def wire_triangle2():
'''
isosceles triangle
output
w: TopoDS_Wire
'''
ang = random.gauss(2 * pi / 3, pi / 6)
amin = pi / 3
amax = 5 * pi / 6
if ang > amax:
ang = amax
if ang < amin:
ang = amin
pt1 = gp_Pnt(-1, 0, 0)
pt2 = gp_Pnt(-1, 0, 0)
pt2.Rotate(gp_OZ(), ang)
pt3 = gp_Pnt(-1, 0, 0)
pt3.Rotate(gp_OZ(), -ang)
ed1 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt1, pt2).Value()).Edge()
ed2 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt2, pt3).Value()).Edge()
ed3 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt3, pt1).Value()).Edge()
wire = BRepBuilderAPI_MakeWire(ed1, ed2, ed3).Wire()
return wire
def test_memory_handle_getobject(self):
"""
See https://github.com/tpaviot/pythonocc-generator/pull/24
This commit tries to fix the issue tpaviot/pythonocc-core#292.
When we got a handle from ann API function and called GetObject()
the lifetime of the object was determined only by the handle.
This lead to crashes, when only a reference to the object was stored.
The commit registers the handle with its object to prevent premature
destruction.
This test case ensures everything is ok. Following lines used to crash
on pythonocc-0.16.5
"""
a = gp_Pnt(0., 0., 0.)
b = gp_Pnt(100., 100., 100.)
line3 = GC_MakeSegment(a, b).Value().GetObject()
assert line3.FirstParameter() == 0.
assert GC_MakeSegment(a, b).Value().GetObject().FirstParameter() == 0.
assert GC_MakeSegment(a, b).Value().GetObject().GetHandle().GetObject(
).GetHandle().GetObject().FirstParameter() == 0.
assert b.IsEqual(line3.EndPoint(), 0.01)
assert b.IsEqual(
GC_MakeSegment(a, b).Value().GetObject().EndPoint(), 0.01)
assert b.IsEqual(
GC_MakeSegment(a, b).Value().GetObject().GetHandle().GetObject().
GetHandle().GetObject().EndPoint(), 0.01)
def __init__(
self,
HChord=0,
CentreLocation=[0, 0, 0],
ScarfAngle=3,
HighlightRadius=1.45,
MeanNacelleLength=5.67,
construct_geometry=True,
):
if HChord == 0:
print("No HChord specified to fit engine to: creating default")
SP = gp_Pnt(MeanNacelleLength * 2.2, 0, HighlightRadius * 1.75)
EP = gp_Pnt(MeanNacelleLength * 0.5, 0, HighlightRadius * 1.75)
HChord = GC_MakeSegment(SP, EP).Value()
# Add all kwargs as attributes
super(Engine, self).__init__(
components={},
construct_geometry=construct_geometry,
HChord=HChord,
CentreLocation=CentreLocation,
ScarfAngle=ScarfAngle,
HighlightRadius=HighlightRadius,
MeanNacelleLength=MeanNacelleLength,
)
def CutSect(Shape, SpanStation):
"""
Parameters
----------
Shape : TopoDS_Shape
The Shape to find planar cut section (parallel to xz plane)
SpanStation : scalar in range (0, 1)
y-direction location at which to cut Shape
Returns
-------
Section : result of OCC.BRepAlgoAPI.BRepAlgoAPI_Section (TopoDS_Shape)
The cut section of shape given a cut plane parallel to xz at input
Spanstation.
