occ_airconics API reference¶
airconics.base module¶
Base classes used by OCC_Airconics
Container classes (AirconicsBase, AirconicsShape, AirconicsCollection) which behaves like a dictionary of sub component shapes/parts with some extended functionality.
Created on Mon Apr 18 10:26:22 2016
@author: pchambers

class
airconics.base.
AirconicsBase
(*args, **kwargs)¶ Bases:
_abcoll.MutableMapping
,object
Base container class from which other base classes are derived from. This is a an abstract base class and should not be used directly by users.
Notes
When properly defined in inherited functions, this class should behave like a dictionary.
As this class inherits from MutableMapping, any class inherting from AirconicsBase must also define the abstract methods of Mutable mapping, i.e. __setitem__, __getitem__, __len__, __iter__, __delitem__
Methods
Build
(*args, **kwargs)Display
(*args, **kwargs)Write
(*args, **kwargs)clear
(() > None. Remove all items from D.)get
((k[,d]) > D[k] if k in D, ...)items
(() > list of D’s (key, value) pairs, ...)iteritems
(() > an iterator over the (key, ...)iterkeys
(() > an iterator over the keys of D)itervalues
(...)keys
(() > list of D’s keys)pop
((k[,d]) > v, ...)If key is not found, d is returned if given, otherwise KeyError is raised. popitem
(() > (k, v), ...)as a 2tuple; but raise KeyError if D is empty. setdefault
((k[,d]) > D.get(k,d), ...)update
(([E, ...)If E present and has a .keys() method, does: for k in E: D[k] = E[k] values
(() > list of D’s values)
Build
(*args, **kwargs)¶

Display
(*args, **kwargs)¶

Write
(*args, **kwargs)¶


class
airconics.base.
AirconicsCollection
(parts={}, construct_geometry=False, *args, **kwargs)¶ Bases:
airconics.base.AirconicsBase
Base class from which collections of parts defined by other Airconics classes will be stored.
AirconicsCollection represents a collection of ‘parts’ (i.e. AirconicsShapes’) which are logically grouped. For example, an aircraft comprised of multiple parts (engine, lifting surfaces, fuselage) all of which may contain sub ‘components’ and are therefore instances of AirconicsShapes’
Parameters: parts : dictionary
(name: part) pairs, where name is a string for accessing the part, and ‘part’ is an AirconicsShape derived class e.g. Fuselage, LiftingSurface or Engine instance
See also
Notes
 Derived classes should call the AirconicsCollection init with
 super(DerivedClass, self).__init__(self, *args, **kwargs)
Attributes
_Parts (Airconics Container) Mapping of name(string):component(AirconicsShape) pairs. Note that this should not be interacted with directly, and instead users should use assignment or the AddPart method: :Example: >>> a = AirconicsCollection() >>> a[‘name’] = part >>> #OR: a.AddPart(‘name’, part) This also supports mapping of attributes to parts, i.e: :Example: >>> a[‘name’] == a._Parts.name # returns True Methods
AddPart
(part[, name])Adds a component to self Build
()Does nothing for AirconicsCollection. Display
(context[, material, color])Displays all Parts of the engine to input context Write
(filename[, single_export])Writes the Parts contained in this instance to file specified by filename. clear
(() > None. Remove all items from D.)get
((k[,d]) > D[k] if k in D, ...)items
(() > list of D’s (key, value) pairs, ...)iteritems
(() > an iterator over the (key, ...)iterkeys
(() > an iterator over the keys of D)itervalues
(...)keys
(() > list of D’s keys)pop
((k[,d]) > v, ...)If key is not found, d is returned if given, otherwise KeyError is raised. popitem
(() > (k, v), ...)as a 2tuple; but raise KeyError if D is empty. setdefault
((k[,d]) > D.get(k,d), ...)update
(([E, ...)If E present and has a .keys() method, does: for k in E: D[k] = E[k] values
(() > list of D’s values)
AddPart
(part, name=None)¶ Adds a component to self
Parameters: part : TopoDS_Shape
name : string

Build
()¶ Does nothing for AirconicsCollection.
This method allows AirconicsColection to be instantiated alone, as Build is called in the __init__. ‘Build’ Should be redefined by all derived classes.
Notes
 If Class.Build is not redefined in a derived class, confusion may
arise as no geometry will result from passing construct_geometry=True

Display
(context, material=<Mock id='140104105887440'>, color=None)¶ Displays all Parts of the engine to input context
Parameters: context : OCC.Display.OCCViewer.Viewer3d or WebRenderer
The display context  should have a Display or DisplayShape method
meterial : OCC.Graphic3d_NOM_* type
The material for display: note some renderers do not allow this

Write
(filename, single_export=True)¶ Writes the Parts contained in this instance to file specified by filename.
One file is produced, unless single_export is False when one file is written for each Part.
 filename : string
 the BASE.ext name of the file e.g. ‘airliner.stp’. Note the part name will be prepended to the base name of each output file
 single_export : bool
 returns a single output file if true, otherwise writes one file per part
Returns: status : list
The flattened list of error codes returned by writing each part
See also
Notes
 Calls the .Write method belonging to each Part

