def setup(self):
const = self.add_subsystem('const',IndepVarComp(),promotes_outputs=["*"])
const.add_output('W_fluids', val=20, units='kg')
const.add_output('structural_fudge', val=1.6, units='m/m')
self.add_subsystem('wing',WingWeight_SmallTurboprop(),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('empennage',EmpennageWeight_SmallTurboprop(),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('fuselage',FuselageWeight_SmallTurboprop(),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('nacelle',NacelleWeight_SmallSingleTurboprop(),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('gear',LandingGearWeight_SmallTurboprop(),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('fuelsystem', FuelSystemWeight_SmallTurboprop(), promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('equipment',EquipmentWeight_SmallTurboprop(), promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('structural',AddSubtractComp(output_name='W_structure',input_names=['W_wing','W_fuselage','W_nacelle','W_empennage','W_gear'], units='lb'),promotes_outputs=['*'],promotes_inputs=["*"])
self.add_subsystem('structural_fudge',ElementMultiplyDivideComp(output_name='W_structure_adjusted',input_names=['W_structure','structural_fudge'],input_units=['lb','m/m']),promotes_inputs=["*"],promotes_outputs=["*"])
self.add_subsystem('totalempty',AddSubtractComp(output_name='OEW',input_names=['W_structure_adjusted','W_fuelsystem','W_equipment','W_engine','W_propeller','W_fluids'], units='lb'),promotes_outputs=['*'],promotes_inputs=["*"])
def setup(self):
nn = self.options['num_nodes']
flight_phase = self.options['flight_phase']
# any control variables other than throttle and braking need to be defined here
controls = self.add_subsystem('controls', IndepVarComp(), promotes_outputs=['*'])
controls.add_output('proprpm',val=np.ones((nn,))*2000, units='rpm')
# assume TO happens on battery backup
if flight_phase in ['climb', 'cruise','descent']:
controls.add_output('hybridization',val=0.0)
else:
controls.add_output('hybridization',val=1.0)
hybrid_factor = self.add_subsystem('hybrid_factor', LinearInterpolator(num_nodes=nn),
promotes_inputs=[('start_val', 'hybridization'),
('end_val', 'hybridization')])
propulsion_promotes_outputs = ['fuel_flow','thrust']
propulsion_promotes_inputs = ["fltcond|*", "ac|propulsion|*", "throttle", "propulsor_active",
"ac|weights*", 'duration']
self.add_subsystem('propmodel',
TwinSeriesHybridElectricPropulsionSystem(num_nodes=nn),
promotes_inputs=propulsion_promotes_inputs,
promotes_outputs=propulsion_promotes_outputs)
self.connect('proprpm', ['propmodel.prop1.rpm', 'propmodel.prop2.rpm'])
self.connect('hybrid_factor.vec', 'propmodel.hybrid_split.power_split_fraction')
# use a different drag coefficient for takeoff versus cruise
if flight_phase not in ['v0v1', 'v1v0', 'v1vr', 'rotate']:
cd0_source = 'ac|aero|polar|CD0_cruise'
else:
cd0_source = 'ac|aero|polar|CD0_TO'
self.add_subsystem('drag', PolarDrag(num_nodes=nn),
promotes_inputs=['fltcond|CL', 'ac|geom|*', ('CD0', cd0_source),
'fltcond|q', ('e', 'ac|aero|polar|e')],
promotes_outputs=['drag'])
self.add_subsystem('OEW',TwinSeriesHybridEmptyWeight(),
promotes_inputs=[('P_TO','ac|propulsion|engine|rating'),'*'],
promotes_outputs=['OEW'])
self.connect('propmodel.propellers_weight', 'W_propeller')
self.connect('propmodel.eng1.component_weight', 'W_engine')
self.connect('propmodel.gen1.component_weight', 'W_generator')
self.connect('propmodel.motors_weight', 'W_motors')
intfuel = self.add_subsystem('intfuel', Integrator(num_nodes=nn, method='simpson', diff_units='s',
time_setup='duration'), promotes_inputs=['*'], promotes_outputs=['*'])
intfuel.add_integrand('fuel_used', rate_name='fuel_flow', val=1.0, units='kg')
self.add_subsystem('weight', AddSubtractComp(output_name='weight',
input_names=['ac|weights|MTOW', 'fuel_used'],
units='kg', vec_size=[1, nn],
scaling_factors=[1, -1]),
promotes_inputs=['*'],
promotes_outputs=['weight'])
def setup(self):
# set fudge factors on structure / equipment weight
const = self.add_subsystem('const', IndepVarComp(), promotes_outputs=["*"])
const.add_output('structural_fudge', val=1., units='m/m')
const.add_output('equipment_fudge', val=1.0, units='m/m')
# structural weight
self.add_subsystem('wing', WingWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('hstab', HorizontalTailWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('vstab', VerticalTailWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('fuselage', FuselageWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('nacelle', NacelleWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('gear', LandingGearWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('structural', AddSubtractComp(output_name='W_structure',input_names=['W_wing','W_fuselage','W_nacelle','W_hstab','W_vstab','W_gear'], units='lb'),promotes_outputs=['*'],promotes_inputs=["*"])
self.add_subsystem('structural_fudge',ElementMultiplyDivideComp(output_name='W_structure_adjusted',input_names=['W_structure','structural_fudge'],input_units=['lb','m/m']),promotes_inputs=["*"],promotes_outputs=["*"])
# engine weight
self.add_subsystem('engines', EngineWeight_TurbofanSystem(), promotes_inputs=["*"], promotes_outputs=["*"])
# other weights
self.add_subsystem('equipment', EquipmentWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('operation', OperationalWeight_JetAirliner(), promotes_inputs=["*"], promotes_outputs=["*"])
