"""
Python module for maximum fuel weight calculation with detailed approach, part of the geometry
component.
"""
# This file is part of FAST-OAD_CS23 : A framework for rapid Overall Aircraft Design
# Copyright (C) 2025 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 openmdao.api as om
import fastoad.api as oad
from ...constants import SERVICE_MFW, SUBMODEL_MFW_ADVANCED
from .components import (
ComputeWingTankSpans,
ComputeWingTankYArray,
ComputeWingTankChordArray,
ComputeWingTankRelativeThicknessArray,
ComputeWingTankThicknessArray,
ComputeWingTankWidthArray,
ComputeWingTankReducedWidthArray,
ComputeWingTankCrossSectionArray,
ComputeWingTanksCapacity,
ComputeMFWFromWingTanksCapacity,
)
[docs]@oad.RegisterSubmodel(SERVICE_MFW, SUBMODEL_MFW_ADVANCED)
class ComputeMFWAdvanced(om.Group):
"""
Max fuel weight estimation based on :cite:`jenkinson:2003` p.65. It discretizes the fuel tank in
the wings along the span. Only works for linear chord and thickness profiles. The xml
quantities "data:geometry:propulsion:tank:LE_chord_percentage",
"data:geometry:propulsion:tank:TE_chord_percentage",
"data:geometry:propulsion:tank:y_ratio_tank_beginning" and
"data:geometry:propulsion:tank:y_ratio_tank_end" have to be determined as close to possible
as the real aircraft quantities. The quantity "settings:geometry:fuel_tanks:depth" allows to
calibrate the model for each aircraft. WARNING : If this class is updated, update_wing_area
will have to be updated as well as it uses the same approach.
"""
# pylint: disable=missing-function-docstring
# Overriding OpenMDAO initialize
[docs] def initialize(self):
self.options.declare(
"number_points_wing_mfw",
default=50,
types=int,
desc="Number of points to use in the computation of the maximum fuel weight using the "
"advanced model. Reducing that number can improve convergence.",
)
# pylint: disable=missing-function-docstring
# Overriding OpenMDAO setup
[docs] def setup(self):
nb_point_wing = self.options["number_points_wing_mfw"]
self.add_subsystem(name="tank_span", subsys=ComputeWingTankSpans(), promotes=["*"])
self.add_subsystem(
name="tank_y_array",
subsys=ComputeWingTankYArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_chord_array",
subsys=ComputeWingTankChordArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_relative_thickness_array",
subsys=ComputeWingTankRelativeThicknessArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_thickness_array",
subsys=ComputeWingTankThicknessArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_width_array",
subsys=ComputeWingTankWidthArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_reduced_width_array",
subsys=ComputeWingTankReducedWidthArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tank_cross_section_array",
subsys=ComputeWingTankCrossSectionArray(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(
name="tanks_capacity",
subsys=ComputeWingTanksCapacity(number_points_wing_mfw=nb_point_wing),
promotes=["*"],
)
self.add_subsystem(name="mfw", subsys=ComputeMFWFromWingTanksCapacity(), promotes=["*"])