class
airconics.base.
AirconicsShape
(components={}, construct_geometry=False, *args, **kwargs)¶ Bases:
airconics.base.AirconicsBase
Base class from which airconics parts will be made.
AirconicsShapes represent a ‘part’ of an aircraft e.g. the engine, which consists of a group of logically shape ‘components’ but with no relative or relational contact information: class methods are intended to manipulate the part as a whole.
This is intended as a base class, but can be used as a simple amorphic collection of shape components.
Example: >>> shape = Airconics() >>> shape['wing'] = wing # OR >>> shape.AddComponent(wing, 'WingSurface')
Parameters: components : dictionary of components to be added as attributes
To add attributes directly. Values must be OCC.TopoDS.TopoDS_Shape
construct_geometry : bool
If true, Build method will be called on construction. Defaults to False for AirconicsShape, as the Build method only prints. Derived classes should pass construct_geometry=True if a Build method should be called on construction
**kwargs : All other keyword arguments will be added as an attribute
to the resulting class calling super(subclass, self).__init__
See also
Notes
 Derived classes should call the AirconicsCollection init with
 super(DerivedClass, self).__init__(self, *args, **kwargs)
Attributes
_Components (Airconics Container) Mapping of name(string):component(TopoDS_Shape) pairs. Note that this should not be interacted with directly, and instead users should use assignment or the AddComponent method: :Example: >>> a = AirconicsShape() >>> a[‘name’] = shape >>> #OR: a.AddComponent(‘name’, shape) This also supports mapping of attributes to parts, i.e: :Example: >>> a[‘name’] == a._Components.name # returns True Methods
AddComponent
(component[, name])Adds a component to self Build
()Does nothing for AirconicsShape. Display
(context[, material, color])Displays all components of this instance to input context DisplayBBox
(display[, single])Displays the bounding box on input display. Extents
([tol, as_vec])Returns the extents of the bounding box encapsulating all shapes in MirrorComponents
([plane, axe2])Returns a mirrored version of this airconics shape PrintComponents
()Lists the names of components in self RemoveComponent
(name)Removes a named component from self RotateComponents
(ax, deg)Rotation of each component in self._Components around ax by ScaleComponents_Uniformal
(factor[, origin])General scaling and translation of components in self TransformComponents_Nonuniformal
(scaling, vec)General scaling and translation of components in self TranslateComponents
(vec)Apply translation by vec to each component in self Write
(filename[, single_export])Writes the Components in this Airconics shape to filename using file format specified in extension of filename. clear
(() > None. Remove all items from D.)get
((k[,d]) > D[k] if k in D, ...)items
(() > list of D’s (key, value) pairs, ...)iteritems
(() > an iterator over the (key, ...)iterkeys
(() > an iterator over the keys of D)itervalues
(...)keys
(() > list of D’s keys)pop
((k[,d]) > v, ...)If key is not found, d is returned if given, otherwise KeyError is raised. popitem
(() > (k, v), ...)as a 2tuple; but raise KeyError if D is empty. setdefault
((k[,d]) > D.get(k,d), ...)update
(([E, ...)If E present and has a .keys() method, does: for k in E: D[k] = E[k] values
(() > list of D’s values)
AddComponent
(component, name=None)¶ Adds a component to self
Parameters: component : TopoDS_Shape
name : string

Build
()¶ Does nothing for AirconicsShape.
This method allows AirconicsShape to be instantiated alone, as Build is called in the __init__. ‘Build’ Should be redefined by all derived classes
Notes
 If Class.Build is not redefined in a derived class, confusion may
arise as no geometry will result from passing construct_geometry=True

Display
(context, material=<Mock id='140104105887440'>, color=None)¶ Displays all components of this instance to input context
Parameters: context : OCC.Display.OCCViewer.Viewer3d or WebRenderer
The display context  should have a Display or DisplayShape method
meterial : OCC.Graphic3d_NOM_* type (default=ALUMINIUM)
The material for display: note some renderers do not allow this
color : string
The color for all components in this shape

DisplayBBox
(display, single=True)¶ Displays the bounding box on input display.
Parameters: display : OCC.Display.OCCViewer.Viewer3d
Note that this function only currently works with the OCC core viewer as the bounding box is an AIS_Shape handle
single : bool (default True)
If false, separate bounding boxes will be draw for each component

Extents
(tol=1e06, as_vec=False)¶ Returns the extents of the bounding box encapsulating all shapes in self.__Components__
Parameters: tol : scalar (default 1e6)
tolerance of the triangulation used in the bounding box extents
as_vec : bool (default True)
Returns two OCC.gp.gp_Vec objects if True
Returns: extents : tuple of scalar or OCC.gp.gp_Vec
Type depends on input ‘as_vec’. If as_vec is false, this returns a tuple xmin, ymin, zmin, xmax, ymax, zmax; otherwise, the min and max vectors will be returned as OCC types.

MirrorComponents
(plane='xz', axe2=None)¶ Returns a mirrored version of this airconics shape
Parameters: plane : string (default=’xz’)
The plane in which to mirror components
axe2 : OCC.gp.gp_Ax2
The axes through which to mirror (overwrites input ‘plane’)
Returns: mirrored : AirconicsShape
the mirrored shape
Notes
Due to problem with swig and deepcopy, the mirrored object is the base class ‘AirconicsShape”, not the original type. This is will remove other subclassderived attributes and methods
It is also expected that the remaining attributes and methods will not be required or meaningful after mirroring, however this behaviour may change in future versions

PrintComponents
()¶ Lists the names of components in self

RemoveComponent
(name)¶ Removes a named component from self
Parameters: name : string

RotateComponents
(ax, deg)¶ Rotation of each component in self._Components around ax by angle deg
Parameters: ax : OCC.gp.gp_Ax1
The axis of rotation
deg : scalar
Rotation in degrees

ScaleComponents_Uniformal
(factor, origin=<Mock name='mock()' id='140103916305872'>)¶ General scaling and translation of components in self (applies act.transform_nonuniformal)
Parameters: origin : gp_Pnt
The origin of the scaling operation
factor : scalar
The scaling factor to apply in x,y,z

TransformComponents_Nonuniformal
(scaling, vec)¶ General scaling and translation of components in self (applies act.transform_nonuniformal)
Parameters: scaling : list or array, length 3
[x, y, z] scaling factors
vec : List of x,y,z or gp_Vec
the translation vector (default is [0,0,0])

TranslateComponents
(vec)¶ Apply translation by vec to each component in self
Parameters: vec : OCC.gp.gp_vec
vector through which components will be translated

Write
(filename, single_export=True)¶ Writes the Components in this Airconics shape to filename using file format specified in extension of filename. Currently stl only (TODO: step, iges)
Parameters: filename : string
the BASE.ext name of the file e.g. ‘airliner.stp’. Note the Component name will be prepended to the base name of each output file
single_export : bool
Writes a single output file if true, otherwise writes one file per component
Returns: status : list of int
error status of the file output of EACH component
Notes
File format is extracted from filename.
stl file write will prepend filename onto the Component name to be written to file (cannot write multiple files )
Primitives¶

