Source code for RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Central_Fuel_Tank
# RCAIDE/Library/Components/Powertrain/Energy/Sources/Fuel_Tanks/Central_Fuel_Tank.py
#
#
# Created: September 2024, A. Molloy and M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from .Fuel_Tank import Fuel_Tank
from RCAIDE.Library.Methods.Powertrain.Sources.Fuel_Tanks.append_fuel_tank_conditions import append_fuel_tank_conditions
# ----------------------------------------------------------------------------------------------------------------------
# Fuel Tank
# ---------------------------------------------------------------------------------------------------------------------
[docs]
class Central_Fuel_Tank(Fuel_Tank):
"""
Class for modeling central fuel tank characteristics and behavior
Attributes
----------
tag : str
Identifier for the fuel tank (default: 'Central_fuel_tank')
fuel_selector_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 central fuel tank is located in the aircraft's center section,
often integrated with the wing box or fuselage structure.
See Also
--------
RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Fuel_Tank
Base fuel tank class
RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Wing_Fuel_Tank
Wing-mounted fuel tank class
"""
def __defaults__(self):
"""
Sets default values for central fuel tank attributes
"""
self.tag = 'Central_fuel_tank'
self.fuel_selector_ratio = 1.0
self.mass_properties.empty_mass = 0.0
self.secondary_fuel_flow = 0.0
self.length = 0.0
self.width = 0.0
self.height = 0.0
self.fuel = None
[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
