"""Convenience module for computing leading edge X positions of wing chords."""
# This file is part of FAST-OAD_CS25
# Copyright (C) 2024 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
[docs]
class VTChordGlobalPositions(om.Group):
"""
Computes leading edge X positions of vertical tail chords (root, tip)
with respect to aircraft nose.
"""
[docs]
def setup(self):
self.add_subsystem("compute", ComputeChordGlobalPositions(), promotes=["*"])
# AddSubtractComp does not allow to set default values of inputs and we do not
# manage value discrepancies at global level, so we need to do it here, hence
# the need for the current group.
# Cannot set default inputs because it is already set for the wing and OpenMDAO tries to
# verify np.nan == np.nan which is False
# self.set_input_defaults("data:geometry:wing:MAC:at25percent:x", val=np.nan, units="m")
self.set_input_defaults(
"data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25", val=np.nan, units="m"
)
self.set_input_defaults(
"data:geometry:vertical_tail:tip:leading_edge:x:local", val=np.nan, units="m"
)
self.set_input_defaults(
"data:geometry:vertical_tail:MAC:leading_edge:x:local", val=np.nan, units="m"
)
self.set_input_defaults("data:geometry:vertical_tail:MAC:length", val=np.nan, units="m")
[docs]
class ComputeChordGlobalPositions(om.AddSubtractComp):
"""
Computes leading edge X positions of vertical tail chords with respect to aircraft nose.
"""
[docs]
def setup(self):
self.add_equation(
"data:geometry:vertical_tail:MAC:at25percent:x",
[
"data:geometry:wing:MAC:at25percent:x",
"data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25",
],
scaling_factors=[1.0, 1.0],
units="m",
)
self.add_equation(
"data:geometry:vertical_tail:root:leading_edge:x",
[
"data:geometry:wing:MAC:at25percent:x",
"data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25",
"data:geometry:vertical_tail:MAC:leading_edge:x:local",
"data:geometry:vertical_tail:MAC:length",
],
scaling_factors=[1.0, 1.0, -1.0, -0.25],
units="m",
)
self.add_equation(
"data:geometry:vertical_tail:MAC:leading_edge:x",
[
"data:geometry:wing:MAC:at25percent:x",
"data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25",
"data:geometry:vertical_tail:MAC:length",
],
scaling_factors=[1.0, 1.0, -0.25],
units="m",
)
self.add_equation(
"data:geometry:vertical_tail:tip:leading_edge:x",
[
"data:geometry:vertical_tail:tip:leading_edge:x:local",
"data:geometry:wing:MAC:at25percent:x",
"data:geometry:vertical_tail:MAC:at25percent:x:from_wingMAC25",
"data:geometry:vertical_tail:MAC:leading_edge:x:local",
"data:geometry:vertical_tail:MAC:length",
],
scaling_factors=[1.0, 1.0, 1.0, -1.0, -0.25],
units="m",
)