class
airconics.primitives.
Airfoil
(LeadingEdgePoint=[0.0, 0.0, 0.0], ChordLength=1, Rotation=0, Twist=0, SeligProfile=None, Naca4Profile=None, Naca5Profile=None, CRMProfile=None, CRM_Epsilon=0.0, InterpProfile=None, Epsilon=0, Af1=None, Af2=None, Eps1=0, Eps2=1, EnforceSharpTE=False)¶ Bases:
object
Class for defining a range of splinefitted airfoil curves
Parameters: LeadingEdgePoint : array of float (,3)
(x, y, z) origin of the airfoil LE
ChordLength : scalar
Length of the airfoil chord
Rotation : scalar
Angle (deg) at which the base airfoil is inclined (angle of attack, rotation around y axis)
Twist : scalar
Angle (deg) at which the base airfoil is twisted (dihedral, rotation around x axis)
SeligProfile : string
Name of the Selig airfoil: see http://mselig.ae.illinois.edu/ads/coord_database.html
NACA4Profile : string
Name of the airfoil in NACA 4 format
NACA5Profile : string
Name of the airfoil in NACA 5 format. TODO: NACA5 profile not yet implemented
CRM_Profile : bool
If true, airfoil profile will be interpolated from Common Research Model (CRM). Must also declare ‘CRMEpsilon’ variable.
CRM_Epsilon : float
Spanwise fraction between 0 and 1 to interpolate profile from CRM
InterpProfile : bool
If True, a set of points between Af1 and Af2 will be interpolated for BSpline curve fitting (see AddInterp2)
Eps : scalar
Spanwise coordinate between Eps1 and Eps2 (used if InterpProfile is True)
Af1 : airconics.Airfoil
The Airfoil located at spanwise location Eps1. Af1.x and Af1.z. (used if InterpProfile is True)
Af2 : airconics.Airfoil
The Airfoil located at spanwise location Eps2. (used if InterpProfile is True)
Eps1 : scalar
Spanwise coordinate location of Airfoil Af1. Expected to range from 0 (root of a lifting surface) to 1 (tip of a lifting surface) (used if InterpProfile is True)
Eps2 : scalar
Spanwise coordinate location of Airfoil Af2. Expected to range from 0 (root of a lifting surface) to 1 (tip of a lifting surface), and also expected to be greater than Eps1 (used if InterpProfile is True)
EnforceSharpTE : bool
Enforces sharp trailing edge (NACA airfoils only)
Notes
 NACA5 profiles are not yet supported in OCC_AirCONICS.
 Preference is that users allow the class constructor to handle building the Airfoil i.e. pass all physical definitions as class arguments.
 Although the physical attributes can changed i.e. rotation, twist, ChordLength, LeadingEdgePoint etc., it is the users responsibility to rebuild the Airfoil with the ‘Add***Airfoil’ afterwards
Attributes
points (array of scalar, shape (N, 2)) The xz coordinates of points on the airfoils surface Curve  OCC.Geom.Handle_Geom_BsplineCurve The generated airfoil spline Methods
AddAirfoilFromSeligFile
AddCRMLinear
AddLinear2
AddNACA4

AddAirfoilFromSeligFile
(SeligProfile, Smoothing=1)¶ Adds an airfoil generated by fitting a NURBS curve to a set of points whose coordinates are given in a Selig formatted file
Parameters: SeligProfile : string
base selig airfoil name e.g. ‘b707a’.
Smoothing : int (default=1)
TODO: Airfoil curve smoothing
Returns: None
Notes
See Selig database online for other available base names

AddCRMLinear
(CRM_Epsilon, Smoothing=1)¶ Linearly interpolate airfoil curve from CRM
Parameters: CRM_Epsilon : scalar
Spanwise coordinate at which to sample the CRM airfoil database (range between 0 and 1)
Smoothing : int
TODO: Airfoil curve smoothing
Returns: None

AddLinear2
(Eps, Af1, Af2, Eps1=0, Eps2=1)¶ Interpolates the bspline control points fitted between two other Airfoil objects.
Interpolates the x and z values of an Airfoil at spanwise location Eps between Af1 (at Eps1) and Af2 (at Eps2). The BSpline Curve is then fitted to the resulting points with Airfoil._fitAirfoiltoPoints, and transformed to the orientation specified in self.Rotation, self.Twist, self.ChordLength and self.LEPoint via the _TransformAirfoil function.
Parameters: Eps : scalar
Spanwise coordinate between Eps1 and Eps2
Af1 : airconics.Airfoil
The Airfoil located at spanwise location Eps1. Af1.x and Af1.z
Af2 : airconics.Airfoil
The Airfoil located at spanwise location Eps2.
Eps1 : scalar
Spanwise coordinate location of Airfoil Af1. Expected to range from 0 (root of a lifting surface) to 1 (tip of a lifting surface)
Eps2 : scalar
Spanwise coordinate location of Airfoil Af2. Expected to range from 0 (root of a lifting surface) to 1 (tip of a lifting surface), and also expected to be greater than Eps1

AddNACA4
(Naca4Profile, Smoothing=1)¶ Adds a NACA 4 digit airfoil to the current document
Parameters: Naca4Profile : string
Naca 4 profile identifier. Should be length 4 string, however also accepts negative camber i.e. ‘5310’ gives a flipped camber airfoil (primarily used for box wing)
Smoothing  int
TODO: fair airfoil curve
Returns: None

