Source code for RCAIDE.Library.Components.Powertrain.Propulsors.Propulsor
# RCAIDE/Library/Components/Propulsors/Propulsor.py
#
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia import compute_cylinder_moment_of_inertia
import numpy as np
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# Propusor
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Propulsor(Component):
"""
Base class for all propulsion system components in RCAIDE.
Attributes
----------
tag : str
Identifier for the propulsor, defaults to 'propulsor'
active : bool
Flag indicating if the propulsor is operational, defaults to True
wing_mounted : bool
Flag indicating if the propulsor is mounted on a wing, defaults to True
Notes
-----
This class serves as the foundation for all propulsion system implementations
in RCAIDE. It provides the basic structure and common attributes needed for:
* Electric propulsion systems (rotors, ducted fans)
* Internal combustion engine systems (fixed and constant-speed propellers)
* Gas turbine systems (turbofans, turbojets, turboprops)
The class inherits from Component, providing basic component functionality
while adding propulsion-specific features. Derived classes must implement
their own performance calculation methods and system-specific attributes.
**Definitions**
'Propulsor'
Any device that generates thrust or lift force through the manipulation
of fluid momentum (air in most cases)
'Wing-mounted'
Configuration where the propulsor is attached to the aircraft's wing
rather than the fuselage or other structures
See Also
--------
RCAIDE.Library.Components.Component
RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Rotor
RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Ducted_Fan
RCAIDE.Library.Components.Powertrain.Propulsors.ICE_Propeller
RCAIDE.Library.Components.Powertrain.Propulsors.Constant_Speed_ICE_Propeller
"""
def __defaults__(self):
""" This sets the default values.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.tag = 'propulsor'
self.active = True
self.wing_mounted = True
self.nacelle = None
self.sealevel_static_thrust = 0.0
self.diameter = 0.0
self.length = 0.0
self.height = 0.0
self.working_fluid = RCAIDE.Library.Attributes.Gases.Air()
[docs]
def compute_moments_of_inertia(self,vehicle,center_of_gravity=[[0, 0, 0]]):
"""
Computes the moment of inertia tensor for the propulsor.
Parameters
----------
center_of_gravity : list, optional
Reference point coordinates, defaults to [[0, 0, 0]]
Returns
-------
ndarray
3x3 moment of inertia tensor
"""
_, _ = compute_cylinder_moment_of_inertia(self, self.length, self.diameter/2, 0, 0, center_of_gravity=center_of_gravity)
return
