Source code for fastoad_cs25.models.geometry.geom_components.wing.components.compute_mfw

"""
Estimation of max fuel weight
"""
#  This file is part of FAST-OAD_CS25
#  Copyright (C) 2024 ONERA & ISAE-SUPAERO
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import fastoad.api as oad
import numpy as np
import openmdao.api as om

from ..constants import SERVICE_WING_GEOMETRY_MFW


# TODO: This belongs more to mass breakdown than geometry
[docs] @oad.RegisterSubmodel(SERVICE_WING_GEOMETRY_MFW, "fastoad.submodel.geometry.wing.mfw.legacy") class ComputeMFW(om.ExplicitComponent): # TODO: Document equations. Cite sources """Max fuel weight estimation"""
[docs] def setup(self): self.add_input("data:geometry:wing:area", val=np.nan, units="m**2") self.add_input("data:geometry:wing:aspect_ratio", val=np.nan, units="unitless") self.add_input("data:geometry:wing:root:thickness_ratio", val=np.nan, units="unitless") self.add_input("data:geometry:wing:tip:thickness_ratio", val=np.nan, units="unitless") self.add_output("data:weight:aircraft:MFW", units="kg")
[docs] def setup_partials(self): self.declare_partials("data:weight:aircraft:MFW", "*", method="fd")
[docs] def compute(self, inputs, outputs): wing_area = inputs["data:geometry:wing:area"] lambda_wing = inputs["data:geometry:wing:aspect_ratio"] el_emp = inputs["data:geometry:wing:root:thickness_ratio"] el_ext = inputs["data:geometry:wing:tip:thickness_ratio"] # TODO: remove hard coded value mfw = 224 * (wing_area**1.5 * lambda_wing ** (-0.4) * (0.6 * el_emp + 0.4 * el_ext)) + 1570 outputs["data:weight:aircraft:MFW"] = mfw