points
¶
LiftingSurface¶

class
airconics.liftingsurface.
LiftingSurface
(ApexPoint=<Mock name='mock()' id='140103916408016'>, SweepFunct=False, DihedralFunct=False, TwistFunct=False, ChordFunct=False, AirfoilFunct=False, ChordFactor=1, ScaleFactor=1, OptimizeChordScale=0, LooseSurf=1, SegmentNo=11, TipRequired=False, max_degree=8, continuity=<Mock id='140103916407568'>, construct_geometry=True)¶ Bases:
airconics.base.AirconicsShape
Airconics class for defining lifting surface shapes
Parameters: ApexPoint  array, length 3
Foremost point of the wing (x direction). Updating will rebuild the geometry.
SweepFunct  function
function defining the leading edge sweep vs epsilon spanwise variable coordinate between 0 and 1 (curvilinear attached coordinates). Updating will rebuild the geometry.
DihedralFunct  function
function defining the leading edge dihedral vs epsilon spanwise variable coordinate between 0 and 1 (curvilinear attached). Updating will rebuild the geometry.
TwistFunc  function
function defining the sectional twist vs epsilon spanwise variable coordinate between 0 and 1 (curvilinear attached). Updating will rebuild the geometry.
ChordFunct  function
function defining the leading edge chord vs epsilon spanwise variable coordinate between 0 and 1 (curvilinear attached) Updating will rebuild the geometry.
AirfoilFunct  function
function defining the sectional Airfoil (see primitives.Airfoil) vs epsilon spanwise variable coordinate between 0 and 1 (curvilinear attached). Updating will rebuild the geometry.
ChordFactor  int (default = 1)
Scaling factor applied in chordwise direction. Updating will rebuild the geometry.
ScaleFactor  int (default = 1)
Scaling factor applied in all directions (uniform). Updating will rebuild the geometry.
OptimizeChordScale  int or bool (default = 0)
TODO: Not yet used.
LooseSurf  (default = 1)
TODO:
NSegments  int (default = 11)
Number of segments to sample the wing defined by input functions. Updating will rebuild the geometry.
TipRequired  bool (default = False)
TODO: Not yet used adds the wing tip face to components if true
max_degree  (default = 8)
maximum degree of the fitted NURBS surface
continuity  OCC.GeomAbs.GeomAbs_XX Type
the order of continuity i.e. C^0, C^1, C^2... would be GeomAbs_C0, GeomAbs_C1, GeomAbs_C2 ...
construct_geometry : bool
If true, Build method will be called on construction
Notes
 Output surface is stored in self[‘Surface’]
 See airconics.examples.wing_example_transonic_airliner for example input functions
Attributes
self[‘Surface’] (TopoDS_Shape) The generated lifting surface Sections (list of airconics.primitives.Airfoil objects) The rib curves from which the main surface is lofted. Updating any of the spanwise functions (ChordFunct, TwistFunct, etc...), SpanFactor, ChordFactor Raises an error if attempting to write over it manually. RootChord (Scalar) The length of the Root Chord. Updated by GenerateLiftingSurface AR (Scalar) The Aspect ratio of the Lifting Surface. Updated on call to Build LSP_area (Scalar) the projected area of the lifting surface. Updated on call to Build SA (Scalar) The wetted area of the lifting surface. Updated on call to Build ActualSemiSpan (Scalar) Calculated semi span of the lifting surface. Updated on call to Build Methods
AddComponent
Build
CalculateAspectRatio
CalculateProjectedArea
CalculateSemiSpan
CreateConstructionGeometry
Display
DisplayBBox
Extents
Fit_BlendedTipDevice
GenerateLeadingEdge
GenerateLiftingSurface
GenerateSectionCurves
MirrorComponents
PrintComponents
RemoveComponent
RotateComponents
ScaleComponents_Uniformal
TransformComponents_Nonuniformal
TranslateComponents
Write
clear
get
items
iteritems
iterkeys
itervalues
keys
pop
popitem
setdefault
update
values

AirfoilFunct
¶

ApexPoint
¶

Build
()¶ Builds the section curves and lifting surface using the current
Uses the current ChordFactor, ScaleFactor, NSegments, ApexPoint, and all spanwise variation functions (e.g. ChordFunct) defined in self to produce a surface
Notes
Called on initialisation of a lifting surface class.
Example: >>> Wing = liftingsurface.LiftingSurface(P, mySweepAngleFunction, myDihedralFunction, myTwistFunction, myChordFunction, myAirfoilFunction) >>> Surface = Wing['Surface']

CalculateAspectRatio
()¶ Calculates and returns the aspect ratio of this lifting surface
Uses information about the wings projected area and the current bounding box. If the project area (LSP_Area) is zero, this will be calculated.
Returns: AR : Scalar
Aspect ratio, calculated by b^2 / A, where b is the semi span and A is the project area of this lifting surface
See also
airconics.LiftingSurface.ProjectedArea
,airconics.LiftingSurface.SemiSpan

CalculateProjectedArea
()¶ Calculates the projected area of the current lifting surface
From Airconics documentation: In some cases the projected section cannot all be lofted in one go (it happens when parts of the wing fold back onto themselves), so we loft them section by section and compute the area as a sum.

CalculateSemiSpan
()¶ Calculates and returns the span of this lifting surface.
Uses the OCC bounding box algorithm.
Returns: ActualSemiSpan : Scalar

ChordFactor
¶

ChordFunct
¶

CreateConstructionGeometry
()¶ Creates the plane and vector used for projecting wetted area

DihedralFunct
¶

Fit_BlendedTipDevice
(rootchord_norm, spanfraction=0.1, cant=40, transition=0.1, sweep=40, taper=0.7)¶ Fits a blended wing tip device [1],
Parameters: rootchord_norm : scalar
The root chord of the straight part of the winglet, normalised by the tip chord of this lifting surface.
spanfraction : scalar
span of the winglet normalised by the span of the main wing
cant : scalar (default 40)
Angle (deg) of the wing tip from vertical
transition : scalar
The percentage along the span at which the transition to a straight segment is located
sweep : scalar
Sweep angle of the wing tip (uniform along the straight section)
taper : scalar
ratio of the tip chord to the root chord of the straight segment
References
[1] L. B. Gratzer, “Blended winglet,” Google Patents, 1994

GenerateLeadingEdge
()¶ Epsilon coordinate attached to leading edge defines sweep Returns airfoil leading edge points

GenerateLiftingSurface
()¶ Builds a lifting surface (wing, tailplane, etc.) with the Chord and Scale factors, and section list defined in self.
This function should be called after GenerateSectionCurves. Note that both operations are performed with `Build’, which should be used preferentially
Returns: None Notes
Adds a (‘Surface’: Shape) key value pair to self.

GenerateSectionCurves
()¶ Generates the loft section curves based on the current functional parameters and ChordFactor of the object.
Uses self._AirfoilFunct, _ChordFunct etc. and other attributes to update the content of self._Sections.
Returns: None

NSegments
¶

ScaleFactor
¶

Sections
¶

SweepFunct
¶

TwistFunct
¶
Fuselage¶

class
airconics.fuselage_oml.
Fuselage
(NoseLengthRatio=0.182, TailLengthRatio=0.293, Scaling=[55.902, 55.902, 55.902], NoseCoordinates=[0.0, 0.0, 0], CylindricalMidSection=False, SimplificationReqd=False, Maxi_attempt=5, construct_geometry=True)¶ Bases:
airconics.base.AirconicsShape
AirCONICS Fuselage class: builds a parameterised instance of an aircraft fuselage
Parameters: NoseLengthRatio : Scalar
The fraction of nose to fuselage length (default 0.182)
TailLengthRatio : Scalar
The fraction of tail to fuselage length (default 0.293)
Scaling : array, length 3
(x, y, z) scaling factor
NoseCoordinates : array of float
Location of nose apex
CylindricalMidSection : bool
If True, fuselage will have a cylindrical midsection
SimplificationReqd : bool
TODO
MaxFittingAtempts : integer
Maximum number of times to attempt to fit surface to guide curves
construct_geometry : bool
If true, Build method will be called on construction
Notes
Geometry building is done on initialisation of a Fuselage instance. It is therefore not expected that users will do this through the BuildFuselageOML function
Methods
AddComponent
AirlinerFuselagePlanView
AirlinerFuselageSideView
Build
BuildFuselageOML
CockpitWindowContours
Display
DisplayBBox
Extents
FuselageLongitudinalGuideCurves
MakeWindow
MirrorComponents
PrintComponents
RemoveComponent
RotateComponents
ScaleComponents_Uniformal
TransformComponents_Nonuniformal
TransformOML
TranslateComponents
WindowContour
Write
clear
get
items
iteritems
iterkeys
itervalues
keys
pop
popitem
setdefault
update
values

