"""
Estimation of fixed operational systems weight
"""
# This file is part of FAST-OAD : A framework for rapid Overall Aircraft Design
# Copyright (C) 2021 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 FixedOperationalSystemsWeight(ExplicitComponent):
"""
Weight estimation for fixed operational systems (weather radar, flight recorder, ...)
Based on formulas in :cite:`supaero:2014`, mass contribution C5
"""
[docs] def setup(self):
self.add_input("data:geometry:fuselage:front_length", val=np.nan, units="m")
self.add_input("data:geometry:fuselage:rear_length", val=np.nan, units="m")
self.add_input("data:geometry:fuselage:length", val=np.nan, units="m")
self.add_input("data:geometry:cabin:seats:economical:count_by_row", val=np.nan)
self.add_input("data:geometry:wing:root:chord", val=np.nan, units="m")
self.add_input("data:geometry:cabin:containers:count_by_row", val=np.nan)
self.add_input("tuning:weight:systems:operational:mass:k", val=1.0)
self.add_input("tuning:weight:systems:operational:mass:offset", val=0.0, units="kg")
self.add_output("data:weight:systems:operational:radar:mass", units="kg")
self.add_output("data:weight:systems:operational:cargo_hold:mass", units="kg")
[docs] def setup_partials(self):
self.declare_partials("*", "*", method="fd")
# pylint: disable=too-many-locals
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
front_section_length = inputs["data:geometry:fuselage:front_length"]
aft_section_length = inputs["data:geometry:fuselage:rear_length"]
fuselage_length = inputs["data:geometry:fuselage:length"]
front_seat_number_eco = inputs["data:geometry:cabin:seats:economical:count_by_row"]
l2_wing = inputs["data:geometry:wing:root:chord"]
side_by_side_container_number = inputs["data:geometry:cabin:containers:count_by_row"]
k_c5 = inputs["tuning:weight:systems:operational:mass:k"]
offset_c5 = inputs["tuning:weight:systems:operational:mass:offset"]
cylindrical_section_length = fuselage_length - front_section_length - aft_section_length
cargo_compartment_length = (
cylindrical_section_length + 0.864 * (front_seat_number_eco - 5) - 0.8 * l2_wing
)
# Radar
temp_c51 = 100.0
outputs["data:weight:systems:operational:radar:mass"] = k_c5 * temp_c51 + offset_c5
# Cargo container systems
temp_c52 = 23.4 * cargo_compartment_length * side_by_side_container_number
outputs["data:weight:systems:operational:cargo_hold:mass"] = k_c5 * temp_c52 + offset_c5