# RCAIDE/Compoments/Fuselages/Fuselage.py
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data
from RCAIDE.Library.Components.Component import Container
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_fuselage_moment_of_inertia import compute_fuselage_moment_of_inertia
# ----------------------------------------------------------------------------------------------------------------------
# Fuselage
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Fuselage(Component):
"""
Base class for aircraft fuselage components providing core functionality for
geometric definition and analysis.
Attributes
----------
tag : str
Unique identifier for the fuselage component, defaults to 'fuselage'
origin : list
3D coordinates [x, y, z] defining the fuselage's reference point,
defaults to [[0.0, 0.0, 0.0]]
aerodynamic_center : list
3D coordinates [x, y, z] of the fuselage's aerodynamic center,
defaults to [0.0, 0.0, 0.0]
differential_pressure : float
Cabin pressurization differential, defaults to 0.0
areas : Data
Collection of fuselage area measurements
- front_projected : float
Frontal area, defaults to 0.0
- side_projected : float
Side profile area, defaults to 0.0
- wetted : float
Total wetted surface area, defaults to 0.0
effective_diameter : float
Equivalent circular diameter, defaults to 0.0
width : float
Maximum fuselage width, defaults to 0.0
heights : Data
Collection of height measurements along the fuselage
- maximum : float
Maximum height in meters, defaults to 0.0
- at_quarter_length : float
Height at 25% of fuselage length, defaults to 0.0
- at_three_quarters_length : float
Height at 75% of fuselage length, defaults to 0.0
- at_wing_root_quarter_chord : float
Height at wing root quarter chord, defaults to 0.0
- at_vertical_root_quarter_chord : float
Height at vertical tail root quarter chord, defaults to 0.0
lengths : Data
Collection of length measurements
- nose : float
Length of nose section, defaults to 0.0
- tail : float
Length of tail section, defaults to 0.0
- total : float
Total fuselage length, defaults to 0.0
- cabin : float
Length of passenger cabin, defaults to 0.0
- fore_space : float
Length of forward equipment bay, defaults to 0.0
- aft_space : float
Length of aft equipment bay, defaults to 0.0
x_rotation : float
Rotation angle about x-axis, defaults to 0.0
y_rotation : float
Rotation angle about y-axis, defaults to 0.0
z_rotation : float
Rotation angle about z-axis, defaults to 0.0
fineness : Data
Fineness ratio parameters
- nose : float
Ratio of nose length to maximum diameter, defaults to 0.0
- tail : float
Ratio of tail length to maximum diameter, defaults to 0.0
nose_curvature : float
Shape parameter defining nose profile curvature, defaults to 1.5
tail_curvature : float
Shape parameter defining tail profile curvature, defaults to 1.5
fuel_tanks : Container
Collection of fuel tank components within the fuselage, initialized empty
vsp_data : Data
OpenVSP-specific geometry parameters
- xsec_surf_id : str
OpenVSP cross-section surface identifier
- xsec_num : int
Number of cross-sections in OpenVSP model, defaults to None
segments : Container
Collection of fuselage segment components, initialized empty
Notes
-----
This class serves as the foundation for all fuselage types in RCAIDE, providing:
* Geometric definition capabilities
* Integration with OpenVSP for visualization and analysis
* Support for fuel tank and segment management
* Basic structural configuration parameters
**Definitions**
'Fineness Ratio'
Ratio of length to maximum diameter, important for drag characteristics
'Wetted Area'
Total surface area exposed to airflow
'Equipment Bay'
Non-pressurized volume for systems and equipment storage
See Also
--------
RCAIDE.Library.Components.Fuselages.Tube_Fuselage
Implementation for conventional tube-and-wing aircraft
RCAIDE.Library.Components.Fuselages.Blended_Wing_Body_Fuselage
Implementation for blended wing body aircraft
"""
def __defaults__(self):
"""
Sets default values for all fuselage attributes.
"""
self.tag = 'fuselage'
self.origin = [[0.0,0.0,0.0]]
self.aerodynamic_center = [0.0,0.0,0.0]
self.differential_pressure = 0.0
self.number_of_passengers = 0.0
self.layout_of_passenger_accommodations = None
self.areas = Data()
self.areas.front_projected = 0.0
self.areas.side_projected = 0.0
self.areas.wetted = 0.0
self.effective_diameter = 0.0
self.width = 0.0
self.heights = Data()
self.heights.maximum = 0.0
self.heights.at_quarter_length = 0.0
self.heights.at_three_quarters_length = 0.0
self.heights.at_wing_root_quarter_chord = 0.0
self.heights.at_vertical_root_quarter_chord = 0.0
self.lengths = Data()
self.lengths.nose = 0.0
self.lengths.tail = 0.0
self.lengths.total = 0.0
self.x_rotation = 0.0
self.y_rotation = 0.0
self.z_rotation = 0.0
self.fineness = Data()
self.fineness.nose = 0.0
self.fineness.tail = 0.0
self.nose_curvature = 1.5
self.tail_curvature = 1.5
self.fuel_tanks = Container()
self.vsp_data = Data()
self.vsp_data.xsec_surf_id = '' # There is only one XSecSurf in each VSP geom.
self.vsp_data.xsec_num = None # Number if XSecs in fuselage geom.
self.segments = Container()
self.cabins = Container()
self.vsp_data = Data()
self.vsp_data.xsec_id = ''
self.vsp_data.shape = ''
[docs]
def append_segment(self,segment):
"""
Adds a new segment to the fuselage's segment container.
Parameters
----------
segment : Data
Fuselage segment to be added
"""
# Assert database type
if not isinstance(segment,RCAIDE.Library.Components.Fuselages.Segments.Segment):
raise Exception('input component must be of type Segment')
# Store data
self.segments.append(segment)
return
[docs]
def append_cabin(self,cabin):
"""
Adds a new segment to the fuselage's segment container.
Parameters
----------
segment : Data
Fuselage segment to be added
"""
# Assert database type
if not isinstance(cabin,RCAIDE.Library.Components.Fuselages.Cabins.Cabin):
raise Exception('input component must be of type Cabin')
# Store data
self.cabins.append(cabin)
return
[docs]
def append_fuel_tank(self,fuel_tank):
"""
Adds a new fuel tank to the fuselage's fuel tank container.
Parameters
----------
fuel_tank : Data
Fuel tank component to be added
"""
# Assert database type
if not isinstance(fuel_tank,Data):
raise Exception('input component must be of type Data()')
# Store data
self.Fuel_Tanks.append(fuel_tank)
return
[docs]
def compute_moment_of_inertia(self, center_of_gravity=[[0, 0, 0]]):
"""
Computes the moment of inertia tensor for the fuselage.
Parameters
----------
center_of_gravity : list, optional
Reference point coordinates for moment calculation, defaults to [[0, 0, 0]]
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