Chord : result of OCC.GC.GC_MakeSegment.Value (Geom_TrimmedCurve)
The Chord line between x direction extremeties
"""
(Xmin, Ymin, Zmin, Xmax, Ymax, Zmax) = ObjectsExtents([Shape])
YStation = Ymin + (Ymax - Ymin) * SpanStation
OriginX = Xmin - 1
OriginZ = Zmin - 1
P = gp_Pln(gp_Pnt(OriginX, YStation, OriginZ), gp_Dir(gp_Vec(0, 1, 0)))
# Note: using 2*extents here as previous +1 trimmed plane too short
CutPlaneSrf = make_face(P, 0, Zmax + 2, 0, Xmax + 2)
I = BRepAlgoAPI_Section(Shape, CutPlaneSrf)
I.ComputePCurveOn1(True)
I.Approximation(True)
I.Build()
Section = I.Shape()
(Xmin, Ymin, Zmin, Xmax, Ymax, Zmax) = ObjectsExtents([Section])
# Currently assume only one edge exists in the intersection:
exp = TopExp_Explorer(Section, TopAbs_EDGE)
edge = topods_Edge(exp.Current())
# Find the apparent chord of the section (that is, the line connecting the
# fore most and aftmost points on the curve
DivPoints = Uniform_Points_on_Curve(edge, 200)
Xs = np.array([pt.X() for pt in DivPoints])
min_idx = np.argmin(Xs)
LeadingPoint = gp_Pnt(Xs[min_idx], DivPoints[min_idx].Y(),
DivPoints[min_idx].Z())
max_idx = np.argmax(Xs)
TrailingPoint = gp_Pnt(Xs[max_idx], DivPoints[max_idx].Y(),
DivPoints[max_idx].Z())
HChord = GC_MakeSegment(TrailingPoint, LeadingPoint).Value()
# Chord = HChord.GetObject()
return Section, HChord
def update_shape(self, change):
d = self.declaration
points = self.get_points()
if len(points) > 1:
edges = []
for i in range(1, len(points)):
segment = GC_MakeSegment(points[i - 1], points[i]).Value()
edges.append(BRepBuilderAPI_MakeEdge(segment))
self.shape = edges
def wire_rectangle():
'''
output
w: TopoDS_Wire
'''
pt1 = gp_Pnt(0, 1, 0)
pt2 = gp_Pnt(-1, 0, 0)
pt3 = gp_Pnt(0, -1, 0)
pt4 = gp_Pnt(1, 0, 0)
ed1 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt1, pt2).Value()).Edge()
ed2 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt2, pt3).Value()).Edge()
ed3 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt3, pt4).Value()).Edge()
ed4 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt4, pt1).Value()).Edge()
wire = BRepBuilderAPI_MakeWire(ed1, ed2, ed3, ed4).Wire()
return wire
def create_shape(self):
d = self.declaration
points = [gp_Pnt(*p) for p in d.points]
if len(points) < 2:
raise ValueError("A segment requires at least two points")
edges = []
for i in range(1, len(points)):
segment = GC_MakeSegment(points[i - 1], points[i]).Value()
edges.append(BRepBuilderAPI_MakeEdge(segment))
self.shape = edges
def wire_triangle3():
'''
equal sided triangle, centered at origin
output
w: TopoDS_Wire
'''
pt1 = gp_Pnt(-1, 0, 0)
pt2 = gp_Pnt(-1, 0, 0)
pt2.Rotate(gp_OZ(), 2 * pi / 3)
pt3 = gp_Pnt(-1, 0, 0)
pt3.Rotate(gp_OZ(), 4 * pi / 3)
ed1 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt1, pt2).Value()).Edge()
ed2 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt2, pt3).Value()).Edge()
ed3 = BRepBuilderAPI_MakeEdge(GC_MakeSegment(pt3, pt1).Value()).Edge()
wire = BRepBuilderAPI_MakeWire(ed1, ed2, ed3).Wire()
return wire
def _TransformAirfoil(self):
"""Given a normal airfoil, nose in origin, chord along
x axis, applies rotations, translation and (soon) smoothing
"""
# TODO: Smoothing
# for i in range(self.SmoothingIterations):
# rs.FairCurve(self.Curve)
# Can assume that the chord is from 0,0,0 to 1,0,0 before translation
h_ChordLine = GC_MakeSegment(gp_Pnt(0, 0, 0), gp_Pnt(1, 0, 0)).Value()
ChordLine = h_ChordLine.GetObject()
