"""
Python module for wing half-span calculation, 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_B50, SUBMODEL_WING_B50_LEGACY
[docs]@oad.RegisterSubmodel(SERVICE_WING_B50, SUBMODEL_WING_B50_LEGACY)
class ComputeWingB50(om.ExplicitComponent):
"""Wing B50 estimation, obtained from :cite:`supaero:2014`."""
# pylint: disable=missing-function-docstring
# Overriding OpenMDAO setup
[docs] def setup(self):
self.add_input("data:geometry:wing:span", val=np.nan, units="m")
self.add_input("data:geometry:wing:sweep_50", val=np.nan, units="rad")
self.add_output("data:geometry:wing:b_50", units="m")
self.declare_partials("*", "*", 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):
span = inputs["data:geometry:wing:span"]
sweep_50 = inputs["data:geometry:wing:sweep_50"]
b_50 = span / np.cos(sweep_50)
outputs["data:geometry:wing:b_50"] = b_50
# 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):
span = inputs["data:geometry:wing:span"]
sweep_50 = inputs["data:geometry:wing:sweep_50"]
partials["data:geometry:wing:b_50", "data:geometry:wing:span"] = 1.0 / np.cos(sweep_50)
partials["data:geometry:wing:b_50", "data:geometry:wing:sweep_50"] = (
span * np.tan(sweep_50) / np.cos(sweep_50)
)