"""
Estimation of wing Ys (sections span)
"""
# This file is part of FAST-OAD : A framework for rapid Overall Aircraft Design
# Copyright (C) 2021 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 math
import numpy as np
from openmdao.core.explicitcomponent import ExplicitComponent
[docs]class ComputeYWing(ExplicitComponent):
# TODO: Document equations. Cite sources
""" Wing Ys estimation """
[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=np.nan)
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")
[docs] def setup_partials(self):
self.declare_partials(
"data:geometry:wing:span",
["data:geometry:wing:area", "data:geometry:wing:aspect_ratio"],
method="fd",
)
self.declare_partials(
"data:geometry:wing:root:y", "data:geometry:fuselage:maximum_width", method="fd"
)
self.declare_partials(
"data:geometry:wing:kink:y",
[
"data:geometry:wing:area",
"data:geometry:wing:aspect_ratio",
"data:geometry:wing:kink:span_ratio",
],
method="fd",
)
self.declare_partials(
"data:geometry:wing:tip:y",
["data:geometry:wing:area", "data:geometry:wing:aspect_ratio"],
method="fd",
)
[docs] def compute(self, inputs, outputs):
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 = math.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