Curve = self.Curve.GetObject()
# Scaling:
Curve.Scale(gp_Pnt(0, 0, 0), self.ChordLength)
ChordLine.Scale(gp_Pnt(0, 0, 0), self.ChordLength)
# Rotations - Note that direction is opposite to Rhino
# Dihedral:
if self.Rotation:
Curve.Rotate(gp_OX(), np.radians(self.Rotation))
ChordLine.Rotate(gp_OX(), np.radians(self.Rotation))
# Twist:
if self.Twist:
Curve.Rotate(gp_OY(), -np.radians(self.Twist))
ChordLine.Rotate(gp_OY(), -np.radians(self.Twist))
# Translation:
# self.Curve = Handle_Geom_BSplineCurve_DownCast(Curve.Translated(
# gp_Vec(*self.LE))
# )
Curve.Translate(gp_Vec(*self.LE))
ChordLine.Translate(gp_Vec(*self.LE))
self.ChordLine = ChordLine.GetHandle()
return None
def _BuildPanels(self, ChordFactor, ScaleFactor):
LESpar, TESpar, MIDSpar, StringerUp, StringerDown, PointsUp, PointsDown = self._BuildSpars(
self.ChordFactor, self.ScaleFactor)
PanelUp = []
PanelDown = []
cont = 1
for ii in range(0, len(PointsUp) - self.NoStiffners - 1):
if cont == self.NoStiffners:
cont = 0
else:
cont = cont
# Panel from segments
SegH1 = GC_MakeSegment(
PointsUp[ii], PointsUp[ii + self.NoStiffners]).Value()
SegH2 = GC_MakeSegment(PointsUp[ii + 1],
PointsUp[ii + self.NoStiffners +
1]).Value()
SegV1 = GC_MakeSegment(PointsUp[ii], PointsUp[ii + 1]).Value()
SegV2 = GC_MakeSegment(PointsUp[ii + self.NoStiffners],
PointsUp[ii + self.NoStiffners +
1]).Value()
EdgeHUp1 = act.make_edge(SegH1)
EdgeHUp2 = act.make_edge(SegH2)
EdgeVUp1 = act.make_edge(SegV1)
EdgeVUp2 = act.make_edge(SegV2)
WirePanelUp = act.make_wire(
[EdgeHUp1, EdgeVUp1, EdgeHUp2, EdgeVUp2])
PanelUpi = act.make_face(WirePanelUp)
# In this way the pannel will be ordered in alternance between upper and lower surface
SegH1 = GC_MakeSegment(
PointsDown[ii], PointsDown[ii + self.NoStiffners]).Value()
SegH2 = GC_MakeSegment(PointsDown[ii + 1],
PointsDown[ii + self.NoStiffners +
1]).Value()
SegV1 = GC_MakeSegment(PointsDown[ii],
PointsDown[ii + 1]).Value()
SegV2 = GC_MakeSegment(PointsDown[ii + self.NoStiffners],
PointsDown[ii + self.NoStiffners +
1]).Value()
EdgeHUp1 = act.make_edge(SegH1)
EdgeHUp2 = act.make_edge(SegH2)
EdgeVUp1 = act.make_edge(SegV1)
EdgeVUp2 = act.make_edge(SegV2)
WirePanelDown = act.make_wire(
[EdgeHUp1, EdgeVUp1, EdgeHUp2, EdgeVUp2])
PanelDowni = act.make_face(WirePanelDown)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
PanelUpi = act.scale_uniformal(PanelUpi, Origin,
self.ScaleFactor)
PanelDowni = act.scale_uniformal(PanelDowni, Origin,
self.ScaleFactor)
PanelUp.append(PanelUpi)
PanelDown.append(PanelDowni)
cont = cont + 1
return PanelUp, PanelDown
def _BuildRibs(self, ChordFactor, ScaleFactor):
"""Generates Ribs surface along the wingspan, given the general,
nondimensional parameters of the object (variations of chord length,
dihedral, etc.) and the two scaling factors.
Parameters
----------
ChordFactor - float
Factor againt which the standard shape is scaled in the chordwise
direction
ScaleFactor - float
Factor againt which the standard shape is scaled in the world
coordinates
Returns
-------
Ribs : TopoDS_Shape
The generated Ribs surface
"""
SectionsRibs = []
RibsFace = []
Step = (self.SegmentNoLoft) / (self.NoRibs - 1)
LEPointsR = self._GenerateLeadingEdge()
Eps = np.linspace(0, 1, self.SegmentNoLoft + 1)
SectionsRibs = [
self.AirfoilFunct(Eps[i], LEPointsR[i], self.ChordFunct,
ChordFactor, self.DihedralFunct,
self.TwistFunct).Curve
for i in xrange(0, self.SegmentNoLoft + 1, Step)
