/
simple_all_electric.py
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/
simple_all_electric.py
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from openconcept.propulsion import SimpleMotor, SimplePropeller
from openconcept.energy_storage import SOCBattery
from openconcept.utilities import DVLabel
from openmdao.api import Group, IndepVarComp
from openconcept.thermal import (
LiquidCooledComp,
CoolantReservoir,
ImplicitCompressibleDuct,
ExplicitIncompressibleDuct,
HXGroup,
)
import numpy as np
class AllElectricSinglePropulsionSystemWithThermal_Compressible(Group):
"""This is an example model of the an electric propulsion system
consisting of a constant-speed prop, motor, and battery.
Thermal management is provided using a compressible 1D duct
with heat exchanger.
Inputs
------
ac|propulsion|motor|rating : float
The maximum rated continuous shaft power of the motor
ac|propulsion|propeller|diameter : float
Diameter of the propeller
ac|weights|W_battery : float
Battery weight
Options
-------
num_nodes : float
Number of analysis points to run (default 1)
"""
def initialize(self):
self.options.declare("num_nodes", default=1, desc="Number of mission analysis points to run")
self.options.declare("specific_energy", default=300, desc="Battery spec energy in Wh/kg")
def setup(self):
nn = self.options["num_nodes"]
e_b = self.options["specific_energy"]
# rename incoming design variables
dvlist = [
["ac|propulsion|motor|rating", "motor1_rating", 850, "hp"],
["ac|propulsion|propeller|diameter", "prop1_diameter", 2.3, "m"],
["ac|weights|W_battery", "battery1_weight", 300, "kg"],
]
self.add_subsystem("dvs", DVLabel(dvlist), promotes_inputs=["*"], promotes_outputs=["*"])
# introduce model components
self.add_subsystem(
"motor1",
SimpleMotor(num_nodes=nn, weight_inc=1 / 5000, weight_base=0, efficiency=0.97),
promotes_inputs=["throttle"],
)
self.add_subsystem(
"prop1",
SimplePropeller(num_nodes=nn, num_blades=4, design_J=2.2, design_cp=0.55),
promotes_inputs=["fltcond|*"],
promotes_outputs=["thrust"],
)
self.add_subsystem(
"batt1", SOCBattery(num_nodes=nn, specific_energy=e_b, efficiency=0.97), promotes_inputs=["duration"]
)
# connect design variables to model component inputs
self.connect("motor1_rating", "motor1.elec_power_rating")
self.connect("motor1_rating", "prop1.power_rating")
self.connect("prop1_diameter", "prop1.diameter")
self.connect("battery1_weight", "batt1.battery_weight")
# connect components to each other
self.connect("motor1.shaft_power_out", "prop1.shaft_power_in")
self.connect("motor1.elec_load", "batt1.elec_load")
iv = self.add_subsystem("iv", IndepVarComp(), promotes_outputs=["*"])
iv.add_output("mdot_coolant", val=0.1 * np.ones((nn,)), units="kg/s")
iv.add_output("rho_coolant", val=997 * np.ones((nn,)), units="kg/m**3")
iv.add_output("coolant_mass", val=10.0, units="kg")
iv.add_output("channel_width", val=1, units="mm")
iv.add_output("channel_height", val=20, units="mm")
iv.add_output("channel_length", val=0.2, units="m")
iv.add_output("n_parallel", val=50)
lc_promotes = ["duration", "channel_*", "n_parallel"]
self.add_subsystem(
"motorheatsink", LiquidCooledComp(num_nodes=nn, quasi_steady=False), promotes_inputs=lc_promotes
)
self.connect("motor1.heat_out", "motorheatsink.q_in")
self.connect("motor1.component_weight", "motorheatsink.mass")
self.add_subsystem(
"duct",
ImplicitCompressibleDuct(num_nodes=nn),
promotes_inputs=[("p_inf", "fltcond|p"), ("T_inf", "fltcond|T"), ("Utrue", "fltcond|Utrue")],
)
self.connect("motorheatsink.T_out", "duct.T_in_hot")
self.connect("rho_coolant", "duct.rho_hot")
self.add_subsystem(
"reservoir", CoolantReservoir(num_nodes=nn), promotes_inputs=["duration", ("mass", "coolant_mass")]
)
self.connect("duct.T_out_hot", "reservoir.T_in")
self.connect("reservoir.T_out", "motorheatsink.T_in")
self.connect("mdot_coolant", ["motorheatsink.mdot_coolant", "duct.mdot_hot", "reservoir.mdot_coolant"])
class AllElectricSinglePropulsionSystemWithThermal_Incompressible(Group):
"""This is an example model of the an electric propulsion system
consisting of a constant-speed prop, motor, and battery.
