"""
Test module for geometry functions of cg components.
"""
# This file is part of FAST-OAD_CS23 : A framework for rapid Overall Aircraft Design
# Copyright (C) 2022 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 pandas as pd
from openmdao.core.component import Component
from typing import Union
import numpy as np
from stdatm import Atmosphere
import fastoad.api as oad
from fastga.models.propulsion.fuel_propulsion.base import AbstractFuelPropulsion
from fastga.models.propulsion.propulsion import IPropulsion
from fastga.models.propulsion.fuel_propulsion.base import FuelEngineSet
ENGINE_WRAPPER_BE76 = "test.wrapper.performances.beechcraft.dummy_engine"
ENGINE_WRAPPER_SR22 = "test.wrapper.performances.cirrus.dummy_engine"
ENGINE_WRAPPER_TBM900 = "test.wrapper.performances.daher.dummy_engine"
####################################################################################################
# Beechcraft BE76 dummy engine #####################################################################
####################################################################################################
[docs]class DummyEngineBE76(AbstractFuelPropulsion):
def __init__(
self,
max_power: float,
design_altitude_propeller: float,
fuel_type: float,
strokes_nb: float,
prop_layout: float,
):
"""
Dummy engine model returning nacelle aerodynamic drag force.
"""
super().__init__()
self.prop_layout = prop_layout
self.max_power = max_power
self.design_altitude_propeller = design_altitude_propeller
self.fuel_type = fuel_type
self.strokes_nb = strokes_nb
self.max_thrust = 3500.0
[docs] def compute_flight_points(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]):
mach = np.array(flight_points.mach)
thrust = np.array(flight_points.thrust)
sigma = Atmosphere(flight_points.altitude).density / Atmosphere(0.0).density
max_power = self.max_power * (sigma - (1 - sigma) / 7.55)
max_thrust = np.minimum(
self.max_thrust * sigma ** (1.0 / 3.0),
max_power
* 0.8
/ np.maximum(mach * Atmosphere(flight_points.altitude).speed_of_sound, 1e-20),
)
if flight_points.thrust_rate is None:
flight_points.thrust = min(max_thrust, thrust)
flight_points.thrust_rate = thrust / max_thrust
elif flight_points.thrust is None:
flight_points.thrust = max_thrust * np.array(flight_points.thrust_rate)
else:
flight_points.thrust_rate = np.where(
flight_points.thrust_is_regulated,
np.maximum(thrust, np.full_like(thrust, max_thrust))
/ np.full_like(thrust, max_thrust),
flight_points.thrust_rate,
)
flight_points.thrust = np.where(
flight_points.thrust_is_regulated,
flight_points.thrust,
max_thrust * np.array(flight_points.thrust_rate),
)
sfc_pmax = 7.96359441e-08 # fixed whatever the thrust ratio, sfc for ONE 130kW engine !
sfc = (
sfc_pmax
* flight_points.thrust_rate
* mach
* Atmosphere(flight_points.altitude).speed_of_sound
)
flight_points.sfc = sfc
[docs] def compute_weight(self) -> float:
return 0.0
[docs] def compute_dimensions(self) -> (float, float, float, float, float, float):
return [0.0, 0.0, 0.0, 0.0, 0.0, 0.0]
[docs] def compute_drag(self, mach, unit_reynolds, wing_mac):
return 0.0
[docs] def compute_max_power(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]) -> float:
return 0.0
[docs]@oad.RegisterPropulsion(ENGINE_WRAPPER_BE76)
class DummyEngineWrapperBE76(oad.IOMPropulsionWrapper):
[docs] def setup(self, component: Component):
component.add_input("data:propulsion:IC_engine:max_power", np.nan, units="W")
component.add_input("data:propulsion:fuel_type", np.nan)
component.add_input("data:propulsion:IC_engine:strokes_nb", np.nan)
component.add_input("data:aerodynamics:propeller:cruise_level:altitude", np.nan, units="m")
component.add_input("data:geometry:propulsion:engine:layout", np.nan)
component.add_input("data:geometry:propulsion:engine:count", np.nan)
[docs] @staticmethod
def get_model(inputs) -> IPropulsion:
engine_params = {
"max_power": inputs["data:propulsion:IC_engine:max_power"],
"design_altitude_propeller": inputs[
"data:aerodynamics:propeller:cruise_level:altitude"
],
"fuel_type": inputs["data:propulsion:fuel_type"],
"strokes_nb": inputs["data:propulsion:IC_engine:strokes_nb"],
"prop_layout": inputs["data:geometry:propulsion:engine:layout"],
}
return FuelEngineSet(
DummyEngineBE76(**engine_params), inputs["data:geometry:propulsion:engine:count"]
)
####################################################################################################
# Cirrus SR22 dummy engine #########################################################################
####################################################################################################
[docs]class DummyEngineSR22(AbstractFuelPropulsion):
def __init__(self):
"""
Dummy engine model returning thrust in particular conditions defined for htp/vtp areas.