]
LESpar, TESpar, MIDSpar, StringerUp, StringerDown, PointsUp, PointsDown = self._BuildSpars(
self.ChordFactor, self.ScaleFactor)
# RIBS generated from segments
for i in range(0, self.NoRibs):
for ii in range(0, self.NoStiffners - 1):
SegUp = GC_MakeSegment(
PointsUp[ii + i * self.NoStiffners * (Step)],
PointsUp[ii + i * self.NoStiffners * (Step) + 1]).Value()
SegDown = GC_MakeSegment(
PointsDown[ii + i * self.NoStiffners * (Step) + 1],
PointsDown[ii + i * self.NoStiffners * (Step)]).Value()
SegSide1 = GC_MakeSegment(
PointsDown[ii + i * self.NoStiffners * (Step)],
PointsUp[ii + i * self.NoStiffners * (Step)]).Value()
SegSide2 = GC_MakeSegment(
PointsUp[ii + i * self.NoStiffners * (Step) + 1],
PointsDown[ii + i * self.NoStiffners * (Step) +
1]).Value()
EdgeSegUp = act.make_edge(SegUp)
EdgeSegDown = act.make_edge(SegDown)
EdgeSide1 = act.make_edge(SegSide1)
EdgeSide2 = act.make_edge(SegSide2)
WireRib = act.make_wire(
[EdgeSide1, EdgeSegUp, EdgeSide2, EdgeSegDown])
FaceRibi = act.make_face(WireRib)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
FaceRib = act.scale_uniformal(FaceRibi, Origin,
self.ScaleFactor)
RibsFace.append(FaceRib)
return SectionsRibs, RibsFace
def _BuildSpars(self, ChordFactor, ScaleFactor):
LE = self._GenerateLeadingEdge()
self.NoStiffners = self.NoStiffnersLE + self.NoStiffnersTE
SectionsProfiles = []
SparLEFullWing = []
SparTEFullWing = []
SparMIDFullWing = []
SparLEup = []
SparLEdown = []
SparMIDup = []
SparMIDdown = []
SparTEup = []
SparTEdown = []
planeStiffEps = []
PStiffUpFullWing = []
PStiffDownFullWing = []
StringerUpFullWing = []
StringerDownFullWing = []
EpsS = np.linspace(0, 1, self.SegmentNoLoft + 1)
SectionsProfiles = [
self.AirfoilFunct(EpsS[d], LE[d], self.ChordFunct, ChordFactor,
self.DihedralFunct, self.TwistFunct).Curve
for d in xrange(self.SegmentNoLoft + 1)
]
# Stringers generation
h = 0
cont3 = 0
PointsUp = []
PointsDown = []
PointsMIDup = []
PointsMIDdown = []
for SecR in SectionsProfiles:
ChordLenght = ((ChordFactor * self.ChordFunct(EpsS[h])) /
np.cos(np.radians(self.TwistFunct(EpsS[h]))))
LELengthX = LE[h, 0]
LEplanePositionX = (self.PositionLESpar * ChordLenght) * np.cos(
self.TwistFunct(EpsS[h])) + LELengthX
TEplanePositionX = (self.PositionTESpar * ChordLenght) * np.cos(
self.TwistFunct(EpsS[h])) + LELengthX
MIDplanePositionX = (self.PositionMIDSpar * ChordLenght) * np.cos(
self.TwistFunct(EpsS[h])) + LELengthX
planeLEi = Geom_Plane(
gp_Pln(gp_Pnt(LEplanePositionX, 0., 0.),
gp_Dir(gp_Vec(gp_Pnt(0., 0., 0.), gp_Pnt(1., 0., 0.)))))
planeMIDi = Geom_Plane(
gp_Pln(gp_Pnt(MIDplanePositionX, 0., 0.),
gp_Dir(gp_Vec(gp_Pnt(0., 0., 0.), gp_Pnt(1., 0., 0.)))))
planeTEi = Geom_Plane(
gp_Pln(gp_Pnt(TEplanePositionX, 0., 0.),
gp_Dir(gp_Vec(gp_Pnt(0., 0., 0.), gp_Pnt(1., 0., 0.)))))
# planeLEi.Rotate(gp_OY(), -np.radians(self.TwistFunct(EpsS[h])))
# planeMIDi.Rotate(gp_OY(), -np.radians(self.TwistFunct(EpsS[h])))
# planeTEi.Rotate(gp_OY(), -np.radians(self.TwistFunct(EpsS[h])))
SegmentStiffLE = (MIDplanePositionX -
LEplanePositionX) / (self.NoStiffnersLE - 1)
SegmentStiffTE = (TEplanePositionX -
MIDplanePositionX) / (self.NoStiffnersTE)
NoStiffners = self.NoStiffnersLE + self.NoStiffnersTE
PStiffUpi = []
PStiffDowni = []
PosStiffiEps = LEplanePositionX
for g in xrange(NoStiffners):
planeStiffEps = Geom_Plane(
gp_Pln(
gp_Pnt(PosStiffiEps, 0., 0.),
gp_Dir(gp_Vec(gp_Pnt(0., 0., 0.), gp_Pnt(1., 0.,
0.)))))
