# 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 fastga.models.performances.mission.mission_components import (
POINTS_NB_CLIMB,
POINTS_NB_CRUISE,
POINTS_NB_DESCENT,
)
from ..initialization.initialize_cg import InitializeCoG
from ..initialization.initialize_airspeed import InitializeAirspeed
from ..initialization.initialize_airspeed_derivatives import InitializeAirspeedDerivatives
from ..initialization.initialize_altitude import InitializeAltitude
from ..initialization.initialize_gamma import InitializeGamma
from ..initialization.initialize_horizontal_speed import InitializeHorizontalSpeed
from ..initialization.initialize_time_and_distance import InitializeTimeAndDistance
[docs]class Initialize(om.Group):
"""Find the conditions necessary for the aircraft equilibrium."""
[docs] def initialize(self):
self.options.declare(
"number_of_points", default=1, desc="number of equilibrium to be treated"
)
[docs] def setup(self):
number_of_points = self.options["number_of_points"]
engine_setting = np.concatenate(
(
np.full(POINTS_NB_CLIMB, 2),
np.full(POINTS_NB_CRUISE, 3),
np.full(POINTS_NB_DESCENT, 2),
)
)
ivc_engine_setting = om.IndepVarComp()
ivc_engine_setting.add_output(
"engine_setting", val=engine_setting, units=None, shape=number_of_points
)
self.add_subsystem("initialize_engine_setting", subsys=ivc_engine_setting, promotes=[])
self.add_subsystem(
"initialize_altitude",
InitializeAltitude(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_airspeed",
InitializeAirspeed(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_gamma",
InitializeGamma(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_horizontal_speed",
InitializeHorizontalSpeed(number_of_points=number_of_points),
promotes_inputs=[],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_time_and_distance",
InitializeTimeAndDistance(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_airspeed_time_derivatives",
InitializeAirspeedDerivatives(number_of_points=number_of_points),
promotes_inputs=[],
promotes_outputs=[],
)
self.add_subsystem(
"initialize_center_of_gravity",
InitializeCoG(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.connect(
"initialize_horizontal_speed.horizontal_speed",
"initialize_time_and_distance.horizontal_speed",
)
self.connect(
"initialize_airspeed.true_airspeed",
[
"initialize_gamma.true_airspeed",
"initialize_horizontal_speed.true_airspeed",
"initialize_time_and_distance.true_airspeed",
"initialize_airspeed_time_derivatives.true_airspeed",
],
)
self.connect(
"initialize_airspeed.equivalent_airspeed",
"initialize_airspeed_time_derivatives.equivalent_airspeed",
)
self.connect(
"initialize_gamma.gamma",
["initialize_airspeed_time_derivatives.gamma", "initialize_horizontal_speed.gamma"],
)
self.connect(
"initialize_altitude.altitude",
[
"initialize_airspeed.altitude",
"initialize_gamma.altitude",
"initialize_time_and_distance.altitude",
"initialize_airspeed_time_derivatives.altitude",
],
)