Source code for RCAIDE.Library.Components.Wings.Main_Wing
# RCAIDE/Library/Compoments/Wings/Main_Wing.py
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from .Wing import Wing
from RCAIDE.Framework.Core import Container
from RCAIDE.Library.Components.Wings.Segments.Segment import Segment
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_moment_of_inertia import compute_wing_moment_of_inertia
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# Main_Wing
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Main_Wing(Wing):
"""
A class representing the primary lifting surface of an aircraft.
Attributes
----------
tag : str
Unique identifier for the main wing, defaults to 'main_wing'
segments : Segment_Container
Collection of wing segments defining the wing geometry, initialized empty
Notes
-----
The main wing provides primary lift generation for the aircraft. It inherits all
geometric and aerodynamic functionality from the Wing class and adds specific
attributes for main wing operation.
See Also
--------
RCAIDE.Library.Components.Wings.Wing
Base wing class providing core functionality
RCAIDE.Library.Components.Wings.Segments.Segment
Wing segment components used to build the wing
RCAIDE.Library.Components.Wings.Control_Surfaces
Control surfaces that can be mounted on the wing
"""
def __defaults__(self):
"""
Sets default values for the main wing attributes.
"""
self.tag = 'main_wing'
self.segments = Segment_Container()
[docs]
def moment_of_inertia(wing, center_of_gravity):
"""
Computes the moment of inertia tensor for the main wing.
Parameters
----------
wing : Component
Wing component data
center_of_gravity : list
Reference point coordinates for moment calculation
Returns
-------
ndarray
3x3 moment of inertia tensor
"""
I = compute_wing_moment_of_inertia(wing, center_of_gravity)
return I
[docs]
class Segment_Container(Container):
"""
Container class for managing wing segments. Provides organization and
access methods for segment components.
Notes
-----
This container is designed to hold and manage Segment objects that define
the wing geometry. It inherits from the base Container class and provides
specialized functionality for wing segments.
See Also
--------
RCAIDE.Library.Components.Wings.Segments.Segment
The segment components stored in this container
"""
[docs]
def get_children(self):
"""
Returns a list of allowable child component types for the segment container.
Returns
-------
list
List containing the Segment class as the only allowable child type
"""
return [Segment]
[docs]
def append(self, val):
"""
Appends a segment to the container with automatic name handling.
Parameters
----------
val : Segment
Wing segment to be added
Notes
-----
Automatically modifies segment tags to avoid duplicates by appending
numbers to repeated tags
"""
# See if the component exists, if it does modify the name
keys = self.keys()
if val.tag in keys:
string_of_keys = "".join(self.keys())
n_comps = string_of_keys.count(val.tag)
val.tag = val.tag + str(n_comps+1)
Container.append(self, val)
