False for everyone
for comp in allComps:
vsp.SetSetFlag(comp, self.exportSet, False)
self.exportComps = []
for comp in allComps:
# Check if this one is in our list:
compName = vsp.GetContainerName(comp)
if compName in comps:
vsp.SetSetFlag(comp, self.exportSet, True)
self.exportComps.append(compName)
# Create a directory in which we will put the temporary files
# we need. We *should* use something like tmepfile.mkdtemp()
# but that behaves badly on pleiades.
tmpDir = None
if self.comm.rank == 0:
tmpDir = './tmpDir_%d_%s' % (MPI.COMM_WORLD.rank, time.time())
print('Temp dir is: %s' % tmpDir)
if not os.path.exists(tmpDir):
os.makedirs(tmpDir)
self.tmpDir = self.comm.bcast(tmpDir)
# Initial list of DVs
self.DVs = OrderedDict()
# Run the update. This will also set the conn on the first pass
self.conn = None
self.pts0 = None
self.cumSizes = None
self.sizes = None
if self.comm.rank == 0:
self.pts0, self.conn, self.cumSizes, self.sizes = self._getUpdatedSurface(
)
self.pts0 = self.comm.bcast(self.pts0)
self.conn = self.comm.bcast(self.conn)
self.cumSizes = self.comm.bcast(self.cumSizes)
self.sizes = self.comm.bcast(self.sizes)
self.pts = self.pts0.copy()
# Finally process theintersection information. We had to wait
# until all processors have the surface information.
self.intersectComps = []
if intersectedComps is None:
intersectedComps = []
for i in range(len(intersectedComps)):
c = intersectedComps[i]
# Get the index of each of the two comps:
compIndexA = self.exportComps.index(c[0])
compIndexB = self.exportComps.index(c[1])
direction = c[2]
dStar = c[3]
extraComps = []
if len(c) == 5:
for j in range(len(c[4])):
extraComps.append(self.exportComps.index(c[4][j]))
self.intersectComps.append(
CompIntersection(compIndexA, compIndexB, extraComps, direction,
dStar, self.pts, self.cumSizes, self.sizes,
self.tmpDir))
vsp.PasteGeomClipboard(fuse_id) # make fuse parent
# Set Name
vsp.SetGeomName(pod_id, "Original_Pod")
second_pod_id = vsp.FindGeom("Pod", 0)
# Change Location and Symmetry
vsp.SetParmVal(second_pod_id, "Sym_Planar_Flag", "Sym", 0)
vsp.SetParmVal(second_pod_id, "Y_Location", "XForm", 0.0)
vsp.SetParmVal(second_pod_id, "Z_Location", "XForm", 1.0)
fname = "apitest1.vsp3"
vsp.WriteVSPFile(fname)
geoms = vsp.FindGeoms()
print("All geoms in Vehicle.")
print(geoms)
errorMgr.PopErrorAndPrint(stdout)
# ==== Use Case 2 ====#
vsp.VSPRenew()
errorMgr.PopErrorAndPrint(stdout)
geoms = vsp.FindGeoms()
print("All geoms in Vehicle.")
