"""
FAST - Copyright (c) 2016 ONERA ISAE
"""
# 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.service_registry import RegisterSubmodel
from .constants import (
SERVICE_FLIGHT_CONTROLS_CG,
SERVICE_HORIZONTAL_TAIL_CG,
SERVICE_OTHERS_CG,
SERVICE_TANKS_CG,
SERVICE_VERTICAL_TAIL_CG,
SERVICE_WING_CG,
SERVICE_GLOBAL_CG,
SERVICE_MLG_CG,
SERVICE_AIRCRAFT_CG,
)
from ..constants import SERVICE_CENTERS_OF_GRAVITY
[docs]@RegisterSubmodel(SERVICE_CENTERS_OF_GRAVITY, "fastoad.submodel.weight.cg.legacy")
class CG(om.Group):
""" Model that computes the global center of gravity """
[docs] def setup(self):
self.add_subsystem(
"ht_cg", RegisterSubmodel.get_submodel(SERVICE_HORIZONTAL_TAIL_CG), promotes=["*"]
)
self.add_subsystem(
"vt_cg", RegisterSubmodel.get_submodel(SERVICE_VERTICAL_TAIL_CG), promotes=["*"]
)
self.add_subsystem(
"compute_cg_wing", RegisterSubmodel.get_submodel(SERVICE_WING_CG), promotes=["*"]
)
self.add_subsystem(
"compute_cg_control_surface",
RegisterSubmodel.get_submodel(SERVICE_FLIGHT_CONTROLS_CG),
promotes=["*"],
)
self.add_subsystem(
"compute_cg_tanks", RegisterSubmodel.get_submodel(SERVICE_TANKS_CG), promotes=["*"]
)
self.add_subsystem(
"compute_cg_others", RegisterSubmodel.get_submodel(SERVICE_OTHERS_CG), promotes=["*"]
)
self.add_subsystem(
"compute_cg", RegisterSubmodel.get_submodel(SERVICE_GLOBAL_CG), promotes=["*"]
)
self.add_subsystem(
"update_mlg", RegisterSubmodel.get_submodel(SERVICE_MLG_CG), promotes=["*"]
)
self.add_subsystem(
"aircraft", RegisterSubmodel.get_submodel(SERVICE_AIRCRAFT_CG), promotes=["*"]
)
# Solvers setup
self.nonlinear_solver = om.NonlinearBlockGS()
self.nonlinear_solver.options["iprint"] = 0
self.nonlinear_solver.options["maxiter"] = 200
self.linear_solver = om.LinearBlockGS()
self.linear_solver.options["iprint"] = 0
[docs]@RegisterSubmodel(SERVICE_AIRCRAFT_CG, "fastoad.submodel.weight.cg.aircraft.legacy")
class ComputeAircraftCG(om.ExplicitComponent):
""" Compute position of aircraft CG from CG ratio """
[docs] def setup(self):
self.add_input("data:weight:aircraft:CG:aft:MAC_position", val=np.nan)
self.add_input("data:geometry:wing:MAC:at25percent:x", val=np.nan, units="m")
self.add_input("data:geometry:wing:MAC:length", val=np.nan, units="m")
self.add_output("data:weight:aircraft:CG:aft:x", units="m")
[docs] def setup_partials(self):
self.declare_partials("*", "*", method="fd")
[docs] def compute(self, inputs, outputs):
cg_ratio = inputs["data:weight:aircraft:CG:aft:MAC_position"]
l0_wing = inputs["data:geometry:wing:MAC:length"]
mac_position = inputs["data:geometry:wing:MAC:at25percent:x"]
outputs["data:weight:aircraft:CG:aft:x"] = (
mac_position - 0.25 * l0_wing + cg_ratio * l0_wing
)