Source code for RCAIDE.Framework.Analyses.Weights.Electric_VTOL
# RCAIDE/Framework/Analyses/Weights/Electric_VTOL.py
#
# Created: Feb 2025, S. Shekar
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Framework.Core import Data
from .Weights import Weights
# ----------------------------------------------------------------------------------------------------------------------
# Electric VTOL Weights class
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Electric_VTOL(Weights):
""" This is class that evaluates the weight of an electric VTOL class aircraft
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
def __defaults__(self):
"""This sets the default values and methods for the tube and wing
aircraft weight analysis.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.method = 'Physics_Based'
self.aircraft_type = 'VTOL'
self.propulsion_architecture = 'Electric'
self.settings.advanced_composites = False
self.settings.fuselage_mounted_landing_gear_factor = 1.12 # assumes fuselage mounted landing gear. Change to 1 if False
self.settings.cargo_doors_number = 1 # 0 if no cargo doors, 1 if 1 cargo door, 2 if 2 cargo doors
self.settings.cargo_doors_clamshell = False # True if clamshell cargo doors, False if not
# FLOPS settings
self.settings.FLOPS = Data()
self.settings.FLOPS.fidelity = 'Simple'
self.settings.FLOPS.aeroelastic_tailoring_factor = 0. # Aeroelastic tailoring factor [0 no aeroelastic tailoring, 1 maximum aeroelastic tailoring]
self.settings.FLOPS.strut_braced_wing_factor = 0. # Wing strut bracing factor [0 for no struts, 1 for struts]
# EVTOL settings factor
self.settings.miscelleneous_weight_factor = 1.1