print(geoms)
def UpdateGeometry(self, actions):
# OpenVSP Script Part
os.chdir("/home/simonx/Documents/Udacity/ML/Projects/capstone/OpenVSP")
stdout = vsp.cvar.cstdout
errorMgr = vsp.ErrorMgrSingleton_getInstance()
# WingBodyTestCase
vsp.VSPRenew()
errorMgr.PopErrorAndPrint(stdout)
# Add Wing
WingBody = vsp.AddGeom("WING", "")
# Insert A Couple More Sections
InsertXSec(WingBody, 1, XS_FOUR_SERIES)
InsertXSec(WingBody, 1, XS_FOUR_SERIES)
InsertXSec(WingBody, 1, XS_FOUR_SERIES)
# Cut The Original Section
CutXSec(WingBody, 1)
# Change Driver
SetDriverGroup(WingBody, 1, AREA_WSECT_DRIVER, ROOTC_WSECT_DRIVER,
TIPC_WSECT_DRIVER)
SetParmVal(WingBody, "RotateAirfoilMatchDideralFlag", "WingGeom", 1.0)
# Change Some Parameters 1st Section
SetParmVal(WingBody, "Root_Chord", "XSec_1", 7.0)
SetParmVal(WingBody, "Tip_Chord", "XSec_1", 3.0)
SetParmVal(WingBody, "Area", "XSec_1", actions[0])
SetParmVal(WingBody, "Sweep", "XSec_1", actions[1])
# Because Sections Are Connected Change One Section At A Time Then Update
Update()
# Change Some Parameters 2nd Section
SetParmVal(WingBody, "Tip_Chord", "XSec_2", 2.0)
SetParmVal(WingBody, "Sweep", "XSec_2", 60.0)
SetParmVal(WingBody, "Dihedral", "XSec_2", 30.0)
Update()
# Change Some Parameters 3rd Section
SetParmVal(WingBody, "Sweep", "XSec_3", 60.0)
SetParmVal(WingBody, "Dihedral", "XSec_3", 80.0)
Update()
# Change Airfoil
SetParmVal(WingBody, "Camber", "XSecCurve_0", 0.02)
Update()
# print "All geoms in Vehicle."
geoms = vsp.FindGeoms()
print geoms
# File basename
baseName = "WingBody"
csvName = baseName + "_Dege nGeom.csv"
stlName = baseName + "_DegenGeom.stl"
vspName = baseName + ".vsp3"
# Set File Name
SetComputationFileName(DEGEN_GEOM_CSV_TYPE, csvName)
SetComputationFileName(CFD_STL_TYPE, stlName)
WriteVSPFile(vspName)
# ComputeDegenGeom( SET_ALL, DEGEN_GEOM_CSV_TYPE );
# ComputeCFDMesh( SET_ALL, CFD_STL_TYPE ); # Mesh
# Check for errors
num_err = errorMgr.GetNumTotalErrors()
for i in range(0, num_err):
err = errorMgr.PopLastError()
print "error = ", err.m_ErrorString
def vsp_read(tag, units_type='SI',specified_network=None):
"""This reads an OpenVSP vehicle geometry and writes it into a SUAVE vehicle format.
Includes wings, fuselages, and propellers.
Assumptions:
1. OpenVSP vehicle is composed of conventionally shaped fuselages, wings, and propellers.
1a. OpenVSP fuselage: generally narrow at nose and tail, wider in center).
1b. Fuselage is designed in VSP as it appears in real life. That is, the VSP model does not rely on
superficial elements such as canopies, stacks, or additional fuselages to cover up internal lofting oddities.
1c. This program will NOT account for multiple geometries comprising the fuselage. For example: a wingbox mounted beneath
is a separate geometry and will NOT be processed.
2. Fuselage origin is located at nose. VSP file origin can be located anywhere, preferably at the forward tip
of the vehicle or in front (to make all X-coordinates of vehicle positive).
3. Written for OpenVSP 3.21.1
Source:
N/A
Inputs:
1. A tag for an XML file in format .vsp3.
2. Units_type set to 'SI' (default) or 'Imperial'
3. User-specified network
Outputs:
Writes SUAVE vehicle with these geometries from VSP: (All values default to SI. Any other 2nd argument outputs Imperial.)
Wings.Wing. (* is all keys)
origin [m] in all three dimensions
spans.projected [m]
chords.root [m]
chords.tip [m]
aspect_ratio [-]
sweeps.quarter_chord [radians]
twists.root [radians]
twists.tip [radians]
thickness_to_chord [-]
dihedral [radians]
symmetric <boolean>
tag <string>
areas.reference [m^2]
areas.wetted [m^2]
Segments.
tag <string>
twist [radians]
percent_span_location [-] .1 is 10%
root_chord_percent [-] .1 is 10%
dihedral_outboard [radians]
sweeps.quarter_chord [radians]
thickness_to_chord [-]
airfoil <NACA 4-series, 6 series, or airfoil file>
Fuselages.Fuselage.
origin [m] in all three dimensions
width [m]
lengths.
total [m]
nose [m]
tail [m]
heights.
