"""Simple module for taxi computation."""
# 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 logging
import numpy as np
import openmdao.api as om
# noinspection PyProtectedMember
from fastoad.module_management._bundle_loader import BundleLoader
import fastoad.api as oad
from fastoad.constants import EngineSetting
from stdatm import Atmosphere
from ..constants import SUBMODEL_TAXI
_LOGGER = logging.getLogger(__name__)
oad.RegisterSubmodel.active_models[SUBMODEL_TAXI] = (
"fastga.submodel.performances.mission.taxi.legacy"
)
[docs]@oad.RegisterSubmodel(SUBMODEL_TAXI, "fastga.submodel.performances.mission.taxi.legacy")
class ComputeTaxi(om.ExplicitComponent):
"""Compute the fuel consumption for taxi based on speed and duration."""
def __init__(self, **kwargs):
super().__init__(**kwargs)
self._engine_wrapper = None
[docs] def initialize(self):
self.options.declare("propulsion_id", default="", types=str)
self.options.declare("taxi_out", default=True, types=bool)
[docs] def setup(self):
self._engine_wrapper = BundleLoader().instantiate_component(self.options["propulsion_id"])
self._engine_wrapper.setup(self)
if self.options["taxi_out"]:
self.add_input("data:mission:sizing:taxi_out:thrust_rate", np.nan)
self.add_input("data:mission:sizing:taxi_out:duration", np.nan, units="s")
self.add_input("data:mission:sizing:taxi_out:speed", np.nan, units="m/s")
self.add_output("data:mission:sizing:taxi_out:fuel", units="kg")
else:
self.add_input("data:mission:sizing:taxi_in:thrust_rate", np.nan)
self.add_input("data:mission:sizing:taxi_in:duration", np.nan, units="s")
self.add_input("data:mission:sizing:taxi_in:speed", np.nan, units="m/s")
self.add_output("data:mission:sizing:taxi_in:fuel", units="kg")
self.declare_partials("*", "*", method="fd")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
if self.options["taxi_out"]:
_LOGGER.info("Entering mission computation")
propulsion_model = self._engine_wrapper.get_model(inputs)
if self.options["taxi_out"]:
thrust_rate = inputs["data:mission:sizing:taxi_out:thrust_rate"]
duration = inputs["data:mission:sizing:taxi_out:duration"]
mach = inputs["data:mission:sizing:taxi_out:speed"] / Atmosphere(0.0).speed_of_sound
else:
thrust_rate = inputs["data:mission:sizing:taxi_in:thrust_rate"]
duration = inputs["data:mission:sizing:taxi_in:duration"]
mach = inputs["data:mission:sizing:taxi_in:speed"] / Atmosphere(0.0).speed_of_sound
# FIXME: no specific settings for taxi (to be changed in fastoad\constants.py)
flight_point = oad.FlightPoint(
mach=mach, altitude=0.0, engine_setting=EngineSetting.TAKEOFF, thrust_rate=thrust_rate
)
propulsion_model.compute_flight_points(flight_point)
fuel_mass = propulsion_model.get_consumed_mass(flight_point, duration)
if self.options["taxi_out"]:
outputs["data:mission:sizing:taxi_out:fuel"] = fuel_mass
else:
outputs["data:mission:sizing:taxi_in:fuel"] = fuel_mass