"""
Computation of wing position
"""
# 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 numpy as np
import openmdao.api as om
from fastoad.module_management.constants import ModelDomain
from fastoad.module_management.service_registry import RegisterOpenMDAOSystem
[docs]@RegisterOpenMDAOSystem("fastoad.loop.wing_position", domain=ModelDomain.OTHER)
class ComputeWingPosition(om.ExplicitComponent):
"""
Computes the wing position for a static margin target
"""
[docs] def setup(self):
self.add_input("data:handling_qualities:static_margin", val=np.nan)
self.add_input("data:handling_qualities:static_margin:target", val=np.nan)
self.add_input("data:geometry:wing:MAC:length", val=np.nan, units="m")
self.add_input("data:weight:aircraft:CG:aft:MAC_position", val=np.nan)
self.add_input("data:weight:aircraft:CG:aft:x", val=np.nan, units="m")
self.add_output("data:geometry:wing:MAC:at25percent:x", val=17.0, units="m")
[docs] def setup_partials(self):
self.declare_partials(of="*", wrt="*", method="fd")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
static_margin = inputs["data:handling_qualities:static_margin"]
target_static_margin = inputs["data:handling_qualities:static_margin:target"]
l0_wing = inputs["data:geometry:wing:MAC:length"]
cg_ratio = inputs["data:weight:aircraft:CG:aft:MAC_position"]
cg_x = inputs["data:weight:aircraft:CG:aft:x"]
mac_position = (
cg_x
+ 0.25 * l0_wing
- cg_ratio * l0_wing
- (static_margin - target_static_margin) * l0_wing
)
outputs["data:geometry:wing:MAC:at25percent:x"] = mac_position