StiffiEps = GeomAPI_IntCS(SecR, planeStiffEps.GetHandle())
with act.assert_isdone(StiffiEps,
'failed to calculate intersection'):
nb_results = StiffiEps.NbPoints()
if nb_results == 1:
return StiffiEps.Point(1)
#print("One point intersection")
elif nb_results >= 1:
#print("More than one intersection point")
PStiff = []
for i in range(1, nb_results + 1):
PStiff.append(StiffiEps.Point(i))
else:
return None
PStiffUpi.append(PStiff[0])
PStiffDowni.append(PStiff[nb_results - 1])
if g <= self.NoStiffnersLE - 2:
PosStiffiEps = PosStiffiEps + SegmentStiffLE
else:
PosStiffiEps = PosStiffiEps + SegmentStiffTE
PointsUp.append(PStiff[0])
PointsDown.append(PStiff[nb_results - 1])
SparLEi = GeomAPI_IntCS(SecR, planeLEi.GetHandle())
with act.assert_isdone(SparLEi,
'failed to calculate intersection'):
nb_results = SparLEi.NbPoints()
#print(nb_results)
if nb_results == 1:
return SparLEi.Point(1)
#print("One point intersection")
elif nb_results >= 1:
#print("More than one intersection point")
PLE = []
for i in range(1, nb_results + 1):
PLE.append(SparLEi.Point(i))
else:
return None
SegLE = GC_MakeSegment(PLE[0], PLE[nb_results - 1]).Value()
SparMIDi = GeomAPI_IntCS(SecR, planeMIDi.GetHandle())
with act.assert_isdone(SparMIDi,
'failed to calculate intersection'):
nb_results = SparMIDi.NbPoints()
#print(nb_results)
if nb_results == 1:
return SparMIDi.Point(1)
#print("One point intersection")
elif nb_results >= 1:
#print("More than one intersection point")
PMID = []
for i in range(1, nb_results + 1):
PMID.append(SparMIDi.Point(i))
else:
return None
SegMID = GC_MakeSegment(PMID[0], PMID[nb_results - 1]).Value()
PointsMIDup.append(PMID[0])
PointsMIDdown.append(PMID[nb_results - 1])
SparTEi = GeomAPI_IntCS(SecR, planeTEi.GetHandle())
with act.assert_isdone(SparTEi,
'failed to calculate intersection'):
nb_results = SparTEi.NbPoints()
#print(nb_results)
if nb_results == 1:
return SparTEi.Point(1)
#print("One point intersection")
elif nb_results >= 1:
#print("More than one intersection point")
PTE = []
for i in range(1, nb_results + 1):
PTE.append(SparTEi.Point(i))
else:
return None
SegTE = GC_MakeSegment(PTE[0], PTE[nb_results - 1]).Value()
#print(len(SparMIDdown))
#print(len(SparMIDup))
#print(len(SparLEup))
#print(len(SparLEdown))
SparLEFullWing.append(SegLE)
SparMIDFullWing.append(SegMID)
SparTEFullWing.append(SegTE)
SparLEup.append(PLE[0])
SparLEdown.append(PLE[nb_results - 1])
SparMIDup.append(PMID[0])
#print(PMID[nb_results-1])
SparMIDdown.append(PMID[nb_results - 1])
SparTEup.append(PTE[0])
SparTEdown.append(PTE[nb_results - 1])
PStiffUpFullWing.append(PStiffUpi)
PStiffDownFullWing.append(PStiffDowni)
cont3 = cont3 + 1
h = h + 1
# Method to create spars - VIA SEGMENTS
#LE
LoftLESparFullWing = []
for iii in xrange(0,
len(PointsUp) - 2 * (self.NoStiffners - 1),
self.NoStiffners):
SegUp = GC_MakeSegment(PointsUp[iii],
PointsUp[iii + self.NoStiffners]).Value()
SegDown = GC_MakeSegment(PointsDown[iii + self.NoStiffners],
PointsDown[iii]).Value()
SegSide1 = GC_MakeSegment(PointsDown[iii], PointsUp[iii]).Value()
SegSide2 = GC_MakeSegment(PointsUp[iii + self.NoStiffners],
PointsDown[iii +
self.NoStiffners]).Value()
EdgeSegUp = act.make_edge(SegUp)
EdgeSegDown = act.make_edge(SegDown)
EdgeSide1 = act.make_edge(SegSide1)
EdgeSide2 = act.make_edge(SegSide2)
WireSparLE = act.make_wire(
[EdgeSide1, EdgeSegUp, EdgeSide2, EdgeSegDown])
FaceSparLEi = act.make_face(WireSparLE)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
FaceSparLE = act.scale_uniformal(FaceSparLEi, Origin,
self.ScaleFactor)
LoftLESparFullWing.append(FaceSparLE)
#MID
LoftMIDSparFullWing = []
for iii in xrange(0, self.SegmentNoLoft):
SegUp = GC_MakeSegment(PointsMIDup[iii],
PointsMIDup[iii + 1]).Value()
SegDown = GC_MakeSegment(PointsMIDdown[iii + 1],
PointsMIDdown[iii]).Value()
SegSide1 = GC_MakeSegment(PointsMIDdown[iii],
PointsMIDup[iii]).Value()
SegSide2 = GC_MakeSegment(PointsMIDup[iii + 1],
