# 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,
)
[docs]class InitializeGamma(om.ExplicitComponent):
"""Initializes the climb angle at each time step."""
[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"]
self.add_input("data:mission:sizing:main_route:cruise:altitude", val=np.nan, units="m")
self.add_input(
"data:mission:sizing:main_route:climb:climb_rate:sea_level", val=np.nan, units="m/s"
)
self.add_input(
"data:mission:sizing:main_route:climb:climb_rate:cruise_level", val=np.nan, units="m/s"
)
self.add_input("data:mission:sizing:main_route:descent:descent_rate", np.nan, units="m/s")
self.add_input(
"altitude", shape=number_of_points, val=np.full(number_of_points, np.nan), units="m"
)
self.add_input(
"true_airspeed",
shape=number_of_points,
val=np.full(number_of_points, np.nan),
units="m/s",
)
self.add_output("vertical_speed", val=np.full(number_of_points, 0.0), units="m/s")
self.add_output("gamma", val=np.full(number_of_points, 0.0), units="deg")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
cruise_altitude = np.array(inputs["data:mission:sizing:main_route:cruise:altitude"]).item()
climb_rate_sl = float(inputs["data:mission:sizing:main_route:climb:climb_rate:sea_level"])
climb_rate_cl = float(
inputs["data:mission:sizing:main_route:climb:climb_rate:cruise_level"]
)
descent_rate = -abs(inputs["data:mission:sizing:main_route:descent:descent_rate"])
altitude = inputs["altitude"]
true_airspeed = inputs["true_airspeed"]
altitude_climb = altitude[0:POINTS_NB_CLIMB]
altitude_cruise = altitude[POINTS_NB_CLIMB : POINTS_NB_CLIMB + POINTS_NB_CRUISE]
altitude_descent = altitude[POINTS_NB_CLIMB + POINTS_NB_CRUISE :]
vertical_speed_climb = np.interp(
altitude_climb, [0.0, cruise_altitude], [climb_rate_sl, climb_rate_cl]
)
vertical_speed_cruise = np.full_like(altitude_cruise, 0.0)
vertical_speed_descent = np.full_like(altitude_descent, descent_rate)
vertical_speed = np.concatenate(
(vertical_speed_climb, vertical_speed_cruise, vertical_speed_descent)
)
outputs["vertical_speed"] = vertical_speed
gamma = np.arcsin(vertical_speed / true_airspeed) * 180.0 / np.pi
outputs["gamma"] = gamma