"""
Python module for airframe mass calculation,
part of the Operating Empty Weight (OEW) estimation.
"""
# 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 numpy as np
import fastoad.api as oad
import openmdao.api as om
from fastga.models.weight.mass_breakdown.a_airframe.constants import (
SERVICE_WING_MASS,
SERVICE_FUSELAGE_MASS,
SERVICE_TAIL_MASS,
SERVICE_FLIGHT_CONTROLS_MASS,
SERVICE_LANDING_GEAR_MASS,
SERVICE_PAINT_MASS,
)
from fastga.models.weight.mass_breakdown.constants import (
SERVICE_AIRFRAME_MASS,
SUBMODEL_AIRFRAME_MASS_LEGACY,
)
oad.RegisterSubmodel.active_models[SERVICE_AIRFRAME_MASS] = SUBMODEL_AIRFRAME_MASS_LEGACY
[docs]
@oad.RegisterSubmodel(SERVICE_AIRFRAME_MASS, "fastga.submodel.weight.mass.airframe.weight_nan")
class AirframeWeight(om.Group):
"""Computes mass of airframe."""
# pylint: disable=missing-function-docstring
# Overriding OpenMDAO setup
[docs]
def setup(self):
self.add_subsystem(
"wing_weight", oad.RegisterSubmodel.get_submodel(SERVICE_WING_MASS), promotes=["*"]
)
self.add_subsystem(
"fuselage_weight",
oad.RegisterSubmodel.get_submodel(SERVICE_FUSELAGE_MASS),
promotes=["*"],
)
self.add_subsystem(
"empennage_weight",
oad.RegisterSubmodel.get_submodel(SERVICE_TAIL_MASS),
promotes=["*"],
)
self.add_subsystem(
"flight_controls_weight",
oad.RegisterSubmodel.get_submodel(SERVICE_FLIGHT_CONTROLS_MASS),
promotes=["*"],
)
self.add_subsystem(
"landing_gear_weight",
oad.RegisterSubmodel.get_submodel(SERVICE_LANDING_GEAR_MASS),
promotes=["*"],
)
self.add_subsystem(
"paint_weight",
oad.RegisterSubmodel.get_submodel(SERVICE_PAINT_MASS),
promotes=["*"],
)
self.add_subsystem("airframe_weight_sum", AirframeWeightSum(), promotes=["*"])
[docs]
class AirframeWeightSum(om.ExplicitComponent):
[docs]
def setup(self):
self.add_input("data:weight:airframe:wing:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:fuselage:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:horizontal_tail:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:vertical_tail:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:flight_controls:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:landing_gear:main:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:landing_gear:front:mass", val=np.nan, units="kg")
self.add_input("data:weight:airframe:paint:mass", val=np.nan, units="kg")
self.add_output(
"data:weight:airframe:mass", units="kg", desc="Mass of the airframe", val=0.0
)
[docs]
def setup_partials(self):
self.declare_partials(of="*", wrt="*", val=1.0)
[docs]
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
outputs["data:weight:airframe:mass"] = np.sum(inputs.values())