Source code for RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank
# RCAIDE/Library/Components/Powertrain/Energy/Sources/Fuel_Tanks/Integral_Tank.py
#
# Created: Sep 2024, A. Molloy and M. Clarke
# Modified: Aug 2025, S. Shekar
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from .Fuel_Tank import Fuel_Tank
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.Integral_Tank.compute_fuselage_integral_tank_volume import compute_fuselage_integral_tank_volume
from RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.Integral_Tank.compute_wing_integral_tank_volume import compute_wing_integral_tank_volume
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_integral_tank_moment_of_inertia import compute_wing_integral_tank_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity.compute_wing_integral_tank_center_of_gravity import compute_wing_integral_tank_center_of_gravity
# ----------------------------------------------------------------------------------------------------------------------
# Fuel Tank
# ---------------------------------------------------------------------------------------------------------------------
[docs]
class Integral_Tank(Fuel_Tank):
"""Fuel tank compoment.
Class for modeling integral fuel tank characteristics and behavior
Attributes
----------
tag : str
Identifier for the fuel tank (default: 'wing_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)
length : float
Tank length [m] (default: 0.0)
width : float
Tank width [m] (default: 0.0)
height : float
Tank height [m] (default: 0.0)
fuel : Component, optional
Fuel type stored in tank (default: None)
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
"""
def __defaults__(self):
"""
Sets default values for wing fuel tank attributes
"""
self.tag = 'integral_tank'
[docs]
def __init__ (self, compoment=None):
"""
Initialize
"""
if compoment is not None:
if isinstance(compoment, RCAIDE.Library.Components.Wings.Wing):
self.wing_tag = compoment.tag
if isinstance(compoment, RCAIDE.Library.Components.Fuselages.Fuselage):
self.fuselage_tag = compoment.tag
[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_volume(self, wings, fuselages, _):
"""
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 : float
Internal volume of the fuel tank [m³]
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
See Also
--------
RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.Integral_Tank.compute_integral_tank_volume
Equations for computing integral tank volume for both wing and fuselage tanks
"""
if self.wing_tag is not None:
wing = wings[self.wing_tag]
compute_wing_integral_tank_volume(self, wing)
elif self.fuselage_tag is not None:
fuselage = fuselages[self.fuselage_tag]
compute_fuselage_integral_tank_volume(self, fuselage)
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
"""
if self.wing_tag != None:
wing = vehicle.wings[self.wing_tag]
_, _ = compute_wing_integral_tank_moment_of_inertia(self, wing, center_of_gravity = center_of_gravity)
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
"""
if self.wing_tag != None:
_ = compute_wing_integral_tank_center_of_gravity(self,vehicle)
return
