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
"""Test the OpenVSP Python Interface."""
from __future__ import print_function
import vsp as vsp
stdout = vsp.cvar.cstdout
errorMgr = vsp.ErrorMgrSingleton_getInstance()
# ==== Test Enums ==== #
print("SET_ALL = ", vsp.SET_ALL)
print("SET_SHOWN = ", vsp.SET_SHOWN)
print("SET_NOT_SHOWN = ", vsp.SET_NOT_SHOWN)
print("SET_FIRST_USER = "******"EXPORT_FELISA = ", vsp.EXPORT_FELISA)
print("EXPORT_XSEC = ", vsp.EXPORT_XSEC)
print("EXPORT_STL = ", vsp.EXPORT_STL)
print("EXPORT_AWAVE = ", vsp.EXPORT_AWAVE)
print("EXPORT_NASCART = ", vsp.EXPORT_NASCART)
print("EXPORT_POVRAY = ", vsp.EXPORT_POVRAY)
print("EXPORT_CART3D = ", vsp.EXPORT_CART3D)
print("EXPORT_VORXSEC = ", vsp.EXPORT_VORXSEC)
print("EXPORT_XSECGEOM = ", vsp.EXPORT_XSECGEOM)
print("EXPORT_GMSH = ", vsp.EXPORT_GMSH)
print("EXPORT_X3D = ", vsp.EXPORT_X3D)
print("EXPORT_STEP = ", vsp.EXPORT_STEP)
print("VSP_OK = ", vsp.VSP_OK)
print("VSP_INVALID_PTR = ", vsp.VSP_INVALID_PTR)
print("VSP_CANT_FIND_TYPE = ", vsp.VSP_CANT_FIND_TYPE)
print("VSP_CANT_FIND_PARM = ", vsp.VSP_CANT_FIND_PARM)
print("VSP_CANT_FIND_NAME = ", vsp.VSP_CANT_FIND_NAME)
print("VSP_INVALID_GEOM_ID = ", vsp.VSP_INVALID_GEOM_ID)
def write_vsp_fuselage(fuselage,area_tags, main_wing, fuel_tank_set_ind, OML_set_ind):
"""This writes a fuselage into OpenVSP format.
Assumptions:
None
Source:
N/A
Inputs:
fuselage
width [m]
lengths.total [m]
heights.
maximum [m]
at_quarter_length [m]
at_wing_root_quarter_chord [m]
at_three_quarters_length [m]
effective_diameter [m]
fineness.nose [-] ratio of nose section length to fuselage width
fineness.tail [-] ratio of tail section length to fuselage width
tag <string>
OpenVSP_values. (optional)
nose.top.angle [degrees]
nose.top.strength [-] this determines how much the specified angle influences that shape
nose.side.angle [degrees]
nose.side.strength [-]
nose.TB_Sym <boolean> determines if top angle is mirrored on bottom
nose.z_pos [-] z position of the nose as a percentage of fuselage length (.1 is 10%)
tail.top.angle [degrees]
tail.top.strength [-]
tail.z_pos (optional, 0.02 default) [-] z position of the tail as a percentage of fuselage length (.1 is 10%)
Segments. (optional)
width [m]
height [m]
percent_x_location [-] .1 is 10% length
percent_z_location [-] .1 is 10% length
area_tags <dict> used to keep track of all tags needed in wetted area computation
main_wing.origin [m]
main_wing.chords.root [m]
fuel_tank_set_index <int> OpenVSP object set containing the fuel tanks
Outputs:
Operates on the active OpenVSP model, no direct output
Properties Used:
N/A
"""
num_segs = len(fuselage.Segments)
length = fuselage.lengths.total
fuse_x = fuselage.origin[0][0]
fuse_y = fuselage.origin[0][1]
fuse_z = fuselage.origin[0][2]
fuse_x_rotation = fuselage.x_rotation
fuse_y_rotation = fuselage.y_rotation
fuse_z_rotation = fuselage.z_rotation
if num_segs==0: # SUAVE default fuselage shaping
width = fuselage.width
hmax = fuselage.heights.maximum
height1 = fuselage.heights.at_quarter_length
height2 = fuselage.heights.at_wing_root_quarter_chord
height3 = fuselage.heights.at_three_quarters_length
effdia = fuselage.effective_diameter
n_fine = fuselage.fineness.nose
t_fine = fuselage.fineness.tail
try:
if main_wing != None:
w_origin = main_wing.origin
w_c_4 = main_wing.chords.root/4.
else:
w_origin = 0.5*length
w_c_4 = 0.5*length
except AttributeError:
raise AttributeError('Main wing not detected. Fuselage must have specified sections in this configuration.')
