Source code for RCAIDE.Library.Components.Powertrain.Distributors.Fuel_Line
# RCAIDE/Library/Components/Powertrain/Distributors/Fuel_Line.py
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data, Units
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Components.Component import Container
from RCAIDE.Library.Methods.Powertrain.Distributors.Fuel_Line import *
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_distributor_moment_of_inertia import compute_distributor_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity.compute_distributor_center_of_gravity import compute_distributor_center_of_gravity
# ----------------------------------------------------------------------------------------------------------------------
# Fuel Line
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Fuel_Line(Component):
"""
Class for managing fuel distribution between aircraft fuel system components
Attributes
----------
tag : str
Identifier for the fuel line (default: 'fuel_line')
fuel_tanks : Container
Collection of fuel tanks connected to this line
assigned_propulsors : list
List of propulsion systems supplied by this fuel line
active : bool
Flag indicating if the fuel line is operational (default: True)
efficiency : float
Fuel transfer efficiency (default: 1.0)
Notes
-----
The fuel line manages fuel distribution between tanks and engines, handling
fuel transfer and flow control. It supports multiple fuel tanks and propulsors
in various aircraft configurations.
See Also
--------
RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks
Fuel tank components
RCAIDE.Library.Components.Powertrain.Propulsors
Aircraft propulsion system components
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
None
"""
self.tag = 'fuel_line'
self.fuel_tanks = Container()
self.assigned_propulsors = []
self.assigned_converters = []
self.converters = Container()
self.active = True
self.additional_line_flow_rate = 0.0
self.efficiency = 1.0
self.valve_unit_mass = 3 * Units.lbs
self.fuel_probe_unit_mass = 2.5 * Units.lbs
self.boost_pump_unit_mass = 12.5 * Units.lbs
self.venting_system_length = 0.0
self.pipe = Data()
self.pipe.rigid_material = RCAIDE.Library.Attributes.Materials.Aluminum()
self.pipe.flexible_material = RCAIDE.Library.Attributes.Materials.Stainless_Steel_304()
self.pipe.flexible_material_ratio = 0.25
self.pipe.diameters = Data()
self.pipe.diameters.external = 0.0
self.pipe.diameters.internal = 0.0
self.insulation = Data()
self.insulation.rigid_material = RCAIDE.Library.Attributes.Materials.Aluminum()
self.insulation.flexible_material = RCAIDE.Library.Attributes.Materials.Stainless_Steel_304()
self.insulation.flexible_material_ratio = 0.25
self.insulation.diameters = Data()
self.insulation.diameters.external = 0.0
self.insulation.diameters.internal = 0.0
[docs]
def append_operating_conditions(self, segment):
"""
Append operating conditions for a flight segment
Parameters
----------
segment : Segment
Flight segment containing operating conditions
"""
append_fuel_line_conditions(self, segment)
return
[docs]
def append_segment_conditions(self, segment):
"""
Append segment-specific conditions to the bus
Parameters
----------
conditions : Data
Container for segment conditions
segment : Segment
Flight segment data
"""
append_fuel_line_segment_conditions(self, segment)
return
[docs]
def compute_moments_of_inertia(self,vehicle,center_of_gravity=[[0, 0, 0]]):
"""
Computes the moment of inertia tensor for the fuel line.
Parameters
----------
center_of_gravity : list, optional
Reference point coordinates for moment calculation, defaults to [[0, 0, 0]]
See Also
--------
RCAIDE.Library.Methods.weights.vehicle.moments_of_inertia.compute_fuselage_moment_of_inertia
Implementation of the moment of inertia calculation
"""
_ , _ = compute_distributor_moment_of_inertia(self,vehicle,center_of_gravity= center_of_gravity)
return
[docs]
def compute_center_of_gravity(self,vehicle):
"""
Computes the center of gravity for the distributor.
See Also
--------
RCAIDE.Library.Methods.weights.vehicle.center_of_gravity.compute_fuselage_center_of_gravity
Implementation of the moment of inertia calculation
"""
_ = compute_distributor_center_of_gravity(self,vehicle)
return
