From a80f9527726d24b434a1f109fdebd39c46ee1a98 Mon Sep 17 00:00:00 2001 From: jkirk5 Date: Wed, 10 Apr 2024 13:03:22 -0400 Subject: [PATCH 01/17] initial simple battery model --- aviary/mission/flight_phase_builder.py | 5 + aviary/subsystems/energy/__init__.py | 0 aviary/subsystems/energy/battery_builder.py | 53 ++++++++ aviary/subsystems/energy/battery_sizing.py | 64 +++++++++ aviary/subsystems/energy/test/__init__.py | 0 aviary/subsystems/energy/test/test_battery.py | 75 +++++++++++ .../test_bench_mission_battery.py | 106 +++++++++++++++ aviary/variable_info/variable_meta_data.py | 127 ++++++++++++++++++ aviary/variable_info/variables.py | 13 ++ 9 files changed, 443 insertions(+) create mode 100644 aviary/subsystems/energy/__init__.py create mode 100644 aviary/subsystems/energy/battery_builder.py create mode 100644 aviary/subsystems/energy/battery_sizing.py create mode 100644 aviary/subsystems/energy/test/__init__.py create mode 100644 aviary/subsystems/energy/test/test_battery.py create mode 100644 aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py diff --git a/aviary/mission/flight_phase_builder.py b/aviary/mission/flight_phase_builder.py index 64c826f4b..9de17dc6a 100644 --- a/aviary/mission/flight_phase_builder.py +++ b/aviary/mission/flight_phase_builder.py @@ -220,6 +220,11 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO output_name=Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL, units='lbm/h' ) + phase.add_timeseries_output( + Dynamic.Mission.ELECTRIC_POWER_TOTAL, + output_name=Dynamic.Mission.ELECTRIC_POWER_TOTAL, units='kW' + ) + phase.add_timeseries_output( Dynamic.Mission.ALTITUDE_RATE, output_name=Dynamic.Mission.ALTITUDE_RATE, units='ft/s' diff --git a/aviary/subsystems/energy/__init__.py b/aviary/subsystems/energy/__init__.py new file mode 100644 index 000000000..e69de29bb diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py new file mode 100644 index 000000000..c7e4332b5 --- /dev/null +++ b/aviary/subsystems/energy/battery_builder.py @@ -0,0 +1,53 @@ +import numpy as np +import openmdao.api as om + +from aviary.subsystems.subsystem_builder_base import SubsystemBuilderBase +from aviary.subsystems.energy.battery_sizing import SizeBattery +from aviary.variable_info.variables import Aircraft, Dynamic + + +class BatteryBuilder(SubsystemBuilderBase): + def build_pre_mission(self, aviary_options=None): + return SizeBattery(aviary_options=aviary_options) + + def get_mass_names(self): + return [Aircraft.Battery.MASS] + + def build_mission(self, num_nodes=1, aviary_inputs=None) -> om.Group: + battery_group = om.Group() + soc = om.ExecComp('state_of_charge = (energy_capacity - (mission_energy/efficiency)) / energy_capacity', + state_of_charge={'val': np.zeros( + num_nodes), 'units': 'unitless'}, + energy_capacity={'val': 0.0, 'units': 'kJ'}, + mission_energy={'val': np.zeros(num_nodes), 'units': 'kJ'}, + efficiency={'val': 0.0, 'units': 'unitless'}) + + battery_group.add_subsystem('state_of_charge', + subsys=soc, + promotes_inputs=[('energy_capacity', Aircraft.Battery.ENERGY_CAPACITY), + ('mission_energy', + Dynamic.Mission.MISSION_ENERGY), + ('efficiency', Aircraft.Battery.EFFICIENCY)], + promotes_outputs=[('state_of_charge', Dynamic.Mission.BATTERY_STATE_OF_CHARGE)]) + + return battery_group + + def get_states(self): + state_dict = {Dynamic.Mission.MISSION_ENERGY: {'fix_initial': True, + 'fix_final': False, + 'lower': 0.0, + 'ref': 1e4, + 'defect_ref': 1e6, + 'units': 'kJ', + 'rate_source': Dynamic.Mission.ELECTRIC_POWER_TOTAL, + 'targets': Dynamic.Mission.MISSION_ENERGY, + 'input_initial': 0.0}} + + return state_dict + + def get_constraints(self): + # discharge_limit = aviary_options.get_val(Aircraft.Battery.DISCHARGE_LIMIT) + constraint_dict = {f'path_{Dynamic.Mission.BATTERY_STATE_OF_CHARGE} = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE} - {Aircraft.Battery.DISCHARGE_LIMIT}': + {'type': 'path', + 'lower': 0.0}} + return constraint_dict diff --git a/aviary/subsystems/energy/battery_sizing.py b/aviary/subsystems/energy/battery_sizing.py new file mode 100644 index 000000000..80df05d6b --- /dev/null +++ b/aviary/subsystems/energy/battery_sizing.py @@ -0,0 +1,64 @@ +import openmdao.api as om + +from openmdao.utils.units import convert_units + +from aviary.utils.aviary_values import AviaryValues +from aviary.variable_info.functions import add_aviary_input, add_aviary_output +from aviary.variable_info.variables import Aircraft, Dynamic + + +class SizeBattery(om.ExplicitComponent): + ''' + Calculates battery mass from specific energy and additional mass + ''' + + def initialize(self): + self.options.declare( + 'aviary_options', types=AviaryValues, + desc='collection of Aircraft/Mission specific options') + + def setup(self): + add_aviary_input(self, Aircraft.Battery.PACK_MASS, val=0.0, units='lbm', + desc='mass of energy-storing components of battery') + add_aviary_input(self, Aircraft.Battery.ADDITIONAL_MASS, val=0.0, units='lbm', + desc='mass of non energy-storing components of battery') + add_aviary_input(self, Aircraft.Battery.PACK_ENERGY_DENSITY, val=0.0, units='kW*h/kg', + desc='energy density of battery pack') + + add_aviary_output(self, Aircraft.Battery.MASS, val=0.0, + units='lbm', desc='total battery mass') + add_aviary_output(self, Aircraft.Battery.ENERGY_CAPACITY, val=0.0, + units='kJ', desc='total battery energy storage') + + def compute(self, inputs, outputs): + energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] * 3600 + addtl_mass = inputs[Aircraft.Battery.ADDITIONAL_MASS] + pack_mass_lbm = inputs[Aircraft.Battery.PACK_MASS] + pack_mass_kg = convert_units(pack_mass_lbm, 'lbm', 'kg') + + total_mass = pack_mass_lbm + addtl_mass + total_energy = pack_mass_kg * energy_density_kj_kg + + outputs[Aircraft.Battery.MASS] = total_mass + outputs[Aircraft.Battery.ENERGY_CAPACITY] = total_energy + + def setup_partials(self): + self.declare_partials(Aircraft.Battery.ENERGY_CAPACITY, + Aircraft.Battery.PACK_ENERGY_DENSITY) + self.declare_partials(Aircraft.Battery.ENERGY_CAPACITY, + Aircraft.Battery.PACK_MASS) + + self.declare_partials(Aircraft.Battery.MASS, + Aircraft.Battery.ADDITIONAL_MASS, val=1.0) + self.declare_partials(Aircraft.Battery.MASS, + Aircraft.Battery.PACK_MASS, val=1.0) + + def