def setUp(self):
self.nn = 5
self.p = om.Problem()
ivc = om.IndepVarComp()
ivc.add_output(name='a', shape=(self.nn, 3))
ivc.add_output(name='b', shape=(self.nn, 3))
self.p.model.add_subsystem(name='ivc',
subsys=ivc,
promotes_outputs=['a', 'b'])
adder = self.p.model.add_subsystem(name='add_subtract_comp',
subsys=om.AddSubtractComp())
adder.add_equation('adder_output', ['input_a', 'input_b'],
vec_size=self.nn,
length=3)
self.p.model.connect('a', 'add_subtract_comp.input_a')
self.p.model.connect('b', 'add_subtract_comp.input_b')
self.p.setup()
self.p['a'] = np.random.rand(self.nn, 3)
self.p['b'] = np.random.rand(self.nn, 3)
self.p.run_model()
def test_for_bad_scale_factors(self):
self.nn = 5
self.p = om.Problem()
ivc = om.IndepVarComp()
ivc.add_output(name='a', shape=(self.nn, 3))
ivc.add_output(name='b', shape=(self.nn, 3))
ivc.add_output(name='c', shape=(self.nn, 3))
self.p.model.add_subsystem(name='ivc',
subsys=ivc,
promotes_outputs=['a', 'b', 'c'])
adder = self.p.model.add_subsystem(name='add_subtract_comp',
subsys=om.AddSubtractComp())
with self.assertRaises(ValueError) as err:
adder.add_equation('adder_output',
['input_a', 'input_b', 'input_c'],
vec_size=self.nn,
length=3,
scaling_factors=[1, -1])
expected_msg = "'add_subtract_comp' <class AddSubtractComp>: Scaling factors list needs to be " \
"same length as input names"
self.assertEqual(str(err.exception), expected_msg)
def setup(self):
# Airframe
self.add_subsystem("loads", Loads(), promotes=["*"])
self.add_subsystem("wing_weight", WingWeight(), promotes=["*"])
self.add_subsystem("fuselage_weight", FuselageWeight(), promotes=["*"])
self.add_subsystem("empennage_weight", EmpennageWeight(), promotes=["*"])
self.add_subsystem("flight_controls_weight", FlightControlsWeight(), promotes=["*"])
self.add_subsystem("landing_gear_weight", LandingGearWeight(), promotes=["*"])
self.add_subsystem("pylons_weight", PylonsWeight(), promotes=["*"])
self.add_subsystem("paint_weight", PaintWeight(), promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:airframe:mass",
[
"data:weight:airframe:wing:mass",
"data:weight:airframe:fuselage:mass",
"data:weight:airframe:horizontal_tail:mass",
"data:weight:airframe:vertical_tail:mass",
"data:weight:airframe:flight_controls:mass",
"data:weight:airframe:landing_gear:main:mass",
"data:weight:airframe:landing_gear:front:mass",
"data:weight:airframe:pylon:mass",
"data:weight:airframe:paint:mass",
],
units="kg",
desc="Mass of airframe",
)
self.add_subsystem(
"airframe_weight_sum", weight_sum, promotes=["*"],
)
def setup(self):
