"""
FAST - Copyright (c) 2016 ONERA ISAE
"""
# This file is part of FAST : 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 openmdao.api as om
from fastoad.models.geometry.compute_aero_center import ComputeAeroCenter
from fastoad.models.geometry.geom_components import ComputeTotalArea
from fastoad.models.geometry.geom_components.fuselage.compute_fuselage import (
ComputeFuselageGeometryBasic,
ComputeFuselageGeometryCabinSizing,
)
from fastoad.models.geometry.geom_components.ht import ComputeHorizontalTailGeometry
from fastoad.models.geometry.geom_components.nacelle_pylons.compute_nacelle_pylons import (
ComputeNacelleAndPylonsGeometry,
)
from fastoad.models.geometry.geom_components.vt import ComputeVerticalTailGeometry
from fastoad.models.geometry.geom_components.wing.compute_wing import ComputeWingGeometry
from fastoad.models.options import CABIN_SIZING_OPTION
[docs]class Geometry(om.Group):
"""
Computes geometric characteristics of the (tube-wing) aircraft:
- fuselage size is computed from payload requirements
- wing dimensions are computed from global parameters (area, taper ratio...)
- tail planes are dimensioned from HQ requirements
This module also computes centers of gravity and static margin
"""
[docs] def initialize(self):
self.options.declare(CABIN_SIZING_OPTION, types=float, default=1.0)
[docs] def setup(self):
if self.options[CABIN_SIZING_OPTION] == 1.0:
self.add_subsystem(
"compute_fuselage", ComputeFuselageGeometryCabinSizing(), promotes=["*"]
)
else:
self.add_subsystem("compute_fuselage", ComputeFuselageGeometryBasic(), promotes=["*"])
self.add_subsystem("compute_wing", ComputeWingGeometry(), promotes=["*"])
self.add_subsystem(
"compute_engine_nacelle", ComputeNacelleAndPylonsGeometry(), promotes=["*"]
)
self.add_subsystem("compute_ht", ComputeHorizontalTailGeometry(), promotes=["*"])
self.add_subsystem("compute_vt", ComputeVerticalTailGeometry(), promotes=["*"])
self.add_subsystem("compute_total_area", ComputeTotalArea(), promotes=["*"])
self.add_subsystem("compute_aero_center", ComputeAeroCenter(), promotes=["*"])