AirlinerFuselagePlanView
(NoseLengthRatio, TailLengthRatio)¶ Internal function. Defines the control polygons of the fuselage in side view

AirlinerFuselageSideView
(NoseLengthRatio, TailLengthRatio)¶ Internal function. Defines the control polygons of the fuselage in side view

Build
()¶ Overrides the AirconicsShape empty Build method.
Calls BuildFuselageOML, which has been maintained for older versions.

BuildFuselageOML
(Max_attempt=5)¶ Builds the Fuselage outer mould line Notes —– It is not expected that users will interact with this directly. Use the Fuslage class initialisation fuction instead

CockpitWindowContours
(Height=1.62, Depth=5)¶ This function is currently not tested

FuselageLongitudinalGuideCurves
(NoseLengthRatio, TailLengthRatio)¶ Internal function. Defines the four longitudinal curves that outline the fuselage (outer mould line).

MakeWindow
(Xwc, Zwc)¶ Makes at Window centered at Wxc Zwc using the bspline wire returned by WindowContour
THIS FUNCTION IS IN DEVELOPMENT AND NOT YET TESTED FULLY
Parameters: Xwc : scalar
The window center x coordinate
Zwc : scalar
The window center z coordinate
Returns: WinStbd : TopoDS_Shape
The window surface cut out (starboard side)
WinPort : TopoDS_Shape
The window surface cut out (Port side)
Notes
Changes the contents of self[‘OML’]. Makes both the port and starboard windows at the input location.

TransformOML
()¶ Use parameters defined in self to scale and translate the fuselage

WindowContour
(WinCenter)¶ Creates and returns the contour of the window at WinCenter
Parameters: WinCenter : list or array, length 2
The [X, Z] coordinate of the center of the window
Returns: W_wire : TopoDS_Wire
The wire of the Bspline contour

Engine¶

class
airconics.engine.
Engine
(HChord=0, CentreLocation=[0, 0, 0], ScarfAngle=3, HighlightRadius=1.45, MeanNacelleLength=5.67, construct_geometry=True)¶ Bases:
airconics.base.AirconicsShape
A class for generating aircraft engine and pylon geometries.
Currently only yields a turbofan engine with nacelle similar to that of an RR Trent 1000 / GEnx. Shapes produced include the nacelle, spinner cone, tail cone, Fan disk, Bypass disk, and pylon symmetry plane. The nacelle is produced by inclining an inlet disk by its scarf angle about the span wise (y) axis and uniformly spacing airfoil ‘ribs’ before lofting a surface through them. The pylon is currently the symetry plane of a fully pylon only
Parameters: HChord : OCC.Geom.Handle_Geom_TrimmedCurve
The chord line at which the engine will be fitted. The result of OCC.GC.GC_MakeSegment.Value() (can be return from helper function CutSect from AirCONICStools).
CentreLocation : list, length 3 (default=[0,0,0])
Location of the centre of the inlet highlight disk
ScarfAngle : scalar, deg (default=3)
angle of inclination of engine intake (rotated around y axis)
HighlightRadius : scalar (default=1.45)
Intake highlight radius
MeanNacelleLength : scalar (default=5.67)
Mean length of the nacelle, to be used as the airfoil rib chordlength
construct_geometry : bool
If true, Build method will be called on construction
Notes
 Also calls the initialiser of parent class AirconicsShape which stores all keywords as attributes
Attributes
_Components (dictionary of shapes) Methods
AddComponent
Build
BuildTurbofanNacelle
Display
DisplayBBox
Extents
MirrorComponents
PrintComponents
RemoveComponent
RotateComponents
ScaleComponents_Uniformal
TransformComponents_Nonuniformal
TranslateComponents
Write
clear
get
items
iteritems
iterkeys
itervalues
keys
pop
popitem
setdefault
update
values

Build
()¶ Currently only calls BuildTurbofanNacelle.
Notes
May add options for other engine types

BuildTurbofanNacelle
()¶ The defaults yield a nacelle similar to that of an RR Trent 1000 / GEnx
#TODO: break this down into modular function calls
Topology¶

class
airconics.topology.
Topology
(parts={}, construct_geometry=False)¶ Bases:
airconics.base.AirconicsCollection
Class to define abstract aircraft topologies as extensible lists of lifting surfaces, enclosure, and propulsion type objects.
Parameters: parts  dictionary
 Should contain the following,
{name: (Part, arity)}
 i.e. the string ‘name’ values are presented as a tuple or list of:
 Part  TopoDS_Shape
The shape
 arity  int
the arity (number of descendant nodes) attached to part
A warning is raised if arities are not provided, in which case arity is assumed to be zero
Notes
 warning will be raised if no affinities are provided
 example:
 # (Wing is an airconics Lifting Surface instace): aircraft = Topology(parts={‘Wing’: (Wing[‘Surface’], 2)})
Although not enforced, parts should be added to this class recursively (from the top node first) to represent the aircraft’s flattened topological tree suggested by Sobester [1]. It is the users responsibility to ensure the input nodes are a valid lisp tree for a correct graph to result (no checks are currently performed)
See Also: AirconicsCollection
References
 [1] Sobester, A., “Four Suggestions for Better Parametric Geometries,”
 10th AIAA Multidisciplinary Design Optimization Conference, AIAA SciTech, American Institute of Aeronautics and Astronautics, jan 2014.
Attributes
_Tree  list the list of LISPlike instructions (in the order they were called with AddPart) Methods
AddPart
Build
Display
MirrorSubtree
Write
clear
export_graphviz
get
items
iteritems
iterkeys
itervalues
keys
pop
popitem
setdefault
update
values

AddPart
(part, name, arity=0)¶ Overloads the AddPart method of AirconicsCollection base class to append the arity of the input topology node
Parameters: part  LiftingSurface, Engine or Fuselage class instance
the part to be added to the tree
name  string
name of the part (will be used to look up this part in self.aircraft)
arity  int
The number of terminals attached to this part; this will be randomized at a later stage
Notes
This method is expected to be used recursively, therefore the order in which parts are added dictates the tree topology. The first item added will be the top of the tree.
See also: AirconicsCollection.AddPart

Build
()¶ Recursively builds all sub components in the current topology tree if self.construct_geometry is true. Will also mirror components if a mirror node has been added, regardless of if construct_geometry is true.
Uses the the Build method of all sub components. Any user defined classes must therefore define the Build method in order for this to work correctly.