compute_partials(self, inputs, J): + energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] * 3600 + # addtl_mass = inputs[Aircraft.Battery.ADDITIONAL_MASS] + pack_mass_kg = convert_units(inputs[Aircraft.Battery.PACK_MASS], 'lbm', 'kg') + + J[Aircraft.Battery.ENERGY_CAPACITY, + Aircraft.Battery.PACK_ENERGY_DENSITY] = pack_mass_kg * 3600 + J[Aircraft.Battery.ENERGY_CAPACITY, + Aircraft.Battery.PACK_MASS] = energy_density_kj_kg * convert_units(1, 'lbm', 'kg') diff --git a/aviary/subsystems/energy/test/__init__.py b/aviary/subsystems/energy/test/__init__.py new file mode 100644 index 000000000..e69de29bb diff --git a/aviary/subsystems/energy/test/test_battery.py b/aviary/subsystems/energy/test/test_battery.py new file mode 100644 index 000000000..18e9a76e3 --- /dev/null +++ b/aviary/subsystems/energy/test/test_battery.py @@ -0,0 +1,75 @@ +import unittest + +import numpy as np +import openmdao.api as om + +from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal + +from aviary.subsystems.energy.battery_builder import BatteryBuilder +from aviary.utils.aviary_values import AviaryValues +from aviary.variable_info.variables import Aircraft, Dynamic + + +class BatteryTest(unittest.TestCase): + def setUp(self): + self.prob = prob = om.Problem() + + self.options = AviaryValues() + + self.battery = BatteryBuilder() + + def test_battery_premission(self): + prob = self.prob + prob.model.add_subsystem('battery_premission', + self.battery.build_pre_mission(self.options), + promotes=['*']) + + prob.setup(force_alloc_complex=True) + + prob.set_val(Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') + prob.set_val(Aircraft.Battery.PACK_MASS, 1200, units='lbm') + prob.set_val(Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') + + prob.run_model() + + mass_expected = 1_315 + energy_expected = 1_077_735_471.12 + + mass = prob.get_val(Aircraft.Battery.MASS, 'lbm') + energy = prob.get_val(Aircraft.Battery.ENERGY_CAPACITY, 'kJ') + + assert_near_equal(mass, mass_expected, tolerance=1e-10) + assert_near_equal(energy, energy_expected, tolerance=1e-10) + + partial_data = prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=1e-10, rtol=1e-10) + + def test_battery_mission(self): + prob = self.prob + prob.model.add_subsystem('battery_mission', + subsys=self.battery.build_mission(num_nodes=4), + promotes=['*']) + + efficiency = 0.95 + prob.model.set_input_defaults( + Aircraft.Battery.ENERGY_CAPACITY, 10_000, units='kJ') + prob.model.set_input_defaults( + Aircraft.Battery.EFFICIENCY, efficiency, units='unitless') + prob.model.set_input_defaults(Dynamic.Mission.MISSION_ENERGY, [ + 0, 2_000, 5_000, 9_500], units='kJ') + + prob.setup(force_alloc_complex=True) + + prob.run_model() + + soc_expected = np.array([1., 0.7894736842105263, 0.4736842105263159, 0.]) + soc = prob.get_val(Dynamic.Mission.BATTERY_STATE_OF_CHARGE, 'unitless') + + assert_near_equal(soc, soc_expected, tolerance=1e-10) + + partial_data = prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=1e-10, rtol=1e-10) + + +if __name__ == "__main__": + unittest.main() diff --git a/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py b/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py new file mode 100644 index 000000000..76b4cac26 --- /dev/null +++ b/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py @@ -0,0 +1,106 @@ +import unittest + +import numpy as np +import openmdao.api as om + +from numpy.testing import assert_almost_equal +from openmdao.utils.testing_utils import use_tempdirs + +from aviary.interface.methods_for_level2 import AviaryProblem +from aviary.variable_info.enums import Verbosity +from aviary.variable_info.variables import Aircraft, Dynamic +from aviary.subsystems.subsystem_builder_base import SubsystemBuilderBase +from aviary.subsystems.energy.battery_builder import BatteryBuilder + + +@use_tempdirs +class TestSubsystemsMission(unittest.TestCase): + def setUp(self): + self.phase_info = { + 'cruise': { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + 'external_subsystems': [DummyPowerComp('power_generator'), BatteryBuilder('battery')], + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "num_segments": 2, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.72, "unitless"), + "final_mach": (0.72, "unitless"), + "mach_bounds": ((0.7, 0.74), "unitless"), + "initial_altitude": (35000.0, "ft"), + "final_altitude": (35000.0, "ft"), + "altitude_bounds": ((23000.0, 38000.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((10., 30.), "min"), + }, + "initial_guesses": {"times": ([0, 30], "min")}, + }} + + def test_HE_mission(self): + prob = AviaryProblem() + + prob.load_inputs( + "models/test_aircraft/aircraft_for_bench_GwFm.csv", self.phase_info) + + # Preprocess inputs + prob.check_and_preprocess_inputs() + + prob.add_pre_mission_systems() + + prob.add_phases() + + prob.add_post_mission_systems() + + # Link phases and variables + prob.link_phases() + + prob.add_driver("SLSQP", max_iter=0, verbosity=Verbosity.QUIET) + + prob.add_design_variables() + + prob.add_objective('fuel_burned') + + prob.setup() + + prob.phase_info['cruise']['initial_guesses'][f'states:{Mission.Dummy.VARIABLE}'] = ([ + 10., 100.], 'm') + prob.set_initial_guesses() + + # add an assert to see if the initial guesses are correct for Mission.Dummy.VARIABLE + assert_almost_equal(prob[f'traj.phases.cruise.states:{Mission.Dummy.VARIABLE}'], [[10.], + [25.97729616], + [48.02270384], + [55.], + [70.97729616], + [93.02270384], + [100.]]) + + prob.run_aviary_problem() + + # add an assert to see if MoreMission.Dummy.TIMESERIES_VAR was correctly added to the dymos problem + assert_almost_equal(prob[f'traj.phases.cruise.timeseries.