def setup(self):
#define design variables that are independent of flight condition or control states
dvlist = [['ac|propulsion|engine|rating', 'eng1_rating', 260.0, 'kW'],
['dv_prop1_diameter', 'prop1_diameter', 2.5, 'm'],
['dv_motor1_rating', 'motor1_rating', 240.0, 'kW'],
['dv_gen1_rating', 'gen1_rating', 250.0, 'kW'],
['dv_batt1_weight', 'batt1_weight', 2000, 'kg']]
self.add_subsystem('dvs',
DVLabel(dvlist),
promotes_inputs=["*"],
promotes_outputs=["*"])
nn = self.options['num_nodes']
#introduce model components
self.add_subsystem('motor1',
SimpleMotor(efficiency=0.97, num_nodes=nn),
promotes_inputs=["throttle"])
self.add_subsystem('hybrid_split',
PowerSplit(rule='fraction', num_nodes=nn))
self.add_subsystem('gen1',
SimpleGenerator(efficiency=0.97, num_nodes=nn))
self.add_subsystem('eng1',
SimpleTurboshaft(num_nodes=nn),
promotes_outputs=["fuel_flow"])
self.add_subsystem('batt1', SimpleBattery(num_nodes=nn))
self.add_subsystem('prop1',
SimplePropeller(num_nodes=nn),
promotes_inputs=["fltcond_*"],
promotes_outputs=["thrust"])
#connect design variables to model component inputs
self.connect('eng1_rating', 'eng1.shaft_power_rating')
self.connect('prop1_diameter', 'prop1.diameter')
self.connect('motor1_rating', 'motor1.elec_power_rating')
self.connect('motor1_rating', 'prop1.power_rating')
self.connect('gen1_rating', 'gen1.elec_power_rating')
self.connect('batt1_weight', 'batt1.battery_weight')
#connect components to each other
self.connect('motor1.shaft_power_out', 'prop1.shaft_power_in')
self.connect('eng1.shaft_power_out', 'gen1.shaft_power_in')
self.connect('motor1.elec_load', 'hybrid_split.power_in')
self.connect('hybrid_split.power_out_A', 'batt1.elec_load')
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')