# RCAIDE/Library/Components/Wings/Wing.py
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data,Container
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_moment_of_inertia import compute_wing_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity.compute_wing_center_of_gravity import compute_wing_center_of_gravity
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Wing
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Wing(Component):
"""
Base class for aircraft lifting surfaces providing core functionality for geometric
definition and analysis.
Attributes
----------
tag : str
Unique identifier for the wing, defaults to 'wing'
mass_properties : Mass_Properties
Mass and inertia properties, initialized empty
origin : ndarray
3D coordinates [x, y, z] defining wing's reference point, defaults to [0.0, 0.0, 0.0]
vertical : bool
Flag indicating if wing is vertically oriented, defaults to False
t_tail : bool
Flag indicating if wing is mounted on vertical tail, defaults to False
taper : float
Wing taper ratio, defaults to 0.0
dihedral : float
Wing dihedral angle, defaults to 0.0
aspect_ratio : float
Wing aspect ratio, defaults to 0.0
thickness_to_chord : float
Average thickness-to-chord ratio, defaults to 0.0
aerodynamic_center : list
Location of aerodynamic center [x, y, z], defaults to [0.0, 0.0, 0.0]
percent_span_unexposed : float
Offset of exposed root from centerline, defaults to 0.0
total_length : float
Total length of wing, defaults to 0.0
spans : Data
Collection of span measurements
- projected : float
Projected span, defaults to 0.0
- total : float
Total span including dihedral effects, defaults to 0.0
areas : Data
Collection of area measurements
- reference : float
Reference area, defaults to 0.0
- exposed : float
Exposed area, defaults to 0.0
- affected : float
Area affected by high-lift devices, defaults to 0.0
- wetted : float
Wetted area, defaults to 0.0
chords : Data
Collection of chord measurements
- mean_aerodynamic : float
Mean aerodynamic chord, defaults to 0.0
- mean_geometric : float
Mean geometric chord, defaults to 0.0
- root : float
Root chord, defaults to 0.0
- tip : float
Tip chord, defaults to 0.0
sweeps : Data
Collection of sweep angles
- quarter_chord : float
Quarter-chord sweep angle, defaults to 0.0
- leading_edge : float
Leading edge sweep angle, defaults to None
twists : Data
Collection of twist angles
- root : float
Root section twist angle, defaults to 0.0
- tip : float
Tip section twist angle, defaults to 0.0
symbolic : bool
Flag for symbolic computation mode, defaults to False
vortex_lift : bool
Flag for vortex lift modeling, defaults to False
transition_x_upper : float
Upper surface transition location, defaults to 0.0
transition_x_lower : float
Lower surface transition location, defaults to 0.0
Airfoil : Container
Collection of airfoil definitions, initialized empty
segments : Container
Collection of wing segments, initialized empty
control_surfaces : Container
Collection of control surfaces, initialized empty
fuel_tanks : Container
Collection of fuel tanks, initialized empty
Notes
-----
The Wing class serves as the foundation for all lifting surfaces in RCAIDE.
It provides:
* Geometric definition capabilities
* Segment management
* Control surface integration
* Fuel tank integration
* Mass properties computation
See Also
--------
RCAIDE.Library.Components.Wings.Main_Wing
Primary lifting surface implementation
RCAIDE.Library.Components.Wings.Horizontal_Tail
Horizontal stabilizer implementation
RCAIDE.Library.Components.Wings.Vertical_Tail
Vertical stabilizer implementation
"""
def __defaults__(self):
"""
Sets default values for the wing attributes.
"""
self.tag = 'wing'
self.origin = np.array([[0.0,0.0,0.0]])
self.xz_plane_symmetric = True
self.vertical = False
self.t_tail = False
self.taper = 0.0
self.dihedral = 0.0
self.aspect_ratio = 0.0
self.thickness_to_chord = 0.0
self.aerodynamic_center = [0.0,0.0,0.0]
self.percent_span_unexposed = 0.0
self.total_length = 0.0
self.spans = Data()
self.spans.projected = 0.0
self.spans.total = 0.0
self.areas = Data()
self.areas.reference = 0.0
self.areas.exposed = 0.0
self.areas.affected = 0.0
self.areas.wetted = 0.0
self.areas.planform = 0.0
self.chords = Data()
self.chords.mean_aerodynamic = 0.0
self.chords.mean_geometric = 0.0
self.chords.root = 0.0
self.chords.tip = 0.0
self.outer_mold_line_cabin_offset_factor = 0.95
self.sweeps = Data()
self.sweeps.quarter_chord = None
self.sweeps.leading_edge = None
self.twists = Data()
self.twists.root = 0.0
self.twists.tip = 0.0
self.symbolic = False
self.vortex_lift = False
self.transition_x_upper = 0.45
self.transition_x_lower = 0.45
self.airfoil = None
self.segments = Container()
self.control_surfaces = Container()
self.structural = Data()
self.structural.rib = False
self.structural.front_spar_percent_chord = 0.1
self.structural.rear_spar_percent_chord = 0.6
self.structural.stringer_percent_chords = []
[docs]
def append_segment(self, segment):
"""
Adds a new segment to the wing's segment container.
Parameters
----------
segment : Data
Wing segment to be added
"""
# Assert database type
if not isinstance(segment,RCAIDE.Library.Components.Wings.Segments.Segment):
raise Exception('input component must be of type Segment')
# Store data
self.segments.append(segment)
return
[docs]
def append_airfoil(self, airfoil):
"""
Adds an airfoil definition to the wing.
Parameters
----------
airfoil : Data
Airfoil data to be added
"""
# Assert database type
if not isinstance(airfoil,RCAIDE.Library.Components.Airfoils.Airfoil):
raise Exception('input component must be of type Airfoil')
# Store data
self.airfoil = airfoil
return
[docs]
def append_control_surface(self, control_surface):
"""
Adds a control surface to the wing.
Parameters
----------
control_surface : Data
Control surface to be added
"""
# Assert database type
if not isinstance(control_surface,Data):
raise Exception('input control surface must be of type Data()')
# Store data
self.control_surfaces.append(control_surface)
return
[docs]
def compute_moments_of_inertia(self,vehicle,center_of_gravity=[[0, 0, 0]]):
"""
Computes the moment of inertia tensor for the wing.
Parameters
----------
center_of_gravity : list, optional
Reference point coordinates, defaults to [[0, 0, 0]]
fuel_flag : bool, optional
Flag to include fuel mass, defaults to False
Returns
-------
ndarray
3x3 moment of inertia tensor
"""
_, _ = compute_wing_moment_of_inertia(self, center_of_gravity)
return
[docs]
def compute_center_of_gravity(self,vehicle):
"""
Computes the center of gravity for the wing.
See Also
--------
RCAIDE.Library.Methods.weights.vehicle.center_of_gravity.compute_fuselage_center_of_gravity
Implementation of the center of gravity calculation
"""
compute_wing_center_of_gravity(self, vehicle)
return
[docs]
class Container(Component.Container):
[docs]
def get_children(self):
""" Returns the components that can go inside
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
from . import Main_Wing
from . import Vertical_Tail
from . import Horizontal_Tail
return [Main_Wing,Vertical_Tail,Horizontal_Tail]
# ------------------------------------------------------------
# Handle Linking
# ------------------------------------------------------------
Wing.Container = Container