{MoreMission.Dummy.TIMESERIES_VAR}'], np.array( + [[0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5]]).T) + + +class DummyPowerComp(SubsystemBuilderBase): + def build_mission(self, num_nodes=1, aviary_inputs=None): + mission_group = om.Group() + comp = om.IndepVarComp('power', val=np.ones(num_nodes)*1000, units='kW') + mission_group.add_subsystem('dummy_comp', subsys=comp, promotes=[ + ('power', Dynamic.Mission.ELECTRIC_POWER_TOTAL)]) + + return mission_group + + +if __name__ == "__main__": + # unittest.main() + test = TestSubsystemsMission() + test.setUp() + test.test_HE_mission() diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index b6522a9ef..99fcf3426 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -189,6 +189,122 @@ default_value=1.0, ) +# ____ _ _ +# | _ \ | | | | +# | |_) | __ _ | |_ | |_ ___ _ __ _ _ +# | _ < / _` | | __| | __| / _ \ | '__| | | | | +# | |_) | | (_| | | |_ | |_ | __/ | | | |_| | +# |____/ \__,_| \__| \__| \___| |_| \__, | +# __/ | +# |___/ +# ================================================= +add_meta_data( + Aircraft.Battery.ADDITIONAL_MASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": 'aircraft.inputs.L0_battery.weight_offset' + }, + units='lbm', + desc='mass of non energy-storing parts of the battery', + default_value=0.0, +) + +add_meta_data( + Aircraft.Battery.DISCHARGE_LIMIT, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": 'aircraft.inputs.L0_battery.depth_of_discharge' + }, + units='unitless', + desc='default constraint on how far the battery can discharge, as a percentage of ' + 'total energy capacity' +) + +add_meta_data( + Aircraft.Battery.EFFICIENCY, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='unitless', + desc="battery pack efficiency" +) + +add_meta_data( + Aircraft.Battery.ENERGY_CAPACITY, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='kJ', + desc="total energy the battery can store" +) + +add_meta_data( + Aircraft.Battery.MASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": 'aircraft.inputs.L0_battery.weight' + }, + units='lbm', + desc='total mass of the battery', + default_value=0.0, +) + +add_meta_data( + Aircraft.Battery.PACK_ENERGY_DENSITY, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": 'aircraft.inputs.L0_battery.energy_density' + }, + units='kW*h/kg', + desc='specific energy density of the battery pack', + default_value=1.0, +) + + +add_meta_data( + Aircraft.Battery.PACK_MASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='lbm', + desc='mass of the energy-storing components of the battery', + default_value=0.0, +) + +add_meta_data( + Aircraft.Battery.PACK_VOLUMETRIC_DENSITY, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='kW*h/kg', + desc='volumetric density of the battery pack', + default_value=0, +) + +add_meta_data( + Aircraft.Battery.VOLUME, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='ft*3', + desc='total volume of the battery pack', + default_value=0.0, +) + # ____ _ _ _ __ __ _ ____ _ # | _ \ | | | | | | \ \ / / (_) | _ \ | | @@ -5931,6 +6047,17 @@ '(at hypothetical maximum thrust condition)' ) +add_meta_data( + Dynamic.Mission.BATTERY_STATE_OF_CHARGE, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='unitless', + desc="battery's current state of charge" +) + add_meta_data( Dynamic.Mission.DENSITY, meta_data=_MetaData, diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 0bd51a7f7..d0e24a75b 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -25,6 +25,17 @@ class Avionics: MASS = 'aircraft:avionics:mass' MASS_SCALER = 'aircraft:avionics:mass_scaler' + class Battery: + ADDITIONAL_MASS = 'aircraft:battery:additional_mass' + DISCHARGE_LIMIT = 'aircraft:battery:discharge_limit' + EFFICIENCY = 'aircraft:battery:efficiency' + ENERGY_CAPACITY = 'aircraft:battery:energy_capacity' + MASS = 'aircraft:battery:mass' + PACK_ENERGY_DENSITY = 'aircraft:battery:pack_energy_density' + PACK_MASS = 'aircraft:battery:pack_mass' + PACK_VOLUMETRIC_DENSITY = 'aircraft:battery:pack_volumetric_density' + VOLUME = 'aircraft:battery:volume' + class BWB: CABIN_AREA = 'aircraft:blended_wing_body_design:cabin_area' NUM_BAYS = 'aircraft:blended_wing_body_design:num_bays' @@ -583,6 +594,7 @@ class Mission: ALTITUDE = 'altitude' ALTITUDE_RATE = 'altitude_rate' ALTITUDE_RATE_MAX = 'altitude_rate_max' + BATTERY_STATE_OF_CHARGE = 'battery_state_of_charge' DENSITY = 'density' DISTANCE = 'distance' DISTANCE_RATE = 'distance_rate' @@ -604,6 +616,7 @@ class Mission: MACH_RATE = 'mach_rate' MASS = 'mass' MASS_RATE = 'mass_rate' + MISSION_ENERGY = 'mission_energy' NOX_RATE = 'nox_rate' NOX_RATE_TOTAL = 'nox_rate_total' PERCENT_ROTOR_RPM_CORRECTED = 'percent_rotor_rpm_corrected' From 5551247126819b7bc3aef07572de9da3c3d59dd6 Mon Sep 17 00:00:00 2001 From: jkirk5 Date: Mon, 15 Apr 2024 11:32:51 -0400 Subject: [PATCH 02/17] test changes to promotions and constraint setup --- aviary/mission/flops_based/ode/mission_ODE.py | 7 ++- aviary/subsystems/energy/battery_builder.py | 8 ++- aviary/subsystems/propulsion/engine_model.py | 6 +- .../propulsion/propulsion_premission.py | 12 ++-- .../test_bench_mission_battery.py | 55 ++++++++++--------- 5 files changed, 49 insertions(+), 39 deletions(-) diff --git a/aviary/mission/flops_based/ode/mission_ODE.py b/aviary/mission/flops_based/ode/mission_ODE.py index 87756a921..acbea354a 100644 --- a/aviary/mission/flops_based/ode/mission_ODE.py +++ b/aviary/mission/flops_based/ode/mission_ODE.py @@ -135,7 +135,7 @@ def setup(self): # Create a lightly modified version of an OM group to add external subsystems # to the ODE with a special configure() method that promotes # all aircraft:* and mission:* variables to the ODE. - external_subsystem_group = ExternalSubsystemGroup() + external_subsystem_group = om.Group() add_subsystem_group = False for subsystem in self.options['external_subsystems']: @@ -143,7 +143,10 @@ def setup(self): num_nodes=nn, aviary_inputs=aviary_options) if subsystem_mission is not None: add_subsystem_group = True - external_subsystem_group.add_subsystem(subsystem.name, subsystem_mission) + external_subsystem_group.add_subsystem(subsystem.name, + subsystem_mission, + promotes_inputs=['*'], + promotes_outputs=['*']) # Only add the external subsystem group if it has at least one subsystem. # Without this logic there'd be an empty OM group