maximum [m]
at_quarter_length [m]
at_three_quarters_length [m]
effective_diameter [m]
fineness.nose [-] ratio of nose section length to fuselage effective diameter
fineness.tail [-] ratio of tail section length to fuselage effective diameter
areas.wetted [m^2]
tag <string>
segment[]. (segments are in ordered container and callable by number)
vsp.shape [point,circle,round_rect,general_fuse,fuse_file]
vsp.xsec_id <10 digit string>
percent_x_location
percent_z_location
height
width
length
effective_diameter
tag
vsp.xsec_num <integer of fuselage segment quantity>
vsp.xsec_surf_id <10 digit string>
Propellers.Propeller.
location[X,Y,Z] [radians]
rotation[X,Y,Z] [radians]
tip_radius [m]
hub_radius [m]
thrust_angle [radians]
Properties Used:
N/A
"""
vsp.ClearVSPModel()
vsp.ReadVSPFile(tag)
vsp_fuselages = []
vsp_wings = []
vsp_props = []
vsp_nacelles = []
vsp_nacelle_type = []
vsp_geoms = vsp.FindGeoms()
geom_names = []
vehicle = SUAVE.Vehicle()
vehicle.tag = tag
if units_type == 'SI':
units_type = 'SI'
elif units_type == 'inches':
units_type = 'inches'
else:
units_type = 'imperial'
# The two for-loops below are in anticipation of an OpenVSP API update with a call for GETGEOMTYPE.
# This print function allows user to enter VSP GeomID manually as first argument in vsp_read functions.
print("VSP geometry IDs: ")
# Label each geom type by storing its VSP geom ID.
for geom in vsp_geoms:
geom_name = vsp.GetGeomName(geom)
geom_names.append(geom_name)
print(str(geom_name) + ': ' + geom)
# --------------------------------
# AUTOMATIC VSP ENTRY & PROCESSING
# --------------------------------
for geom in vsp_geoms:
geom_name = vsp.GetGeomName(geom)
geom_type = vsp.GetGeomTypeName(str(geom))
if geom_type == 'Fuselage':
vsp_fuselages.append(geom)
if geom_type == 'Wing':
vsp_wings.append(geom)
if geom_type == 'Propeller':
vsp_props.append(geom)
if (geom_type == 'Stack') or (geom_type == 'BodyOfRevolution'):
vsp_nacelle_type.append(geom_type)
vsp_nacelles.append(geom)
# --------------------------------------------------
# Read Fuselages
# --------------------------------------------------
for fuselage_id in vsp_fuselages:
sym_planar = vsp.GetParmVal(fuselage_id, 'Sym_Planar_Flag', 'Sym') # Check for symmetry
sym_origin = vsp.GetParmVal(fuselage_id, 'Sym_Ancestor_Origin_Flag', 'Sym')
if sym_planar == 2. and sym_origin == 1.:
num_fus = 2
sym_flag = [1,-1]
else:
num_fus = 1
sym_flag = [1]
for fux_idx in range(num_fus): # loop through fuselages on aircraft
fuselage = read_vsp_fuselage(fuselage_id,fux_idx,sym_flag[fux_idx],units_type)
vehicle.append_component(fuselage)
# --------------------------------------------------
# Read Wings
# --------------------------------------------------
for wing_id in vsp_wings:
wing = read_vsp_wing(wing_id, units_type)
vehicle.append_component(wing)
# --------------------------------------------------
# Read Nacelles
# --------------------------------------------------
for nac_id, nacelle_id in enumerate(vsp_nacelles):
nacelle = read_vsp_nacelle(nacelle_id,vsp_nacelle_type[nac_id], units_type)
vehicle.append_component(nacelle)
# --------------------------------------------------
# Read Propellers/Rotors and assign to a network
# --------------------------------------------------
# Initialize rotor network elements
number_of_lift_rotor_engines = 0
number_of_propeller_engines = 0
lift_rotors = Data()
propellers = Data()
for prop_id in vsp_props:
prop = read_vsp_propeller(prop_id,units_type)
