Source code for RCAIDE.Library.Components.Wings.Stabilator
# RCAIDE/Library/Compoments/Wings/Stabilator.py
#
# Created: Mar 2024, M. Clarke
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# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from .Horizontal_Tail import Horizontal_Tail
from .All_Moving_Surface import All_Moving_Surface
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_moment_of_inertia import compute_wing_moment_of_inertia
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# Stabilator
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[docs]
class Stabilator(Horizontal_Tail, All_Moving_Surface):
"""
A class representing an all-moving horizontal tail (stabilator) that provides
pitch control and longitudinal stability.
Attributes
----------
tag : str
Unique identifier for the stabilator, defaults to 'stabilator'
sign_duplicate : float
Sign convention for duplicate stabilator deflection, defaults to 1.0
(synchronized deflection for pitch control)
Notes
-----
The stabilator combines the functions of a horizontal stabilizer and elevator
by pivoting as a complete surface. It inherits from both Horizontal_Tail and
All_Moving_Surface to combine their functionality.
See Also
--------
RCAIDE.Library.Components.Wings.Horizontal_Tail
Base class providing horizontal tail functionality
RCAIDE.Library.Components.Wings.All_Moving_Surface
Base class providing pivoting surface functionality
RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator
Alternative pitch control using conventional elevator
"""
def __defaults__(self):
"""
Sets default values for the stabilator attributes.
Notes
-----
See All_Moving_Surface.__defaults__ and Wing.__defaults__ for
additional inherited attributes.
"""
self.tag = 'stabilator'
self.sign_duplicate = 1.0
[docs]
def moment_of_inertia(wing, center_of_gravity):
"""
Computes the moment of inertia tensor for the stabilator.
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