added to the ODE. diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index c7e4332b5..1b89fa25d 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -40,14 +40,16 @@ def get_states(self): 'defect_ref': 1e6, 'units': 'kJ', 'rate_source': Dynamic.Mission.ELECTRIC_POWER_TOTAL, - 'targets': Dynamic.Mission.MISSION_ENERGY, 'input_initial': 0.0}} return state_dict def get_constraints(self): # discharge_limit = aviary_options.get_val(Aircraft.Battery.DISCHARGE_LIMIT) - constraint_dict = {f'path_{Dynamic.Mission.BATTERY_STATE_OF_CHARGE} = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE} - {Aircraft.Battery.DISCHARGE_LIMIT}': + # constraint_dict = {f'path_{Dynamic.Mission.BATTERY_STATE_OF_CHARGE} = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE} - {Aircraft.Battery.DISCHARGE_LIMIT}': + # {'type': 'path', + # 'lower': 0.0}} + constraint_dict = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE: {'type': 'path', - 'lower': 0.0}} + 'lower': 0.2}} return constraint_dict diff --git a/aviary/subsystems/propulsion/engine_model.py b/aviary/subsystems/propulsion/engine_model.py index 28b2a5c82..64b7d9182 100644 --- a/aviary/subsystems/propulsion/engine_model.py +++ b/aviary/subsystems/propulsion/engine_model.py @@ -38,9 +38,10 @@ class EngineModel(SubsystemBuilderBase): default_name = 'engine_model' def __init__( - self, name: str = None, options: AviaryValues = None, meta_data: dict = None, + self, name: str = None, options: AviaryValues = AviaryValues(), meta_data: dict = None, ): super().__init__(name, meta_data=meta_data) + self.options = options.deepcopy() # Hybrid throttle is currently the only optional independent variable, requiring @@ -118,9 +119,6 @@ def _preprocess_inputs(self): """ options = self.options - if options is None: - return # options are allowed to be empty - if not isinstance(options, AviaryValues): raise TypeError('EngineModel options must be an AviaryValues object') diff --git a/aviary/subsystems/propulsion/propulsion_premission.py b/aviary/subsystems/propulsion/propulsion_premission.py index 82867d151..fd95ab41e 100644 --- a/aviary/subsystems/propulsion/propulsion_premission.py +++ b/aviary/subsystems/propulsion/propulsion_premission.py @@ -25,11 +25,13 @@ def setup(self): engine_models = options.get_val('engine_models') for engine in engine_models: - self.add_subsystem(engine.name, - subsys=engine.build_pre_mission(options), - promotes_inputs=['*'], - promotes_outputs=['*'], - ) + pre_mission_model = engine.build_pre_mission(options) + if pre_mission_model is not None: + self.add_subsystem(engine.name, + subsys=pre_mission_model, + promotes_inputs=['*'], + promotes_outputs=['*'], + ) self.add_subsystem( 'propulsion_sum', diff --git a/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py b/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py index 76b4cac26..322aee842 100644 --- a/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py +++ b/aviary/validation_cases/benchmark_tests/test_bench_mission_battery.py @@ -9,8 +9,9 @@ from aviary.interface.methods_for_level2 import AviaryProblem from aviary.variable_info.enums import Verbosity from aviary.variable_info.variables import Aircraft, Dynamic -from aviary.subsystems.subsystem_builder_base import SubsystemBuilderBase +from aviary.subsystems.propulsion.engine_model import EngineModel from aviary.subsystems.energy.battery_builder import BatteryBuilder +from aviary.utils.preprocessors import preprocess_propulsion @use_tempdirs @@ -19,7 +20,7 @@ def setUp(self): self.phase_info = { 'cruise': { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - 'external_subsystems': [DummyPowerComp('power_generator'), BatteryBuilder('battery')], + 'external_subsystems': [BatteryBuilder('battery')], "user_options": { "optimize_mach": False, "optimize_altitude": False, @@ -47,7 +48,16 @@ def test_HE_mission(self): prob = AviaryProblem() prob.load_inputs( - "models/test_aircraft/aircraft_for_bench_GwFm.csv", self.phase_info) + "models/test_aircraft/aircraft_for_bench_GwFm.csv", + self.phase_info) + + aviary_inputs = prob.aviary_inputs + engine_models = aviary_inputs.get_val('engine_models') + engine_models.append(DummyPowerComp(options=aviary_inputs)) + aviary_inputs.set_val('engine_models', engine_models) + preprocess_propulsion(aviary_inputs, engine_models) + + prob.aviary_inputs.set_val(Aircraft.Battery.DISCHARGE_LIMIT, 0.2) # Preprocess inputs prob.check_and_preprocess_inputs() @@ -69,34 +79,29 @@ def test_HE_mission(self): prob.setup() - prob.phase_info['cruise']['initial_guesses'][f'states:{Mission.Dummy.VARIABLE}'] = ([ - 10., 100.], 'm') prob.set_initial_guesses() - # add an assert to see if the initial guesses are correct for Mission.Dummy.VARIABLE - assert_almost_equal(prob[f'traj.phases.cruise.states:{Mission.Dummy.VARIABLE}'], [[10.], - [25.97729616], - [48.02270384], - [55.], - [70.97729616], - [93.02270384], - [100.]]) - prob.run_aviary_problem() - # add an assert to see if MoreMission.Dummy.TIMESERIES_VAR was correctly added to the dymos problem - assert_almost_equal(prob[f'traj.phases.cruise.timeseries.{MoreMission.Dummy.TIMESERIES_VAR}'], np.array( - [[0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5]]).T) - -class DummyPowerComp(SubsystemBuilderBase): +class DummyPowerComp(EngineModel): + # A dummy component that adds electric power demand to the otherwise all fuel-burning aircraft def build_mission(self, num_nodes=1, aviary_inputs=None): - mission_group = om.Group() - comp = om.IndepVarComp('power', val=np.ones(num_nodes)*1000, units='kW') - mission_group.add_subsystem('dummy_comp', subsys=comp, promotes=[ - ('power', Dynamic.Mission.ELECTRIC_POWER_TOTAL)]) - - return mission_group + comp = om.ExplicitComponent() + comp.add_input(Dynamic.Mission.ALTITUDE, val=np.zeros(num_nodes), units='ft') + comp.add_input(Dynamic.Mission.MACH, val=np.zeros(num_nodes), units='unitless') + comp.add_input(Dynamic.Mission.THROTTLE, + val=np.zeros(num_nodes), units='unitless') + + comp.add_output(Dynamic.Mission.ELECTRIC_POWER, + val=np.ones(num_nodes)*10, units='kW') + comp.add_output(Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, + val=np.zeros(num_nodes), units='lbm/h') + comp.add_output(Dynamic.Mission.NOX_RATE, val=np.zeros(num_nodes), units='lbm/h') + comp.add_output(Dynamic.Mission.THRUST, val=np.zeros(num_nodes), units='lbf') + comp.add_output(Dynamic.Mission.THRUST_MAX, val=np.zeros(num_nodes), units='lbf') + + return