def transonic_airliner(display=None,
Propulsion=1,
EngineDia=2.9,
FuselageScaling=[55.902, 55.902, 55.902],
NoseLengthRatio=0.182,
TailLengthRatio=0.293,
WingScaleFactor=44.56,
WingChordFactor=1.0,
Topology=1,
SpanStation1=0.35,
SpanStation2=0.675,
EngineCtrBelowLE=0.3558,
EngineCtrFwdOfLE=0.9837,
Scarf_deg=3):
"""
Parameters
----------
Propulsion - int
1 - twin
2 - quad
EngineDia - float
Diameter of engine intake highlight
FuselageScaling - list, length 3
Fx, Fy, Fz scaling factors of fuselage
NoseLengthRatio - scalar
Proportion of forward tapering section of the fuselage
TailLengthRatio - scalar
Proportion of aft tapering section of the fuselage
WingScaleFactor - scalar
Scale Factor of the main wing
WingChordFactor - scalar
Chord factor of the main wing
Topology - int
Topology = 2 should yield a box wing airliner - use with caution
SpanStation - float
Inboard engine at this span station
SpanStation2 - float
Outboard engine at this span station (ignored if Propulsion=1)
EngineCtrBelowLE - float
Engine below leading edge, normalised by the length of the nacelle -
range: [0.35,0.5]
EngineCtrFwdOfLE - float
Engine forward of leading edge, normalised by the length of the nacelle
range: [0.85,1.5]
Scarf_deg - scalar # Engine scarf angle
Returns
-------
airliner - 'Aircraft' class instance
The collection of aircraft parts
See also
--------
class Aircraft
"""
try:
Fus = fuselage_oml.Fuselage(NoseLengthRatio,
TailLengthRatio,
Scaling=FuselageScaling,
NoseCoordinates=[0, 0, 0])
except:
print "Fuselage fitting failed - stopping."
return None
FuselageHeight = FuselageScaling[2] * 0.105
FuselageLength = FuselageScaling[0]
FuselageWidth = FuselageScaling[1] * 0.106
if Fus['OML'] is None:
print "Failed to fit fuselage surface, stopping."
return None
# FSurf = rs.CopyObject(FuselageOMLSurf)
# Position of the apex of the wing
if FuselageHeight < 8.0:
#787:[9.77,0,-0.307]
WingApex = [0.1748 * FuselageLength, 0, -0.0523 * FuselageHeight]
else:
WingApex = [0.1748 * FuselageLength, 0,
-0.1 * FuselageHeight] #787:[9.77,0,-0.307]
# Set up the wing object, including the list of user-defined functions that
# describe the spanwise variations of sweep, dihedral, etc.
if Topology == 1:
NSeg = 10
Wing = liftingsurface.LiftingSurface(WingApex,
mySweepAngleFunctionAirliner,
myDihedralFunctionAirliner,
myTwistFunctionAirliner,
myChordFunctionAirliner,
myAirfoilFunctionAirliner,
SegmentNo=NSeg,
ScaleFactor=WingScaleFactor,
ChordFactor=WingChordFactor)
RootChord = Wing.RootChord
elif Topology == 2:
NSeg = 101
Wing = liftingsurface.LiftingSurface(WingApex,
mySweepAngleFunctionAirliner,
bw.myDihedralFunctionBoxWing,
myTwistFunctionAirliner,
myChordFunctionAirliner,
myAirfoilFunctionAirliner,
SegmentNo=NSeg,
ScaleFactor=WingScaleFactor,
ChordFactor=WingChordFactor)
RootChord = Wing.RootChord
if Topology == 1:
# Add wing to body fairing
WTBFXCentre = WingApex[
0] + RootChord / 2.0 + RootChord * 0.1297 # 787: 23.8
if FuselageHeight < 8.0:
#Note: I made changes to this in OCC Airconics to get a better fit
