Source code for RCAIDE.Library.Components.Fuselages.Tube_Fuselage
# RCAIDE/Compoments/Fuselages/Tube_Fuselage.py
#
# Created: Mar 2024, M. Clarke
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# IMPORT
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# RCAIDE imports
from .Fuselage import Fuselage
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_fuselage_moment_of_inertia import compute_fuselage_moment_of_inertia
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# Tube_Fuselage
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[docs]
class Tube_Fuselage(Fuselage):
"""
A conventional cylindrical fuselage design commonly used in commercial and general
aviation aircraft.
Attributes
----------
tag : str
Unique identifier for the fuselage component, defaults to 'tube_fuselage'
Notes
-----
The tube fuselage is the most common configuration in modern aircraft design.
**Major Assumptions**
* Cross-sections are primarily circular or near-circular
* Smooth transitions between different diameter sections
**Definitions**
'Tube Fuselage'
A fuselage design with predominantly circular cross-sections, typically
consisting of a constant-diameter center section with tapered nose and
tail sections
See Also
--------
RCAIDE.Library.Components.Fuselages.Fuselage
Base class providing core fuselage functionality
RCAIDE.Library.Components.Fuselages.Blended_Wing_Body_Fuselage
Alternative fuselage design for comparison
"""
def __defaults__(self):
"""
Sets default values for the tube fuselage attributes.
"""
self.tag = 'tube_fuselage'
[docs]
def compute_moment_of_inertia(self, center_of_gravity):
"""
Computes the moment of inertia tensor for the tube fuselage.
Parameters
----------
center_of_gravity : list
Reference point coordinates [x, y, z] for moment calculation
Returns
-------
I : ndarray
3x3 moment of inertia tensor in kg*m^2
See Also
--------
RCAIDE.Library.Methods.Weights.Moment_of_Inertia.compute_fuselage_moment_of_inertia
Implementation of the moment of inertia calculation
"""
I = compute_fuselage_moment_of_inertia(self,center_of_gravity)
return I
