RCAIDE.Library.Components.Booms.Boom

Boom#

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

Bases: Component

A structural boom component model for aircraft and rotorcraft applications.

tag#

Identifier for the boom component. Default is ‘boom’.

Type:

str

origin#

3D coordinates of the boom origin [m]. Default is [[0.0,0.0,0.0]].

Type:

list

aerodynamic_center#

3D coordinates of the aerodynamic center [m]. Default is [0.0,0.0,0.0].

Type:

list

areas#

Collection of area measurements

  • front_projectedfloat

    Front projected area [m²]. Default is 0.0.

  • side_projectedfloat

    Side projected area [m²]. Default is 0.0.

  • wettedfloat

    Wetted area of the boom [m²]. Default is 0.0.

Type:

Data

effective_diameter#

Effective diameter of the boom [m]. Default is 0.0.

Type:

float

width#

Width of the boom [m]. Default is 0.0.

Type:

float

heights#

Collection of height measurements

  • maximumfloat

    Maximum height of the boom [m]. Default is 0.0.

  • at_quarter_lengthfloat

    Height at 25% of boom length [m]. Default is 0.0.

  • at_three_quarters_lengthfloat

    Height at 75% of boom length [m]. Default is 0.0.

  • at_wing_root_quarter_chordfloat

    Height at wing root quarter chord [m]. Default is 0.0.

  • at_vertical_root_quarter_chordfloat

    Height at vertical root quarter chord [m]. Default is 0.0.

Type:

Data

x_rotation#

Rotation angle around x-axis [rad]. Default is 0.0.

Type:

float

y_rotation#

Rotation angle around y-axis [rad]. Default is 0.0.

Type:

float

z_rotation#

Rotation angle around z-axis [rad]. Default is 0.0.

Type:

float

lengths#

Collection of length measurements

  • nosefloat

    Length of the nose section [m]. Default is 0.0.

  • totalfloat

    Total length of the boom [m]. Default is 0.0.

  • cabinfloat

    Length of the cabin section [m]. Default is 0.0.

  • fore_spacefloat

    Length of space in front [m]. Default is 0.0.

  • aft_spacefloat

    Length of space in rear [m]. Default is 0.0.

Type:

Data

fineness#

Fineness ratios

  • nosefloat

    Fineness ratio of nose. Default is 0.0.

  • tailfloat

    Fineness ratio of tail. Default is 0.0.

Type:

Data

differential_pressure#

Pressure differential across the boom [Pa]. Default is 0.0.

Type:

float

vsp_data#

Vehicle Sketch Pad related data

  • xsec_surf_idstr

    VSP cross-section surface identifier. Default is ‘’.

  • xsec_numint

    Number of cross-sections in boom geometry. Default is None.

Type:

Data

segments#

Container for boom segments. Default is empty container.

Type:

Container

Notes

The Boom class provides a comprehensive framework for modeling structural booms in aircraft and rotorcraft, including:

  • Geometric definition

  • Cross-sectional properties

  • Aerodynamic characteristics

  • Structural interfaces

  • VSP integration

  • Segmentation capabilities

Definitions

‘Fineness Ratio’

Ratio of length to maximum diameter

‘Wetted Area’

Total surface area exposed to airflow

‘Differential Pressure’

Pressure difference between inside and outside of boom

append_segment(segment)[source]#
Assumptions:

None

Source:

None

Parameters:

  • self – boom [unitless]

  • segment – cross-section of boom [unitless]

Outputs:

None

class Container(*args, **kwarg)#

Bases: Container

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

Bases: Container