RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.Integral_Tank.compute_wing_integral_tank_volume

compute_wing_integral_tank_volume#

compute_wing_integral_tank_volume(fuel_tank, wing, n_points=101, scale_factor=0.85)[source]#

Computes the fuel volume for an integral fuel tank within a wing structure.

This function calculates the volume of fuel that can be stored in an integral tank within the wing. It handles both single-segment and multi-segment wing configurations, updating the fuel tank’s mass properties and center of gravity accordingly.

Parameters:

fuel_tank (Fuel_Tank) – The fuel tank object containing fuel properties and mass characteristics
wing (Wing) – The wing object containing segment geometry, airfoil data, and fuel tank specifications

Returns:

volume – The calculated fuel volume in cubic units

Return type:

float

Notes

The function determines the fuel tank origin from the wing origin and calculates volume based on whether the wing has multiple segments or is a single segment. For multi-segment wings, it iterates through adjacent segments to find fuel tank locations and accumulates moments of inertia.

Major Assumptions

Fuel tank geometry follows the wing’s airfoil profile
Fuel density is uniform throughout the tank
Wing segments are properly connected and oriented

Theory

For multi-segment wings, the volume is calculated segment by segment using truncated prism geometry. The center of gravity is computed as a weighted average of segment centers.

Definitions

‘Integral Wing Tank’: A fuel tank built into the wing structure, typically within the wing box
‘Wing Box’: The structural box formed by the front and rear spars of the wing