"""
Python module for span calculations of different wing sections, part of the wing geometry.
"""
# This file is part of FAST-OAD_CS23 : A framework for rapid Overall Aircraft Design
# Copyright (C) 2025 ONERA & ISAE-SUPAERO
# FAST is free software: you can redistribute it and/or modify
# it under the terms of the GNU General Public License as published by
# the Free Software Foundation, either version 3 of the License, or
# (at your option) any later version.
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <https://www.gnu.org/licenses/>.
import numpy as np
import openmdao.api as om
import fastoad.api as oad
from ..constants import SERVICE_WING_SPAN, SUBMODEL_WING_SPAN_LEGACY
[docs]@oad.RegisterSubmodel(SERVICE_WING_SPAN, SUBMODEL_WING_SPAN_LEGACY)
class ComputeWingY(om.ExplicitComponent):
"""Wing Ys estimation, obtained from :cite:`supaero:2014`."""
# pylint: disable=missing-function-docstring
# Overriding OpenMDAO setup
[docs] def setup(self):
self.add_input("data:geometry:wing:aspect_ratio", val=np.nan)
self.add_input("data:geometry:fuselage:maximum_width", val=np.nan, units="m")
self.add_input("data:geometry:wing:area", val=np.nan, units="m**2")
self.add_input("data:geometry:wing:kink:span_ratio", val=0.5)
self.add_output("data:geometry:wing:span", units="m")
self.add_output("data:geometry:wing:root:y", units="m")
self.add_output("data:geometry:wing:kink:y", units="m")
self.add_output("data:geometry:wing:tip:y", units="m")
self.declare_partials(
of="data:geometry:wing:span",
wrt=["data:geometry:wing:area", "data:geometry:wing:aspect_ratio"],
method="exact",
)
self.declare_partials(
of="data:geometry:wing:root:y",
wrt="data:geometry:fuselage:maximum_width",
method="exact",
val=0.5,
)
self.declare_partials(
of="data:geometry:wing:kink:y",
wrt=[
"data:geometry:wing:area",
"data:geometry:wing:aspect_ratio",
"data:geometry:wing:kink:span_ratio",
],
method="exact",
)
self.declare_partials(
of="data:geometry:wing:tip:y",
wrt=[
"data:geometry:wing:area",
"data:geometry:wing:aspect_ratio",
],
method="exact",
)
# pylint: disable=missing-function-docstring, unused-argument
# Overriding OpenMDAO compute, not all arguments are used
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
lambda_wing = inputs["data:geometry:wing:aspect_ratio"]
wing_area = inputs["data:geometry:wing:area"]
wing_break = inputs["data:geometry:wing:kink:span_ratio"]
width_max = inputs["data:geometry:fuselage:maximum_width"]
span = np.sqrt(lambda_wing * wing_area)
# Wing geometry
y4_wing = span / 2.0
y2_wing = width_max / 2.0
y3_wing = y4_wing * wing_break
outputs["data:geometry:wing:span"] = span
outputs["data:geometry:wing:root:y"] = y2_wing
outputs["data:geometry:wing:kink:y"] = y3_wing
outputs["data:geometry:wing:tip:y"] = y4_wing
# pylint: disable=missing-function-docstring, unused-argument
# Overriding OpenMDAO compute_partials, not all arguments are used
[docs] def compute_partials(self, inputs, partials, discrete_inputs=None):
lambda_wing = inputs["data:geometry:wing:aspect_ratio"]
wing_area = inputs["data:geometry:wing:area"]
wing_break = inputs["data:geometry:wing:kink:span_ratio"]
partials["data:geometry:wing:span", "data:geometry:wing:aspect_ratio"] = 0.5 * np.sqrt(
wing_area / lambda_wing
)
partials["data:geometry:wing:span", "data:geometry:wing:area"] = 0.5 * np.sqrt(
lambda_wing / wing_area
)
partials["data:geometry:wing:tip:y", "data:geometry:wing:aspect_ratio"] = 0.25 * np.sqrt(
wing_area / lambda_wing
)
partials["data:geometry:wing:tip:y", "data:geometry:wing:area"] = 0.25 * np.sqrt(
lambda_wing / wing_area
)
partials["data:geometry:wing:kink:y", "data:geometry:wing:aspect_ratio"] = (
0.5 * np.sqrt(wing_area / lambda_wing) * wing_break
)
partials["data:geometry:wing:kink:y", "data:geometry:wing:area"] = (
0.5 * np.sqrt(lambda_wing / wing_area) * wing_break
)
partials["data:geometry:wing:kink:y", "data:geometry:wing:kink:span_ratio"] = 0.5 * np.sqrt(
lambda_wing * wing_area
)