# 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 openmdao.api as om
from fastga.models.performances.mission.mission_components import (
POINTS_NB_CLIMB,
POINTS_NB_CRUISE,
POINTS_NB_DESCENT,
)
from fastga.models.performances.mission_vector.initialization.initialize import Initialize
from fastga.models.performances.mission_vector.mission.mission_core import MissionCore
from fastga.models.performances.mission_vector.to_csv import ToCSV
from fastga.models.weight.cg.cg_variation import InFlightCGVariation
[docs]class MissionVector(om.Group):
"""Computes and potentially save mission based on options."""
def __init__(self, **kwargs):
super().__init__(**kwargs)
# Solvers setup
self.nonlinear_solver = om.NewtonSolver(solve_subsystems=True)
self.nonlinear_solver.options["iprint"] = 0
self.nonlinear_solver.options["maxiter"] = 50
self.nonlinear_solver.options["rtol"] = 1e-5
self.linear_solver = om.DirectSolver()
[docs] def initialize(self):
self.options.declare("propulsion_id", default=None, types=str, allow_none=True)
self.options.declare("out_file", default="", types=str)
[docs] def setup(self):
number_of_points = POINTS_NB_CLIMB + POINTS_NB_CRUISE + POINTS_NB_DESCENT
self.add_subsystem("in_flight_cg_variation", InFlightCGVariation(), promotes=["*"])
self.add_subsystem(
"initialization",
Initialize(number_of_points=number_of_points),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.add_subsystem(
"solve_equilibrium",
MissionCore(
number_of_points=number_of_points, propulsion_id=self.options["propulsion_id"]
),
promotes_inputs=["data:*", "settings:*"],
promotes_outputs=["data:*"],
)
self.add_subsystem(
"to_csv",
ToCSV(number_of_points=number_of_points, out_file=self.options["out_file"]),
promotes_inputs=["data:*"],
promotes_outputs=[],
)
self.connect(
"initialization.initialize_engine_setting.engine_setting",
[
"solve_equilibrium.compute_dep_equilibrium.preparation_for_energy_consumption"
+ ".engine_setting",
"to_csv.engine_setting",
],
)
self.connect(
"initialization.initialize_center_of_gravity.x_cg",
[
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.x_cg",
"to_csv.x_cg",
],
)
self.connect(
"initialization.initialize_time_and_distance.position",
["solve_equilibrium.performance_per_phase.position", "to_csv.position"],
)
self.connect(
"initialization.initialize_time_and_distance.time",
[
"solve_equilibrium.compute_time_step.time",
"solve_equilibrium.performance_per_phase.time",
"to_csv.time",
],
)
self.connect(
"initialization.initialize_airspeed_time_derivatives.d_vx_dt",
[
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.d_vx_dt",
"to_csv.d_vx_dt",
],
)
self.connect(
"initialization.initialize_airspeed.true_airspeed",
[
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.true_airspeed",
"solve_equilibrium.compute_dep_equilibrium.compute_dep_effect.true_airspeed",
"solve_equilibrium.compute_dep_equilibrium.preparation_for_energy_consumption"
+ ".true_airspeed",
"to_csv.true_airspeed",
],
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_dep_effect.delta_Cl",
"to_csv.delta_Cl",
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_dep_effect.delta_Cd",
"to_csv.delta_Cd",
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_dep_effect.delta_Cm",
"to_csv.delta_Cm",
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.alpha", "to_csv.alpha"
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.thrust", "to_csv.thrust"
)
self.connect(
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.delta_m",
"to_csv.delta_m",
)
self.connect(
"initialization.initialize_airspeed.equivalent_airspeed", "to_csv.equivalent_airspeed"
)
self.connect(
"solve_equilibrium.update_mass.mass",
[
"to_csv.mass",
"initialization.initialize_airspeed.mass",
],
)
self.connect(
"solve_equilibrium.performance_per_phase.fuel_consumed_t",
[
"to_csv.fuel_consumed_t",
"initialization.initialize_center_of_gravity.fuel_consumed_t",
],
)
self.connect(
"solve_equilibrium.performance_per_phase.non_consumable_energy_t",
[
"to_csv.non_consumable_energy_t",
],
)
self.connect(
"solve_equilibrium.performance_per_phase.thrust_rate_t", "to_csv.thrust_rate_t"
)
self.connect(
"initialization.initialize_gamma.gamma",
["to_csv.gamma", "solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.gamma"],
)
self.connect(
"initialization.initialize_altitude.altitude",
[
"to_csv.altitude",
"solve_equilibrium.compute_dep_equilibrium.compute_equilibrium.altitude",
"solve_equilibrium.compute_dep_equilibrium.compute_dep_effect.altitude",
"solve_equilibrium.compute_dep_equilibrium.preparation_for_energy_consumption"
+ ".altitude",
],
)
self.connect("solve_equilibrium.compute_time_step.time_step", "to_csv.time_step")