# RCAIDE/Library/Components/Powertrain/Sources/Fuel_Tanks/Fuel_Tank.py
#
#
# Created: Mar 2024, M. Clarke
# Modified: Aug 2025, S. Shekar
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Data
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks import *
from RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.append_fuel_tank_conditions import append_fuel_tank_conditions
from RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.Non_Integral_Tank.compute_prismatic_tank_volume import compute_prismatic_tank_volume
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia import compute_cuboid_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity import compute_cuboid_center_of_gravity
# ----------------------------------------------------------------------------------------------------------------------
# Fuel Tank
# ---------------------------------------------------------------------------------------------------------------------
[docs]
class Fuel_Tank(Component):
"""
Base class for aircraft fuel tank implementations
Attributes
----------
tag : str
Identifier for the fuel tank (default: 'fuel_tank')
fuel_flow_split_ratio : float
Ratio of fuel flow allocation (default: 1.0)
mass_properties.empty_mass : float
Mass of empty tank structure [kg] (default: 0.0)
secondary_fuel_flow : float
Secondary fuel flow rate [kg/s] (default: 0.0)
fuel : Component, optional
Fuel type stored in tank (default: None)
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
"""
def __defaults__(self):
"""
Sets default values for fuel tank attributes
"""
self.tag = 'fuel_tank'
self.fuel = None
self.secondary_mass_flow_rate = 0.0
self.wall_clearance = 0.0
self.wall_thickness = 1E-3
self.fuel_flow_split_ratio = None
self.xz_plane_symmetric = True
self.wing_tag = None
self.fuselage_tag = None
self.transverse_tank = False
self.gravimetric_efficiency = 1.0
self.lengths = Data()
self.lengths.external = 0.0
self.lengths.internal = 0.0
self.widths = Data()
self.widths.external = 0.0
self.widths.internal = 0.0
self.heights = Data()
self.heights.external = 0.0
self.heights.internal = 0.0
self.diameters = Data()
self.diameters.external = 0.0
self.diameters.internal = 0.0
# Insulation sub-component
self.insulation = Component()
self.insulation.lengths = Data()
self.insulation.lengths.external = 0.0
self.insulation.lengths.internal = 0.0
self.insulation.widths = Data()
self.insulation.widths.external = 0.0
self.insulation.widths.internal = 0.0
self.insulation.heights = Data()
self.insulation.heights.external = 0.0
self.insulation.heights.internal = 0.0
self.insulation.diameters = Data()
self.insulation.diameters.external = 0.0
self.insulation.diameters.internal = 0.0
# Inner structure (pressure vessel) sub-component
self.inner_structure = Component()
self.inner_structure.lengths = Data()
self.inner_structure.lengths.external = 0.0
self.inner_structure.lengths.internal = 0.0
self.inner_structure.widths = Data()
self.inner_structure.widths.external = 0.0
self.inner_structure.widths.internal = 0.0
self.inner_structure.heights = Data()
self.inner_structure.heights.external = 0.0
self.inner_structure.heights.internal = 0.0
self.inner_structure.diameters = Data()
self.inner_structure.diameters.external = 0.0
self.inner_structure.diameters.internal = 0.0
self.tank_accesories_weight_factor = 1.0
self.segments_bounding_tank = [None, None]
self.segments_percent_chord_start = [0.1,0.1]
self.segments_percent_chord_end = [0.7,0.7]
self.percent_span_location = 0.0
[docs]
def append_operating_conditions(self,segment,fuel_line):
"""
Append fuel tank operating conditions for a flight segment
Parameters
----------
segment : Segment
Flight segment containing state conditions
fuel_line : Component
Connected fuel line component
"""
append_fuel_tank_conditions(self,segment, fuel_line)
return
[docs]
def compute_tank_properties(self,state,fuel_line):
compute_fuel_tank_properties(self,state,fuel_line)
return
[docs]
def compute_volume(self, wings, fuselages,fuel_tanks):
"""
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 : float
Computed volume of the fuel tank [m³]
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_prismatic_tank_volume(self)
return
[docs]
def compute_moments_of_inertia(self,vehicle,center_of_gravity=[[0, 0, 0]]):
"""
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 : ndarray
3x3 moment of inertia tensor in kg*m^2
"""
_, _ = compute_cuboid_moment_of_inertia(self,
outer_length=self.lengths.external,
outer_width=self.widths.external,
outer_height=self.heights.external,\
inner_length=self.lengths.external- 2*self.wall_thickness,
inner_width=self.widths.external- 2*self.wall_thickness,
inner_height=self.heights.external- 2*self.wall_thickness,
center_of_gravity=center_of_gravity,
fuel_tank=True)
return
[docs]
def compute_center_of_gravity(self,vehicle):
"""
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 : ndarray
3x3 moment of inertia tensor in kg*m^2
"""
_ = compute_cuboid_center_of_gravity(self, length=self.lengths.external)
return
