RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.Non_Integral_Tank.compute_wing_non_integral_tank_volume

compute_wing_non_integral_tank_volume#

Functions

compute_non_dimensional_rib_coordinates(...)

Computes non-dimensional rib coordinates for wing segments based on airfoil geometry.

compute_wing_non_integral_tank_fuel_volume(...)

Computes the fuel volume for a non-integral tank between two wing segments.

compute_wing_non_integral_tank_volume(...)

Computes the volume of non-integral fuel tanks within wing segments.
compute_wing_non_integral_tank_volume(fuel_tank, wing, fuel_tanks)[source]#

Computes the volume of non-integral fuel tanks within wing segments.

This function iterates through wing segments to find suitable locations for non-integral fuel tanks and calculates their volumes. It handles cases where tanks cannot be placed in specified segments and attempts placement in subsequent segments.

Parameters:

  • fuel_tank (Fuel_Tank) –

    Fuel tank object containing tank specifications
    • fuelFuel

      Fuel properties including density

    • symmetricbool

      Whether the tank is symmetric about aircraft centerline

    • lengthfloat

      Length of the tank (computed)

    • outer_diameterfloat

      Outer diameter of the tank (computed)

  • wing (Wing) –

    Wing object containing segment geometry
    • segmentsdict

      Dictionary of wing segments with their properties

    • spans.projectedfloat

      Projected wing span

Returns:

volume – Net volume of the non-integral fuel tank

Return type:

float

Notes

The function attempts to place tanks in wing segments that have fuel tank capability. If placement fails in one segment, it tries the next available segment.

Major Assumptions

  • Wing segments are properly ordered from root to tip

  • At least one wing segment has fuel tank capability

  • Tank placement constraints are reasonable

compute_wing_non_integral_tank_fuel_volume(fuel_tank, wing, inner_segment_0, outer_segment, tank_percent_span_location)[source]#

Computes the fuel volume for a non-integral tank between two wing segments.

This function calculates the optimal tank dimensions and volume that can fit between two wing segments, considering wing geometry, structural constraints, and tank specifications. The tank is designed as a cylindrical tank with hemispherical end caps.

Parameters:

  • fuel_tank (Fuel_Tank) –

    Fuel tank object containing tank specifications
    • wall_thicknessfloat

      Thickness of tank walls

    • symmetricbool

      Whether the tank is symmetric about aircraft centerline

    • fuelFuel

      Fuel properties including density

  • wing (Wing) –

    Wing object containing geometry and span information
    • chords.rootfloat

      Root chord length

    • spans.projectedfloat

      Projected wing span

  • inner_segment_0 (Wing_Segment) –

    Initial inner wing segment for tank placement
    • percent_span_locationfloat

      Spanwise location as fraction of total span

    • root_chord_percentfloat

      Root chord as fraction of wing root chord

    • originlist

      Origin coordinates of the segment

    • sweeps.leading_edgefloat

      Leading edge sweep angle

    • dihedral_outboardfloat

      Outboard dihedral angle

    • fuel_tankFuel_Tank_Segment

      Fuel tank segment properties

  • outer_segment (Wing_Segment) – Outer wing segment defining tank boundary

  • tank_percent_span_location (float) – Current spanwise location of tank as fraction of total span

Returns:

  • volume (float) – Net volume of the fuel tank

  • tank_percent_span_location (float) – Updated spanwise location for next tank placement

Notes

The function uses an iterative approach to find the optimal tank diameter that fits within the wing geometry constraints. It considers wing sweep, dihedral, and structural clearances in the calculation.

Major Assumptions

  • Tank is cylindrical with hemispherical end caps

  • Wing segments have linear variation in geometry

  • Structural clearances are maintained

  • Tank placement follows wing sweep and dihedral

Theory

The tank volume is calculated as:

\[V = \pi r^2 (l - D) + \frac{4}{3}\pi r^3\]

where r is the internal radius, l is the tank length, and D is the tank diameter.

Definitions

‘Non-Integral Tank’

Fuel tank that is not structurally integrated with the wing, typically mounted between wing ribs or spars

compute_non_dimensional_rib_coordinates(compoment, fuel_tank, front_rib_nondim_x, rear_rib_nondim_x)[source]#

Computes non-dimensional rib coordinates for wing segments based on airfoil geometry.

This function extracts the upper and lower surface coordinates at the front and rear rib locations of a wing segment, accounting for structural clearances and airfoil geometry variations.

Parameters:

compoment (Wing_Segment) –

Wing segment object containing airfoil and fuel tank information
  • airfoilAirfoil

    Airfoil object containing geometry data

  • fuel_tankFuel_Tank_Segment
    Fuel tank segment properties
    • percent_chord_start_locationfloat

      Front rib location as fraction of chord

    • percent_chord_end_locationfloat

      Rear rib location as fraction of chord

Returns:

  • front_rib_nondim_y_upper (float) – Non-dimensional upper surface coordinate at front rib

  • rear_rib_nondim_y_upper (float) – Non-dimensional upper surface coordinate at rear rib

  • front_rib_nondim_y_lower (float) – Non-dimensional lower surface coordinate at front rib

  • rear_rib_nondim_y_lower (float) – Non-dimensional lower surface coordinate at rear rib

Notes

The function handles both NACA 4-series airfoils and custom airfoil coordinate files. A structural clearance is applied to ensure the tank fits within the wing structure.

Major Assumptions

  • Airfoil geometry is properly defined

  • Fuel tank chord locations are within valid range

  • Structural clearance is appropriate for the application

Definitions

‘Non-dimensional Coordinates’

Airfoil coordinates normalized by chord length, typically ranging from 0 to 1

‘Rib Coordinates’

Airfoil surface coordinates at specific chordwise locations where wing ribs or structural elements are positioned