self.add_subsystem('equipment_fudge',ElementMultiplyDivideComp(output_name='W_equip_adjusted',input_names=['W_equip','equipment_fudge'],input_units=['lb','m/m']),promotes_inputs=["*"],promotes_outputs=["*"])
# sum
self.add_subsystem('totalempty', AddSubtractComp(output_name='OEW',input_names=['W_structure_adjusted', 'W_engines', 'W_equip_adjusted', 'W_op'], units='lb'), promotes_outputs=['*'], promotes_inputs=["*"])
def setup(self):
nn = self.options['num_nodes']
flight_phase = self.options['flight_phase']
# no control variables other than throttle and braking
"""
# propulsion system 1: simple turbofan (textbook formula)
from examples.propulsion_layouts.simple_turbofan import TurbofanPropulsionSystem
self.add_subsystem('propmodel', TurbofanPropulsionSystem(num_nodes=nn),
promotes_inputs=['fltcond|*', 'ac|propulsion|max_thrust', 'throttle', 'ac|propulsion|num_engine'],
promotes_outputs=['thrust', 'fuel_flow'])
"""
# propulsion system 2: pycycle surrogate
from examples.propulsion_layouts.turbofan_surrogate import TurbofanPropulsionSystem
self.add_subsystem('propmodel', TurbofanPropulsionSystem(num_nodes=nn),
promotes_inputs=['fltcond|*', 'throttle'],
promotes_outputs=['thrust', 'fuel_flow'])
#"""
# aerodynamic model
if flight_phase not in ['v0v1', 'v1v0', 'v1vr', 'rotate']:
cd0_source = 'ac|aero|polar|CD0_cruise'
else:
cd0_source = 'ac|aero|polar|CD0_TO'
self.add_subsystem('drag', PolarDrag(num_nodes=nn),
promotes_inputs=['fltcond|CL', 'ac|geom|*', ('CD0', cd0_source),
'fltcond|q', ('e', 'ac|aero|polar|e')],
promotes_outputs=['drag'])
# weight estimation models
self.add_subsystem('OEW', JetAirlinerEmptyWeight(),
promotes_inputs=['ac|geom|*', 'ac|weights|*', 'ac|propulsion|*', 'ac|misc|*'],
promotes_outputs=['OEW'])
# airplanes which consume fuel will need to integrate
# fuel usage across the mission and subtract it from TOW
nn_simpson = int((nn - 1) / 2)
self.add_subsystem('intfuel', Integrator(num_intervals=nn_simpson, method='simpson',
quantity_units='kg', diff_units='s',
time_setup='duration'),
promotes_inputs=[('dqdt', 'fuel_flow'), 'duration',
('q_initial', 'fuel_used_initial')],
promotes_outputs=[('q', 'fuel_used'), ('q_final', 'fuel_used_final')])
self.add_subsystem('weight', AddSubtractComp(output_name='weight',
input_names=['ac|weights|MTOW', 'fuel_used'],
units='kg', vec_size=[1, nn],
scaling_factors=[1, -1]),
promotes_inputs=['*'],
promotes_outputs=['weight'])
def setup(self):
nn = self.options['num_nodes']
flight_phase = self.options['flight_phase']
# any control variables other than throttle and braking need to be defined here
controls = self.add_subsystem('controls',
IndepVarComp(),
promotes_outputs=['*'])
controls.add_output('prop|rpm',
val=np.ones((nn, )) * 1900,
units='rpm')
# a propulsion system needs to be defined in order to provide thrust
# information for the mission analysis code
propulsion_promotes_outputs = ['fuel_flow', 'thrust']
propulsion_promotes_inputs = [
"fltcond|*", "ac|propulsion|*", "throttle", "propulsor_active"
]
self.add_subsystem('propmodel',
TwinTurbopropPropulsionSystem(num_nodes=nn),
promotes_inputs=propulsion_promotes_inputs,
promotes_outputs=propulsion_promotes_outputs)
self.connect('prop|rpm',
['propmodel.prop1.rpm', 'propmodel.prop2.rpm'])
# use a different drag coefficient for takeoff versus cruise
if flight_phase not in ['v0v1', 'v1v0', 'v1vr', 'rotate']:
cd0_source = 'ac|aero|polar|CD0_cruise'
else:
cd0_source = 'ac|aero|polar|CD0_TO'
self.add_subsystem('drag',
PolarDrag(num_nodes=nn),
promotes_inputs=[
'fltcond|CL', 'ac|geom|*', ('CD0', cd0_source),
'fltcond|q', ('e', 'ac|aero|polar|e')
],
promotes_outputs=['drag'])
# generally the weights module will be custom to each airplane
self.add_subsystem(
'OEW',
SingleTurboPropEmptyWeight(),
promotes_inputs=['*', ('P_TO', 'ac|propulsion|engine|rating')],
promotes_outputs=['OEW'])
self.connect('propmodel.propellers_weight', 'W_propeller')
self.connect('propmodel.engines_weight', 'W_engine')
# airplanes which consume fuel will need to integrate
# fuel usage across the mission and subtract it from TOW
nn_simpson = int((nn - 1) / 2)
self.add_subsystem('intfuel',
Integrator(num_intervals=nn_simpson,
method='simpson',
quantity_units='kg',
diff_units='s',
time_setup='duration'),
promotes_inputs=[('dqdt', 'fuel_flow'), 'duration',
('q_initial', 'fuel_used_initial')
],
promotes_outputs=[('q', 'fuel_used'),
('q_final', 'fuel_used_final')])
self.add_subsystem('weight',
AddSubtractComp(
output_name='weight',
input_names=['ac|weights|MTOW', 'fuel_used'],
units='kg',
vec_size=[1, nn],
scaling_factors=[1, -1]),
promotes_inputs=['*'],
promotes_outputs=['weight'])
def setup(self):
nn = self.options['num_nodes']
#define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 260.0, 'kW'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.5, 'm'],
['ac|propulsion|motor|rating', 'motor_rating', 240.0, 'kW'],
['ac|propulsion|generator|rating', 'gen_rating', 250.0, 'kW'],
['ac|weights|W_battery', 'batt_weight', 2000, 'kg'],
[
'ac|propulsion|thermal|hx|mdot_coolant', 'mdot_coolant',
0.1 * np.ones((nn, )), 'kg/s'
],
[
'ac|propulsion|thermal|hx|coolant_mass', 'coolant_mass', 10.,
'kg'
],
[
'ac|propulsion|thermal|hx|channel_width', 'channel_width', 1.,
'mm'
],
[
'ac|propulsion|thermal|hx|channel_height', 'channel_height',
20., 'mm'
],
[
'ac|propulsion|thermal|hx|channel_length', 'channel_length',
0.2, 'm'
],
['ac|propulsion|thermal|hx|n_parallel', 'n_parallel', 50, None],
# ['ac|propulsion|thermal|duct|area_nozzle','area_nozzle',58.*np.ones((nn,)),'inch**2'],
[
'ac|propulsion|battery|specific_energy', 'specific_energy',
300, 'W*h/kg'
]
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
