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)
# Add Fuse
fuse_id = vsp.AddGeom("FUSELAGE")
# Get XSec Surf ID
xsurf_id = vsp.GetXSecSurf(fuse_id, 0)
# Change Type of First XSec
vsp.ChangeXSecShape(xsurf_id, 0, vsp.XS_SUPER_ELLIPSE)
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