"""
super().__init__()
self.max_power = 231000.0
self.max_thrust = 5417.0
[docs] def compute_flight_points(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]):
mach = np.array(flight_points.mach)
thrust = np.array(flight_points.thrust)
sigma = Atmosphere(flight_points.altitude).density / Atmosphere(0.0).density
max_power = self.max_power * (sigma - (1 - sigma) / 7.55)
max_thrust = np.minimum(
self.max_thrust * sigma ** (1.0 / 3.0),
max_power
* 0.8
/ np.maximum(mach * Atmosphere(flight_points.altitude).speed_of_sound, 1e-20),
)
if flight_points.thrust_rate is None:
flight_points.thrust = min(max_thrust, thrust)
flight_points.thrust_rate = thrust / max_thrust
elif flight_points.thrust is None:
flight_points.thrust = max_thrust * np.array(flight_points.thrust_rate)
else:
flight_points.thrust_rate = np.where(
flight_points.thrust_is_regulated,
np.maximum(thrust, np.full_like(thrust, max_thrust))
/ np.full_like(thrust, max_thrust),
flight_points.thrust_rate,
)
flight_points.thrust = np.where(
flight_points.thrust_is_regulated,
flight_points.thrust,
max_thrust * np.array(flight_points.thrust_rate),
)
sfc_pmax = 8.5080e-08 # fixed whatever the thrust ratio, sfc for ONE 130kW engine !
sfc = (
sfc_pmax
* flight_points.thrust_rate
* mach
* Atmosphere(flight_points.altitude).speed_of_sound
)
flight_points.sfc = sfc
[docs] def compute_weight(self) -> float:
return 0.0
[docs] def compute_dimensions(self) -> (float, float, float, float):
return [0.0, 0.0, 0.0, 0.0]
[docs] def compute_drag(self, mach, unit_reynolds, wing_mac):
return 0.0
[docs] def compute_max_power(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]) -> float:
return 0.0
[docs]@oad.RegisterPropulsion(ENGINE_WRAPPER_SR22)
class DummyEngineWrapperSR22(oad.IOMPropulsionWrapper):
[docs] def setup(self, component: Component):
component.add_input("data:aerodynamics:propeller:cruise_level:altitude", np.nan, units="m")
component.add_input("data:geometry:propulsion:engine:count", np.nan)
[docs] @staticmethod
def get_model(inputs) -> IPropulsion:
return FuelEngineSet(DummyEngineSR22(), inputs["data:geometry:propulsion:engine:count"])
####################################################################################################
# Daher TBM900 dummy engine ########################################################################
####################################################################################################
[docs]class DummyEngineTBM900(AbstractFuelPropulsion):
def __init__(self):
"""
Dummy engine model returning thrust in particular conditions defined for htp/vtp areas.
"""
super().__init__()
self.max_power = 634000.0
self.max_thrust = 30000.0
[docs] def compute_flight_points(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]):
mach = np.array(flight_points.mach)
thrust = np.array(flight_points.thrust)
sigma = Atmosphere(flight_points.altitude).density / Atmosphere(0.0).density
max_power = self.max_power * (sigma - (1 - sigma) / 7.55)
max_thrust = np.minimum(
self.max_thrust * sigma ** (1.0 / 3.0),
max_power
* 0.8
/ np.maximum(mach * Atmosphere(flight_points.altitude).speed_of_sound, 1e-20),
)
if flight_points.thrust_rate is None:
flight_points.thrust = min(max_thrust, thrust)
flight_points.thrust_rate = thrust / max_thrust
elif flight_points.thrust is None:
flight_points.thrust = max_thrust * np.array(flight_points.thrust_rate)
else:
flight_points.thrust_rate = np.where(
flight_points.thrust_is_regulated,
np.maximum(thrust, np.full_like(thrust, max_thrust))
/ np.full_like(thrust, max_thrust),
flight_points.thrust_rate,
)
flight_points.thrust = np.where(
flight_points.thrust_is_regulated,
flight_points.thrust,
max_thrust * np.array(flight_points.thrust_rate),
)
sfc_pmax = 1.5e-5 # fixed whatever the thrust rate
sfc = sfc_pmax * flight_points.thrust_rate
flight_points.sfc = sfc
[docs] def compute_weight(self) -> float:
return 0.0
[docs] def compute_dimensions(self) -> (float, float, float, float):
return [0.0, 0.0, 0.0, 0.0]
[docs] def compute_drag(self, mach, unit_reynolds, wing_mac):
return 0.0
[docs] def compute_max_power(self, flight_points: Union[oad.FlightPoint, pd.DataFrame]) -> float:
return 0.0
[docs]@oad.RegisterPropulsion(ENGINE_WRAPPER_TBM900)
class DummyEngineWrapperTBM900(oad.IOMPropulsionWrapper):
[docs] def setup(self, component: Component):
component.add_input("data:aerodynamics:propeller:cruise_level:altitude", np.nan, units="m")
component.add_input("data:geometry:propulsion:engine:count", np.nan)
[docs] @staticmethod
def get_model(inputs) -> IPropulsion:
return FuelEngineSet(DummyEngineTBM900(), inputs["data:geometry:propulsion:engine:count"])