#introduce model components
self.add_subsystem('motor1',
SimpleMotor(efficiency=0.97, num_nodes=nn),
promotes_inputs=['throttle'])
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
#propulsion models expect a high-level 'throttle' parameter and a 'propulsor_active' flag to set individual throttles
failedengine = ElementMultiplyDivideComp()
failedengine.add_equation('motor2throttle',
input_names=['throttle', 'propulsor_active'],
vec_size=nn)
self.add_subsystem('failedmotor',
failedengine,
promotes_inputs=['throttle', 'propulsor_active'])
self.add_subsystem('motor2', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop2',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor2.shaft_power_out', 'prop2.shaft_power_in')
self.connect('failedmotor.motor2throttle', 'motor2.throttle')
addpower = AddSubtractComp(
output_name='motors_elec_load',
input_names=['motor1_elec_load', 'motor2_elec_load'],
units='kW',
vec_size=nn)
addpower.add_equation(output_name='thrust',
input_names=['prop1_thrust', 'prop2_thrust'],
units='N',
vec_size=nn)
self.add_subsystem('add_power',
subsys=addpower,
promotes_outputs=['*'])
self.connect('motor1.elec_load', 'add_power.motor1_elec_load')
self.connect('motor2.elec_load', 'add_power.motor2_elec_load')
self.connect('prop1.thrust', 'add_power.prop1_thrust')
self.connect('prop2.thrust', 'add_power.prop2_thrust')
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.connect('motors_elec_load', 'hybrid_split.power_in')
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
promotes_outputs=["fuel_flow"])
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.add_subsystem('batt1',
SOCBattery(num_nodes=nn, efficiency=0.97),
promotes_inputs=["duration", 'specific_energy'])
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
# TODO set val= right number of nn
self.add_subsystem(
'eng_throttle_set',
BalanceComp(name='eng_throttle',
val=np.ones((nn, )) * 0.5,
units=None,
eq_units='kW',
rhs_name='gen_power_required',
lhs_name='gen_power_available'))
#need to use the optimizer to drive hybrid_split.power_out_B to the same value as gen1.elec_power_out
self.connect('hybrid_split.power_out_B',
'eng_throttle_set.gen_power_required')
self.connect('gen1.elec_power_out',
'eng_throttle_set.gen_power_available')
self.connect('eng_throttle_set.eng_throttle', 'eng1.throttle')
adder = AddSubtractComp(output_name='motors_weight',
input_names=['motor1_weight', 'motor2_weight'],
units='kg')
adder.add_equation(output_name='propellers_weight',
input_names=['prop1_weight', 'prop2_weight'],
units='kg')
adder.add_equation(output_name='motors_heat',
input_names=['motor1_heat', 'motor2_heat'],
vec_size=nn,
units='W')
self.add_subsystem('adder',
subsys=adder,
promotes_inputs=['*'],
promotes_outputs=['*'])
relabel = [[
'hybrid_split_A_in', 'battery_load',
np.ones(nn) * 260.0, 'kW'
]]
self.add_subsystem('relabel',
DVLabel(relabel),
promotes_outputs=["battery_load"])
self.connect('hybrid_split.power_out_A', 'relabel.hybrid_split_A_in')
self.connect('motor1.component_weight', 'motor1_weight')
self.connect('motor2.component_weight', 'motor2_weight')
self.connect('prop1.component_weight', 'prop1_weight')
self.connect('prop2.component_weight', 'prop2_weight')
self.connect('motor1.heat_out', 'motor1_heat')
self.connect('motor2.heat_out', 'motor2_heat')
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('prop_diameter', ['prop1.diameter', 'prop2.diameter'])
self.connect('motor_rating',
['motor1.elec_power_rating', 'motor2.elec_power_rating'])
self.connect('motor_rating',
['prop1.power_rating', 'prop2.power_rating'])
self.connect('gen_rating', 'gen1.elec_power_rating')
self.connect('batt_weight', 'batt1.battery_weight')
iv = self.add_subsystem('iv', IndepVarComp(), promotes_outputs=['*'])
iv.add_output('rho_coolant',
val=997 * np.ones((nn, )),
units='kg/m**3')
lc_promotes = ['duration', 'channel_*', 'n_parallel']
self.add_subsystem('batteryheatsink',
LiquidCooledComp(num_nodes=nn, quasi_steady=False),
promotes_inputs=lc_promotes)
self.connect('batt1.heat_out', 'batteryheatsink.q_in')
self.connect('batt_weight', 'batteryheatsink.mass')
self.add_subsystem('motorheatsink',
LiquidCooledComp(num_nodes=nn, quasi_steady=False),
promotes_inputs=lc_promotes)
self.connect('motors_heat', 'motorheatsink.q_in')
self.connect('motors_weight', 'motorheatsink.mass')
self.add_subsystem('duct',
ExplicitIncompressibleDuct(num_nodes=nn),
promotes_inputs=['fltcond|*'])
iv.add_output('ac|propulsion|thermal|duct|area_nozzle',
val=58. * np.ones((nn, )),
units='inch**2')
self.connect('ac|propulsion|thermal|duct|area_nozzle',
'duct.area_nozzle')
self.add_subsystem('hx',
HXGroup(num_nodes=nn),
promotes_inputs=[
'ac|*', ('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', 'batteryheatsink.T_in')
self.connect('batteryheatsink.T_out', 'motorheatsink.T_in')
self.connect('mdot_coolant', [
'batteryheatsink.mdot_coolant', 'motorheatsink.mdot_coolant',
'hx.mdot_hot', 'reservoir.mdot_coolant'
])
def setup(self):
n_int_per_seg = self.options['n_int_per_seg']
track_battery = self.options['track_battery']
track_fuel = self.options['track_fuel']
nn = (n_int_per_seg * 2 + 1)
nn_tot = 3 * nn + 2
#===Some of the generic components take "weight" as an input. Need to re-label Takeoff Weight (TOW) as just weight
dvlist = [['ac|weights|MTOW', 'weight', 2000.0, 'kg'],
['mission|takeoff|v1', 'v1', 40, 'm/s'],
['mission|takeoff|vr', 'vr', 45, 'm/s'],
['ac|aero|polar|CD0_TO', 'CD0', 0.005, None],
['ac|aero|polar|e', 'e', 0.95, None],
[
'fltcond|takeoff|q', 'fltcond|q', 100 * np.ones(nn_tot),
