"""Estimation of center of gravity for a fuel propulsion system."""
# 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 fastoad.api as oad
import numpy as np
import openmdao.api as om
from .b1_engine_cg import ComputeEngineCG
from .b2_fuel_lines_cg import ComputeFuelLinesCG
from ..constants import SUBMODEL_PROPULSION_CG
[docs]@oad.RegisterSubmodel(SUBMODEL_PROPULSION_CG, "fastga.submodel.weight.cg.propulsion.legacy")
class FuelPropulsionCG(om.Group):
[docs] def setup(self):
self.add_subsystem("engine_cg", ComputeEngineCG(), promotes=["*"])
self.add_subsystem("fuel_lines_cg", ComputeFuelLinesCG(), promotes=["*"])
self.add_subsystem("propulsion_cg", ComputeFuelPropulsionCG(), promotes=["*"])
[docs]class ComputeFuelPropulsionCG(om.ExplicitComponent):
[docs] def setup(self):
self.add_input("data:weight:propulsion:engine:CG:x", units="m", val=np.nan)
self.add_input("data:weight:propulsion:fuel_lines:CG:x", units="m", val=np.nan)
self.add_input("data:weight:propulsion:engine:mass", units="kg", val=np.nan)
self.add_input("data:weight:propulsion:fuel_lines:mass", units="kg", val=np.nan)
self.add_input("data:weight:propulsion:mass", units="kg", val=np.nan)
self.add_output("data:weight:propulsion:CG:x", units="m")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
engine_cg = inputs["data:weight:propulsion:engine:CG:x"]
fuel_lines_cg = inputs["data:weight:propulsion:fuel_lines:CG:x"]
engine_mass = inputs["data:weight:propulsion:engine:mass"]
fuel_lines_mass = inputs["data:weight:propulsion:fuel_lines:mass"]
cg_propulsion = (engine_cg * engine_mass + fuel_lines_cg * fuel_lines_mass) / (
engine_mass + fuel_lines_mass
)
outputs["data:weight:propulsion:CG:x"] = cg_propulsion