"""
Computation of wing area depending on which criteria between geometric and aerodynamic is the
most constraining.
"""
# This file is part of FAST-OAD_CS23 : A framework for rapid Overall Aircraft Design
# Copyright (C) 2022 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 logging
import numpy as np
import openmdao.api as om
_LOGGER = logging.getLogger(__name__)
[docs]class UpdateWingArea(om.ExplicitComponent):
"""
Computes needed wing area to:
- have enough lift at required approach speed
- be able to load enough fuel to achieve the sizing mission.
"""
[docs] def setup(self):
self.add_input("wing_area:geometric", val=np.nan, units="m**2")
self.add_input("wing_area:aerodynamic", val=np.nan, units="m**2")
self.add_output("data:geometry:wing:area", val=10.0, units="m**2")
self.declare_partials(
"data:geometry:wing:area",
[
"wing_area:geometric",
"wing_area:aerodynamic",
],
method="exact",
)
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
wing_area_mission = inputs["wing_area:geometric"]
wing_area_approach = inputs["wing_area:aerodynamic"]
_LOGGER.info(
"Looping on wing area with new value equal to %f",
max(wing_area_mission, wing_area_approach),
)
outputs["data:geometry:wing:area"] = max(wing_area_mission, wing_area_approach)
[docs] def compute_partials(self, inputs, partials, discrete_inputs=None):
wing_area_mission = inputs["wing_area:geometric"]
wing_area_approach = inputs["wing_area:aerodynamic"]
if wing_area_mission > wing_area_approach:
partials["data:geometry:wing:area", "wing_area:geometric"] = 1.0
partials["data:geometry:wing:area", "wing_area:aerodynamic"] = 0.0
else:
partials["data:geometry:wing:area", "wing_area:geometric"] = 0.0
partials["data:geometry:wing:area", "wing_area:aerodynamic"] = 1.0