RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Non_Integral_Tank

Non_Integral_Tank#

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

Bases: Fuel_Tank

Class for modeling non-integral fuel tank characteristics and behavior.

Non-integral tanks are separate fuel storage containers that are not structurally integrated into the wing or fuselage. They can be attached to wings, fuselages, or configured as specialized tanks for blended wing body (BWB) aircraft.

tag#

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

Type:

str

orientation_euler_angles#

Euler angles defining tank orientation [rad] (default: [0., 0., 0.])

Type:

list

transverse_tank#

Flag indicating if tank is configured as BWB aft tank (default: False)

Type:

bool

aft_tank_start_root_chord#

Starting position of aft tank along root chord [m] (default: None)

Type:

float, optional

aft_tank_end_rood_chord#

Ending position of aft tank along root chord [m] (default: None)

Type:

float, optional

aft_tank_end_segment_tag#

Tag of wing segment where aft tank ends (default: None)

Type:

str, optional

wing_root_tag#

Tag of the root wing for BWB configurations (default: None)

Type:

str, optional

radial_offset#

Radial offset from attachment surface [m] (default: 0.0)

Type:

float

wing_tag#

Tag of the wing this tank is attached to (default: None)

Type:

str, optional

fuselage_tag#

Tag of the fuselage this tank is attached to (default: None)

Type:

str, optional

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

radial_offset#

Reduction in radius for a tank (default: None)

Type:

float

Notes

Non-integral tanks provide flexibility in fuel storage placement and can be positioned to optimize aircraft balance and structural efficiency. They are commonly used in aircraft where integral wing tanks are not feasible or additional fuel capacity is required.

Definitions

‘Non-integral Tank’

A fuel storage container that is separate from the primary aircraft structure and attached externally to wings, fuselages, or other components.

‘BWB Aft Tank’

A specialized non-integral tank configuration for blended wing body aircraft positioned in the aft section of the wing root.

See also

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

Base fuel tank class

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

Integral fuel tank class

__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, 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