Source code for RCAIDE.Library.Components.Wings.Blended_Wing_Body
# RCAIDE/Components/Wings/Blended_Wing_Body.py
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data
from .Main_Wing import Main_Wing
from RCAIDE.Library.Components.Component import Container
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_bwb_moment_of_inertia import compute_bwb_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity.compute_bwb_center_of_gravity import compute_bwb_center_of_gravity
# python imports
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Blended_Wing_Body
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Blended_Wing_Body(Main_Wing):
"""
A blended wing body (BWB) design that smoothly integrates the wing and fuselage
into a single lifting body configuration.
Attributes
----------
tag : str
Unique identifier for the BWB fuselage component, defaults to 'bwb_fuselage'
aft_center_body.area : float
Cross-sectional area of the aft centerbody section in square meters
aft_center_body.taper : float
Taper ratio of the aft centerbody section, defined as the ratio of tip
to root chord lengths
cabin_area : float
Total available cabin floor area in square meters
Notes
-----
The blended wing body design offers several advantages over conventional tube-and-wing
configurations:
* Reduced wetted area leading to lower skin friction drag
* Improved lift-to-drag ratio due to the lifting body design
* Potential for increased internal volume and better weight distribution
**Definitions**
'Centerbody'
The central section of the BWB that houses the passenger cabin and cargo hold
'Aft Centerbody'
The rear section of the centerbody that transitions into the outer wing sections
See Also
--------
RCAIDE.Library.Components.Fuselages.Fuselage
Base fuselage class that provides common functionality
"""
def __defaults__(self):
"""
Sets the default values for the BWB fuselage component attributes.
Notes
-----
This method initializes all required attributes with default values. Users should
modify these values based on their specific design requirements after instantiation.
"""
self.tag = 'blended_wing_body'
self.center_body = Component()
self.center_body.tag = 'center_body'
self.center_body.area = 0.0
self.aft_center_body = Component()
self.aft_center_body.tag = 'aft_center_body'
self.aft_center_body.taper = 1.0
self.aft_center_body.length = 0.0
self.aft_center_body.area = 0.0
self.cabin_area = 0.0
self.number_of_passengers = 1
self.number_of_seats = 1
self.layout_of_passenger_accommodations = None
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.fineness = Data()
self.fineness.nose = 0.0
self.fineness.tail = 0.0
self.x_rotation = 0.0
self.y_rotation = 0.0
self.z_rotation = 0.0
self.cabins = Container()
self.operational_items = Component()
self.operational_items.tag = 'operational_items'
[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_bwb_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_bwb_center_of_gravity(self, vehicle)
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