# Propulsion should be done before airframe, because it drives pylon mass.
self.add_subsystem("propulsion_weight",
PropulsionWeight(),
promotes=["*"])
self.add_subsystem("airframe_weight", AirframeWeight(), promotes=["*"])
self.add_subsystem("systems_weight", SystemsWeight(), promotes=["*"])
self.add_subsystem("furniture_weight",
FurnitureWeight(),
promotes=["*"])
self.add_subsystem("crew_weight", CrewWeight(), promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:aircraft:OWE",
[
"data:weight:airframe:mass",
"data:weight:propulsion:mass",
"data:weight:systems:mass",
"data:weight:furniture:mass",
"data:weight:crew:mass",
],
units="kg",
desc="Mass of crew",
)
self.add_subsystem("OWE_sum", weight_sum, promotes=["*"])
def setup(self):
self.add_subsystem("passenger_seats_weight",
PassengerSeatsWeight(),
promotes=["*"])
self.add_subsystem("food_water_weight",
FoodWaterWeight(),
promotes=["*"])
self.add_subsystem("security_kit_weight",
SecurityKitWeight(),
promotes=["*"])
self.add_subsystem("toilets_weight", ToiletsWeight(), promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:furniture:mass",
[
"data:weight:furniture:passenger_seats:mass",
"data:weight:furniture:food_water:mass",
"data:weight:furniture:security_kit:mass",
"data:weight:furniture:toilets:mass",
],
units="kg",
desc="Mass of aircraft furniture",
)
self.add_subsystem(
"furniture_weight_sum",
weight_sum,
promotes=["*"],
)
def setup(self):
self.add_subsystem(
"passenger_seats_weight",
RegisterSubmodel.get_submodel(SERVICE_PASSENGER_SEATS_MASS),
promotes=["*"],
)
self.add_subsystem(
"food_water_weight",
RegisterSubmodel.get_submodel(SERVICE_FOOD_WATER_MASS),
promotes=["*"],
)
self.add_subsystem(
"security_kit_weight",
RegisterSubmodel.get_submodel(SERVICE_SECURITY_KIT_MASS, ""),
promotes=["*"],
)
self.add_subsystem("toilets_weight",
RegisterSubmodel.get_submodel(SERVICE_TOILETS_MASS),
promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:furniture:mass",
[
"data:weight:furniture:passenger_seats:mass",
"data:weight:furniture:food_water:mass",
"data:weight:furniture:security_kit:mass",
"data:weight:furniture:toilets:mass",
],
units="kg",
desc="Mass of aircraft furniture",
)
self.add_subsystem("furniture_weight_sum", weight_sum, promotes=["*"])
def setup(self):
# Engine have to be computed before pylons
self.add_subsystem("engines_weight", EngineWeight(), promotes=["*"])
self.add_subsystem("fuel_lines_weight",
FuelLinesWeight(),
promotes=["*"])
self.add_subsystem("unconsumables_weight",
UnconsumablesWeight(),
promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:propulsion:mass",
[
"data:weight:propulsion:engine:mass",
"data:weight:propulsion:fuel_lines:mass",
"data:weight:propulsion:unconsumables:mass",
],
units="kg",
desc="Mass of the propulsion system",
)
self.add_subsystem(
"propulsion_weight_sum",
weight_sum,
promotes=["*"],
)
def setup(self):
# Engine have to be computed before pylons
self.add_subsystem(
"engines_weight", RegisterSubmodel.get_submodel(SERVICE_ENGINE_MASS), promotes=["*"]
)
self.add_subsystem(
"fuel_lines_weight",
RegisterSubmodel.get_submodel(SERVICE_FUEL_LINES_MASS),
promotes=["*"],
)
self.add_subsystem(
"unconsumables_weight",
RegisterSubmodel.get_submodel(SERVICE_UNCONSUMABLES_MASS),
promotes=["*"],
)
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:propulsion:mass",
[
"data:weight:propulsion:engine:mass",
"data:weight:propulsion:fuel_lines:mass",
"data:weight:propulsion:unconsumables:mass",
],
units="kg",
desc="Mass of the propulsion system",
)
self.add_subsystem("propulsion_weight_sum", weight_sum, promotes=["*"])
def setup(self):
self.add_subsystem(
"power_systems_weight",