PointsMIDdown[iii + 1]).Value()
EdgeSegUp = act.make_edge(SegUp)
EdgeSegDown = act.make_edge(SegDown)
EdgeSide1 = act.make_edge(SegSide1)
EdgeSide2 = act.make_edge(SegSide2)
WireSparMID = act.make_wire(
[EdgeSide1, EdgeSegUp, EdgeSide2, EdgeSegDown])
FaceSparMIDi = act.make_face(WireSparMID)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
FaceSparMID = act.scale_uniformal(FaceSparMIDi, Origin,
self.ScaleFactor)
LoftMIDSparFullWing.append(FaceSparMID)
#TE
LoftTESparFullWing = []
for iii in xrange(self.NoStiffners - 1,
len(PointsUp) - (self.NoStiffners),
self.NoStiffners):
SegUp = GC_MakeSegment(PointsUp[iii],
PointsUp[iii + self.NoStiffners]).Value()
SegDown = GC_MakeSegment(PointsDown[iii + self.NoStiffners],
PointsDown[iii]).Value()
SegSide1 = GC_MakeSegment(PointsDown[iii], PointsUp[iii]).Value()
SegSide2 = GC_MakeSegment(PointsUp[iii + self.NoStiffners],
PointsDown[iii +
self.NoStiffners]).Value()
EdgeSegUp = act.make_edge(SegUp)
EdgeSegDown = act.make_edge(SegDown)
EdgeSide1 = act.make_edge(SegSide1)
EdgeSide2 = act.make_edge(SegSide2)
WireSparTE = act.make_wire(
[EdgeSide1, EdgeSegUp, EdgeSide2, EdgeSegDown])
FaceSparTEi = act.make_face(WireSparTE)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
FaceSparTE = act.scale_uniformal(FaceSparTEi, Origin,
self.ScaleFactor)
LoftTESparFullWing.append(FaceSparTE)
for g in range(self.NoStiffners):
for gg in range(self.SegmentNoLoft):
SegStringerUp = GC_MakeSegment(
PointsUp[gg * self.NoStiffners + g],
PointsUp[gg * self.NoStiffners + g +
self.NoStiffners]).Value()
SegStringerDown = GC_MakeSegment(
PointsDown[gg * self.NoStiffners + g],
PointsDown[gg * self.NoStiffners + g +
self.NoStiffners]).Value()
EdgeUp = act.make_edge(SegStringerUp)
EdgeDown = act.make_edge(SegStringerDown)
WireStringUp = act.make_wire(EdgeUp)
WireStringDown = act.make_wire(EdgeDown)
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
StrUpFullWingi = act.scale_uniformal(
WireStringUp, Origin, self.ScaleFactor)
StrDownFullWingi = act.scale_uniformal(
WireStringDown, Origin, self.ScaleFactor)
#print('hello')
#print(self.ScaleFactor)
StringerUpFullWing.append(StrUpFullWingi)
StringerDownFullWing.append(StrDownFullWingi)
return LoftLESparFullWing, LoftTESparFullWing, LoftMIDSparFullWing, StringerUpFullWing, StringerDownFullWing, PointsUp, PointsDown
return Handle_Geom_Plane.DownCast(BRep_Tool_Surface(aFace)).GetObject() height = 70 width = 50 thickness = 30 # The points we'll use to create the profile of the bottle's body aPnt1 = gp_Pnt(-width / 2.0, 0, 0) aPnt2 = gp_Pnt(-width / 2.0, -thickness / 4.0, 0) aPnt3 = gp_Pnt(0, -thickness / 2.0, 0) aPnt4 = gp_Pnt(width / 2.0, -thickness / 4.0, 0) aPnt5 = gp_Pnt(width / 2.0, 0, 0) aArcOfCircle = GC_MakeArcOfCircle(aPnt2, aPnt3, aPnt4) aSegment1 = GC_MakeSegment(aPnt1, aPnt2) aSegment2 = GC_MakeSegment(aPnt4, aPnt5) # Could also construct the line edges directly using the points # instead of the resulting line aEdge1 = BRepBuilderAPI_MakeEdge(aSegment1.Value()) aEdge2 = BRepBuilderAPI_MakeEdge(aArcOfCircle.Value()) aEdge3 = BRepBuilderAPI_MakeEdge(aSegment2.Value()) # Create a wire out of the edges aWire = BRepBuilderAPI_MakeWire(aEdge1.Edge(), aEdge2.Edge(), aEdge3.Edge()) # Quick way to specify the X axis xAxis = gp_OX() # Set up the mirror
display, start_display = init_display()[:2] myWidth = 50 myHeight = 70 myThickness = 30 # Profile : Define Support Points aPnt1 = gp_Pnt(-myWidth / 2, 0, 0) aPnt2 = gp_Pnt(-myWidth / 2, -myThickness / 4, 0) aPnt3 = gp_Pnt(0, -myThickness / 2, 0) aPnt4 = gp_Pnt(myWidth / 2, -myThickness / 4, 0) aPnt5 = gp_Pnt(myWidth / 2, 0, 0) # Profile : Define the Geometry aArcOfCircle = GC_MakeArcOfCircle(aPnt2, aPnt3, aPnt4) aSegment1 = GC_MakeSegment(aPnt1, aPnt2) aSegment2 = GC_MakeSegment(aPnt4, aPnt5) # Profile : Define the Topology aEdge1 = MakeEdge(aSegment1.Value()) aEdge2 = MakeEdge(aArcOfCircle.Value()) aEdge3 = MakeEdge(aSegment2.Value()) aWire = MakeWire(aEdge1.Edge(), aEdge2.Edge(), aEdge3.Edge()) # Complete Profile xAxis = OCC.gp.gp_OX() aTrsf = OCC.gp.gp_Trsf() aTrsf.SetMirror(xAxis) aBRepTrsf = Transform(aWire.Wire(), aTrsf) aMirroredShape = aBRepTrsf.Shape() aMirroredWire = OCC.TopoDS.TopoDS_Shape(aMirroredShape)
