Source code for RCAIDE.Library.Components.Fuselages.Cabins.Cabin

# RCAIDE/Components/Fuselages/Cabins/Cabin.py
#
# Created:  Mar 2024, M. Clarke

# ----------------------------------------------------------------------------------------------------------------------
#  IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data,  Units
from RCAIDE.Library.Components.Component import Container
from RCAIDE.Library.Components import Component
from RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_cabin_moment_of_inertia import compute_cabin_moment_of_inertia
from RCAIDE.Library.Methods.Mass_Properties.Center_of_Gravity.compute_cabin_center_of_gravity import compute_cabin_center_of_gravity

# ----------------------------------------------------------------------------------------------------------------------
#  Fuselage
# ----------------------------------------------------------------------------------------------------------------------




class Cabin(Component):

    def __defaults__(self):
        """
        Sets default values for all fuselage attributes.
        """

        self.tag                       = 'cabin'
        self.number_of_passengers      = 0
        self.number_of_seats           = 0
        self.segments_bounding_cabin   = []
        self.filled_seats_arrangement  = 'random'
        self.type_A_door_length        = 36 * Units.inches
        self.galley_lavatory_length    = 32 * Units.inches
        self.emergency_exit_seat_pitch = 36 * Units.inches
        self.length                    = 0
        self.width                     = 0
        self.height                    = 0
        self.wide_body                 = False
        self.tail                      = Data()
        self.tail.fineness_ratio       = 0
        self.nose                      = Data()
        self.nose.fineness_ratio       = 0
        self.classes                   = Container() 
        self.segments                  = Container()



    def append_segment(self, segment):
        """
        Adds a new segment to the cabin's segment container.

        Parameters
        ----------
        segment : Data
            Cabin segment to be added
        """
        # Assert database type
        if not isinstance(segment, RCAIDE.Library.Components.Fuselages.Cabins.Segments.Segment):
            raise Exception('input component must be of type Segment')

        # Store data
        self.segments.append(segment)

        return




    def append_cabin_class(self, cabin_class):

        # Assert database type
        if not (isinstance(cabin_class, RCAIDE.Library.Components.Fuselages.Cabins.Classes.Economy) or
                isinstance(cabin_class, RCAIDE.Library.Components.Fuselages.Cabins.Classes.Business) or
                isinstance(cabin_class, RCAIDE.Library.Components.Fuselages.Cabins.Classes.First)):
            raise Exception('input component must be of type Cabin_Class')

        # Store data
        self.classes.append(cabin_class)

        return




    def compute_moments_of_inertia(self, vehicle, center_of_gravity=[[0, 0, 0]]):
        """
        Computes the moment of inertia tensor for the cabin.

        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
        """

        for fuselage in vehicle.fuselages:
            for cabin in fuselage.cabins:
                if cabin.tag == self.tag:
                    _, _ = compute_cabin_moment_of_inertia(
                        self, fuselage, center_of_gravity)
        for wing in vehicle.wings:
            if type(wing) == RCAIDE.Library.Components.Wings.Blended_Wing_Body:
                for cabin in wing.cabins:
                    if cabin.tag == self.tag:
                        _, _ = compute_cabin_moment_of_inertia(
                            self, wing, center_of_gravity)
        return




    def compute_center_of_gravity(self, vehicle):
        """
        Computes the center of gravity for the cabin.

        See Also
        --------
        RCAIDE.Library.Methods.weights.vehicle.center_of_gravity.compute_fuselage_center_of_gravity
            Implementation of the center of gravity calculation
        """

        for fuselage in vehicle.fuselages:
            for cabin in fuselage.cabins:
                if cabin.tag == self.tag and fuselage.layout_of_passenger_accommodations != None:
                    _ = compute_cabin_center_of_gravity(self, fuselage)

        for wing in vehicle.wings:
            if isinstance(wing, RCAIDE.Library.Components.Wings.Blended_Wing_Body):
                for cabin in wing.cabins:
                    if cabin.tag == self.tag and wing.layout_of_passenger_accommodations != None:
                        _ = compute_cabin_center_of_gravity(self, wing)
        return