RegisterSubmodel.get_submodel(SERVICE_POWER_SYSTEMS_MASS),
promotes=["*"],
)
self.add_subsystem(
"life_support_systems_weight",
RegisterSubmodel.get_submodel(SERVICE_LIFE_SUPPORT_SYSTEMS_MASS),
promotes=["*"],
)
self.add_subsystem(
"navigation_systems_weight",
RegisterSubmodel.get_submodel(SERVICE_NAVIGATION_SYSTEMS_MASS),
promotes=["*"],
)
self.add_subsystem(
"transmission_systems_weight",
RegisterSubmodel.get_submodel(SERVICE_TRANSMISSION_SYSTEMS_MASS),
promotes=["*"],
)
self.add_subsystem(
"fixed_operational_systems_weight",
RegisterSubmodel.get_submodel(SERVICE_FIXED_OPERATIONAL_SYSTEMS_MASS),
promotes=["*"],
)
self.add_subsystem(
"flight_kit_weight",
RegisterSubmodel.get_submodel(SERVICE_FLIGHT_KIT_MASS),
promotes=["*"],
)
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:systems:mass",
[
"data:weight:systems:power:auxiliary_power_unit:mass",
"data:weight:systems:power:electric_systems:mass",
"data:weight:systems:power:hydraulic_systems:mass",
"data:weight:systems:life_support:insulation:mass",
"data:weight:systems:life_support:air_conditioning:mass",
"data:weight:systems:life_support:de-icing:mass",
"data:weight:systems:life_support:cabin_lighting:mass",
"data:weight:systems:life_support:seats_crew_accommodation:mass",
"data:weight:systems:life_support:oxygen:mass",
"data:weight:systems:life_support:safety_equipment:mass",
"data:weight:systems:navigation:mass",
"data:weight:systems:transmission:mass",
"data:weight:systems:operational:radar:mass",
"data:weight:systems:operational:cargo_hold:mass",
"data:weight:systems:flight_kit:mass",
],
units="kg",
desc="Mass of aircraft systems",
)
self.add_subsystem("systems_weight_sum", weight_sum, promotes=["*"])
def test(self):
"""
A simple example to compute the resultant force on an aircraft and demonstrate the AddSubtract component
"""
import numpy as np
import openmdao.api as om
n = 3
p = om.Problem()
ivc = om.IndepVarComp()
# The vector represents forces at 3 time points (rows) in 2 dimensional plane (cols)
ivc.add_output(name='thrust', shape=(n, 2), units='kN')
ivc.add_output(name='drag', shape=(n, 2), units='kN')
ivc.add_output(name='lift', shape=(n, 2), units='kN')
ivc.add_output(name='weight', shape=(n, 2), units='kN')
p.model.add_subsystem(
name='ivc',
subsys=ivc,
promotes_outputs=['thrust', 'drag', 'lift', 'weight'])
# Construct an adder/subtracter here. create a relationship through the add_equation method
adder = om.AddSubtractComp()
adder.add_equation('total_force',
input_names=['thrust', 'drag', 'lift', 'weight'],
vec_size=n,
length=2,
scaling_factors=[1, -1, 1, -1],
units='kN')
# Note the scaling factors. we assume all forces are positive sign upstream
p.model.add_subsystem(name='totalforcecomp', subsys=adder)
p.model.connect('thrust', 'totalforcecomp.thrust')
p.model.connect('drag', 'totalforcecomp.drag')
p.model.connect('lift', 'totalforcecomp.lift')
p.model.connect('weight', 'totalforcecomp.weight')
p.setup()
# Set thrust to exceed drag, weight to equal lift for this scenario
p['thrust'][:, 0] = [500, 600, 700]
p['drag'][:, 0] = [400, 400, 400]
p['weight'][:, 1] = [1000, 1001, 1002]
p['lift'][:, 1] = [1000, 1000, 1000]
p.run_model()
# print(p.get_val('totalforcecomp.total_force', units='kN'))
# Verify the results
expected_i = np.array([[100, 200, 300], [0, -1, -2]]).T
assert_rel_error(self,
p.get_val('totalforcecomp.total_force', units='kN'),
expected_i)
def setup(self):
# Airframe
self.add_subsystem("loads",
RegisterSubmodel.get_submodel(SERVICE_GUST_LOADS),
promotes=["*"])
self.add_subsystem("wing_weight",
RegisterSubmodel.get_submodel(SERVICE_WING_MASS),
promotes=["*"])
self.add_subsystem(
"fuselage_weight",
RegisterSubmodel.get_submodel(SERVICE_FUSELAGE_MASS),
