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 _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 rotate_shp_3_axis(shape, rx, ry, rz, unity="deg"):
""" Rotate a shape around (O,x), (O,y) and (O,z).
@param rx_degree : rotation around (O,x)
@param ry_degree : rotation around (O,y)
@param rz_degree : rotation around (O,z)
@return : the rotated shape.
"""
if unity == "deg": # convert angle to radians
rx = radians(rx)
ry = radians(ry)
rz = radians(rz)
alpha = gp_Trsf()
alpha.SetRotation(gp_OX(), rx)
beta = gp_Trsf()
beta.SetRotation(gp_OY(), ry)
gamma = gp_Trsf()
gamma.SetRotation(gp_OZ(), rz)
brep_trns = BRepBuilderAPI_Transform(shape, alpha*beta*gamma, False)
shp = brep_trns.Shape()
return shp
def rotate_shp_3_axis(shape, rx, ry, rz, unity="deg"):
""" Rotate a shape around (O,x), (O,y) and (O,z).
@param rx_degree : rotation around (O,x)
@param ry_degree : rotation around (O,y)
@param rz_degree : rotation around (O,z)
@return : the rotated shape.
"""
if unity == "deg": # convert angle to radians
rx = radians(rx)
ry = radians(ry)
rz = radians(rz)
alpha = gp_Trsf()
alpha.SetRotation(gp_OX(), rx)
beta = gp_Trsf()
beta.SetRotation(gp_OY(), ry)
gamma = gp_Trsf()
gamma.SetRotation(gp_OZ(), rz)
brep_trns = BRepBuilderAPI_Transform(shape, alpha*beta*gamma, False)
shp = brep_trns.Shape()
return shp
lim_coord1 = (xmin, xmax)
lim_coord2 = (ymin, ymax)
section_height = zmax - 0.18
# A horizontal plane is created from which a face is constructed to intersect with
# the building. The face is transparently displayed along with the building.
section_plane = gp_Pln(gp_Pnt(0, 0, section_height), gp_Dir(0, 0, 1))
section_face = BRepBuilderAPI_MakeFace(section_plane, xmin, xmax, ymin,
ymax).Face()
plt.figure()
plt.xlim(lim_coord1)
plt.ylim(lim_coord2)
# Quick way to specify the Y axis
xAxis = gp_OY()
# Set up the mirror
aTrsf = gp_Trsf()
aTrsf.SetMirror(xAxis)
# Explore the faces of the shape (these are known to be named)
exp = TopExp_Explorer(shape, TopAbs_FACE)
while exp.More():
s = exp.Current()
tp = Topo(s)
for face in tp.faces():
section = BRepAlgoAPI_Section(section_face, face).Shape()
# Apply the mirror transformation
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
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