'Pa'
]]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
#===We assume the takeoff starts at 1 m/s to avoid singularities at v=0
const = self.add_subsystem('const', IndepVarComp())
const.add_output('v0', val=1, units='m/s')
const.add_output('reaction_time', val=2, units='s')
#===Lift and Drag Calculations feed the EOMs for the takeoff roll===
self.add_subsystem(
'CL',
TakeoffCLs(n_int_per_seg=n_int_per_seg),
promotes_inputs=["ac|geom|*", "fltcond|*", "weight"],
)
self.add_subsystem(
'drag',
PolarDrag(num_nodes=nn_tot),
promotes_inputs=['ac|geom|*', 'fltcond|q', 'CD0', 'e'],
promotes_outputs=['drag'])
self.add_subsystem('lift',
Lift(num_nodes=nn_tot),
promotes_inputs=['ac|geom|*', 'fltcond|q'],
promotes_outputs=['lift'])
self.connect('CL.CL_takeoff', 'drag.fltcond|CL')
self.connect('CL.CL_takeoff', 'lift.fltcond|CL')
#==The takeoff distance integrator numerically integrates the quantity (speed / acceleration) with respect to speed to obtain distance. Obtain this quantity:
self.add_subsystem(
'accel',
TakeoffAccels(n_int_per_seg=n_int_per_seg),
promotes_inputs=['lift', 'drag', 'takeoff|thrust', 'weight'],
promotes_outputs=['_inverse_accel'])
self.add_subsystem(
'mult',
ElementMultiplyDivideComp(
output_name='_rate_to_integrate',
input_names=['_inverse_accel', 'fltcond|takeoff|Utrue'],
vec_size=nn_tot,
input_units=['s**2/m', 'm/s']),
promotes_inputs=['*'],
promotes_outputs=['_*'])
if track_fuel:
self.add_subsystem(
'fuelflowmult',
ElementMultiplyDivideComp(
output_name='_fuel_flow_rate_to_integrate',
input_names=['_inverse_accel', 'takeoff|fuel_flow'],
vec_size=nn_tot,
input_units=['s**2/m', 'kg/s']),
promotes_inputs=['*'],
promotes_outputs=['_*'])
if track_battery:
self.add_subsystem(
'batterymult',
ElementMultiplyDivideComp(
output_name='_battery_rate_to_integrate',
input_names=['_inverse_accel', 'takeoff|battery_load'],
vec_size=nn_tot,
input_units=['s**2/m', 'J / s']),
promotes_inputs=['*'],
promotes_outputs=['*'])
#==The following boilerplate splits the input flight conditions, thrusts, and fuel flows into the takeoff segments for further analysis
inputs_to_split = [
'_rate_to_integrate', 'fltcond|takeoff|Utrue', 'takeoff|thrust',
'drag', 'lift'
]
units = ['s', 'm/s', 'N', 'N', 'N']
if track_battery:
inputs_to_split.append('_battery_rate_to_integrate')
units.append('J*s/m')
if track_fuel:
inputs_to_split.append('_fuel_flow_rate_to_integrate')
units.append('kg*s/m')
segments_to_split_into = ['v0v1', 'v1vr', 'v1v0', 'vtrans', 'v2']
nn_each_segment = [nn, nn, nn, 1, 1]
split_inst = VectorSplitComp()
for kth, input_name in enumerate(inputs_to_split):
output_names_list = []
for segment in segments_to_split_into:
output_names_list.append(input_name + '_' + segment)
split_inst.add_relation(output_names=output_names_list,
input_name=input_name,
vec_sizes=nn_each_segment,
units=units[kth])
splitter = self.add_subsystem('splitter',
subsys=split_inst,
promotes_inputs=["*"],
promotes_outputs=["*"])
#==Now integrate the three continuous segments: 0 to v1, v1 to rotation with reduced power if applicable, and hard braking
self.add_subsystem(
'v0v1_dist',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='m',
diff_units='m/s',
force_signs=True))
self.add_subsystem(
'v1vr_dist',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='m',
diff_units='m/s',
force_signs=True))
self.add_subsystem(
'v1v0_dist',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='m',
diff_units='m/s',
force_signs=True))
self.connect('_rate_to_integrate_v0v1', 'v0v1_dist.rate')
self.connect('_rate_to_integrate_v1vr', 'v1vr_dist.rate')
self.connect('_rate_to_integrate_v1v0', 'v1v0_dist.rate')
self.connect('const.v0', 'v0v1_dist.lower_limit')
self.connect('v1', 'v0v1_dist.upper_limit')
self.connect('v1', 'v1v0_dist.lower_limit')
self.connect('const.v0', 'v1v0_dist.upper_limit')
self.connect('v1', 'v1vr_dist.lower_limit')
self.connect('vr', 'v1vr_dist.upper_limit')
if track_fuel:
self.add_subsystem(
'v0v1_fuel',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='kg',
diff_units='m/s',
force_signs=True))
self.add_subsystem(
'v1vr_fuel',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='kg',
diff_units='m/s',
force_signs=True))
self.connect('_fuel_flow_rate_to_integrate_v0v1', 'v0v1_fuel.rate')
self.connect('_fuel_flow_rate_to_integrate_v1vr', 'v1vr_fuel.rate')
self.connect('const.v0', 'v0v1_fuel.lower_limit')
self.connect('v1',
['v0v1_fuel.upper_limit', 'v1vr_fuel.lower_limit'])
self.connect('vr', 'v1vr_fuel.upper_limit')
if track_battery:
self.add_subsystem(
'v0v1_battery',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='J',
diff_units='m/s',
force_signs=True))
self.add_subsystem(
'v1vr_battery',
IntegrateQuantity(num_intervals=n_int_per_seg,
quantity_units='J',
diff_units='m/s',
force_signs=True))
self.connect('_battery_rate_to_integrate_v0v1',
'v0v1_battery.rate')
self.connect('_battery_rate_to_integrate_v1vr',
'v1vr_battery.rate')
self.connect('const.v0', 'v0v1_battery.lower_limit')
self.connect(
'v1', ['v0v1_battery.upper_limit', 'v1vr_battery.lower_limit'])
self.connect('vr', 'v1vr_battery.upper_limit')
#==Next compute the transition and climb phase to the specified clearance height. First, need the steady climb-out angle at v2 speed
self.add_subsystem(
'gamma',
TakeoffV2ClimbAngle(),
promotes_inputs=["drag_v2", "takeoff|thrust_v2", "weight"],
promotes_outputs=["takeoff|climb|gamma"])
self.add_subsystem('transition',
TakeoffTransition(),
promotes_inputs=[
"fltcond|takeoff|Utrue_vtrans",
"takeoff|climb|gamma"
],
