RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank

Integral_Tank#

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

Bases: Fuel_Tank

Fuel tank compoment.

Class for modeling integral fuel tank characteristics and behavior

tag#

Identifier for the fuel tank (default: ‘wing_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

length#

Tank length [m] (default: 0.0)

Type:: float

width#

Tank width [m] (default: 0.0)

Type:: float

height#

Tank height [m] (default: 0.0)

Type:: float

fuel#

Fuel type stored in tank (default: None)

Type:: Component, optional

Notes

The intergral tank is integrated into the aircraft wing structure, utilizing the space between wing spars and ribs for fuel storage.

See also

RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Fuel_Tank: Base fuel tank class
RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Non_Integral_Tank: Non-integral fuel tank

__init__(compoment=None)[source]#: Initialize

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_volume(wings, fuselages, _)[source]#

Compute the internal volume of an integral fuel tank based on its location.

Calculates the fuel tank volume by determining whether the tank is integrated into a wing or fuselage structure and computing the appropriate volume using geometric properties of the host component.

Parameters:

wings (dict) – Dictionary containing wing components indexed by wing tag
fuselages (dict) – Dictionary containing fuselage components indexed by fuselage tag

Returns:

volume – Internal volume of the fuel tank [m³]

Return type:

float

Notes

The function determines the tank location using the wing_tag or fuselage_tag attributes set during initialization. If wing_tag is set, it computes wing integral tank volume. If fuselage_tag is set, it computes fuselage integral tank volume. See compute_wing_integral_tank_volume and compute_fuselage_integral_tank_fuel_volume for more details on the volume calculations.

Major Assumptions

Tank is fully integrated into the host component structure
Wing tanks use the space between front and rear spars
Fuselage tanks use the space between specified fuselage segments
Volume calculations assume truncated prism geometry for wing tanks
Volume calculations assume truncated cone geometry for fuselage tanks

Definitions

‘Integral Tank’: Fuel tank that is structurally integrated into the aircraft’s primary structure (wing or fuselage) rather than being a separate component
‘Wing Integral Tank’: Fuel tank that utilizes the space between wing spars and ribs for fuel storage, typically located in the wing box
‘Fuselage Integral Tank’: Fuel tank that utilizes the space within fuselage segments for fuel storage, typically located between structural frames