promotes=["*"])
self.add_subsystem(
"empennage_weight",
RegisterSubmodel.get_submodel(SERVICE_EMPENNAGE_MASS),
promotes=["*"],
)
self.add_subsystem(
"flight_controls_weight",
RegisterSubmodel.get_submodel(SERVICE_FLIGHT_CONTROLS_MASS),
promotes=["*"],
)
self.add_subsystem(
"landing_gear_weight",
RegisterSubmodel.get_submodel(SERVICE_LANDING_GEARS_MASS),
promotes=["*"],
)
self.add_subsystem("pylons_weight",
RegisterSubmodel.get_submodel(SERVICE_PYLONS_MASS),
promotes=["*"])
self.add_subsystem("paint_weight",
RegisterSubmodel.get_submodel(SERVICE_PAINT_MASS),
promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:airframe:mass",
[
"data:weight:airframe:wing:mass",
"data:weight:airframe:fuselage:mass",
"data:weight:airframe:horizontal_tail:mass",
"data:weight:airframe:vertical_tail:mass",
"data:weight:airframe:flight_controls:mass",
"data:weight:airframe:landing_gear:main:mass",
"data:weight:airframe:landing_gear:front:mass",
"data:weight:airframe:pylon:mass",
"data:weight:airframe:paint:mass",
],
units="kg",
desc="Mass of airframe",
)
self.add_subsystem("airframe_weight_sum", weight_sum, promotes=["*"])
def setup(self):
self.add_subsystem("power_systems_weight",
PowerSystemsWeight(),
promotes=["*"])
self.add_subsystem("life_support_systems_weight",
LifeSupportSystemsWeight(),
promotes=["*"])
self.add_subsystem("navigation_systems_weight",
NavigationSystemsWeight(),
promotes=["*"])
self.add_subsystem("transmission_systems_weight",
TransmissionSystemsWeight(),
promotes=["*"])
self.add_subsystem("fixed_operational_systems_weight",
FixedOperationalSystemsWeight(),
promotes=["*"])
self.add_subsystem("flight_kit_weight",
FlightKitWeight(),
promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:systems:mass",
[
"data:weight:systems:power:auxiliary_power_unit:mass",
"data:weight:systems:power:electric_systems:mass",
"data:weight:systems:power:hydraulic_systems:mass",
"data:weight:systems:life_support:insulation:mass",
"data:weight:systems:life_support:air_conditioning:mass",
"data:weight:systems:life_support:de-icing:mass",
"data:weight:systems:life_support:cabin_lighting:mass",
"data:weight:systems:life_support:seats_crew_accommodation:mass",
"data:weight:systems:life_support:oxygen:mass",
"data:weight:systems:life_support:safety_equipment:mass",
"data:weight:systems:navigation:mass",
"data:weight:systems:transmission:mass",
"data:weight:systems:operational:radar:mass",
"data:weight:systems:operational:cargo_hold:mass",
"data:weight:systems:flight_kit:mass",
],
units="kg",
desc="Mass of aircraft systems",
)
self.add_subsystem(
"systems_weight_sum",
weight_sum,
promotes=["*"],
)
def setup(self):
nn = self.options['num_nodes']
geom = self.options['geom']
num_cells = self.options['num_cells']
pcm_bool = self.options['pcm_bool']
# Set inputs/outputs based on geometry
if geom == 'round':
inpts = ['LW:L_flux', 'LW:L_adiabatic', 'XS:t_w', 'XS:t_wk', 'XS:D_v']
outpts = ['XS:D_od','XS:r_i', 'LW:A_flux', 'LW:A_inter']
elif geom == 'flat':
inpts = ['LW:L_flux', 'LW:L_adiabatic', 'XS:t_w', 'XS:t_wk']
outpts = ['LW:A_flux', 'LW:A_inter', 'XS:W_hp']
# Size the pack components
self.add_subsystem(name = 'size',
subsys = HPgeom(num_nodes=nn, geom=geom),
promotes_inputs=inpts,
promotes_outputs=outpts)
# Calculate total mass
self.add_subsystem(name='massPCM',
subsys = pcmMass(num_nodes=nn),
promotes_inputs=['t_pad', 'A_pad', 'porosity'],
promotes_outputs=['mass_pcm'])
self.add_subsystem(name='massInsulation',
subsys = insulationMass(num_nodes=nn),
promotes_inputs=['num_cells','batt_l','L_flux','batt_h','ins_thickness'],
promotes_outputs=['ins_mass'])
if geom == 'flat':
self.add_subsystem(name='massHP',