prop.tag = vsp.GetGeomName(prop_id)
if prop.orientation_euler_angles[1] >= 70 * Units.degrees:
lift_rotors.append(prop)
number_of_lift_rotor_engines += 1
else:
propellers.append(prop)
number_of_propeller_engines += 1
if specified_network == None:
# If no network specified, assign a network
if number_of_lift_rotor_engines>0 and number_of_propeller_engines>0:
net = Lift_Cruise()
else:
net = Battery_Propeller()
else:
net = specified_network
# Create the rotor network
if net.tag == "Lift_Cruise":
# Lift + Cruise network
for i in range(number_of_lift_rotor_engines):
net.lift_rotors.append(lift_rotors[list(lift_rotors.keys())[i]])
net.number_of_lift_rotor_engines = number_of_lift_rotor_engines
for i in range(number_of_propeller_engines):
net.propellers.append(propellers[list(propellers.keys())[i]])
net.number_of_propeller_engines = number_of_propeller_engines
elif net.tag == "Battery_Propeller":
# Append all rotors as propellers for the battery propeller network
for i in range(number_of_lift_rotor_engines):
# Accounts for multicopter configurations
net.propellers.append(lift_rotors[list(lift_rotors.keys())[i]])
for i in range(number_of_propeller_engines):
net.propellers.append(propellers[list(propellers.keys())[i]])
net.number_of_propeller_engines = number_of_lift_rotor_engines + number_of_propeller_engines
vehicle.networks.append(net)
return vehicle
def set_sources(geometry):
"""This sets meshing sources in a way similar to the OpenVSP default. Some source values can
also be optionally specified as below.
Assumptions:
None
Source:
https://github.com/OpenVSP/OpenVSP (with some modifications)
Inputs:
geometry.
wings.*. (passed to add_segment_sources())
tag <string>
Segments.*.percent_span_location [-] (.1 is 10%)
Segments.*.root_chord_percent [-] (.1 is 10%)
chords.root [m]
chords.tip [m]
vsp_mesh (optional) - This holds settings that are used in add_segment_sources
fuselages.*.
tag <string>
vsp_mesh. (optional)
length [m]
radius [m]
lengths.total (only used if vsp_mesh is not defined for the fuselage)
Outputs:
<tag>.stl
Properties Used:
N/A
"""
# Extract information on geometry type (for some reason it seems VSP doesn't have a simple
# way to do this)
comp_type_dict = dict()
comp_dict = dict()
for wing in geometry.wings:
comp_type_dict[wing.tag] = 'wing'
comp_dict[wing.tag] = wing
for fuselage in geometry.fuselages:
comp_type_dict[fuselage.tag] = 'fuselage'
comp_dict[fuselage.tag] = fuselage
# network sources have not been implemented
#for network in geometry.networks:
#comp_type_dict[network.tag] = 'turbojet'
#comp_dict[network.tag] = network
components = vsp.FindGeoms()
# The default source values are (mostly) based on the OpenVSP scripts, wing for example:
# https://github.com/OpenVSP/OpenVSP/blob/a5ac5302b320e8e318830663bb50ba0d4f2d6f64/src/geom_core/WingGeom.cpp
for comp in components:
comp_name = vsp.GetGeomName(comp)
if comp_name not in comp_dict:
continue
comp_type = comp_type_dict[comp_name]
# Nacelle sources are not implemented
#if comp_name[0:8] == 'turbofan':
#comp_type = comp_type_dict[comp_name[0:8]]
#else:
#comp_type = comp_type_dict[comp_name]
if comp_type == 'wing':
wing = comp_dict[comp_name]
if len(wing.Segments) == 0: # check if segments exist
num_secs = 1
use_base = True
else:
if wing.Segments[
0].percent_span_location == 0.: # check if first segment starts at the root
num_secs = len(wing.Segments)
use_base = False
else:
num_secs = len(wing.Segments) + 1
use_base = True
u_start = 0.