# - Paul
WTBFZ = RootChord * 0.009 #787: 0.2
WTBFheight = 1.8 * 0.1212 * RootChord #787:2.7
WTBFwidth = 1.08 * FuselageWidth
else:
WTBFZ = WingApex[2] + 0.005 * RootChord
WTBFheight = 0.09 * RootChord
WTBFwidth = 1.15 * FuselageWidth
WTBFlength = 1.167 * RootChord #787:26
WBF_shape = act.make_ellipsoid([WTBFXCentre, 0, WTBFZ], WTBFlength,
WTBFwidth, WTBFheight)
WBF = AirconicsShape(components={'WBF': WBF_shape})
# Trim wing inboard section
CutCirc = act.make_circle3pt([0, WTBFwidth / 4., -45],
[0, WTBFwidth / 4., 45],
[90, WTBFwidth / 4., 0])
CutCircDisk = act.PlanarSurf(CutCirc)
Wing['Surface'] = act.TrimShapebyPlane(Wing['Surface'], CutCircDisk)
elif Topology == 2:
# Overlapping wing tips
CutCirc = act.make_circle3pt((0, 0, -45), (0, 0, 45), (90, 0, 0))
CutCircDisk = act.PlanarSurf(CutCirc)
Wing['Surface'] = act.TrimShapebyPlane(Wing['Surface'], CutCircDisk)
# Engine installation (nacelle and pylon)
NacelleLength = 1.95 * EngineDia
if Propulsion == 1:
SpanStations = [SpanStation1]
elif Propulsion == 2:
SpanStations = [SpanStation1, SpanStation2]
engines = []
for i, SpanStation in enumerate(SpanStations):
EngineSection, Chord = act.CutSect(Wing['Surface'], SpanStation)
CEP = Chord.EndPoint()
Centreloc = [
CEP.X() - EngineCtrFwdOfLE * NacelleLength,
CEP.Y(),
CEP.Z() - EngineCtrBelowLE * NacelleLength
]
eng = engine.Engine(Chord,
CentreLocation=Centreloc,
ScarfAngle=Scarf_deg,
HighlightRadius=EngineDia / 2.0,
MeanNacelleLength=NacelleLength)
engines.append(eng)
# # Script for generating and positioning the fin
# # Position of the apex of the fin
P = [0.6524 * FuselageLength, 0.003, FuselageHeight * 0.384]
#P = [36.47,0.003,2.254]55.902
if Topology == 1:
ScaleFactor = WingScaleFactor / 2.032 #787:21.93
elif Topology == 2:
ScaleFactor = WingScaleFactor / 3.5
SegmentNo = 100
ChordFactor = 1.01 #787:1.01
Fin = liftingsurface.LiftingSurface(P,
mySweepAngleFunctionFin,
myDihedralFunctionFin,
myTwistFunctionFin,
myChordFunctionFin,
myAirfoilFunctionFin,
SegmentNo=SegmentNo,
ChordFactor=ChordFactor,
ScaleFactor=ScaleFactor)
# Create the rotation axis centered at the apex point in the x direction
RotAxis = gp_Ax1(gp_Pnt(*P), gp_Dir(1, 0, 0))
Fin.RotateComponents(RotAxis, 90)
if Topology == 1:
# Tailplane
P = [0.7692 * FuselageLength, 0.000, FuselageHeight * 0.29]
SegmentNo = 100
ChordFactor = 1.01
ScaleFactor = 0.388 * WingScaleFactor #787:17.3
TP = liftingsurface.LiftingSurface(P,
mySweepAngleFunctionTP,
myDihedralFunctionTP,
myTwistFunctionTP,
myChordFunctionTP,
myAirfoilFunctionTP,
SegmentNo=SegmentNo,
ChordFactor=ChordFactor,
ScaleFactor=ScaleFactor)
# OCC_AirCONICS Note: Nothing below here implemented in OCC_AirCONICS - See
# Rhino version for this functionality (largely for display only)
#
# rs.DeleteObjects([EngineSection, Chord])
# try:
# rs.DeleteObjects([CutCirc])
# except:
# pass
#
# try:
# rs.DeleteObjects([CutCircDisk])
# except:
# pass
#
# # Windows
#
# # Cockpit windows:
CockpitWindowTop = 0.305 * FuselageHeight
print("Making Fuselage Windows...")
