RCAIDE.Library.Components.Fuselages.Fuselage

Fuselage#

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

Bases: Component

Base class for aircraft fuselage components providing core functionality for geometric definition and analysis.

tag#

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

Type:

str

origin#

3D coordinates [x, y, z] defining the fuselage’s reference point, defaults to [[0.0, 0.0, 0.0]]

Type:

list

aerodynamic_center#

3D coordinates [x, y, z] of the fuselage’s aerodynamic center, defaults to [0.0, 0.0, 0.0]

Type:

list

differential_pressure#

Cabin pressurization differential, defaults to 0.0

Type:

float

areas#

Collection of fuselage area measurements

  • front_projectedfloat

    Frontal area, defaults to 0.0

  • side_projectedfloat

    Side profile area, defaults to 0.0

  • wettedfloat

    Total wetted surface area, defaults to 0.0

Type:

Data

effective_diameter#

Equivalent circular diameter, defaults to 0.0

Type:

float

width#

Maximum fuselage width, defaults to 0.0

Type:

float

heights#

Collection of height measurements along the fuselage

  • maximumfloat

    Maximum height in meters, defaults to 0.0

  • at_quarter_lengthfloat

    Height at 25% of fuselage length, defaults to 0.0

  • at_three_quarters_lengthfloat

    Height at 75% of fuselage length, defaults to 0.0

  • at_wing_root_quarter_chordfloat

    Height at wing root quarter chord, defaults to 0.0

  • at_vertical_root_quarter_chordfloat

    Height at vertical tail root quarter chord, defaults to 0.0

Type:

Data

lengths#

Collection of length measurements

  • nosefloat

    Length of nose section, defaults to 0.0

  • tailfloat

    Length of tail section, defaults to 0.0

  • totalfloat

    Total fuselage length, defaults to 0.0

  • cabinfloat

    Length of passenger cabin, defaults to 0.0

  • fore_spacefloat

    Length of forward equipment bay, defaults to 0.0

  • aft_spacefloat

    Length of aft equipment bay, defaults to 0.0

Type:

Data

x_rotation#

Rotation angle about x-axis, defaults to 0.0

Type:

float

y_rotation#

Rotation angle about y-axis, defaults to 0.0

Type:

float

z_rotation#

Rotation angle about z-axis, defaults to 0.0

Type:

float

fineness#

Fineness ratio parameters

  • nosefloat

    Ratio of nose length to maximum diameter, defaults to 0.0

  • tailfloat

    Ratio of tail length to maximum diameter, defaults to 0.0

Type:

Data

nose_curvature#

Shape parameter defining nose profile curvature, defaults to 1.5

Type:

float

tail_curvature#

Shape parameter defining tail profile curvature, defaults to 1.5

Type:

float

fuel_tanks#

Collection of fuel tank components within the fuselage, initialized empty

Type:

Container

vsp_data#

OpenVSP-specific geometry parameters

  • xsec_surf_idstr

    OpenVSP cross-section surface identifier

  • xsec_numint

    Number of cross-sections in OpenVSP model, defaults to None

Type:

Data

segments#

Collection of fuselage segment components, initialized empty

Type:

Container

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

append_segment(segment)[source]#

Adds a new segment to the fuselage’s segment container.

Parameters:

segment (Data) – Fuselage segment to be added

append_cabin(cabin)[source]#

Adds a new segment to the fuselage’s segment container.

Parameters:

segment (Data) – Fuselage segment to be added

append_fuel_tank(fuel_tank)[source]#

Adds a new fuel tank to the fuselage’s fuel tank container.

Parameters:

fuel_tank (Data) – Fuel tank component to be added

compute_moment_of_inertia(center_of_gravity=[[0, 0, 0]])[source]#

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

Return type:

ndarray

See also

RCAIDE.Library.Methods.Weights.Moment_of_Inertia.compute_fuselage_moment_of_inertia

Implementation of the moment of inertia calculation