subsys = flatHPmass(num_nodes=nn),
promotes_inputs=['length_hp', 'width_hp', 'wick_t', 'wall_t','wick_porosity'],
promotes_outputs=['mass_hp'])
if geom == 'round':
self.add_subsystem(name='massHP',
subsys = roundHPmass(num_nodes=nn),
promotes_inputs=['D_od_hp', 'wick_t', 'wall_t','wick_porosity'],
promotes_outputs=['mass_hp'])
adder = om.AddSubtractComp()
adder.add_equation('mass_total',
input_names=['mass_pcm','mass_hp','ins_mass','mass_battery'],
vec_size=nn, units='kg')
self.add_subsystem(name='mass_comp',
subsys = adder,
promotes_inputs=['mass_pcm','mass_hp','ins_mass','mass_battery'],
promotes_outputs=['mass_total'])
def _get_tow_component(mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes TakeOff Weight from ZFW and needed block fuel
"""
tow_computation = om.AddSubtractComp()
tow_computation.add_equation(
"data:mission:%s:TOW" % mission_name,
[
"data:mission:%s:ZFW" % mission_name,
"data:mission:%s:block_fuel" % mission_name,
],
units="kg",
)
return tow_computation
def _get_tow_component(mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes TakeOff Weight from ZFW and loaded fuel at takeoff
"""
tow_computation = om.AddSubtractComp()
tow_computation.add_equation(
f"data:mission:{mission_name}:TOW",
[
f"data:mission:{mission_name}:ZFW",
f"data:mission:{mission_name}:onboard_fuel_at_takeoff",
],
units="kg",
desc=f'TakeOff Weight for mission "{mission_name}"',
)
return tow_computation
def _get_tow_component(mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes TakeOff Weight from ZFW and loaded fuel at takeoff
"""
tow_computation = om.AddSubtractComp()
tow_computation.add_equation(
"data:mission:%s:TOW" % mission_name,
[
"data:mission:%s:ZFW" % mission_name,
"data:mission:%s:onboard_fuel_at_takeoff" % mission_name,
],
units="kg",
desc='TakeOff Weight for mission "%s"' % mission_name,
)
return tow_computation
def _get_block_fuel_component(mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes initial block fuel from TOW and ZFW
"""
block_fuel_computation = om.AddSubtractComp()
block_fuel_computation.add_equation(
"data:mission:%s:block_fuel" % mission_name,
[
"data:mission:%s:TOW" % mission_name,
"data:mission:%s:ZFW" % mission_name
],
units="kg",
scaling_factors=[1, -1],
)
return block_fuel_computation
def _get_zfw_component(self, mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes Zero Fuel Weight from OWE and mission payload
"""
if self.options["is_sizing"]:
payload_var = "data:weight:aircraft:payload"
else:
payload_var = "data:mission:%s:payload" % mission_name
zfw_computation = om.AddSubtractComp()
zfw_computation.add_equation(
"data:mission:%s:ZFW" % mission_name,
["data:weight:aircraft:OWE", payload_var],
units="kg",
)
return zfw_computation
def _get_block_fuel_component(mission_name: str) -> om.AddSubtractComp:
"""
:param mission_name:
:return: component that computes initial block fuel from TOW and ZFW
"""
block_fuel_computation = om.AddSubtractComp()
block_fuel_computation.add_equation(
"data:mission:%s:block_fuel" % mission_name,
[
"data:mission:%s:TOW" % mission_name,
"data:mission:%s:taxi_out:fuel" % mission_name,
"data:mission:%s:takeoff:fuel" % mission_name,
"data:mission:%s:ZFW" % mission_name,
],
units="kg",
scaling_factors=[1, 1, 1, -1],
desc='Loaded fuel before taxi-out for mission "%s"' % mission_name,
)
return block_fuel_computation
def setUp(self):
self.nn = 5
self.p = om.Problem()
ivc = om.IndepVarComp()
ivc.add_output(name='a', shape=(self.nn, 3))
ivc.add_output(name='b', shape=(self.nn, 3))
ivc.add_output(name='c', shape=(self.nn, 3))
self.p.model.add_subsystem(name='ivc',
subsys=ivc,
promotes_outputs=['a', 'b','c'])
adder=self.p.model.add_subsystem(name='add_subtract_comp',