promotes_outputs=["h_transition", "s_transition"])
self.add_subsystem(
'climb',
TakeoffClimb(),
promotes_inputs=["takeoff|climb|gamma", "h_transition"],
promotes_outputs=["s_climb"])
self.add_subsystem('reaction',
ElementMultiplyDivideComp(
output_name='s_reaction',
input_names=['v1', 'reaction_time'],
vec_size=1,
input_units=['m/s', 's']),
promotes_inputs=['v1'])
self.connect('const.reaction_time', 'reaction.reaction_time')
self.add_subsystem('total_to_distance_continue',
AddSubtractComp(output_name='takeoff|distance',
input_names=[
's_v0v1', 's_v1vr',
's_reaction', 's_transition',
's_climb'
],
vec_size=1,
units='m'),
promotes_outputs=["*"])
self.add_subsystem('total_to_distance_abort',
AddSubtractComp(
output_name='takeoff|distance_abort',
input_names=['s_v0v1', 's_v1v0', 's_reaction'],
vec_size=1,
units='m'),
promotes_outputs=["*"])
self.connect('reaction.s_reaction',
'total_to_distance_continue.s_reaction')
self.connect('reaction.s_reaction',
'total_to_distance_abort.s_reaction')
self.connect('v0v1_dist.delta_quantity', [
'total_to_distance_continue.s_v0v1',
'total_to_distance_abort.s_v0v1'
])
self.connect('v1vr_dist.delta_quantity',
'total_to_distance_continue.s_v1vr')
self.connect('s_transition', 'total_to_distance_continue.s_transition')
self.connect('s_climb', 'total_to_distance_continue.s_climb')
self.connect('v1v0_dist.delta_quantity',
'total_to_distance_abort.s_v1v0')
if track_battery:
self.add_subsystem(
'total_battery',
AddSubtractComp(output_name='takeoff|total_battery_energy',
input_names=['battery_v0v1', 'battery_v1vr'],
units='J'),
promotes_outputs=["*"])
self.connect('v0v1_battery.delta_quantity',
'total_battery.battery_v0v1')
self.connect('v1vr_battery.delta_quantity',
'total_battery.battery_v1vr')
if track_fuel:
self.add_subsystem('total_fuel',
AddSubtractComp(
output_name='takeoff|total_fuel',
input_names=['fuel_v0v1', 'fuel_v1vr'],
units='kg',
scaling_factors=[-1, -1]),
promotes_outputs=["*"])
self.connect('v0v1_fuel.delta_quantity', 'total_fuel.fuel_v0v1')
self.connect('v1vr_fuel.delta_quantity', 'total_fuel.fuel_v1vr')
self.add_subsystem(
'climb_weight',
AddSubtractComp(output_name='weight_after_takeoff',
input_names=['weight', 'takeoff|total_fuel'],
units='kg',
scaling_factors=[1, -1]),
promotes_inputs=["*"],
promotes_outputs=["*"])
def setup(self):
#define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 750, 'hp'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.28, 'm'],
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
nn = self.options['num_nodes']
#introduce model components
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
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|*"])
self.add_subsystem(
'eng2',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104))
self.add_subsystem('prop2',
SimplePropeller(num_nodes=nn,
num_blades=4,
design_J=2.2,
design_cp=0.55),
promotes_inputs=["fltcond|*"])
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('eng_rating', 'eng2.shaft_power_rating')
self.connect('eng_rating', 'prop1.power_rating')
self.connect('eng_rating', 'prop2.power_rating')
self.connect('prop_diameter', 'prop1.diameter')
self.connect('prop_diameter', 'prop2.diameter')
#propulsion models expect a high-level 'throttle' parameter and a 'propulsor_active' flag to set individual throttles
failedengine = ElementMultiplyDivideComp()
failedengine.add_equation('eng2throttle',
input_names=['throttle', 'propulsor_active'],
vec_size=nn)
self.add_subsystem('failedengine',
failedengine,
promotes_inputs=['throttle', 'propulsor_active'])
self.connect('failedengine.eng2throttle', 'eng2.throttle')
#connect components to each other
self.connect('eng1.shaft_power_out', 'prop1.shaft_power_in')
self.connect('eng2.shaft_power_out', 'prop2.shaft_power_in')
#add up the weights, thrusts and fuel flows
add1 = AddSubtractComp(
output_name='fuel_flow',
input_names=['eng1_fuel_flow', 'eng2_fuel_flow'],
vec_size=nn,
units='kg/s')
add1.add_equation(output_name='thrust',
input_names=['prop1_thrust', 'prop2_thrust'],
vec_size=nn,
units='N')
add1.add_equation(output_name='engines_weight',
input_names=['eng1_weight', 'eng2_weight'],
units='kg')
add1.add_equation(output_name='propellers_weight',
input_names=['prop1_weight', 'prop2_weight'],
units='kg')
self.add_subsystem('adder',
subsys=add1,
promotes_inputs=["*"],
promotes_outputs=["*"])
self.connect('prop1.thrust', 'prop1_thrust')
self.connect('prop2.thrust', 'prop2_thrust')
self.connect('eng1.fuel_flow', 'eng1_fuel_flow')
self.connect('eng2.fuel_flow', 'eng2_fuel_flow')
self.connect('prop1.component_weight', 'prop1_weight')
self.connect('prop2.component_weight', 'prop2_weight')
self.connect('eng1.component_weight', 'eng1_weight')
self.connect('eng2.component_weight', 'eng2_weight')
def setup(self):
#define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 260.0, 'kW'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.5, 'm'],
['ac|propulsion|motor|rating', 'motor_rating', 240.0, 'kW'],
['ac|propulsion|generator|rating', 'gen_rating', 250.0, 'kW'],
['ac|weights|W_battery', 'batt_weight', 2000, 'kg']
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
nn = self.options['num_nodes']
e_b = self.options['specific_energy']
#introduce model components
self.add_subsystem('motor1', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
self.add_subsystem('motor2', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop2',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor2.shaft_power_out', 'prop2.shaft_power_in')
addpower = AddSubtractComp(
output_name='motors_elec_load',