from OCC.GC import GC_MakeLine
display, start_display, add_menu, add_function_to_menu = init_display(
'qt-pyqt5', (1024, 768))
my_box = BRepPrimAPI_MakeBox(10., 20., 30.).Shape()
pnt1 = gp_Pnt(-1, -1, 40)
pnt2 = gp_Pnt(-1, -10, 40)
origin = gp_Pnt(0, 0, 0)
xdirection = gp_Dir(1, 0, 0)
xaxis = gp.OX()
t = gp_Trsf()
t.SetMirror(xaxis)
xline = GC_MakeLine(gp.OX()).Value()
geom_curve = GC_MakeSegment(pnt1, pnt2).Value()
bt = BRepBuilderAPI_Transform(my_box, t)
# what about a geom line!?
# ok what about something rotated?
#edge = BRepBuilderAPI_MakeEdge(10)
#my_box2 = BRepPrimAPI_MakeBox(5., 5., 5.).Shape()
#wire = BRepBuilderAPI_MakeWire(10, 10).Shape()
def f():
display.DisplayShape(geom_curve, update=True)
display.DisplayShape(bt.Shape(), update=True)
QTimer().singleShot(300, f)
display.DisplayShape(GC_MakeLine(gp.OX()).Value())
def BuildTurbofanNacelle(self):
"""
The defaults yield a nacelle similar to that of an RR Trent 1000 / GEnx
#TODO: break this down into modular function calls
"""
CentreLocation = self.CentreLocation
MeanNacelleLength = self.MeanNacelleLength
HighlightRadius = self.HighlightRadius
HighlightDepth = 0.12 * self.MeanNacelleLength
SectionNo = 100
# Draw the nacelle with centre of the intake highlight circle in 0,0,0
HHighlight = act.make_circle3pt([0, 0, HighlightRadius],
[0, -HighlightRadius, 0],
[0, 0, -HighlightRadius])
Highlight = HHighlight.GetObject()
HHighlightCutterCircle = \
act.make_circle3pt([0, 0, HighlightRadius * 1.5],
[0, -HighlightRadius * 1.5, 0],
[0, 0, -HighlightRadius * 1.5])
HighlightCutterCircle = HHighlightCutterCircle.GetObject()
# Fan disk for CFD boundary conditions
FanCircle = Handle_Geom_Circle.DownCast(
Highlight.Translated(gp_Vec(MeanNacelleLength * 0.25, 0, 0)))
wire = act.make_wire(act.make_edge(FanCircle))
FanDisk = act.make_face(wire)
self.AddComponent(FanDisk, 'FanDisk')
# Aft outflow for CFD boundary conditions
BypassCircle = Handle_Geom_Circle.DownCast(
Highlight.Translated(gp_Vec(MeanNacelleLength * 0.85, 0, 0)))
wire = act.make_wire(act.make_edge(BypassCircle))
BypassDisk = act.make_face(wire)
self.AddComponent(BypassDisk, 'BypassDisk')
# Outflow cone
TailConeBasePoint = np.array([MeanNacelleLength * 0.84, 0, 0])
TailConeHeight = MeanNacelleLength * (1.35 - 0.84)
TailConeRadius = HighlightRadius * 0.782
TailCone = act.AddCone(TailConeBasePoint, TailConeRadius,
TailConeHeight)
self.AddComponent(TailCone, 'TailCone')
# Spinner cone
SpinnerConeBasePoint = np.array([MeanNacelleLength * 0.26, 0, 0])
SpinnerConeHeight = MeanNacelleLength * (0.26 - 0.08)
SpinnerConeRadius = MeanNacelleLength * 0.09
Spinner = act.AddCone(SpinnerConeBasePoint,
SpinnerConeRadius,
SpinnerConeHeight,
direction=gp_Dir(-1, 0, 0))
self.AddComponent(Spinner, 'Spinner')
#
# Tilt the intake
RotAx = gp_OY()
Highlight.Rotate(RotAx, np.radians(self.ScarfAngle))
# # Set up the disk for separating the intake lip later
HighlightCutterCircle.Rotate(RotAx, np.radians(self.ScarfAngle))
HighlightCutterDisk = act.PlanarSurf(HighlightCutterCircle)
HighlightCutterDisk =\
act.translate_topods_from_vector(HighlightCutterDisk,
gp_Vec(HighlightDepth, 0, 0))
# Build the actual airfoil sections to define the nacelle
HighlightPointVector = act.Uniform_Points_on_Curve(
Highlight.GetHandle(), SectionNo)
Sections = []
TailPoints = []
Twist = 0
AirfoilSeligName = 'goe613'
Rotations = np.linspace(0, 360, SectionNo)
for i, pt in enumerate(HighlightPointVector):
AfChord = MeanNacelleLength - pt.X()
Af = primitives.Airfoil([pt.X(), pt.Y(), pt.Z()],
AfChord,
Rotations[i],
Twist,
SeligProfile=AirfoilSeligName).Curve
Sections.append(Af)
TailPoints.append(Af.GetObject().EndPoint())