# solids = Fus.CockpitWindowContours(Height=CockpitWindowTop, Depth=6)
#
## Cut the windows out:
# for solid in solids:
# Fus['OML'] = act.SplitShape(Fus['OML'], solid)
#
#
# print("Cockpit Windows Done.")
##
## (Xmin,Ymin,Zmin,Xmax,Ymax,Zmax) = act.ObjectsExtents([Win1, Win2, Win3, Win4])
CockpitBulkheadX = NoseLengthRatio * FuselageLength * 0.9
##
## CockpitWallPlane = rs.PlaneFromPoints([CockpitBulkheadX, -15,-15],
## [CockpitBulkheadX,15,-15],
## [CockpitBulkheadX,-15,15])
##
## CockpitWall = rs.AddPlaneSurface(CockpitWallPlane, 30, 30)
##
## if 'WTBF' in locals():
## rs.TrimBrep(WTBF, CockpitWall)
##
## rs.DeleteObject(CockpitWall)
#
## # Window lines
WIN = [1]
NOWIN = [0]
##
### # A typical window pattern (including emergency exit windows)
WinVec = WIN + 2 * NOWIN + 9 * WIN + 3 * NOWIN + WIN + NOWIN + 24 * WIN + 2 * NOWIN + WIN + NOWIN + 14 * WIN + 2 * NOWIN + WIN + 20 * WIN + 2 * NOWIN + WIN + NOWIN + 20 * WIN
wires = []
if FuselageHeight < 8.0:
### # Single deck
WindowLineHeight = 0.3555 * FuselageHeight
WinX = 0.1157 * FuselageLength
WindowPitch = 0.609
WinInd = -1
i = 0
while WinX < 0.75 * FuselageLength:
WinInd = WinInd + 1
if WinVec[WinInd] == 1 and WinX > CockpitBulkheadX:
i = i + 1
print("Generating cabin window {}".format(i))
WinCenter = [WinX, WindowLineHeight]
W_wire = Fus.WindowContour(WinCenter)
wires.append(W_wire)
# display.DisplayShape(W_wire, color='black')
# win_port, win_stbd = Fus.MakeWindow(*WinCenter)
# print(type(win_port), type(win_stbd))
#
# display.DisplayShape(win_port, color='Black')
# display.DisplayShape(win_stbd, color='Black')
#
### Note: Need to fix makewindow to return windows WinStbd,
## # WinPort,
# Fus.MakeWindow(WinX, WindowLineHeight)
### act.AssignMaterial(WinStbd,"Plexiglass")
### act.AssignMaterial(WinPort,"Plexiglass")
WinX = WinX + WindowPitch
#
# print("Cabin windows done")
# else:
# # TODO: Fuselage big enough to accommodate two decks
# # Lower deck
# WindowLineHeight = 0.17*FuselageHeight #0.166
# WinX = 0.1*FuselageLength #0.112
# WindowPitch = 0.609
# WinInd = 0
# while WinX < 0.757*FuselageLength:
# WinInd = WinInd + 1
# if WinVec[WinInd] == 1 and WinX > CockpitBulkheadX:
# WinStbd, WinPort, FuselageOMLSurf = fuselage_oml.MakeWindow(FuselageOMLSurf, WinX, WindowLineHeight)
# act.AssignMaterial(WinStbd,"Plexiglass")
# act.AssignMaterial(WinPort,"Plexiglass")
# WinX = WinX + WindowPitch
# # Upper deck
# WindowLineHeight = 0.49*FuselageHeight
# WinX = 0.174*FuselageLength #0.184
# WinInd = 0
# while WinX < 0.757*FuselageLength:
# WinInd = WinInd + 1
# if WinVec[WinInd] == 1 and WinX > CockpitBulkheadX:
# WinStbd, WinPort, FuselageOMLSurf = fuselage_oml.MakeWindow(FuselageOMLSurf, WinX, WindowLineHeight)
# act.AssignMaterial(WinStbd,"Plexiglass")
# act.AssignMaterial(WinPort,"Plexiglass")
# WinX = WinX + WindowPitch
#
#
#
#
#
# act.AssignMaterial(FuselageOMLSurf,"White_composite_external")
# act.AssignMaterial(WingSurf,"White_composite_external")
# try:
# act.AssignMaterial(TPSurf,"ShinyBARedMetal")
# except:
# pass
# act.AssignMaterial(FinSurf,"ShinyBARedMetal")
# act.AssignMaterial(Win1,"Plexiglass")
# act.AssignMaterial(Win2,"Plexiglass")
# act.AssignMaterial(Win3,"Plexiglass")
# act.AssignMaterial(Win4,"Plexiglass")
#
#
# # Mirror the geometry as required
Wing2 = Wing.MirrorComponents(plane='xz')
try:
# this try section allows box wing i.e. no tailplane
TP2 = TP.MirrorComponents(plane='xz')
except:
pass
engines_left = []
for eng in engines:
engines_left.append(eng.MirrorComponents(plane='xz'))
# if Propulsion == 1:
# for ObjId in EngineStbd:
# act.MirrorObjectXZ(ObjId)
# act.MirrorObjectXZ(PylonStbd)
# elif Propulsion == 2:
# raise NotImplementedError
# for ObjId in EngineStbd1:
# act.MirrorObjectXZ(ObjId)
# act.MirrorObjectXZ(PylonStbd1)
# for ObjId in EngineStbd2:
# act.MirrorObjectXZ(ObjId)
# act.MirrorObjectXZ(PylonStbd2)
# Build the return assembly (could change this later based on input 'tree':
airliner = AirconicsCollection(
parts={
'Wing_right': Wing,
'Wing_left': Wing2,
'Fuselage': Fus,
'Fin': Fin,
'Tailplane_right': TP,
'Tailplane_left': TP2,
'WBF': WBF
})
# Loop over the engines and write all components:
for i, eng in enumerate(engines):
name = 'engine_right' + str(i + 1)
airliner.AddPart(eng, name)
for i, eng in enumerate(engines_left):
name = 'engine_left' + str(i + 1)
airliner.AddPart(eng, name)
return airliner, wires
ScaleFactor = 44.56
Wing = LiftingSurface(P, wingex.mySweepAngleFunctionAirliner,
wingex.myDihedralFunctionAirliner,
wingex.myTwistFunctionAirliner,
wingex.myChordFunctionAirliner,
wingex.myAirfoilFunctionAirliner,
SegmentNo=SegmentNo,
ChordFactor=ChordFactor,
ScaleFactor=ScaleFactor)
Wing.Display(display)
SpanStation = 0.3 # The engine is to be placed at 30% span
EngineDia = 2.9
NacelleLength = 1.95*EngineDia
EngineSection, HChord = act.CutSect(Wing['Surface'], SpanStation)
Chord = HChord.GetObject()
CEP = Chord.EndPoint()
display.DisplayShape(Chord, update=True, color='black')
# Variables controlling the position of the engine with respect to the wing
EngineCtrFwdOfLE = 0.98
EngineCtrBelowLE = 0.35
Scarf_deg = 4
Centreloc = [CEP.X()-EngineCtrFwdOfLE*NacelleLength,
CEP.Y(),
CEP.Z()-EngineCtrBelowLE*NacelleLength]
# Now build the engine and its pylon
eng1 = Engine(HChord,
CentreLocation=Centreloc,
ScarfAngle=Scarf_deg,
