RCAIDE.Library.Components.Fuselages.Blended_Wing_Body_Fuselage

Blended_Wing_Body_Fuselage#

class Blended_Wing_Body_Fuselage(*args, **kwarg)[source]#

Bases: Fuselage

A blended wing body (BWB) fuselage design that smoothly integrates the wing and fuselage into a single lifting body configuration.

tag#

Unique identifier for the BWB fuselage component, defaults to ‘bwb_fuselage’

Type:

str

aft_centerbody_area#

Cross-sectional area of the aft centerbody section in square meters

Type:

float

aft_centerbody_taper#

Taper ratio of the aft centerbody section, defined as the ratio of tip to root chord lengths

Type:

float

cabin_area#

Total available cabin floor area in square meters

Type:

float

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

RCAIDE.Library.Components.Fuselages.Tube_Fuselage

Conventional tube fuselage design for comparison

compute_moment_of_inertia(center_of_gravity)[source]#

Computes the moment of inertia tensor for the BWB fuselage.

Parameters:

center_of_gravity (array-like) – The (x, y, z) coordinates of the center of gravity about which to compute the moment of inertia

Returns:

I – 3x3 moment of inertia tensor in kg*m^2

Return type:

ndarray

Notes

Currently returns a zero matrix. This is a placeholder that should be implemented with actual BWB moment of inertia calculations.