Source code for gemseo.problems.aerostructure.aerostructure_design_space

# Copyright 2021 IRT Saint Exupéry,
# This program is free software; you can redistribute it and/or
# modify it under the terms of the GNU Lesser General Public
# License version 3 as published by the Free Software Foundation.
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# Lesser General Public License for more details.
# You should have received a copy of the GNU Lesser General Public License
# along with this program; if not, write to the Free Software Foundation,
# Inc., 51 Franklin Street, Fifth Floor, Boston, MA  02110-1301, USA.
# Contributors:
#    INITIAL AUTHORS - API and implementation and/or documentation
#        :author: Matthias De Lozzo
Aerostructure MDO problem's Design Space
from __future__ import annotations

import numpy as np

from gemseo.algos.design_space import DesignSpace

[docs]class AerostructureDesignSpace(DesignSpace): """**AerostructureDesignSpace** creates the :class:`.DesignSpace` of the Aerostructure problem whose :class:`.MDODiscipline` are :class:`.Aerodynamics`, :class:`.Structure` and :class:`.Mission`. - thick_airfoils belongs to [5., 25.], with initial value equal to 15. - thick_panels belongs to [1., 20.], with initial value equal to 3. - sweep belongs to [10., 35.], with initial value equal to 25. - drag belongs to [100., 1000.], with initial value equal to 340. - forces belongs to [-1000., 1000.], with initial value equal to 400. - lift belongs to [0.1, 1.0], with initial value equal to 0.5 - mass belongs to [100000., 500000.], with initial value equal to 100000. - reserve_fact belongs to [1000., 1000.], with initial value equal to 0. """ def __init__(self) -> None: """Constructor.""" super().__init__() # construct a dictionary with initial solution drag = np.array([340.0], dtype=np.complex128) forces = np.array([400.0], dtype=np.complex128) lift = np.array([0.5], dtype=np.complex128) mass = np.array([100000.0], dtype=np.complex128) displ = np.array([-700.0], dtype=np.complex128) sweep = np.array([25.0], dtype=np.complex128) thick_airfoils = np.array([15.0], dtype=np.complex128) thick_panels = np.array([3.0], dtype=np.complex128) reserve_fact = np.array([0.0], dtype=np.complex128) # design variables self.add_variable("thick_airfoils", l_b=5.0, u_b=25.0, value=thick_airfoils) self.add_variable("thick_panels", l_b=1.0, u_b=20.0, value=thick_panels) # shared design variables self.add_variable("sweep", l_b=10.0, u_b=35.0, value=sweep) # target coupling variables self.add_variable("drag", l_b=100.0, u_b=1000.0, value=drag) self.add_variable("forces", l_b=-1000.0, u_b=1000.0, value=forces) self.add_variable("lift", l_b=0.1, u_b=1.0, value=lift) self.add_variable("mass", l_b=100000.0, u_b=500000.0, value=mass) self.add_variable("displ", l_b=-1000.0, u_b=1000.0, value=displ) self.add_variable("reserve_fact", l_b=-1000.0, u_b=1000.0, value=reserve_fact)