RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Fuel_Tank

Fuel_Tank#

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

Bases: Component

Base class for aircraft fuel tank implementations

tag#

Identifier for the fuel tank (default: ‘fuel_tank’)

Type:

str

fuel_flow_split_ratio#

Ratio of fuel flow allocation (default: 1.0)

Type:

float

mass_properties.empty_mass#

Mass of empty tank structure [kg] (default: 0.0)

Type:

float

secondary_fuel_flow#

Secondary fuel flow rate [kg/s] (default: 0.0)

Type:

float

fuel#

Fuel type stored in tank (default: None)

Type:

Component, optional

Notes

The fuel tank base class provides common attributes and methods for different types of aircraft fuel tanks. It handles basic fuel storage and flow management functionality.

See also

RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Central_Fuel_Tank

Center section fuel tank

RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Wing_Fuel_Tank

Wing-mounted fuel tank

append_operating_conditions(segment, fuel_line)[source]#

Append fuel tank operating conditions for a flight segment

Parameters:

  • segment (Segment) – Flight segment containing state conditions

  • fuel_line (Component) – Connected fuel line component

compute_tank_properties(state, fuel_line)[source]#
compute_volume(wings, fuselages, fuel_tanks)[source]#

Compute the volume of the non-integral fuel tank based on its attachment location.

Parameters:

  • wings (dict) – Dictionary containing wing components indexed by their tags

  • fuselages (dict) – Dictionary containing fuselage components indexed by their tags

Returns:

volume – Computed volume of the fuel tank [m³]

Return type:

float

Notes

The volume computation method depends on where the tank is attached:

  • If attached to a wing, uses wing geometry and tank dimensions

  • If attached to a fuselage, uses fuselage geometry and tank dimensions

  • If configured as a BWB aft tank, uses special BWB-specific computation

Major Assumptions

  • Tank dimensions (length, width, height) are properly defined

  • Wing or fuselage components exist in the provided dictionaries

  • For BWB aft tanks, the wing_root_tag is properly set

See also

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

compute_moments_of_inertia(vehicle, center_of_gravity=[[0, 0, 0]])[source]#

Computes the moment of inertia tensor for a fuel tank.

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

compute_center_of_gravity(vehicle)[source]#

Computes the center of gravity for a fuel tank.

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