RCAIDE.Library.Plots.Geometry.generate_3d_fuel_tank_points

generate_3d_fuel_tank_points#

Functions

generate_aft_integral_wing_tank_points(wing, ...)

Generates 3D points for a BWB aft conformal integral tank.

generate_integral_fuel_tank_points(fuselage, ...)

Generates 3D coordinate points that define a fuel_tank surface.

generate_integral_wing_tank_points(wing, ...)

Generates 3D coordinate points that define a wing surface.

generate_non_integral_fuel_tank_points(fuel_tank)

Generates 3D coordinate points that define a fuel_tank surface.

transverse_tank_chord_bounds(fuel_tank[, ...])

Returns aft tank root chord bounds used by aft BWB tank generators.
generate_integral_wing_tank_points(wing, n_points, segment_list, fuel_tank, plot_centerline=False)[source]#

Generates 3D coordinate points that define a wing surface.

Parameters:

  • wing (Wing) – RCAIDE wing data structure containing geometry information

  • n_points (int) – Number of points used to discretize airfoil sections

  • dim (int) – Number of wing segments

  • plot_centerline (bool, optional) – Include the root centerline cap section in the output, default False

Returns:

G –

Data structure containing generated points with attributes:
  • X, Y, Zndarray

    Raw coordinate points

  • PTSndarray

    Combined coordinate array

  • XA1, YA1, ZA1, XA2, YA2, ZA2ndarray

    Leading edge surface points

  • XB1, YB1, ZB1, XB2, YB2, ZB2ndarray

    Trailing edge surface points

Return type:

Data

Notes

Generates wing geometry by:

  1. Creating airfoil sections at specified span positions

  2. Applying twist, sweep, and dihedral

  3. Scaling sections by local chord

  4. Positioning in aircraft coordinate system

Definitions

‘Leading Edge Sweep’

Angle between leading edge and y-axis

‘Quarter Chord Sweep’

Angle between quarter chord line and y-axis

‘Dihedral’

Upward angle of wing from horizontal

generate_integral_fuel_tank_points(fuselage, fuel_tank, segment_list, tessellation=24)[source]#

Generates 3D coordinate points that define a fuel_tank surface.

Parameters:

  • fuel_tank (fuel_tank) – RCAIDE fuel_tank data structure containing geometry information

  • tessellation (int, optional) – Number of points to use in circumferential discretization (default: 24)

Returns:

G –

Data structure containing generated points
  • PTSndarray

    Array of shape (num_segments, tessellation, 3) containing x,y,z coordinates of surface points

Return type:

Data

Notes

Points are generated by creating super-elliptical cross-sections at each segment and positioning them according to segment locations.

Major Assumptions

  • Cross-sections lie in y-z plane

  • Segments are ordered from nose to tail

  • Origin is at the nose of the fuel_tank

generate_non_integral_fuel_tank_points(fuel_tank, tessellation=24)[source]#

Generates 3D coordinate points that define a fuel_tank surface.

Parameters:

  • fuel_tank (fuel_tank) – RCAIDE fuel_tank data structure containing geometry information

  • tessellation (int, optional) – Number of points to use in circumferential discretization (default: 24)

Returns:

G –

Data structure containing generated points
  • PTSndarray

    Array of shape (num_segments, tessellation, 3) containing x,y,z coordinates of surface points

Return type:

Data

Notes

Points are generated by creating super-elliptical cross-sections at each segment and positioning them according to segment locations.

Major Assumptions

  • Cross-sections lie in y-z plane

  • Segments are ordered from nose to tail

  • Origin is at the nose of the fuel_tank

transverse_tank_chord_bounds(fuel_tank, tessalation=24)[source]#

Returns aft tank root chord bounds used by aft BWB tank generators.

generate_aft_integral_wing_tank_points(wing, n_points, segment_list, fuel_tank)[source]#

Generates 3D points for a BWB aft conformal integral tank.

This mirrors the polygon-intersection logic used by compute_bwb_aft_integral_prismatic_tank_volume so plotting geometry matches volume geometry.