# Figure out the location x location of each section, 3 sections, end of nose, wing origin, and start of tail
x1 = n_fine*width/length
x2 = (w_origin[0][0]+w_c_4)/length
x3 = 1-t_fine*width/length
end_ind = 4
else: # Fuselage shaping based on sections
widths = []
heights = []
x_poses = []
z_poses = []
segs = fuselage.Segments
for seg in segs:
widths.append(seg.width)
heights.append(seg.height)
x_poses.append(seg.percent_x_location)
z_poses.append(seg.percent_z_location)
end_ind = num_segs-1
fuse_id = vsp.AddGeom("FUSELAGE")
vsp.SetGeomName(fuse_id, fuselage.tag)
area_tags[fuselage.tag] = ['fuselages',fuselage.tag]
tail_z_pos = 0.02 # default value
# set fuselage relative location and rotation
vsp.SetParmVal( fuse_id,'X_Rel_Rotation','XForm',fuse_x_rotation)
vsp.SetParmVal( fuse_id,'Y_Rel_Rotation','XForm',fuse_y_rotation)
vsp.SetParmVal( fuse_id,'Z_Rel_Rotation','XForm',fuse_z_rotation)
vsp.SetParmVal( fuse_id,'X_Rel_Location','XForm',fuse_x)
vsp.SetParmVal( fuse_id,'Y_Rel_Location','XForm',fuse_y)
vsp.SetParmVal( fuse_id,'Z_Rel_Location','XForm',fuse_z)
if 'OpenVSP_values' in fuselage:
vals = fuselage.OpenVSP_values
# for wave drag testing
fuselage.OpenVSP_ID = fuse_id
# Nose
vsp.SetParmVal(fuse_id,"TopLAngle","XSec_0",vals.nose.top.angle)
vsp.SetParmVal(fuse_id,"TopLStrength","XSec_0",vals.nose.top.strength)
vsp.SetParmVal(fuse_id,"RightLAngle","XSec_0",vals.nose.side.angle)
vsp.SetParmVal(fuse_id,"RightLStrength","XSec_0",vals.nose.side.strength)
vsp.SetParmVal(fuse_id,"TBSym","XSec_0",vals.nose.TB_Sym)
vsp.SetParmVal(fuse_id,"ZLocPercent","XSec_0",vals.nose.z_pos)
if not vals.nose.TB_Sym:
vsp.SetParmVal(fuse_id,"BottomLAngle","XSec_0",vals.nose.bottom.angle)
vsp.SetParmVal(fuse_id,"BottomLStrength","XSec_0",vals.nose.bottom.strength)
# Tail
# Below can be enabled if AllSym (below) is removed
#vsp.SetParmVal(fuse_id,"RightLAngle","XSec_4",vals.tail.side.angle)
#vsp.SetParmVal(fuse_id,"RightLStrength","XSec_4",vals.tail.side.strength)
#vsp.SetParmVal(fuse_id,"TBSym","XSec_4",vals.tail.TB_Sym)
#vsp.SetParmVal(fuse_id,"BottomLAngle","XSec_4",vals.tail.bottom.angle)
#vsp.SetParmVal(fuse_id,"BottomLStrength","XSec_4",vals.tail.bottom.strength)
if 'z_pos' in vals.tail:
tail_z_pos = vals.tail.z_pos
else:
pass # use above default
if num_segs == 0:
vsp.SetParmVal(fuse_id,"Length","Design",length)
vsp.SetParmVal(fuse_id,"Diameter","Design",width)
vsp.SetParmVal(fuse_id,"XLocPercent","XSec_1",x1)
vsp.SetParmVal(fuse_id,"XLocPercent","XSec_2",x2)
vsp.SetParmVal(fuse_id,"XLocPercent","XSec_3",x3)
vsp.SetParmVal(fuse_id,"ZLocPercent","XSec_4",tail_z_pos)
vsp.SetParmVal(fuse_id, "Ellipse_Width", "XSecCurve_1", width)
vsp.SetParmVal(fuse_id, "Ellipse_Width", "XSecCurve_2", width)
vsp.SetParmVal(fuse_id, "Ellipse_Width", "XSecCurve_3", width)
vsp.SetParmVal(fuse_id, "Ellipse_Height", "XSecCurve_1", height1);
vsp.SetParmVal(fuse_id, "Ellipse_Height", "XSecCurve_2", height2);
vsp.SetParmVal(fuse_id, "Ellipse_Height", "XSecCurve_3", height3);
else:
# OpenVSP vals do not exist:
vals = Data()
vals.nose = Data()
vals.tail = Data()
vals.tail.top = Data()
vals.nose.z_pos = 0.0
vals.tail.top.angle = 0.0
vals.tail.top.strength = 0.0
if len(np.unique(x_poses)) != len(x_poses):
raise ValueError('Duplicate fuselage section positions detected.')