MirrorSubtree
()¶ Mirrors the geometry where required, based on the current topology tree.
Does nothing is no mirror plane has been added

export_graphviz
()¶ Returns a string, Graphviz script for visualizing the topology tree.
Currently only set up to allow a single mirror terminal
Returns: output : string
The Graphviz script to plot the tree representation of the program.
Notes
This function is originally from GPLearns _Program class, but has been modified. Can be visualised with pydot,
Example: >>> topo = Topology() # Add some parts with topo.addPart >>> graph = pydot.graph_from_dot_data(topo.export_graphviz()) >>> Image(graph.create_png())
May add a dependency on GPLearn later and overload the appropriate class methods.
AirCONICStools¶
Various geometry operations of geometric pythonocc primitives for OCC_AirCONICS
Created on Fri Dec 4 11:58:52 2015
@author: pchambers

airconics.AirCONICStools.
AddCone
(BasePoint, Radius, height, direction=<Mock name='mock()' id='140103916487056'>)¶ Generates a cone shape originating at BasePoint with base Radius and height (points in the direction of input ‘direction)
Parameters: BasePoint : OCC.gp.gp_Pnt or array length 3
The centre base point
Radius : scalar
Cone base radius
height : scalar
Cone height
direction : OCC.gp.gp_Dir (default: positive x direction)
the direction of the cones axis i.e. normal to the base: defaults to x axis
Returns: shape : TopoDS_Shape
The generated Cone

airconics.AirCONICStools.
AddSurfaceLoft
(objs, continuity=<Mock id='140104105990032'>, check_compatibility=True, solid=True, first_vertex=None, last_vertex=None, max_degree=8, close_sections=True)¶ Create a lift surface through curve objects
Parameters: objs : list of python classes
Each obj is expected to have an obj.Curve attribute : see airconics.primitives.airfoil class
continuity : OCC.GeomAbs.GeomAbs_XX type (default C2)
The order of continuity (C^0, C^1, C^2, G^0, ....)
check_compatibility : bool (default=True)
Adds a surface compatibility check to the builder
solid : bool (default=True)
Creates a solid object from the loft if True
first_vertex : TopoDS_Vertex (optional, default=None)
The starting vertex of the surface to add to the ‘ThruSections’ algorithm
last_vertex : TopoDS_Vertex (optional, default=None)
The end vertex of the surface to add to the ‘ThruSections’ algorithm
max_degree : int (default=8)
The order of the fitted NURBS surface
close_sections : bool (default=True):
Connects the start and end point of the loft rib curves if true. This has the same effect as adding an airfoil trailing edge.
Returns: shape : TopoDS_Shape
The generated loft surface
Notes
Uses OCC.BRepOffsetAPI.BRepOffsetAPI_ThruSections. This function is ORDER DEPENDANT, i.e. add elements in the order through which they should be lofted

airconics.AirCONICStools.
BBox_FromExtents
(xmin, ymin, zmin, xmax, ymax, zmax)¶ Generates the Wire Edges defining the Bounding Box defined in the input arguments: Can be used to display the bounding box

airconics.AirCONICStools.
CalculateSurfaceArea
(shape)¶ Calculates the surface area of input shape
Parameters: shape : TopoDS_Shape
Returns: Area : scalar
Calculated surface area

airconics.AirCONICStools.
CutSect
(Shape, SpanStation)¶ Parameters: Shape : TopoDS_Shape
The Shape to find planar cut section (parallel to xz plane)
SpanStation : scalar in range (0, 1)
ydirection 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

airconics.AirCONICStools.
ExtrudeFace
(face, vec=<Mock name='mock()' id='140104106028688'>)¶ Extrudes a face by input vector
Parameters: face : TopoDS_Face
vec : OCC.gp.gp_Vec
The offset vector to extrude through
Returns: shape : TopoDS_Shape
The extruded shape
Notes
Uses BRepBuilderAPI_MakePrism

airconics.AirCONICStools.
FilletFaceCorners
(face, radius)¶ Fillets the corners of the input face
Parameters: face : TopoDS_Face
radius : the Fillet radius

airconics.AirCONICStools.
Generate_InterpFunction
(Values, EpsArray=None, uniform=True)¶ Generates a lookup interpolation function.
Given an array of spanwise coordinates epsilon along a curvilinear leadingedge attached coordinate system, and a set of values describing e.g. Chord, Sweep at each station, generate and return a function f(epsilon) which will give the interpolated value.
Parameters: Values : array of float
Values of e.g. chordlength, sweep at each spanwise location in EpsArray
EpsArray : array of float
Distribution of spanwise coordinates at which the Values are known
uniform : bool
If True, assumes that Values corresponds to uniformly distribution epsilon locations along the lifting surface span
Returns: f : function
the function which returns the interpolated epsilon

airconics.AirCONICStools.
ObjectsExtents
(breps, tol=1e06, as_vec=False)¶ Compute the extents in the X, Y and Z direction (in the current coordinate system) of the objects listed in the argument.
Parameters: breps : list of TopoDS_Shape
The shapes to be added for bounding box calculation
tol : float (default=1e6)
Tolerance for bounding box calculation
as_vec : bool (default=False)
If true, returns minimum and maximum points as tuple of gp_Vec
Returns: xmin, ymin, zmin, xmax, ymax, zmax : scalar
the min and max points of bbox (returned if as_vec=False)
( gp_Vec(xmin, ymin, zmin), gp_Vec(xmax, ymax, zmax) ) : tuple of gp_Vec
the min and max points of bbox (returned in as_vec=True)
Notes
Due to the underlying OCC.Bnd.Bnd_Box functions, the bounding box is calculated via triangulation of the shapes to avoid inclusion of the control points of NURBS curves in bounding box calculation

airconics.AirCONICStools.
PlanarSurf
(geomcurve)¶ Adds a planar surface to curve
Parameters: geomcurve : OCC.Geom type curve
The edge of the profile
Returns: surf : TopoDS_face
the planar surface

