"""Simple module for prepping the use of the mission builder."""
# 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
import numpy as np
from stdatm import Atmosphere
import fastoad.api as oad
from fastoad.module_management.constants import ModelDomain
from fastga.models.performances.mission.takeoff import TakeOffPhase
from fastga.models.weight.cg.cg_variation import InFlightCGVariation
[docs]@oad.RegisterOpenMDAOSystem(
"fastga.performances.mission_builder_prep", domain=ModelDomain.PERFORMANCE
)
class PrepareMissionBuilder(om.Group):
[docs] def initialize(self):
self.options.declare("propulsion_id", default="", types=str)
[docs] def setup(self):
self.add_subsystem(
"takeoff", TakeOffPhase(propulsion_id=self.options["propulsion_id"]), promotes=["*"]
)
self.add_subsystem("in_flight_cg_variation", InFlightCGVariation(), promotes=["*"])
self.add_subsystem("mission_builder_preparation", _PrepareMissionBuilder(), promotes=["*"])
class _PrepareMissionBuilder(om.ExplicitComponent):
"""
Make some simple computation in order to enable the use of the mission builder in FAST-OAD-GA
with relevant physic properties
"""
def setup(self):
self.add_input("data:TLAR:v_cruise", val=np.nan, units="m/s")
self.add_input("data:weight:aircraft:MTOW", val=np.nan, units="kg")
self.add_input("data:aerodynamics:wing:low_speed:CL_max_clean", val=np.nan)
self.add_input("data:geometry:wing:area", val=np.nan, units="m**2")
self.add_output("data:mission:sizing:cs23:min_climb_speed", units="m/s")
self.add_output("data:mission:sizing:holding:v_holding", units="m/s")
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
mtow = inputs["data:weight:aircraft:MTOW"]
wing_area = inputs["data:geometry:wing:area"]
cl_max_clean = inputs["data:aerodynamics:wing:low_speed:CL_max_clean"]
altitude = 0.0
g = 9.81
atm = Atmosphere(altitude=altitude, altitude_in_feet=False)
rho = atm.density
v_climb_min = 1.3 * np.sqrt((mtow * g) / (0.5 * rho * wing_area * cl_max_clean))
outputs["data:mission:sizing:cs23:min_climb_speed"] = v_climb_min
# Based on the ratio between the speed of best L/D and the speed of best endurance
# according to Gudmundsson
outputs["data:mission:sizing:holding:v_holding"] = 0.75 * inputs["data:TLAR:v_cruise"]