vsp.SetParmVal(fuse_id,"Length","Design",length)
if num_segs != 5: # reduce to only nose and tail
vsp.CutXSec(fuse_id,1) # remove extra default section
vsp.CutXSec(fuse_id,1) # remove extra default section
vsp.CutXSec(fuse_id,1) # remove extra default section
for i in range(num_segs-2): # add back the required number of sections
vsp.InsertXSec(fuse_id, 0, vsp.XS_ELLIPSE)
vsp.Update()
for i in range(num_segs-2):
# Bunch sections to allow proper length settings in the next step
# This is necessary because OpenVSP will not move a section past an adjacent section
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(i+1),1e-6*(i+1))
vsp.Update()
if x_poses[1] < (num_segs-2)*1e-6:
print('Warning: Second fuselage section is too close to the nose. OpenVSP model may not be accurate.')
for i in reversed(range(num_segs-2)):
# order is reversed because sections are initially bunched in the front and cannot be extended passed the next
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(i+1),x_poses[i+1])
vsp.SetParmVal(fuse_id, "ZLocPercent", "XSec_"+str(i+1),z_poses[i+1])
vsp.SetParmVal(fuse_id, "Ellipse_Width", "XSecCurve_"+str(i+1), widths[i+1])
vsp.SetParmVal(fuse_id, "Ellipse_Height", "XSecCurve_"+str(i+1), heights[i+1])
vsp.Update()
set_section_angles(i, vals.nose.z_pos, tail_z_pos, x_poses, z_poses, heights, widths,length,end_ind,fuse_id)
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(0),x_poses[0])
vsp.SetParmVal(fuse_id, "ZLocPercent", "XSec_"+str(0),z_poses[0])
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(end_ind),x_poses[-1])
vsp.SetParmVal(fuse_id, "ZLocPercent", "XSec_"+str(end_ind),z_poses[-1])
# Tail
if heights[-1] > 0.:
stdout = vsp.cvar.cstdout
errorMgr = vsp.ErrorMgrSingleton_getInstance()
errorMgr.PopErrorAndPrint(stdout)
pos = len(heights)-1
vsp.InsertXSec(fuse_id, pos-1, vsp.XS_ELLIPSE)
vsp.Update()
vsp.SetParmVal(fuse_id, "Ellipse_Width", "XSecCurve_"+str(pos), widths[-1])
vsp.SetParmVal(fuse_id, "Ellipse_Height", "XSecCurve_"+str(pos), heights[-1])
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(pos),x_poses[-1])
vsp.SetParmVal(fuse_id, "ZLocPercent", "XSec_"+str(pos),z_poses[-1])
xsecsurf = vsp.GetXSecSurf(fuse_id,0)
vsp.ChangeXSecShape(xsecsurf,pos+1,vsp.XS_POINT)
vsp.Update()
vsp.SetParmVal(fuse_id, "XLocPercent", "XSec_"+str(pos+1),x_poses[-1])
vsp.SetParmVal(fuse_id, "ZLocPercent", "XSec_"+str(pos+1),z_poses[-1])
# update strengths to make end flat
vsp.SetParmVal(fuse_id,"TopRStrength","XSec_"+str(pos), 0.)
vsp.SetParmVal(fuse_id,"RightRStrength","XSec_"+str(pos), 0.)
vsp.SetParmVal(fuse_id,"BottomRStrength","XSec_"+str(pos), 0.)
vsp.SetParmVal(fuse_id,"TopLStrength","XSec_"+str(pos+1), 0.)
vsp.SetParmVal(fuse_id,"RightLStrength","XSec_"+str(pos+1), 0.)
else:
vsp.SetParmVal(fuse_id,"TopLAngle","XSec_"+str(end_ind),vals.tail.top.angle)
vsp.SetParmVal(fuse_id,"TopLStrength","XSec_"+str(end_ind),vals.tail.top.strength)
vsp.SetParmVal(fuse_id,"AllSym","XSec_"+str(end_ind),1)
vsp.Update()
if 'z_pos' in vals.tail:
tail_z_pos = vals.tail.z_pos
else:
pass # use above default
if 'Fuel_Tanks' in fuselage:
for tank in fuselage.Fuel_Tanks:
write_fuselage_conformal_fuel_tank(fuse_id, tank, fuel_tank_set_ind)
vsp.SetSetFlag(fuse_id, OML_set_ind, True)
return area_tags