Source code for fastga_he.models.propulsion.assemblies.simple_assembly.full_simple_assembly

# This file is part of FAST-OAD_CS23-HE : A framework for rapid Overall Aircraft Design of Hybrid
# Electric Aircraft.
# Copyright (C) 2022 ISAE-SUPAERO

import openmdao.api as om

from .sizing_simple_assembly import SizingAssembly
from .performances_simple_assembly import PerformancesAssembly




class FullSimpleAssembly(om.Group):
    def __init__(self, **kwargs):
        super().__init__(**kwargs)

        # Solvers setup
        self.nonlinear_solver = om.NonlinearBlockGS()
        self.nonlinear_solver.options["iprint"] = 2
        self.nonlinear_solver.options["maxiter"] = 200
        self.nonlinear_solver.options["rtol"] = 1e-5
        self.linear_solver = om.LinearBlockGS()



    def initialize(self):
        self.options.declare(
            "number_of_points", default=1, desc="number of equilibrium to be treated"
        )




    def setup(self):
        number_of_points = self.options["number_of_points"]

        self.add_subsystem(name="sizing", subsys=SizingAssembly(), promotes=["*"])
        self.add_subsystem(
            name="performances",
            subsys=PerformancesAssembly(number_of_points=number_of_points),
            promotes=["*"],
        )