"""
Estimation of fuel lines weight
"""
# This file is part of FAST-OAD : A framework for rapid Overall Aircraft Design
# Copyright (C) 2020 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 FuelLinesWeight(ExplicitComponent):
"""
Weight estimation for fuel lines
Based on formula in :cite:`supaero:2014`, mass contribution B2
"""
[docs] def setup(self):
self.add_input("data:geometry:wing:b_50", val=np.nan, units="m")
self.add_input("data:weight:aircraft:MFW", val=np.nan, units="kg")
self.add_input("data:weight:propulsion:engine:mass", val=np.nan, units="kg")
self.add_input("tuning:weight:propulsion:fuel_lines:mass:k", val=1.0)
self.add_input("tuning:weight:propulsion:fuel_lines:mass:offset", val=0.0, units="kg")
self.add_output("data:weight:propulsion:fuel_lines:mass", units="kg")
self.declare_partials("*", "*", method="fd")
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
b_50 = inputs["data:geometry:wing:b_50"]
mfw = inputs["data:weight:aircraft:MFW"]
k_b2 = inputs["tuning:weight:propulsion:fuel_lines:mass:k"]
offset_b2 = inputs["tuning:weight:propulsion:fuel_lines:mass:offset"]
weight_engines = inputs["data:weight:propulsion:engine:mass"]
temp_b2 = 0.02 * weight_engines + 2.0 * b_50 + 0.35 * mfw ** 0.66
outputs["data:weight:propulsion:fuel_lines:mass"] = k_b2 * temp_b2 + offset_b2