Source code for RCAIDE.Library.Components.Powertrain.Systems.Systems

# RCAIDE/Library/Components/Powertrain/Systems/Systems.py
# 
# Created:  Mar 2024, M. Clarke 

# ----------------------------------------------------------------------------------------------------------------------
#  IMPORT
# ----------------------------------------------------------------------------------------------------------------------   
# RCAIDE imports   
from RCAIDE.Library.Components import Component 
from RCAIDE.Library.Methods.Powertrain.Systems.append_systems_conditions import append_systems_conditions
from RCAIDE.Library.Methods.Powertrain.Systems.compute_systems_power_draw import compute_systems_power_draw
 
# ----------------------------------------------------------------------------------------------------------------------
# System
# ----------------------------------------------------------------------------------------------------------------------            


[docs]
class Systems(Component):
    """
    Base class for aircraft systems providing core functionality for modeling 
    onboard equipment and subsystems.

    Attributes
    ----------
    tag : str
        Unique identifier for the system component, defaults to 'System'
        
    origin : list
        3D coordinates [x, y, z] defining the system's reference point, 
        defaults to [[0.0, 0.0, 0.0]]
        
    control : Data
        Control system interface parameters, defaults to None
        
    accessories : Data
        Associated auxiliary components and equipment, defaults to None

    Notes
    -----
    The system class serves as the foundation for modeling various aircraft systems:
        * Avionics and electronics
        * Environmental control systems
        * Hydraulic systems
        * Fuel systems
        * Auxiliary power units
    
    **Major Assumptions**
        * Systems are treated as point masses at their origin
        * Control interfaces are simplified
        * No dynamic response modeling
    
    **Definitions**

    'Origin'
        Reference point for system location and mass properties
        
    'Control Interface'
        Parameters defining how the system interacts with aircraft controls

    See Also
    --------
    RCAIDE.Library.Components.Powertrain.Systems.Avionics
        Implementation for aircraft avionics
    """  
    def __defaults__(self): 
        """
        Sets default values for the system attributes.
        """        
        self.tag         = 'System' 
        self.power_draw  = 0.0
        self.length      = 0
        self.width       = 0
        self.height      = 0
        self.control     = None
        self.accessories = None 
        self.mass_properties.calculated_flag = False



[docs]
    def append_operating_conditions(self, segment, bus): 
        """
        Adds operating conditions for the avionics system to a mission segment.

        Parameters
        ----------
        segment : Data
            Mission segment to which conditions are being added
        bus : Data
            Electrical bus supplying power to the avionics
        """
        append_systems_conditions(self, segment, bus)
        return    





[docs]
    def compute_performance(self,vehicle,state, bus):   
        """
        Computes the power draw of the system based on the operating conditions.

        Parameters
        ----------
        vehicle : Data
            The aircraft vehicle for which performance is being computed
        segment : Data
            Mission segment for which performance is being computed
        bus : Data
            Electrical bus supplying power to the system

        Notes
        -----
        This method should be overridden by specific system implementations to 
        calculate power draw based on their unique characteristics and operating 
        conditions. The base implementation does not perform any calculations.
        """
        compute_systems_power_draw(self, state, bus)
        return