# 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 numpy as np
import openmdao.api as om
from fastoad.constants import EngineSetting
# noinspection PyProtectedMember
from fastoad.module_management._bundle_loader import BundleLoader
import fastoad.api as oad
from stdatm import Atmosphere
from fastga.models.propulsion.fuel_propulsion.base import FuelEngineSet
[docs]class ThrustTaxi(om.ExplicitComponent):
"""Computes the fuel consumed during the taxi phases."""
def __init__(self, **kwargs):
super().__init__(**kwargs)
self._engine_wrapper = None
[docs] def initialize(self):
self.options.declare("propulsion_id", default="", types=str)
[docs] def setup(self):
self._engine_wrapper = BundleLoader().instantiate_component(self.options["propulsion_id"])
self._engine_wrapper.setup(self)
self.add_input("data:mission:sizing:taxi_out:thrust_rate", np.nan)
self.add_input("data:mission:sizing:taxi_out:speed", np.nan, units="m/s")
self.add_output("data:mission:sizing:taxi_out:thrust", 1500, units="N")
self.add_input("data:mission:sizing:taxi_in:thrust_rate", np.nan)
self.add_input("data:mission:sizing:taxi_in:speed", np.nan, units="m/s")
self.add_output("data:mission:sizing:taxi_in:thrust", 1500, units="N")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
propulsion_model = FuelEngineSet(
self._engine_wrapper.get_model(inputs), inputs["data:geometry:propulsion:engine:count"]
)
thrust_rate_to = inputs["data:mission:sizing:taxi_out:thrust_rate"]
mach_to = inputs["data:mission:sizing:taxi_out:speed"] / Atmosphere(0.0).speed_of_sound
thrust_rate_ti = inputs["data:mission:sizing:taxi_in:thrust_rate"]
mach_ti = 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_to = oad.FlightPoint(
mach=mach_to,
altitude=0.0,
engine_setting=EngineSetting.TAKEOFF,
thrust_rate=thrust_rate_to,
)
propulsion_model.compute_flight_points(flight_point_to)
thrust_to = flight_point_to.thrust
flight_point_ti = oad.FlightPoint(
mach=mach_ti,
altitude=0.0,
engine_setting=EngineSetting.TAKEOFF,
thrust_rate=thrust_rate_ti,
)
propulsion_model.compute_flight_points(flight_point_ti)
thrust_ti = flight_point_ti.thrust
outputs["data:mission:sizing:taxi_out:thrust"] = thrust_to
outputs["data:mission:sizing:taxi_in:thrust"] = thrust_ti