base_root = wing.chords.root
base_tip = wing.chords.tip
for ii in range(0, num_secs):
if (ii == 0) and (use_base
== True): # create sources on root segment
cr = base_root
if len(wing.Segments) > 0:
ct = base_root * wing.Segments[0].root_chord_percent
seg = wing.Segments[ii]
else:
if 'vsp_mesh' in wing:
custom_flag = True
else:
custom_flag = False
ct = base_tip
seg = wing
# extract CFD source parameters
if len(wing.Segments) == 0:
wingtip_flag = True
else:
wingtip_flag = False
add_segment_sources(comp, cr, ct, ii, u_start, num_secs,
custom_flag, wingtip_flag, seg)
elif (ii == 0) and (use_base == False):
cr = base_root * wing.Segments[0].root_chord_percent
if num_secs > 1:
ct = base_root * wing.Segments[1].root_chord_percent
else:
ct = base_tip
# extract CFD source parameters
seg = wing.Segments[ii]
if 'vsp_mesh' in wing.Segments[ii]:
custom_flag = True
else:
custom_flag = False
wingtip_flag = False
add_segment_sources(comp, cr, ct, ii, u_start, num_secs,
custom_flag, wingtip_flag, seg)
elif ii < num_secs - 1:
if use_base == True:
jj = 1
else:
jj = 0
cr = base_root * wing.Segments[ii - jj].root_chord_percent
ct = base_root * wing.Segments[ii + 1 -
jj].root_chord_percent
seg = wing.Segments[ii - jj]
if 'vsp_mesh' in wing.Segments[ii - jj]:
custom_flag = True
else:
custom_flag = False
wingtip_flag = False
add_segment_sources(comp, cr, ct, ii, u_start, num_secs,
custom_flag, wingtip_flag, seg)
else:
if use_base == True:
jj = 1
else:
jj = 0
cr = base_root * wing.Segments[ii - jj].root_chord_percent
ct = base_tip
seg = wing.Segments[ii - jj]
if 'vsp_mesh' in wing.Segments[ii - jj]:
custom_flag = True
else:
custom_flag = False
wingtip_flag = True
add_segment_sources(comp, cr, ct, ii, u_start, num_secs,
custom_flag, wingtip_flag, seg)
pass
elif comp_type == 'fuselage':
fuselage = comp_dict[comp_name]
if 'vsp_mesh' in fuselage:
len1 = fuselage.vsp_mesh.length
rad1 = fuselage.vsp_mesh.radius
else:
len1 = 0.1 * 0.5 # not sure where VSP is getting this value
rad1 = 0.2 * fuselage.lengths.total
uloc = 0.0
wloc = 0.0
vsp.AddCFDSource(vsp.POINT_SOURCE, comp, 0, len1, rad1, uloc, wloc)
uloc = 1.0
vsp.AddCFDSource(vsp.POINT_SOURCE, comp, 0, len1, rad1, uloc, wloc)
pass
def vsp_read(tag, units_type='SI'):
"""This reads an OpenVSP vehicle geometry and writes it into a SUAVE vehicle format.
Includes wings, fuselages, and propellers.
Assumptions:
1. OpenVSP vehicle is composed of conventionally shaped fuselages, wings, and propellers.
1a. OpenVSP fuselage: generally narrow at nose and tail, wider in center).
1b. Fuselage is designed in VSP as it appears in real life. That is, the VSP model does not rely on
superficial elements such as canopies, stacks, or additional fuselages to cover up internal lofting oddities.
1c. This program will NOT account for multiple geometries comprising the fuselage. For example: a wingbox mounted beneath
is a separate geometry and will NOT be processed.
2. Fuselage origin is located at nose. VSP file origin can be located anywhere, preferably at the forward tip
of the vehicle or in front (to make all X-coordinates of vehicle positive).
3. Written for OpenVSP 3.16.1
Source:
N/A
Inputs:
1. A tag for an XML file in format .vsp3.
2. Units_type set to 'SI' (default) or 'Imperial'
Outputs:
Writes SUAVE vehicle with these geometries from VSP: (All values default to SI. Any other 2nd argument outputs Imperial.)