Thermal management is provided using a incompressible
approximation of a 1D duct with heat exchanger.
Inputs
------
ac|propulsion|motor|rating : float
The maximum rated continuous shaft power of the motor
ac|propulsion|propeller|diameter : float
Diameter of the propeller
ac|weights|W_battery : float
Battery weight
Options
-------
num_nodes : float
Number of analysis points to run (default 1)
"""
def initialize(self):
self.options.declare("num_nodes", default=1, desc="Number of mission analysis points to run")
self.options.declare("specific_energy", default=300, desc="Battery spec energy in Wh/kg")
def setup(self):
nn = self.options["num_nodes"]
e_b = self.options["specific_energy"]
# rename incoming design variables
dvlist = [
["ac|propulsion|motor|rating", "motor1_rating", 850, "hp"],
["ac|propulsion|propeller|diameter", "prop1_diameter", 2.3, "m"],
["ac|weights|W_battery", "battery1_weight", 300, "kg"],
]
self.add_subsystem("dvs", DVLabel(dvlist), promotes_inputs=["*"], promotes_outputs=["*"])
# introduce model components
self.add_subsystem(
"motor1",
SimpleMotor(num_nodes=nn, weight_inc=1 / 5000, weight_base=0, efficiency=0.97),
promotes_inputs=["throttle"],
)
self.add_subsystem(
"prop1",
SimplePropeller(num_nodes=nn, num_blades=4, design_J=2.2, design_cp=0.55),
promotes_inputs=["fltcond|*"],
promotes_outputs=["thrust"],
)
self.add_subsystem(
"batt1", SOCBattery(num_nodes=nn, specific_energy=e_b, efficiency=0.97), promotes_inputs=["duration"]
)
# connect design variables to model component inputs
self.connect("motor1_rating", "motor1.elec_power_rating")
self.connect("motor1_rating", "prop1.power_rating")
self.connect("prop1_diameter", "prop1.diameter")
self.connect("battery1_weight", "batt1.battery_weight")
# connect components to each other
self.connect("motor1.shaft_power_out", "prop1.shaft_power_in")
self.connect("motor1.elec_load", "batt1.elec_load")
iv = self.add_subsystem("iv", IndepVarComp(), promotes_outputs=["*"])
iv.add_output("mdot_coolant", val=0.1 * np.ones((nn,)), units="kg/s")
iv.add_output("rho_coolant", val=997 * np.ones((nn,)), units="kg/m**3")
iv.add_output("coolant_mass", val=10.0, units="kg")
iv.add_output("channel_width", val=1, units="mm")
iv.add_output("channel_height", val=20, units="mm")
iv.add_output("channel_length", val=0.2, units="m")
iv.add_output("n_parallel", val=50)
iv.add_output("area_nozzle", val=58 * np.ones((nn,)), units="inch**2")
lc_promotes = ["duration", "channel_*", "n_parallel"]
self.add_subsystem(
"motorheatsink", LiquidCooledComp(num_nodes=nn, quasi_steady=False), promotes_inputs=lc_promotes
)
self.connect("motor1.heat_out", "motorheatsink.q_in")
self.connect("motor1.component_weight", "motorheatsink.mass")
self.add_subsystem("duct", ExplicitIncompressibleDuct(num_nodes=nn), promotes_inputs=["fltcond|*"])
self.connect("area_nozzle", "duct.area_nozzle")
self.add_subsystem(
"hx", HXGroup(num_nodes=nn), promotes_inputs=[("T_in_cold", "fltcond|T"), ("rho_cold", "fltcond|rho")]
)
self.connect("duct.mdot", "hx.mdot_cold")
self.connect("hx.delta_p_cold", "duct.delta_p_hex")
self.connect("motorheatsink.T_out", "hx.T_in_hot")
self.connect("rho_coolant", "hx.rho_hot")
self.add_subsystem(
"reservoir", CoolantReservoir(num_nodes=nn), promotes_inputs=["duration", ("mass", "coolant_mass")]
)
self.connect("hx.T_out_hot", "reservoir.T_in")
self.connect("reservoir.T_out", "motorheatsink.T_in")
self.connect("mdot_coolant", ["motorheatsink.mdot_coolant", "hx.mdot_hot", "reservoir.mdot_coolant"])