"""
Main component for mass breakdown.
"""
# 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
from openmdao.core.explicitcomponent import ExplicitComponent
[docs]class UpdateMLWandMZFW(ExplicitComponent):
"""
Computes Maximum Landing Weight and Maximum Zero Fuel Weight from
Overall Empty Weight and Maximum Payload.
"""
[docs] def setup(self):
self.add_input("data:weight:aircraft:OWE", val=np.nan, units="kg")
self.add_input("data:weight:aircraft:MTOW", val=np.nan, units="kg")
self.add_input("data:weight:aircraft:max_payload", val=np.nan, units="kg")
self.add_input("data:weight:aircraft:payload", val=np.nan, units="kg")
self.add_input("data:TLAR:v_cruise", val=np.nan, units="kn")
self.add_input("settings:weight:aircraft:MLW_MZFW_ratio", val=1.06)
self.add_output("data:weight:aircraft:MZFW", units="kg")
self.declare_partials("data:weight:aircraft:MZFW", "data:weight:aircraft:OWE", val=1.0)
self.declare_partials(
"data:weight:aircraft:MZFW", "data:weight:aircraft:max_payload", val=1.0
)
self.add_output("data:weight:aircraft:ZFW", units="kg")
self.declare_partials("data:weight:aircraft:ZFW", "data:weight:aircraft:OWE", val=1.0)
self.declare_partials("data:weight:aircraft:ZFW", "data:weight:aircraft:payload", val=1.0)
self.add_output("data:weight:aircraft:MLW", units="kg")
self.declare_partials(
"data:weight:aircraft:MLW",
[
"data:weight:aircraft:MTOW",
"data:weight:aircraft:OWE",
"data:weight:aircraft:max_payload",
"settings:weight:aircraft:MLW_MZFW_ratio",
],
method="exact",
)
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
owe = inputs["data:weight:aircraft:OWE"]
mtow = inputs["data:weight:aircraft:MTOW"]
max_pl = inputs["data:weight:aircraft:max_payload"]
pl = inputs["data:weight:aircraft:payload"]
cruise_ktas = inputs["data:TLAR:v_cruise"]
mzfw = owe + max_pl
zfw = owe + pl
if cruise_ktas > 250.0:
mlw = inputs["settings:weight:aircraft:MLW_MZFW_ratio"] * mzfw
else:
mlw = mtow
outputs["data:weight:aircraft:MZFW"] = mzfw
outputs["data:weight:aircraft:ZFW"] = zfw
outputs["data:weight:aircraft:MLW"] = mlw
[docs] def compute_partials(self, inputs, partials, discrete_inputs=None):
owe = inputs["data:weight:aircraft:OWE"]
max_pl = inputs["data:weight:aircraft:max_payload"]
cruise_ktas = inputs["data:TLAR:v_cruise"]
mzfw = owe + max_pl
if cruise_ktas > 250.0:
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:MTOW",
] = 0.0
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:OWE",
] = inputs["settings:weight:aircraft:MLW_MZFW_ratio"]
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:max_payload",
] = inputs["settings:weight:aircraft:MLW_MZFW_ratio"]
partials[
"data:weight:aircraft:MLW",
"settings:weight:aircraft:MLW_MZFW_ratio",
] = mzfw
else:
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:MTOW",
] = 1.0
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:OWE",
] = 0.0
partials[
"data:weight:aircraft:MLW",
"data:weight:aircraft:max_payload",
] = 0.0
partials[
"data:weight:aircraft:MLW",
"settings:weight:aircraft:MLW_MZFW_ratio",
] = 0.0