input_names=['motor1_elec_load', 'motor2_elec_load'],
units='kW',
vec_size=nn)
addpower.add_equation(output_name='thrust',
input_names=['prop1_thrust', 'prop2_thrust'],
units='N',
vec_size=nn)
self.add_subsystem('add_power',
subsys=addpower,
promotes_outputs=['*'])
self.connect('motor1.elec_load', 'add_power.motor1_elec_load')
self.connect('motor2.elec_load', 'add_power.motor2_elec_load')
self.connect('prop1.thrust', 'add_power.prop1_thrust')
self.connect('prop2.thrust', 'add_power.prop2_thrust')
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.connect('motors_elec_load', 'hybrid_split.power_in')
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
promotes_outputs=["fuel_flow"])
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.add_subsystem('batt1',
SimpleBattery(num_nodes=nn, specific_energy=e_b))
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
self.add_subsystem(
'eng_gen_resid',
AddSubtractComp(
output_name='eng_gen_residual',
input_names=['gen_power_available', 'gen_power_required'],
vec_size=nn,
units='kW',
scaling_factors=[1, -1]))
#need to use the optimizer to drive hybrid_split.power_out_B to the same value as gen1.elec_power_out
self.connect('hybrid_split.power_out_B',
'eng_gen_resid.gen_power_required')
self.connect('gen1.elec_power_out',
'eng_gen_resid.gen_power_available')
addweights = AddSubtractComp(
output_name='motors_weight',
input_names=['motor1_weight', 'motor2_weight'],
units='kg')
addweights.add_equation(output_name='propellers_weight',
input_names=['prop1_weight', 'prop2_weight'],
units='kg')
self.add_subsystem('add_weights',
subsys=addweights,
promotes_inputs=['*'],
promotes_outputs=['*'])
relabel = [[
'hybrid_split_A_in', 'battery_load',
np.ones(nn) * 260.0, 'kW'
]]
self.add_subsystem('relabel',
DVLabel(relabel),
promotes_outputs=["battery_load"])
self.connect('hybrid_split.power_out_A', 'relabel.hybrid_split_A_in')
self.connect('motor1.component_weight', 'motor1_weight')
self.connect('motor2.component_weight', 'motor2_weight')
self.connect('prop1.component_weight', 'prop1_weight')
self.connect('prop2.component_weight', 'prop2_weight')
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('prop_diameter', ['prop1.diameter', 'prop2.diameter'])
self.connect('motor_rating',
['motor1.elec_power_rating', 'motor2.elec_power_rating'])
self.connect('motor_rating',
['prop1.power_rating', 'prop2.power_rating'])
self.connect('gen_rating', 'gen1.elec_power_rating')
self.connect('batt_weight', 'batt1.battery_weight')
def setup(self):
nn = self.options['num_nodes']
e_b = self.options['specific_energy']
# define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 260.0, 'kW'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.5, 'm'],
['ac|propulsion|motor|rating', 'motor_rating', 240.0, 'kW'],
['ac|propulsion|generator|rating', 'gen_rating', 250.0, 'kW'],
['ac|weights|W_battery', 'batt_weight', 2000, 'kg']
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
# introduce model components
self.add_subsystem('motor1', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"],
promotes_outputs=['thrust'])
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.connect('motor1.elec_load', 'hybrid_split.power_in')
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
promotes_outputs=["fuel_flow"])
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.add_subsystem('batt1',
SimpleBattery(num_nodes=nn, specific_energy=e_b))
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
# need to use the optimizer to drive hybrid_split.power_out_B to the
# same value as gen1.elec_power_out.
# create a residual equation for power in vs power out from the generator
self.add_subsystem(
'eng_gen_resid',
AddSubtractComp(
output_name='eng_gen_residual',
input_names=['gen_power_available', 'gen_power_required'],
vec_size=nn,
units='kW',
scaling_factors=[1, -1]))
self.connect('hybrid_split.power_out_B',
'eng_gen_resid.gen_power_required')
self.connect('gen1.elec_power_out',
'eng_gen_resid.gen_power_available')
# add the weights of all the motors and props
# (forward-compatibility for twin series hybrid layout)
addweights = AddSubtractComp(output_name='motors_weight',
input_names=['motor1_weight'],
units='kg')
addweights.add_equation(output_name='propellers_weight',
input_names=['prop1_weight'],
units='kg')
self.add_subsystem('add_weights',
subsys=addweights,
promotes_inputs=['*'],
promotes_outputs=['*'])
self.connect('motor1.component_weight', 'motor1_weight')
self.connect('prop1.component_weight', 'prop1_weight')
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('prop_diameter', ['prop1.diameter'])
self.connect('motor_rating', ['motor1.elec_power_rating'])
self.connect('motor_rating', ['prop1.power_rating'])
self.connect('gen_rating', 'gen1.elec_power_rating')
self.connect('batt_weight', 'batt1.battery_weight')
def setup(self):
nn = self.options['num_nodes']
#define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 260.0, 'kW'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.5, 'm'],
['ac|propulsion|motor|rating', 'motor_rating', 240.0, 'kW'],
['ac|propulsion|generator|rating', 'gen_rating', 250.0, 'kW'],
['ac|weights|W_battery', 'batt_weight', 2000, 'kg'],
[
'ac|propulsion|thermal|hx|mdot_coolant', 'mdot_coolant',
0.1 * np.ones((nn, )), 'kg/s'
],
[
'ac|propulsion|thermal|hx|coolant_mass', 'coolant_mass', 10.,
'kg'
],
[
'ac|propulsion|thermal|hx|channel_width', 'channel_width', 1.,
'mm'
],
[
'ac|propulsion|thermal|hx|channel_height', 'channel_height',
20., 'mm'
],
[
'ac|propulsion|thermal|hx|channel_length', 'channel_length',