subsys=om.AddSubtractComp())
adder.add_equation('adder_output',['input_a','input_b','input_c'],vec_size=self.nn,length=3,scaling_factors=[1,-1])
self.p.model.connect('a', 'add_subtract_comp.input_a')
self.p.model.connect('b', 'add_subtract_comp.input_b')
self.p.model.connect('c', 'add_subtract_comp.input_c')
def test_for_bad_input_set(self):
self.nn = 5
self.p = om.Problem()
ivc = om.IndepVarComp()
ivc.add_output(name='a', shape=(self.nn, 3))
ivc.add_output(name='b', shape=(self.nn, 3))
ivc.add_output(name='c', shape=(self.nn, 3))
self.p.model.add_subsystem(name='ivc',
subsys=ivc,
promotes_outputs=['a', 'b', 'c'])
adder = self.p.model.add_subsystem(name='add_subtract_comp',
subsys=om.AddSubtractComp())
with self.assertRaises(ValueError) as err:
adder.add_equation('adder_output', [
'input_a',
],
vec_size=self.nn,
length=3,
scaling_factors=[1, -1])
expected_msg = "'add_subtract_comp' <class AddSubtractComp>: must specify more than one input " \
"name for an equation, but only one given"
self.assertEqual(str(err.exception), expected_msg)
with self.assertRaises(ValueError) as err:
adder.add_equation('adder_output',
'input_a',
vec_size=self.nn,
length=3,
scaling_factors=[1, -1])
expected_msg = "'add_subtract_comp' <class AddSubtractComp>: must specify more than one input " \
"name for an equation, but only one given"
self.assertEqual(str(err.exception), expected_msg)
def test(self):
"""
A simple example to compute the resultant force on an aircraft and demonstrate the AddSubtract component
"""
n = 3
p = om.Problem()
model = p.model
# Construct an adder/subtracter here. create a relationship through the add_equation method
adder = om.AddSubtractComp()
adder.add_equation('total_force',
input_names=['thrust', 'drag', 'lift', 'weight'],
vec_size=n,
length=2,
scaling_factors=[1, -1, 1, -1],
units='kN')
# Note the scaling factors. we assume all forces are positive sign upstream
# The vector represents forces at 3 time points (rows) in 2 dimensional plane (cols)
p.model.add_subsystem(
name='totalforcecomp',
subsys=adder,
promotes_inputs=['thrust', 'drag', 'lift', 'weight'])
p.setup()
# Set thrust to exceed drag, weight to equal lift for this scenario
p['thrust'][:, 0] = [500, 600, 700]
p['drag'][:, 0] = [400, 400, 400]
p['weight'][:, 1] = [1000, 1001, 1002]
p['lift'][:, 1] = [1000, 1000, 1000]
p.run_model()
# Verify the results
expected_i = np.array([[100, 200, 300], [0, -1, -2]]).T
assert_near_equal(p.get_val('totalforcecomp.total_force', units='kN'),
expected_i)
def setup(self):
# Propulsion should be done before airframe, because it drives pylon mass.
self.add_subsystem(
"propulsion_weight",
RegisterSubmodel.get_submodel(SERVICE_PROPULSION_MASS),
promotes=["*"],
)
self.add_subsystem(
"airframe_weight",
RegisterSubmodel.get_submodel(SERVICE_AIRFRAME_MASS),
promotes=["*"])
self.add_subsystem("systems_weight",
RegisterSubmodel.get_submodel(SERVICE_SYSTEMS_MASS),
promotes=["*"])
self.add_subsystem(
"furniture_weight",
RegisterSubmodel.get_submodel(SERVICE_FURNITURE_MASS),
promotes=["*"],
)
self.add_subsystem("crew_weight",
RegisterSubmodel.get_submodel(SERVICE_CREW_MASS),
promotes=["*"])
weight_sum = om.AddSubtractComp()
weight_sum.add_equation(
"data:weight:aircraft:OWE",
[
"data:weight:airframe:mass",
"data:weight:propulsion:mass",
"data:weight:systems:mass",
"data:weight:furniture:mass",
"data:weight:crew:mass",
],
units="kg",
desc="Mass of crew",
)
self.add_subsystem("OWE_sum", weight_sum, promotes=["*"])
def setUp(self):
self.nn = 5
self.p = om.Problem()
ivc = om.IndepVarComp()
ivc.add_output(name='a', shape=(self.nn, 3), units='ft')
ivc.add_output(name='b', shape=(self.nn, 3), units='m')
