# 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
import numpy as np
import fastoad.api as oad
from stdatm import Atmosphere
from fastga.models.aerodynamics.constants import SUBMODEL_THRUST_POWER_SLIPSTREAM
[docs]
@oad.RegisterSubmodel(
SUBMODEL_THRUST_POWER_SLIPSTREAM,
"fastga.submodel.aerodynamics.wing.slipstream.thrust_power_computation.ecopulse",
)
class PropulsionForDPComputationEcoPulse(om.ExplicitComponent):
"""Computes thrust and shaft power for Ecopulse computation fixed values for now."""
[docs]
def initialize(self):
self.options.declare("propulsion_id", default="", types=str)
[docs]
def setup(self):
# Dummy variables
self.add_input("data:geometry:wing:area", val=np.nan, units="ft**2")
self.add_input("mach", val=np.nan)
self.add_input("altitude", val=np.nan, units="m")
self.add_output("thrust", val=0, units="N")
self.add_output("shaft_power", val=1, units="W")
[docs]
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
# 6 engine of 100 kW
shaft_power = 100e3
true_airspeed = (
Atmosphere(inputs["altitude"], altitude_in_feet=False).speed_of_sound * inputs["mach"]
)
# Assumed efficiency of 0.75
outputs["thrust"] = shaft_power * 0.75 / true_airspeed
outputs["shaft_power"] = shaft_power