airconics.AirCONICStools.
SplitShapeFromProjection
(shape, wire, direction, return_section=True)¶ Splits shape by the projection of wire onto its face
Parameters: shape : TopoDS_Shape
the brep to subtract from
wire : TopoDS_Wire
the tool to use for projection and splitting
direction: OCC.gp.gp_Dir
the direction to project the wire
return_section : bool
returns the split shape
Returns: newshape : TopoDS_Shape
input shape with wire subtracted
section : the shape which was substracted
(returned only if return_section is true)
Notes
Currently assumes splits the first face only

airconics.AirCONICStools.
TrimShapebyPlane
(Shape, Plane, pnt=<Mock name='mock()' id='140103916305360'>)¶ Trims an OCC shape by plane. Default trims the negative y side of the plane
Parameters: Shape : TopoDS_Shape
Plane : expect TopoDS_Face
pnt : point defining which side of the halfspace contains its mass

airconics.AirCONICStools.
Uniform_Points_on_Curve
(curve, NPoints)¶ Returns a list of uniformly spaced points on a curve
Parameters: crv : OCC.Geom curve type
NPoints : int
number of sampling points along the curve

class
airconics.AirCONICStools.
assert_isdone
(to_check, error_statement)¶ Bases:
object
raises an assertion error when IsDone() returns false, with the error specified in error_statement > this is from the pythonoccutils utilitymay not use it?

airconics.AirCONICStools.
boolean_cut
(shapeToCutFrom, cuttingShape, debug=False)¶ Boolean cut tool from PythonOCCUtils

airconics.AirCONICStools.
coerce_handle
(obj)¶ coerces an object that has a GetHandle method to call this method and return its handle

airconics.AirCONICStools.
coslin
(TransitionPoint, NCosPoints=24, NLinPoints=24)¶ Creates a series of abscissas with cosine spacing from 0 to a TransitionPoint and a linear spacing thereafter, up to 1. The TransitionPoint corresponds to pi. Distribution suitable for airfoils defined by points. TransitionPoint must be in the range [0,1].
Parameters: TransitionPoint : scalar
Point to transition from cosine to linear distribution in range (0, 1)
NCosPoints : int
Number of points to space by cosine law between 0 and TransitionPoint
NLinPoints : int
Number of points to space by linear law between TransitionPoint and 1
Returns: Abscissa : numpy array
The generated abscissa
NCosPoints : int
Number of cosine points used (same as input)

airconics.AirCONICStools.
export_STEPFile
(shapes, filename)¶ Exports a .stp file containing the input shapes
Parameters: shapes : list of TopoDS_Shape
Shapes to write to file
filename : string
The output filename

airconics.AirCONICStools.
export_STEPFile_Airconics
(AirconicsShapes, filename)¶ Writes a Step file with names defined in the AirconicsShapes. This function is not fully tested and should not yet be used.
Notes
Work in progress

airconics.AirCONICStools.
make_circle3pt
(pt1, pt2, pt3)¶ Makes a circle allowing python lists as input points

airconics.AirCONICStools.
make_edge
(*args)¶

airconics.AirCONICStools.
make_ellipsoid
(centre_pt, dx, dy, dz)¶ Creates an ellipsoid from nonuniformly scaled unit sphere

airconics.AirCONICStools.
make_face
(*args)¶

airconics.AirCONICStools.
make_pipe_shell
(spine, profiles, support=None)¶

airconics.AirCONICStools.
make_vertex
(*args)¶

airconics.AirCONICStools.
make_wire
(*args)¶

airconics.AirCONICStools.
mirror
(brep, plane='xz', axe2=None, copy=False)¶ Originally from pythonoccutils : might add dependency on this? Mirrors object
Parameters: brep : OCC.TopoDS.TopoDS_Shape
The shape to mirror
plane : string (default = ‘xz’)
The name of the plane in which to mirror objects. Acceptable inputs are any of ‘xy’, ‘yx’ , ‘zy’, ‘yz’, ‘yz’, ‘zy’. Overwritten if axe2 is defined.
axe2 : OCC.gp.gp_Ax2
The axes through which to mirror (overwrites input ‘plane’)
copy : bool
Returns: BRepBuilderAPI_Transform.Shape : TopoDS_Shape
The reflected shape
Notes
Pchambers: Added a functionality here to specify a plane using a string so that users could avoid interacting with core occ objects

airconics.AirCONICStools.
point_array_to_TColgp_PntArrayType
(array, _type=<Mock id='140104105957136'>)¶ Function to return curve from numpy array
Parameters: array : array (Npts x 3) or list
Array of xyz points for which to fit a bspline
_type : type of TColgp array
 Tested inputs are,
 TColgp_Array1OfPnt
 TColgp_HArray1OfPnt
See Notes for more information
Returns: pt_arr : TCOLgp_Array1OfPnt
OCC type array of points
Notes
USe TColgp_Harray when interpolating a curve from points with the GeomAPI_Interpolate. Use TColgp_Array when interpolating a curve from points with the GeomAPI_PointsToBspline

airconics.AirCONICStools.
points_from_intersection
(plane, curve)¶ Find intersection points between plane and curve.
Parameters: plane : Geom_Plane
The Plane
curve : Geom_*Curve
The Curve
Returns: P : Point or list of points
A single intersection point (OCC.gp.gp_Pnt) if one intersection is found, or list of points if more than one is found.
 If No Intersection points were found, returns None
Notes
The plane is first converted to a surface As the GeomAPI_IntCS class requires this.

airconics.AirCONICStools.
points_to_BezierCurve
(pnts)¶ Creates a Bezier curve from an array of points.
Parameters: pnts : array or list
x, y, z for an array of points. Allowable inputs are numpy arrays (with dimensions (Npoints x 3)), python list with elements [xi, yi, zi] or list of OCC.gp.gp_Pnt objects
Returns: crv : OCC.Geom.Geom_BezierCurve

airconics.AirCONICStools.
points_to_bspline
(pnts, deg=3, periodic=False, tangents=None, scale=False, continuity=<Mock id='140104105990032'>)¶ Points to bspline: originally from pythonoccutils, changed to allow numpy arrays as input
Returns: crv : OCC.Geom.BSplineCurve

airconics.AirCONICStools.
project_curve_to_plane
(curve, plane, direction)¶ Computes and returns the cylindrically projected curve onto input plane
Parameters: curve  geom_Curve
plane  Geom_Plane
dir  gp_Dir (default None)
The cylindrical projection direction. If None, the project will be normal to the plane
Returns: Hproj_curve : Handle_Geom_Curve

airconics.AirCONICStools.
project_curve_to_surface
(curve, surface, dir)¶ Returns a curve as cylindrically projected onto the surface shape
Parameters: curve : Geom_curve or TopoDS_Edge/Wire
surface : TopoDS_Shape
dir : gp_Dir
the direction of projection
Returns: res_curve : geom_curve (bspline only?)