Wings.Wing. (* is all keys)
origin [m] in all three dimensions
spans.projected [m]
chords.root [m]
chords.tip [m]
aspect_ratio [-]
sweeps.quarter_chord [radians]
twists.root [radians]
twists.tip [radians]
thickness_to_chord [-]
dihedral [radians]
symmetric <boolean>
tag <string>
areas.exposed [m^2]
areas.reference [m^2]
areas.wetted [m^2]
Segments.
tag <string>
twist [radians]
percent_span_location [-] .1 is 10%
root_chord_percent [-] .1 is 10%
dihedral_outboard [radians]
sweeps.quarter_chord [radians]
thickness_to_chord [-]
airfoil <NACA 4-series, 6 series, or airfoil file>
Fuselages.Fuselage.
origin [m] in all three dimensions
width [m]
lengths.
total [m]
nose [m]
tail [m]
heights.
maximum [m]
at_quarter_length [m]
at_three_quarters_length [m]
effective_diameter [m]
fineness.nose [-] ratio of nose section length to fuselage effective diameter
fineness.tail [-] ratio of tail section length to fuselage effective diameter
areas.wetted [m^2]
tag <string>
segment[]. (segments are in ordered container and callable by number)
vsp.shape [point,circle,round_rect,general_fuse,fuse_file]
vsp.xsec_id <10 digit string>
percent_x_location
percent_z_location
height
width
length
effective_diameter
tag
vsp.xsec_num <integer of fuselage segment quantity>
vsp.xsec_surf_id <10 digit string>
Propellers.Propeller.
location[X,Y,Z] [radians]
rotation[X,Y,Z] [radians]
tip_radius [m]
hub_radius [m]
thrust_angle [radians]
Properties Used:
N/A
"""
vsp.ClearVSPModel()
vsp.ReadVSPFile(tag)
vsp_fuselages = []
vsp_wings = []
vsp_props = []
vsp_geoms = vsp.FindGeoms()
geom_names = []
vehicle = SUAVE.Vehicle()
vehicle.tag = tag
if units_type == 'SI':
units_type = 'SI'
else:
units_type = 'Imperial'
# The two for-loops below are in anticipation of an OpenVSP API update with a call for GETGEOMTYPE.
# This print function allows user to enter VSP GeomID manually as first argument in vsp_read functions.
print("VSP geometry IDs: ")
# Label each geom type by storing its VSP geom ID. (The API call for GETGEOMTYPE was not released as of 8/9/18, v 3.16.1)
for geom in vsp_geoms:
geom_name = vsp.GetGeomName(geom)
geom_names.append(geom_name)
print(str(geom_name) + ': ' + geom)
# -----------------------------
# MANUAL VSP ENTRY & PROCESSING
# -----------------------------
#fuselage = read_vsp_fuselage(fuselage_id, units_type=units_type) # Replace fuselage_id manually.
#vehicle.append_component(fuselage)
#wing = read_vsp_wing(wing_id, units_type=units_type) # Replace wing_id manually.
#vehicle.append_component(wing)
#prop = read_vsp_prop(prop_id, units_type=units_type) # Replace prop_id manually.
#vehicle.append_component(prop)
# --------------------------------
# AUTOMATIC VSP ENTRY & PROCESSING
# --------------------------------
#for geom in vsp_geoms:
#if vsp.GETGEOMTYPE(str(geom)) == 'FUSELAGE':
#vsp_fuselages.append(geom)
#if vsp.GETGEOMTYPE(str(geom)) == 'WING':
#vsp_wings.append(geom)
#if vsp.GETGEOMTYPE(str(geom)) == 'PROP':
#vsp_props.append(geom)
# Read VSP geoms and store in SUAVE components.
#for vsp_fuselage in vsp_fuselages:
#fuselage_id = vsp_fuselages[vsp_fuselage]
#fuselage = read_vsp_fuselage(fuselage_id, units_type)
#vehicle.append_component(fuselage)
#for vsp_wing in vsp_wings:
#wing_id = vsp_wings[vsp_wing]
#wing = read_vsp_wing(wing_id, units_type)
#vehicle.append_component(wing)
#for vsp_prop in vsp_props:
#prop_id = vsp_props[vsp_prop]
#prop = read_vsp_prop(prop_id, units_type)
#vehicle.append_component(prop)
return vehicle