ivc.add_output(name='c', shape=(self.nn, 3), units='m')
self.p.model.add_subsystem(name='ivc',
subsys=ivc,
promotes_outputs=['a', 'b', 'c'])
# verify proper handling of constructor args
adder = om.AddSubtractComp(
output_name='adder_output',
input_names=['input_a', 'input_b', 'input_c'],
vec_size=self.nn,
length=3,
scaling_factors=[2., 1., -1],
units='ft')
self.p.model.add_subsystem(name='add_subtract_comp', subsys=adder)
self.p.model.connect('a', 'add_subtract_comp.input_a')
self.p.model.connect('b', 'add_subtract_comp.input_b')
self.p.model.connect('c', 'add_subtract_comp.input_c')
self.p.setup()
self.p['a'] = np.random.rand(self.nn, 3)
self.p['b'] = np.random.rand(self.nn, 3)
self.p['c'] = np.random.rand(self.nn, 3)
self.p.run_model()
def setup(self):
# Airframe
self.add_subsystem("wing_weight", ComputeWingWeight(), promotes=["*"])
self.add_subsystem("fuselage_weight",
ComputeFuselageWeight(),
promotes=["*"])
self.add_subsystem("empennage_weight",
ComputeTailWeight(),
promotes=["*"])
self.add_subsystem("flight_controls_weight",
ComputeFlightControlsWeight(),
promotes=["*"])
self.add_subsystem("landing_gear_weight",
ComputeLandingGearWeight(),
promotes=["*"])
self.add_subsystem(
"engine_weight",
ComputeEngineWeight(propulsion_id=self.options["propulsion_id"]),
promotes=["*"])
self.add_subsystem("fuel_lines_weight",
ComputeFuelLinesWeight(),
promotes=["*"])
self.add_subsystem("navigation_systems_weight",
ComputeNavigationSystemsWeight(),
promotes=["*"])
self.add_subsystem("power_systems_weight",
ComputePowerSystemsWeight(),
promotes=["*"])
self.add_subsystem("life_support_systems_weight",
ComputeLifeSupportSystemsWeight(),
promotes=["*"])
self.add_subsystem("passenger_seats_weight",
ComputePassengerSeatsWeight(),
promotes=["*"])
# Make additions
airframe_sum = om.AddSubtractComp()
airframe_sum.add_equation(
"data:weight:airframe:mass",
[
"data:weight:airframe:wing:mass",
"data:weight:airframe:fuselage:mass",
"data:weight:airframe:horizontal_tail:mass",
"data:weight:airframe:vertical_tail:mass",
"data:weight:airframe:flight_controls:mass",
"data:weight:airframe:landing_gear:main:mass",
"data:weight:airframe:landing_gear:front:mass",
],
units="kg",
desc="Mass of airframe",
)
self.add_subsystem(
"airframe_weight_sum",
airframe_sum,
promotes=["*"],
)
propulsion_sum = om.AddSubtractComp()
propulsion_sum.add_equation(
"data:weight:propulsion:mass",
[
"data:weight:propulsion:engine:mass",
"data:weight:propulsion:fuel_lines:mass",
],
units="kg",
desc="Mass of the propulsion system",
)
self.add_subsystem(
"propulsion_weight_sum",
propulsion_sum,
promotes=["*"],
)
systems_sum = om.AddSubtractComp()
systems_sum.add_equation(
"data:weight:systems:mass",
[
"data:weight:systems:power:electric_systems:mass",
"data:weight:systems:power:hydraulic_systems:mass",
"data:weight:systems:life_support:air_conditioning:mass",
"data:weight:systems:navigation:mass",
],
units="kg",
desc="Mass of aircraft systems",
)
self.add_subsystem(
"systems_weight_sum",
systems_sum,
promotes=["*"],
)
furniture_sum = om.AddSubtractComp()
furniture_sum.add_equation(
"data:weight:furniture:mass",
[
"data:weight:furniture:passenger_seats:mass",
"data:weight:furniture:passenger_seats:mass",
],
scaling_factors=[0.5, 0.5],
units="kg",
desc="Mass of aircraft furniture",
)
self.add_subsystem(
"furniture_weight_sum",
furniture_sum,
promotes=["*"],
)
owe_sum = om.AddSubtractComp()
owe_sum.add_equation(
"data:weight:aircraft:OWE",
[
"data:weight:airframe:mass",
"data:weight:propulsion:mass",
"data:weight:systems:mass",
"data:weight:furniture:mass",
],
units="kg",
desc="Mass of aircraft",
)
self.add_subsystem(
"OWE_sum",
owe_sum,
promotes=["*"],
)