self._sections = Sections
# # Build the actual nacelle OML surface
# EndCircle = act.points_to_bspline(TailPoints) #Dont need this?
# self._EndCircle = EndCircle
Nacelle = act.AddSurfaceLoft(Sections)
self.AddComponent(Nacelle, 'Nacelle')
# TODO: Separate the lip
# Cowling, HighlightSection = act.TrimShapebyPlane(Nacelle,
# HighlightCutterDisk,
# True)
# Move the engine into its actual place on the wing
self.TranslateComponents(gp_Vec(*CentreLocation))
# Now build the pylon between the engine and the chord on the wing
CP1 = gp_Pnt(MeanNacelleLength * 0.26 + CentreLocation[0],
CentreLocation[1],
CentreLocation[2] + HighlightRadius * 0.1)
CP2 = gp_Pnt(MeanNacelleLength * 0.4 + CentreLocation[0],
CentreLocation[1],
HighlightRadius * 1.45 + CentreLocation[2])
# Get the chord from its handle
Chord = self.HChord.GetObject()
CP3 = Chord.EndPoint()
CP4 = Chord.StartPoint()
self._pylonPts = [CP1, CP2, CP3, CP4]
# Pylon wireframe
tangents = np.array([[0, 0, 1], [1, 0, 0]])
PylonTop = act.points_to_bspline([CP1, CP2, CP3, CP4],
tangents=tangents)
self._PylonTop = PylonTop
PylonBase_LE = [CP1.X(), CP1.Y(), CP1.Z()]
PylonAf = primitives.Airfoil(PylonBase_LE,
MeanNacelleLength * 1.35,
90,
0,
Naca4Profile='0012',
EnforceSharpTE=False)
self._PylonAf = PylonAf
LowerTE = PylonAf.ChordLine.GetObject().EndPoint()
# LowerTE = rs.CurveEndPoint(PylonChord)
PylonTE = GC_MakeSegment(LowerTE, CP4).Value()
self._PylonTE = PylonTE
edges = [
act.make_edge(PylonAf.ChordLine),
act.make_edge(PylonTop),
act.make_edge(PylonTE)
]
Pylon_symplane = act.make_face(act.make_wire(*edges))
self.AddComponent(Pylon_symplane, 'Pylon_symplane')
# TODO: Pylon surface. Currently a flat plate at symmetry plane.
# This should be done with a plate surface (similar to NetworkSrf in
# Rhino), but I haven't got this to work yet
# Method 1: Sweep - gives the wrong shape
# Pylon_tip = GC_MakeCircle(gp_Ax1(CP4, gp_Dir(0, 1, 0)),
# PylonAf.ChordLength*0.001
# ).Value()
#
# Pylon_curve = PylonAf.Curve.GetObject()
# PylonAf_TE = act.make_edge(Pylon_curve.StartPoint(),
# Pylon_curve.EndPoint())
# PylonAf_Face = act.PlanarSurf(PylonAf.Curve)
# PylonAf_closedwire = act.make_wire(act.make_edge(PylonAf.Curve),
# PylonAf_TE)
# sections = [PylonAf.Curve, PylonTE]
# spine = act.make_wire(act.make_edge(PylonTop))
# self.PylonLeft = act.make_pipe_shell(spine, sections)
#
# Move into place under the wing
# self._Translate(gp_Vec(0,-CentreLocation[1],0))
#
# TODO: Mirror the pylon half surface
# PylonRight = act.mirror(PylonLeft, plane='xz')
# PylonAfCurve = act.AddTEtoOpenAirfoil(PylonAfCurve)
# PylonAfSrf = rs.AddPlanarSrf(PylonAfCurve)
return None