airconics.AirCONICStools.
rotate
(brep, axe, degree, copy=False)¶ Rotates the brep
Originally from pythonoccutils : might add dependency on this?
Parameters: brep : shape to rotate
axe : axis of rotation
degree : Number of degrees to rotate through
copy : bool (default=False)
Returns: BRepBuilderAPI_Transform.Shape : Shape handle
The handle to the rotated shape

airconics.AirCONICStools.
scale_uniformal
(brep, pnt, factor, copy=False)¶ translate a brep over a vector : from pythonoccutils

airconics.AirCONICStools.
transform_nonuniformal
(brep, factors, vec=[0, 0, 0], copy=False)¶ Nonuniformly scale brep with respect to pnt by the x y z scaling factors provided in ‘factors’, and translate by vector ‘vec’
Parameters: factors : List of factors [Fx, Fy, Fz]
Scaling factors with respect to origin (0,0,0)
vec : List of x,y,z or gp_Vec
the translation vector (default is [0,0,0])
Notes
 Only tested on 3d shapes
 Assumes factors are define with respect to the origin (0,0,0)

airconics.AirCONICStools.
translate_topods_from_vector
(brep_or_iterable, vec, copy=False)¶ Function Originally from pythonoccutils, modified to work on objects
translates a brep over a vector
Parameters: brep : the Topo_DS to translate
vec : the vector defining the translation
copy : copies to brep if True
examples Subpackage¶
Modules in this subpackage are to be used for reconstructing example Airconics shapes, e.g. the transonic airliner lifting surface functions.
Created on Mon Jan 4 17:28:37 2016
Example script for generating a transonic airliner wing external geometry.
@author: pchambers

airconics.examples.wing_example_transonic_airliner.
myAirfoilFunctionAirliner
(Epsilon, LEPoint, ChordFunct, ChordFactor, DihedralFunct, TwistFunct)¶ Defines the variation of cross section as a function of Epsilon

airconics.examples.wing_example_transonic_airliner.
myChordFunctionAirliner
(Epsilon)¶ Userdefined function describing the variation of chord as a function of the leading edge coordinate

airconics.examples.wing_example_transonic_airliner.
myDihedralFunctionAirliner
(Epsilon)¶ Userdefined function describing the variation of dihedral as a function of the leading edge coordinate

airconics.examples.wing_example_transonic_airliner.
mySweepAngleFunctionAirliner
(Epsilon)¶ Userdefined function describing the variation of sweep angle as a function of the leading edge coordinate

airconics.examples.wing_example_transonic_airliner.
myTwistFunctionAirliner
(Epsilon)¶ Userdefined function describing the variation of twist as a function of the leading edge coordinate. The coefficients of the polynomial below come from the following twist values taken off the CRM (used for the AIAA drag prediction workshops): Epsilon = 0: twist = 4.24 Epsilon =0.3: twist = 0.593 Epsilon = 1: twist = 3.343
Created on Fri Jan 15 11:39:16 2016
Example functions for generating the lifting surfaces for the tail of a transport aircraft (fin and tailplane external geometry). Also, this shows that a specific planform can be reconstructed (the tail planform geometry here is an approximation of the B787 tail geometry).
# ============================================================================== # AirCONICS # Aircraft CONfiguration through Integrated Crossdisciplinary Scripting # version 0.2 # Andras Sobester, 2015. # Bug reports to a.sobester@soton.ac.uk or @ASobester please. # ==============================================================================
@author: pchambers

airconics.examples.tailplane_example_transonic_airliner.
myAirfoilFunctionFin
(Epsilon, LEPoint, ChordFunct, ChordFactor, DihedralFunct, TwistFunct)¶ Defines the variation of cross section as a function of Epsilon

airconics.examples.tailplane_example_transonic_airliner.
myAirfoilFunctionTP
(Epsilon, LEPoint, ChordFunct, ChordFactor, DihedralFunct, TwistFunct)¶ Defines the variation of cross section as a function of Epsilon

airconics.examples.tailplane_example_transonic_airliner.
myChordFunctionFin
(Epsilon)¶ Userdefined function describing the variation of the fin chord as a function of the leading edge coordinate

airconics.examples.tailplane_example_transonic_airliner.
myChordFunctionTP
(Epsilon)¶ Userdefined function describing the variation of the tailplane chord as a function of the leading edge coordinate

airconics.examples.tailplane_example_transonic_airliner.
myDihedralFunctionFin
(Epsilon)¶

airconics.examples.tailplane_example_transonic_airliner.
myDihedralFunctionTP
(Epsilon)¶

airconics.examples.tailplane_example_transonic_airliner.
mySweepAngleFunctionFin
(Epsilon)¶ Userdefined function describing the variation of the fin sweep angle as a function of the leading edge coordinate

airconics.examples.tailplane_example_transonic_airliner.
mySweepAngleFunctionTP
(Epsilon)¶ Userdefined function describing the variation of the fin sweep angle as a function of the leading edge coordinate

airconics.examples.tailplane_example_transonic_airliner.
myTwistFunctionFin
(Epsilon)¶

airconics.examples.tailplane_example_transonic_airliner.
myTwistFunctionTP
(Epsilon)¶
Created on Fri Mar 11 11:36:51 2016
@author: pchambers

airconics.examples.boxwing.
myAirfoilFunctionBoxWing
(Epsilon, LEPoint, ChordFunct, ChordFactor, DihedralFunct, TwistFunct)¶

airconics.examples.boxwing.
myChordFunctionBoxWing
(Epsilon)¶

airconics.examples.boxwing.
myDihedralFunctionBoxWing
(Epsilon)¶ Userdefined function describing the variation of dihedral as a function of the leading edge coordinate Notes —– Could also use numpy vectorize in this function

airconics.examples.boxwing.
mySweepAngleFunctionBoxWing
(Epsilon)¶

airconics.examples.boxwing.
myTwistFunctionBoxWing
(Epsilon)¶