Source code for RCAIDE.Framework.Analyses.Weights.Weights
# RCAIDE/Framework/Analyses/Weights/Weights.py
#
# Created: Jun 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
import importlib
from RCAIDE.Framework.Core import Data
from RCAIDE.Framework.Analyses import Analysis
# ----------------------------------------------------------------------
# Analysis
# ----------------------------------------------------------------------
[docs]
class Weights(Analysis):
""" This is a class that call the functions that computes the weight of
an aircraft depending on its configration
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
def __defaults__(self):
"""Set default values and settings for the weights analysis.
Notes
-----
**Settings**
``run_weights_analysis`` (default ``True``)
Perform a full OEW buildup every call. Takeoff weight is always
recomputed as ``OEW + payload + fuel``. Set to ``False`` only when
you want to bypass the buildup entirely and rely on values already
on the vehicle (e.g. a hand-calculated fixed weight).
``overwrite_operating_empty_weight`` (default ``True``)
Replace ``mass_properties.operating_empty`` with the value derived
from the weight breakdown after each evaluation.
``iterate_mtow`` (default ``False``)
Iterate MTOW to satisfy the MTOW capacity fraction constraint.
Requires ``settings.mtow_capacity_fraction`` to be set (0–1).
Significantly increases computational cost; leave ``False``
for most optimizations.
``run_center_of_gravity_analysis`` (default ``False``)
Compute and store the vehicle CG after the weight buildup.
``run_moments_of_inertia_analysis`` (default ``False``)
Compute and store the vehicle MOI tensor after the weight buildup.
``write_mass_properties`` (default ``False``)
Write a weight breakdown Excel report alongside the script output.
``weight_correction_factors``
Multiplicative scale factors applied to individual weight components
after the buildup (e.g. 0.9 applies a 10 % weight reduction).
``weight_correction_additions``
Additive corrections applied to individual weight components after
the buildup.
"""
self.tag = 'weights'
self.method = None
self.aircraft_type = None
self.propulsion_architecture = None
self.print_weight_analysis_report = True
self.settings = Data()
self.settings.overwrite_operating_empty_weight = True
self.settings.run_weights_analysis = True
self.settings.run_center_of_gravity_analysis = False
self.settings.run_moments_of_inertia_analysis = False
self.settings.update_max_fuel_mass = False
self.settings.update_fuel_mass = True
self.settings.write_mass_properties = False
self.settings.iterate_mtow = False
self.settings.mtow_capacity_fraction = 0.0
self.settings.weight_correction_factors = Data()
self.settings.weight_correction_factors.empty = Data()
self.settings.weight_correction_factors.empty.propulsion = Data()
self.settings.weight_correction_factors.empty.structural = Data()
self.settings.weight_correction_factors.empty.systems = Data()
self.settings.weight_correction_additions = Data()
self.settings.weight_correction_additions.empty = Data()
self.settings.weight_correction_additions.empty.propulsion = Data()
self.settings.weight_correction_additions.empty.structural = Data()
self.settings.weight_correction_additions.empty.systems = Data()
self.settings.weight_correction_additions.operational_items = Data()
[docs]
def evaluate(self, vehicle):
"""Evaluate the weight analysis.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results
"""
#unpack
compute_module = importlib.import_module(f"RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.{self.propulsion_architecture}.{self.aircraft_type}.{self.method}.compute_operating_empty_weight")
compute_operating_empty_weight = getattr(compute_module, "compute_operating_empty_weight")
# Call the function
results = compute_operating_empty_weight(vehicle, self.settings)
vehicle.mass_properties.weight_breakdown = results
return results