0.2, 'm'
],
['ac|propulsion|thermal|hx|n_parallel', 'n_parallel', 50, None],
# ['ac|propulsion|thermal|duct|area_nozzle','area_nozzle',58.*np.ones((nn,)),'inch**2'],
[
'ac|propulsion|battery|specific_energy', 'specific_energy',
300, 'W*h/kg'
]
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
#introduce model components
self.add_subsystem('motor1',
SimpleMotor(efficiency=0.97, num_nodes=nn),
promotes_inputs=['throttle'])
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
#propulsion models expect a high-level 'throttle' parameter and a 'propulsor_active' flag to set individual throttles
failedengine = ElementMultiplyDivideComp()
failedengine.add_equation('motor2throttle',
input_names=['throttle', 'propulsor_active'],
vec_size=nn)
self.add_subsystem('failedmotor',
failedengine,
promotes_inputs=['throttle', 'propulsor_active'])
self.add_subsystem('motor2', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop2',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor2.shaft_power_out', 'prop2.shaft_power_in')
self.connect('failedmotor.motor2throttle', 'motor2.throttle')
addpower = AddSubtractComp(output_name='total_elec_load',
input_names=[
'motor1_elec_load', 'motor2_elec_load',
'refrig_elec_load'
],
units='kW',
vec_size=nn)
addpower.add_equation(output_name='thrust',
input_names=['prop1_thrust', 'prop2_thrust'],
units='N',
vec_size=nn)
self.add_subsystem('add_power',
subsys=addpower,
promotes_outputs=['*'])
self.connect('motor1.elec_load', 'add_power.motor1_elec_load')
self.connect('motor2.elec_load', 'add_power.motor2_elec_load')
self.connect('prop1.thrust', 'add_power.prop1_thrust')
self.connect('prop2.thrust', 'add_power.prop2_thrust')
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.connect('total_elec_load', 'hybrid_split.power_in')
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
promotes_outputs=["fuel_flow"])
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.add_subsystem('batt1',
SOCBattery(num_nodes=nn, efficiency=0.97),
promotes_inputs=["duration", 'specific_energy'])
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
# TODO set val= right number of nn
self.add_subsystem(
'eng_throttle_set',
BalanceComp(name='eng_throttle',
val=np.ones((nn, )) * 0.5,
units=None,
eq_units='kW',
rhs_name='gen_power_required',
lhs_name='gen_power_available'))
#need to use the optimizer to drive hybrid_split.power_out_B to the same value as gen1.elec_power_out
self.connect('hybrid_split.power_out_B',
'eng_throttle_set.gen_power_required')
self.connect('gen1.elec_power_out',
'eng_throttle_set.gen_power_available')
self.connect('eng_throttle_set.eng_throttle', 'eng1.throttle')
adder = AddSubtractComp(output_name='motors_weight',
input_names=['motor1_weight', 'motor2_weight'],
units='kg')
adder.add_equation(output_name='propellers_weight',
input_names=['prop1_weight', 'prop2_weight'],
units='kg')
adder.add_equation(output_name='motors_heat',
input_names=['motor1_heat', 'motor2_heat'],
vec_size=nn,
units='W')
self.add_subsystem('adder',
subsys=adder,
promotes_inputs=['*'],
promotes_outputs=['*'])
relabel = [[
'hybrid_split_A_in', 'battery_load',
np.ones(nn) * 260.0, 'kW'
]]
self.add_subsystem('relabel',
DVLabel(relabel),
promotes_outputs=["battery_load"])
self.connect('hybrid_split.power_out_A', 'relabel.hybrid_split_A_in')
self.connect('motor1.component_weight', 'motor1_weight')
self.connect('motor2.component_weight', 'motor2_weight')
self.connect('prop1.component_weight', 'prop1_weight')
self.connect('prop2.component_weight', 'prop2_weight')
self.connect('motor1.heat_out', 'motor1_heat')
self.connect('motor2.heat_out', 'motor2_heat')
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('prop_diameter', ['prop1.diameter', 'prop2.diameter'])
self.connect('motor_rating',
['motor1.elec_power_rating', 'motor2.elec_power_rating'])
self.connect('motor_rating',
['prop1.power_rating', 'prop2.power_rating'])
self.connect('gen_rating', 'gen1.elec_power_rating')
self.connect('batt_weight', 'batt1.battery_weight')
iv = self.add_subsystem('iv', IndepVarComp(), promotes_outputs=['*'])
rho_coolant = 997. # kg/m^3
iv.add_output('rho_coolant',
val=rho_coolant * np.ones((nn, )),
units='kg/m**3')
lc_promotes = ['duration', 'channel_*', 'n_parallel']
# Add the refrigerators electrical load to the splitter with the two motors
# so it pulls power from both the battery and turboshaft at the hybridization ratio
self.add_subsystem(
'refrig',
HeatPumpWithIntegratedCoolantLoop(
num_nodes=nn,
hot_side_balance_param_units='inch**2',
hot_side_balance_param_lower=1e-10,
hot_side_balance_param_upper=1e3))
self.connect('refrig.Wdot', 'add_power.refrig_elec_load')
iv.add_output('refrig_eff_factor', val=0.4, shape=None, units=None)
iv.add_output('refrig_T_h_set', val=450., shape=(nn, ), units='K')
iv.add_output('refrig_T_c_set', val=280., shape=(nn, ), units='K')
iv.add_output('bypass_refrig',
val=np.zeros((nn, )),
shape=(nn, ),
units=None)
self.connect('refrig_eff_factor', 'refrig.eff_factor')
self.connect('refrig_T_h_set', 'refrig.T_h_set')
self.connect('refrig_T_c_set', 'refrig.T_c_set')
self.connect('bypass_refrig', 'refrig.bypass_heat_pump')
# Coolant loop on electrical component side (cooling side of refrigerator)
# ,---> battery ---> motor ---,
# | |
# '---- refrig cold side <----'
self.add_subsystem('batteryheatsink',
LiquidCooledComp(num_nodes=nn, quasi_steady=False),
promotes_inputs=lc_promotes)
self.connect('batt1.heat_out', 'batteryheatsink.q_in')
self.connect('batt_weight', 'batteryheatsink.mass')
self.connect('refrig.T_out_cold', 'batteryheatsink.T_in')
