Source code for RCAIDE.Framework.Analyses.Weights.Electric
# RCAIDE/Framework/Analyses/Weights/Electric.py
#
# Created: Feb 2025, S. Shekar
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# IMPORT
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import RCAIDE
from RCAIDE.Framework.Core import Data
from .Weights import Weights
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#
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[docs]
class Electric(Weights):
""" This is class that evaluates the weight of Transport 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 = 'General_Aviation'
self.propulsion_architecture = 'Electric'
self.settings.use_max_fuel_weight = True
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
self.settings.weight_reduction_factors = Data()
self.settings.weight_reduction_factors.main_wing = 0. # Reduction factors are proportional (.1 is a 10% weight reduction)
self.settings.weight_reduction_factors.fuselage = 0. # Reduction factors are proportional (.1 is a 10% weight reduction)
self.settings.weight_reduction_factors.empennage = 0. # applied to horizontal and vertical stabilizers
# FLOPS settings
self.settings.FLOPS = Data()
self.settings.FLOPS.complexity = '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