self.add_subsystem('motorheatsink',
LiquidCooledComp(num_nodes=nn, quasi_steady=False),
promotes_inputs=lc_promotes)
self.connect('motors_heat', 'motorheatsink.q_in')
self.connect('motors_weight', 'motorheatsink.mass')
self.connect('motorheatsink.T_out', 'refrig.T_in_cold')
self.connect('batteryheatsink.T_out', 'motorheatsink.T_in')
self.connect('mdot_coolant', [
'batteryheatsink.mdot_coolant', 'motorheatsink.mdot_coolant',
'refrig.mdot_coolant_cold'
])
# Coolant loop on hot side of refrigerator to reject heat
# ,----> refrigerator hot side -----,
# | |
# '----- heat exchanger/duct <------'
self.add_subsystem('duct',
ExplicitIncompressibleDuct(num_nodes=nn),
promotes_inputs=['fltcond|*'])
self.add_subsystem('hx',
HXGroup(num_nodes=nn),
promotes_inputs=[
'ac|*', ('rho_cold', 'fltcond|rho'),
('T_in_cold', 'fltcond|T')
])
self.connect('duct.mdot', 'hx.mdot_cold')
self.connect('hx.delta_p_cold', 'duct.delta_p_hex')
self.connect('rho_coolant', 'hx.rho_hot')
self.connect('refrig.T_out_hot', 'hx.T_in_hot')
self.connect('hx.T_out_hot', 'refrig.T_in_hot')
# Modulate the duct inlet area to maintain the desired temperature on the hot side of the refrig
self.connect('refrig.hot_side_balance_param', 'duct.area_nozzle')
self.connect('mdot_coolant',
['refrig.mdot_coolant_hot', 'hx.mdot_hot'])
def setup(self):
nn = self.options['num_nodes']
#define design variables that are independent of flight condition or control states
dvlist = [
['ac|propulsion|engine|rating', 'eng_rating', 260.0, 'kW'],
['ac|propulsion|propeller|diameter', 'prop_diameter', 2.5, 'm'],
['ac|propulsion|motor|rating', 'motor_rating', 240.0, 'kW'],
['ac|propulsion|generator|rating', 'gen_rating', 250.0, 'kW'],
['ac|weights|W_battery', 'batt_weight', 2000, 'kg'],
[
'ac|propulsion|battery|specific_energy', 'specific_energy',
300, 'W*h/kg'
]
]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
#introduce model components
self.add_subsystem('motor1',
SimpleMotor(efficiency=0.97, num_nodes=nn),
promotes_inputs=['throttle'])
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
#propulsion models expect a high-level 'throttle' parameter and a 'propulsor_active' flag to set individual throttles
failedengine = ElementMultiplyDivideComp()
failedengine.add_equation('motor2throttle',
input_names=['throttle', 'propulsor_active'],
vec_size=nn)
self.add_subsystem('failedmotor',
failedengine,
promotes_inputs=['throttle', 'propulsor_active'])
self.add_subsystem('motor2', SimpleMotor(efficiency=0.97,
num_nodes=nn))
self.add_subsystem('prop2',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond|*"])
self.connect('motor2.shaft_power_out', 'prop2.shaft_power_in')
self.connect('failedmotor.motor2throttle', 'motor2.throttle')
addpower = AddSubtractComp(
output_name='motors_elec_load',
input_names=['motor1_elec_load', 'motor2_elec_load'],
units='kW',
vec_size=nn)
addpower.add_equation(output_name='thrust',
input_names=['prop1_thrust', 'prop2_thrust'],
units='N',
vec_size=nn)
self.add_subsystem('add_power',
subsys=addpower,
promotes_outputs=['*'])
self.connect('motor1.elec_load', 'add_power.motor1_elec_load')
self.connect('motor2.elec_load', 'add_power.motor2_elec_load')
self.connect('prop1.thrust', 'add_power.prop1_thrust')
self.connect('prop2.thrust', 'add_power.prop2_thrust')
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.connect('motors_elec_load', 'hybrid_split.power_in')
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn,
weight_inc=0.14 / 1000,
weight_base=104),
promotes_outputs=["fuel_flow"])
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.add_subsystem('batt1',
SOCBattery(num_nodes=nn, efficiency=0.97),
promotes_inputs=["duration", "specific_energy"])
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
# TODO set val= right number of nn
self.add_subsystem(
'eng_throttle_set',
BalanceComp(name='eng_throttle',
val=np.ones((nn, )) * 0.5,
units=None,
eq_units='kW',
rhs_name='gen_power_required',
lhs_name='gen_power_available'))
#need to use the optimizer to drive hybrid_split.power_out_B to the same value as gen1.elec_power_out
self.connect('hybrid_split.power_out_B',
'eng_throttle_set.gen_power_required')
self.connect('gen1.elec_power_out',
'eng_throttle_set.gen_power_available')
self.connect('eng_throttle_set.eng_throttle', 'eng1.throttle')
addweights = AddSubtractComp(
output_name='motors_weight',
input_names=['motor1_weight', 'motor2_weight'],
units='kg')
addweights.add_equation(output_name='propellers_weight',
input_names=['prop1_weight', 'prop2_weight'],
units='kg')
self.add_subsystem('add_weights',
subsys=addweights,
promotes_inputs=['*'],
promotes_outputs=['*'])
relabel = [[
'hybrid_split_A_in', 'battery_load',
np.ones(nn) * 260.0, 'kW'
]]
self.add_subsystem('relabel',
DVLabel(relabel),
promotes_outputs=["battery_load"])
self.connect('hybrid_split.power_out_A', 'relabel.hybrid_split_A_in')
self.connect('motor1.component_weight', 'motor1_weight')
self.connect('motor2.component_weight', 'motor2_weight')
self.connect('prop1.component_weight', 'prop1_weight')
self.connect('prop2.component_weight', 'prop2_weight')
#connect design variables to model component inputs
self.connect('eng_rating', 'eng1.shaft_power_rating')
self.connect('prop_diameter', ['prop1.diameter', 'prop2.diameter'])
self.connect('motor_rating',
['motor1.elec_power_rating', 'motor2.elec_power_rating'])
self.connect('motor_rating',
['prop1.power_rating', 'prop2.power_rating'])
self.connect('gen_rating', 'gen1.elec_power_rating')
self.connect('batt_weight', 'batt1.battery_weight')