comp if __name__ == "__main__": From 928993d25035df49a661ee16168e687d97efe923 Mon Sep 17 00:00:00 2001 From: John Jasa Date: Wed, 29 May 2024 16:18:14 -0400 Subject: [PATCH 03/17] Beginning battery dymos integration --- aviary/subsystems/energy/battery_builder.py | 6 ++-- aviary/subsystems/energy/battery_sizing.py | 2 +- aviary/subsystems/energy/test/test_battery.py | 33 +++++++++++-------- aviary/subsystems/test/subsystem_tester.py | 8 ----- 4 files changed, 23 insertions(+), 26 deletions(-) diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 1b89fa25d..70244730f 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -7,13 +7,13 @@ class BatteryBuilder(SubsystemBuilderBase): - def build_pre_mission(self, aviary_options=None): - return SizeBattery(aviary_options=aviary_options) + def build_pre_mission(self, aviary_inputs=None): + return SizeBattery(aviary_inputs=aviary_inputs) def get_mass_names(self): return [Aircraft.Battery.MASS] - def build_mission(self, num_nodes=1, aviary_inputs=None) -> om.Group: + def build_mission(self, num_nodes, aviary_inputs=None) -> om.Group: battery_group = om.Group() soc = om.ExecComp('state_of_charge = (energy_capacity - (mission_energy/efficiency)) / energy_capacity', state_of_charge={'val': np.zeros( diff --git a/aviary/subsystems/energy/battery_sizing.py b/aviary/subsystems/energy/battery_sizing.py index 80df05d6b..c16d6d72e 100644 --- a/aviary/subsystems/energy/battery_sizing.py +++ b/aviary/subsystems/energy/battery_sizing.py @@ -14,7 +14,7 @@ class SizeBattery(om.ExplicitComponent): def initialize(self): self.options.declare( - 'aviary_options', types=AviaryValues, + 'aviary_inputs', types=AviaryValues, desc='collection of Aircraft/Mission specific options') def setup(self): diff --git a/aviary/subsystems/energy/test/test_battery.py b/aviary/subsystems/energy/test/test_battery.py index 18e9a76e3..247cfc4a2 100644 --- a/aviary/subsystems/energy/test/test_battery.py +++ b/aviary/subsystems/energy/test/test_battery.py @@ -6,15 +6,14 @@ from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal from aviary.subsystems.energy.battery_builder import BatteryBuilder -from aviary.utils.aviary_values import AviaryValues -from aviary.variable_info.variables import Aircraft, Dynamic +import aviary.api as av -class BatteryTest(unittest.TestCase): +class TestBatteryDerivs(unittest.TestCase): def setUp(self): self.prob = prob = om.Problem() - self.options = AviaryValues() + self.options = av.AviaryValues() self.battery = BatteryBuilder() @@ -26,17 +25,17 @@ def test_battery_premission(self): prob.setup(force_alloc_complex=True) - prob.set_val(Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') - prob.set_val(Aircraft.Battery.PACK_MASS, 1200, units='lbm') - prob.set_val(Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') + prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') + prob.set_val(av.Aircraft.Battery.PACK_MASS, 1200, units='lbm') + prob.set_val(av.Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') prob.run_model() mass_expected = 1_315 energy_expected = 1_077_735_471.12 - mass = prob.get_val(Aircraft.Battery.MASS, 'lbm') - energy = prob.get_val(Aircraft.Battery.ENERGY_CAPACITY, 'kJ') + mass = prob.get_val(av.Aircraft.Battery.MASS, 'lbm') + energy = prob.get_val(av.Aircraft.Battery.ENERGY_CAPACITY, 'kJ') assert_near_equal(mass, mass_expected, tolerance=1e-10) assert_near_equal(energy, energy_expected, tolerance=1e-10) @@ -52,10 +51,10 @@ def test_battery_mission(self): efficiency = 0.95 prob.model.set_input_defaults( - Aircraft.Battery.ENERGY_CAPACITY, 10_000, units='kJ') + av.Aircraft.Battery.ENERGY_CAPACITY, 10_000, units='kJ') prob.model.set_input_defaults( - Aircraft.Battery.EFFICIENCY, efficiency, units='unitless') - prob.model.set_input_defaults(Dynamic.Mission.MISSION_ENERGY, [ + av.Aircraft.Battery.EFFICIENCY, efficiency, units='unitless') + prob.model.set_input_defaults(av.Dynamic.Mission.MISSION_ENERGY, [ 0, 2_000, 5_000, 9_500], units='kJ') prob.setup(force_alloc_complex=True) @@ -63,13 +62,19 @@ def test_battery_mission(self): prob.run_model() soc_expected = np.array([1., 0.7894736842105263, 0.4736842105263159, 0.]) - soc = prob.get_val(Dynamic.Mission.BATTERY_STATE_OF_CHARGE, 'unitless') + soc = prob.get_val(av.Dynamic.Mission.BATTERY_STATE_OF_CHARGE, 'unitless') assert_near_equal(soc, soc_expected, tolerance=1e-10) partial_data = prob.check_partials(out_stream=None, method="cs") assert_check_partials(partial_data, atol=1e-10, rtol=1e-10) +class TestBattery(av.TestSubsystemBuilderBase): -if __name__ == "__main__": + def setUp(self): + self.subsystem_builder = BatteryBuilder() + self.aviary_values = av.AviaryValues() + + +if __name__ == '__main__': unittest.main() diff --git a/aviary/subsystems/test/subsystem_tester.py b/aviary/subsystems/test/subsystem_tester.py index 0f16f37db..a3afe461a 100644 --- a/aviary/subsystems/test/subsystem_tester.py +++ b/aviary/subsystems/test/subsystem_tester.py @@ -256,14 +256,6 @@ def test_check_state_variables(self): self.assertTrue(state_var_exists, f"State variable '{key}' not found in the model.") - # Check rate_source variable existence - if 'rate_source' in value: - rate_source = value['rate_source'] - rate_source_exists = any( - rate_source in output[0] for output in outputs) - self.assertTrue( - rate_source_exists, f"Rate source variable '{rate_source}' for state '{key}' not found in the model.") - def test_check_pre_mission(self): if not hasattr(self, 'aviary_values'): self.aviary_values = AviaryValues() From b5d0ac57fd9642383d8bbed7d83fc4c5f71a2a7c Mon Sep 17 00:00:00 2001 From: John Jasa Date: Wed, 29 May 2024 17:53:10 -0400 Subject: [PATCH 04/17] Added first battery builder in a mission test --- aviary/subsystems/energy/battery_builder.py | 4 +- .../energy/test/test_battery_in_a_mission.py | 89 +++++++++++++++++++ aviary/subsystems/test/subsystem_tester.py | 1 - 3 files changed, 91 insertions(+), 3 deletions(-) create mode 100644 aviary/subsystems/energy/test/test_battery_in_a_mission.py diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 70244730f..1d758b02c 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -18,9 +18,9 @@ def build_mission(self, num_nodes, aviary_inputs=None) -> om.Group: soc = om.ExecComp('state_of_charge = (energy_capacity - (mission_energy/efficiency)) / energy_capacity', state_of_charge={'val': np.zeros( num_nodes), 'units': 'unitless'}, - energy_capacity={'val': 0.0, 'units': 'kJ'}, + energy_capacity={'val': 10.0, 'units': 'kJ'}, mission_energy={'val': np.zeros(num_nodes), 'units': 'kJ'}, - efficiency={'val': 0.0, 'units': 'unitless'}) + efficiency={'val': 0.95, 'units': 'unitless'}) battery_group.add_subsystem('state_of_charge', subsys=soc, diff --git a/aviary/subsystems/energy/test/test_battery_in_a_mission.py b/aviary/subsystems/energy/test/test_battery_in_a_mission.py new file mode 100644 index 000000000..49fbb7051 --- /dev/null +++ b/aviary/subsystems/energy/test/test_battery_in_a_mission.py @@ -0,0 +1,89 @@ +import numpy as np +import unittest + +from numpy.testing import assert_almost_equal +from openmdao.utils.testing_utils import use_tempdirs + +import aviary.api as av + +from aviary.subsystems.energy.battery_builder import BatteryBuilder + + +@use_tempdirs +class TestSubsystemsMission(unittest.TestCase): + def setUp(self): + self.phase_info = { + 'pre_mission': { + 'include_takeoff': False, + 'external_subsystems': [BatteryBuilder()], + 'optimize_mass': True, + }, + 'cruise': { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + 'external_subsystems': [BatteryBuilder()], + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "num_segments": 2, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.72, "unitless"), + "final_mach": (0.72, "unitless"), + "mach_bounds": ((0.7, 0.74), "unitless"), + "initial_altitude": (35000.0, "ft"), + "final_altitude": (35000.0, "ft"), + "altitude_bounds": ((23000.0, 38000.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((10., 30.), "min"), + }, + "initial_guesses": {"times": ([0, 30], "min")}, + }, + 'post_mission': { + 'include_landing': False, + 'external_subsystems': [], + } + } + + def test_subsystems_in_a_mission(self): + phase_info = self.phase_info.copy() + + prob = av.AviaryProblem() + + prob.load_inputs("models/test_aircraft/aircraft_for_bench_FwFm.csv", phase_info) + + # Preprocess inputs + prob.check_and_preprocess_inputs() + + prob.add_pre_mission_systems() + + prob.add_phases() + + prob.add_post_mission_systems() + + # Link phases and variables + prob.link_phases() + + prob.add_driver("SLSQP", max_iter=100) + + prob.add_design_variables() + + prob.add_objective('fuel_burned') + + prob.setup() + + prob.set_initial_guesses() + + prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') + prob.set_val(av.Aircraft.Battery.PACK_MASS, 1200, units='lbm') + prob.set_val(av.Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') + + prob.run_aviary_problem() + + +if __name__ == "__main__": + unittest.main() diff --git a/aviary/subsystems/test/subsystem_tester.py b/aviary/subsystems/test/subsystem_tester.py index a3afe461a..5e7859b1b 100644 --- a/aviary/subsystems/test/subsystem_tester.py +++ b/aviary/subsystems/test/subsystem_tester.py @@ -247,7 +247,6 @@ def test_check_state_variables(self): prob.final_setup() inputs = prob.model.list_inputs(out_stream=None, prom_name=True) - outputs = prob.model.list_outputs(out_stream=None, prom_name=True) for key, value in states.items(): if mission_sys is not None: From 67031098be123d71d675d066efb1a3dfc024b145 Mon Sep 17 00:00:00 2001 From: John Jasa Date: Thu, 6 Jun 2024 10:34:00 -0400 Subject: [PATCH 05/17] Adding battery-related files --- aviary/models/engines/process_deck.py | 23 + aviary/models/engines/turbofan_28k.deck | 2 - .../engines/turbofan_28k_with_electric.deck | 1112 +++++++++++++++++ .../aircraft_for_bench_FwFm_with_electric.csv | 158 +++ .../energy/test/test_battery_in_a_mission.py | 7 +- 5 files changed, 1297 insertions(+), 5 deletions(-) create mode 100644 aviary/models/engines/process_deck.py create mode 100644 aviary/models/engines/turbofan_28k_with_electric.deck create mode 100644 aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv diff --git a/aviary/models/engines/process_deck.py b/aviary/models/engines/process_deck.py new file mode 100644 index 000000000..6d8232bdd --- /dev/null +++ b/aviary/models/engines/process_deck.py @@ -0,0 +1,23 @@ +import pandas as pd +import csv + + +# Read the CSV data into a DataFrame +df = pd.read_csv('turbofan_28k.deck') + +# Calculate the electric_power column +df['electric_power (kW)'] = df[' Gross_Thrust (lbf)'] * 0.000000005 + +# Define the output file name +output_file = 'turbofan_28k_with_electric.deck' + +# Write the DataFrame to a CSV file with the desired formatting +with open(output_file, mode='w', newline='') as file: + writer = csv.writer(file) + + # Write the header + writer.writerow(df.columns) + + # Write the data with formatted spacing + for index, row in df.iterrows(): + writer.writerow(['{:>20}'.format(item) for item in row]) \ No newline at end of file diff --git a/aviary/models/engines/turbofan_28k.deck b/aviary/models/engines/turbofan_28k.deck index 4af2acf7c..b3fe01619 100644 --- a/aviary/models/engines/turbofan_28k.deck +++ b/aviary/models/engines/turbofan_28k.deck @@ -1,5 +1,3 @@ -# FLOPS-derived engine deck converted from turbofan_28_ENGDEK - Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h) 0.0, 0.0, 21.0, 1446.4, 0.0, 842.2, 4.7876 0.0, 0.0, 22.0, 2314.3, 0.0, 976.0, 5.1926 diff --git a/aviary/models/engines/turbofan_28k_with_electric.deck b/aviary/models/engines/turbofan_28k_with_electric.deck new file mode 100644 index 000000000..95e370d4d --- /dev/null +++ b/aviary/models/engines/turbofan_28k_with_electric.deck @@ -0,0 +1,1112 @@ +Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h),electric_power (kW) + 0.0, 0.0, 21.0, 1446.4, 0.0, 842.2, 4.7876, 7.232e-06 + 0.0, 0.0, 22.0, 2314.3, 0.0, 976.0, 5.1926,1.1571500000000001e-05 + 0.0, 0.0, 24.0, 4049.9, 0.0, 1281.0, 6.6532, 2.02495e-05 + 0.0, 0.0, 26.0, 5785.6, 0.0, 1659.9, 8.2234, 2.8928e-05 + 0.0, 0.0, 30.0, 9642.7, 0.0, 2621.6, 12.0946, 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5.949e-05 + 0.9, 39000.0, 42.0, 12941.4, 9497.6, 2096.6, 13.3448, 6.4707e-05 + 0.9, 39000.0, 46.0, 13955.2, 9885.2, 2438.2, 14.6669, 6.9776e-05 + 0.9, 39000.0, 48.0, 14447.9, 10064.9, 2618.2, 15.3126, 7.22395e-05 + 0.9, 39000.0, 50.0, 14937.5, 10241.3, 2799.5, 15.9332, 7.46875e-05 diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv new file mode 100644 index 000000000..b8e406e77 --- /dev/null +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv @@ -0,0 +1,158 @@ +aircraft:air_conditioning:mass_scaler,1.0,unitless +aircraft:anti_icing:mass_scaler,1.0,unitless +aircraft:apu:mass_scaler,1.1,unitless +aircraft:avionics:mass_scaler,1.2,unitless +aircraft:canard:area,0.0,ft**2 +aircraft:canard:aspect_ratio,0.0,unitless +aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm +aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm +aircraft:crew_and_payload:misc_cargo,0.0,lbm +aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_business_class,0,unitless +aircraft:crew_and_payload:num_first_class,11,unitless +aircraft:crew_and_payload:num_flight_attendants,3,unitless +aircraft:crew_and_payload:num_flight_crew,2,unitless +aircraft:crew_and_payload:num_galley_crew,0,unitless +aircraft:crew_and_payload:num_non_flight_crew,3,unitless +aircraft:crew_and_payload:num_passengers,169,unitless +aircraft:crew_and_payload:num_tourist_class,158,unitless +aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +aircraft:crew_and_payload:wing_cargo,0.0,lbm +aircraft:design:base_area,0.0,ft**2 +aircraft:design:empty_mass_margin_scaler,0.0,unitless +aircraft:design:lift_dependent_drag_coeff_factor,0.909839381134961,unitless +aircraft:design:touchdown_mass,152800.0,lbm +aircraft:design:reserve_fuel_additional,3000.,lbm +aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +aircraft:design:zero_lift_drag_coeff_factor,0.930890028006548,unitless +aircraft:electrical:mass_scaler,1.25,unitless +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h +aircraft:engine:data_file,models/engines/turbofan_28k_with_electric.deck,unitless +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,True,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.15,unitless +aircraft:engine:mass,7400,lbm +aircraft:engine:num_engines,2,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_wing_engines,2,unitless +aircraft:engine:reference_mass,7400,lbm +aircraft:engine:reference_sls_thrust,28928.1,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,28928.1,lbf +aircraft:engine:subsonic_fuel_flow_scaler,1.,unitless +aircraft:engine:supersonic_fuel_flow_scaler,1.,unitless +aircraft:engine:thrust_reversers_mass_scaler,0.0,unitless +aircraft:engine:wing_locations,[0.26869218],unitless +aircraft:fins:area,0.0,ft**2 +aircraft:fins:mass_scaler,1.0,unitless +aircraft:fins:mass,0.0,lbm +aircraft:fins:num_fins,0,unitless +aircraft:fins:taper_ratio,10.0,unitless 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+aircraft:horizontal_tail:taper_ratio,0.22,unitless +aircraft:horizontal_tail:thickness_to_chord,0.125,unitless +aircraft:horizontal_tail:vertical_tail_fraction,0.0,unitless +aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:wetted_area,592.65,ft**2 +aircraft:hydraulics:mass_scaler,1.0,unitless +aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +aircraft:instruments:mass_scaler,1.25,unitless +aircraft:landing_gear:carrier_based,False,unitless +aircraft:landing_gear:main_gear_mass_scaler,1.1,unitless +aircraft:landing_gear:main_gear_oleo_length,102.0,inch +aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +aircraft:landing_gear:nose_gear_oleo_length,67.0,inch +aircraft:nacelle:avg_diameter,7.94,ft +aircraft:nacelle:avg_length,12.3,ft +aircraft:nacelle:count_factor,2,unitless +aircraft:nacelle:mass_scaler,1.0,unitless +aircraft:nacelle:wetted_area_scaler,1.0,unitless +aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,284.0,ft**2 +aircraft:vertical_tail:aspect_ratio,1.75,unitless +aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.33,unitless +aircraft:vertical_tail:thickness_to_chord,0.1195,unitless +aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:vertical_tail:wetted_area,581.13,ft**2 +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.92669766647637,unitless +aircraft:wing:area,1370.0,ft**2 +aircraft:wing:aspect_ratio,11.22091,unitless +aircraft:wing:bending_mass_scaler,1.0,unitless +aircraft:wing:chord_per_semispan,0.31,0.23,0.084,unitless +aircraft:wing:composite_fraction,0.2,unitless +aircraft:wing:control_surface_area,137,ft**2 +aircraft:wing:control_surface_area_ratio,0.1,unitless +aircraft:wing:glove_and_bat,134.0,ft**2 +aircraft:wing:input_station_dist,0.,0.2759,0.9367,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +aircraft:wing:load_path_sweep_dist,0.,22.,deg +aircraft:wing:mass_scaler,1.23,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +aircraft:wing:misc_mass_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,117.83,ft +aircraft:wing:strut_bracing_factor,0.0,unitless +aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,25.0,deg +aircraft:wing:taper_ratio,0.278,unitless +aircraft:wing:thickness_to_chord_dist,0.145,0.115,0.104,unitless +aircraft:wing:thickness_to_chord,0.13,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:wetted_area,2396.56,ft**2 +mission:constraints:max_mach,0.785,unitless +mission:design:cruise_altitude,35000,ft +mission:design:gross_mass,175400.0,lbm +mission:design:range,3500,NM +mission:design:thrust_takeoff_per_eng,28928.1,lbf +mission:landing:lift_coefficient_max,2.0,unitless +mission:summary:cruise_mach,0.785,unitless +mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,577,lbm +mission:takeoff:lift_coefficient_max,3.0,unitless +mission:takeoff:lift_over_drag,17.354,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS \ No newline at end of file diff --git a/aviary/subsystems/energy/test/test_battery_in_a_mission.py b/aviary/subsystems/energy/test/test_battery_in_a_mission.py index 49fbb7051..a65471bea 100644 --- a/aviary/subsystems/energy/test/test_battery_in_a_mission.py +++ b/aviary/subsystems/energy/test/test_battery_in_a_mission.py @@ -9,7 +9,7 @@ from aviary.subsystems.energy.battery_builder import BatteryBuilder -@use_tempdirs +# @use_tempdirs class TestSubsystemsMission(unittest.TestCase): def setUp(self): self.phase_info = { @@ -25,7 +25,7 @@ def setUp(self): "optimize_mach": False, "optimize_altitude": False, "polynomial_control_order": 1, - "num_segments": 2, + "num_segments": 5, "order": 3, "solve_for_distance": False, "initial_mach": (0.72, "unitless"), @@ -54,7 +54,7 @@ def test_subsystems_in_a_mission(self): prob = av.AviaryProblem() - prob.load_inputs("models/test_aircraft/aircraft_for_bench_FwFm.csv", phase_info) + prob.load_inputs("models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv", phase_info) # Preprocess inputs prob.check_and_preprocess_inputs() @@ -81,6 +81,7 @@ def test_subsystems_in_a_mission(self): prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') prob.set_val(av.Aircraft.Battery.PACK_MASS, 1200, units='lbm') prob.set_val(av.Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') + prob.set_val("traj.cruise.rhs_all.engine_deck.electric_power", 2., units='kW') prob.run_aviary_problem() From 8deb03b8dac918d2b6b4bf1540a9b6ec8cff7bbc Mon Sep 17 00:00:00 2001 From: johnjasa Date: Fri, 7 Jun 2024 14:40:38 -0500 Subject: [PATCH 06/17] Updating built-in battery model --- aviary/interface/methods_for_level2.py | 4 +- aviary/models/engines/process_deck.py | 8 +- .../engines/turbofan_28k_with_electric.deck | 2222 ++++++++--------- aviary/subsystems/energy/battery_builder.py | 4 + aviary/subsystems/energy/battery_sizing.py | 30 +- .../energy/test/test_battery_in_a_mission.py | 10 +- 6 files changed, 1139 insertions(+), 1139 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index d9cd1684b..b70249523 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -2220,7 +2220,7 @@ def run_aviary_problem(self, If True (default), Dymos html plots will be generated as part of the output. """ - if self.aviary_inputs.get_val('verbosity').value >= 2: + if self.aviary_inputs.get_val(Settings.VERBOSITY).value >= 2: self.final_setup() with open('input_list.txt', 'w') as outfile: self.model.list_inputs(out_stream=outfile) @@ -2242,7 +2242,7 @@ def run_aviary_problem(self, failed = self.run_model() warnings.filterwarnings('default', category=UserWarning) - if self.aviary_inputs.get_val('verbosity').value >= 2: + if self.aviary_inputs.get_val(Settings.VERBOSITY).value >= 2: with open('output_list.txt', 'w') as outfile: self.model.list_outputs(out_stream=outfile) diff --git a/aviary/models/engines/process_deck.py b/aviary/models/engines/process_deck.py index 6d8232bdd..d10787c11 100644 --- a/aviary/models/engines/process_deck.py +++ b/aviary/models/engines/process_deck.py @@ -6,7 +6,7 @@ df = pd.read_csv('turbofan_28k.deck') # Calculate the electric_power column -df['electric_power (kW)'] = df[' Gross_Thrust (lbf)'] * 0.000000005 +df['electric_power (kW)'] = df[' Gross_Thrust (lbf)'] * 1.e-2 # Define the output file name output_file = 'turbofan_28k_with_electric.deck' @@ -14,10 +14,10 @@ # Write the DataFrame to a CSV file with the desired formatting with open(output_file, mode='w', newline='') as file: writer = csv.writer(file) - + # Write the header writer.writerow(df.columns) - + # Write the data with formatted spacing for index, row in df.iterrows(): - writer.writerow(['{:>20}'.format(item) for item in row]) \ No newline at end of file + writer.writerow(['{:>20}'.format(item) for item in row]) diff --git a/aviary/models/engines/turbofan_28k_with_electric.deck b/aviary/models/engines/turbofan_28k_with_electric.deck index 95e370d4d..6c151d5a3 100644 --- a/aviary/models/engines/turbofan_28k_with_electric.deck +++ b/aviary/models/engines/turbofan_28k_with_electric.deck @@ -1,1112 +1,1112 @@ Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h),electric_power (kW) - 0.0, 0.0, 21.0, 1446.4, 0.0, 842.2, 4.7876, 7.232e-06 - 0.0, 0.0, 22.0, 2314.3, 0.0, 976.0, 5.1926,1.1571500000000001e-05 - 0.0, 0.0, 24.0, 4049.9, 0.0, 1281.0, 6.6532, 2.02495e-05 - 0.0, 0.0, 26.0, 5785.6, 0.0, 1659.9, 8.2234, 2.8928e-05 - 0.0, 0.0, 30.0, 9642.7, 0.0, 2621.6, 12.0946, 4.82135e-05 - 0.0, 0.0, 34.0, 13499.8, 0.0, 3673.3, 15.0321, 6.7499e-05 - 0.0, 0.0, 38.0, 17356.9, 0.0, 4795.2, 17.5877,8.678450000000001e-05 - 0.0, 0.0, 42.0, 21214.0, 0.0, 5979.1, 19.8547, 0.00010607 - 0.0, 0.0, 46.0, 25071.1, 0.0, 7258.1, 33.3976, 0.0001253555 - 0.0, 0.0, 48.0, 26999.7, 0.0, 7932.6, 49.2185, 0.0001349985 - 0.0, 0.0, 50.0, 28928.1, 0.0, 8662.3, 61.9894, 0.0001446405 - 0.0, 2000.0, 21.0, 1446.4, 0.0, 781.8, 5.2521, 7.232e-06 - 0.0, 2000.0, 22.0, 2314.2, 0.0, 914.2, 5.1431, 1.1571e-05 - 0.0, 2000.0, 24.0, 4049.9, 0.0, 1220.2, 6.7284, 2.02495e-05 - 0.0, 2000.0, 26.0, 5785.6, 0.0, 1608.2, 8.4472, 2.8928e-05 - 0.0, 2000.0, 30.0, 9642.7, 0.0, 2572.5, 12.5205, 4.82135e-05 - 0.0, 2000.0, 34.0, 13499.7, 0.0, 3624.6, 15.6007, 6.74985e-05 - 0.0, 2000.0, 38.0, 17356.8, 0.0, 4748.2, 18.2407, 8.6784e-05 - 0.0, 2000.0, 42.0, 21213.8, 0.0, 5953.1, 20.6168, 0.000106069 - 0.0, 2000.0, 46.0, 25070.8, 0.0, 7274.3, 46.5192, 0.000125354 - 0.0, 2000.0, 48.0, 26999.7, 0.0, 8005.4, 61.6004, 0.0001349985 - 0.0, 2000.0, 50.0, 28928.0, 0.0, 8769.0, 72.5104, 0.00014464 - 0.0, 5000.0, 21.0, 1338.1, 0.0, 706.8, 6.8008, 6.6905e-06 - 0.0, 5000.0, 22.0, 2140.9, 0.0, 828.3, 5.03, 1.07045e-05 - 0.0, 5000.0, 24.0, 3746.7, 0.0, 1111.0, 6.2319, 1.87335e-05 - 0.0, 5000.0, 26.0, 5352.3, 0.0, 1469.9, 7.9885, 2.67615e-05 - 0.0, 5000.0, 30.0, 8920.6, 0.0, 2355.4, 12.0275, 4.4603e-05 - 0.0, 5000.0, 34.0, 12488.9, 0.0, 3323.4, 15.1312, 6.24445e-05 - 0.0, 5000.0, 38.0, 16057.1, 0.0, 4353.1, 17.7742, 8.02855e-05 - 0.0, 5000.0, 42.0, 19625.3, 0.0, 5473.5, 20.1814, 9.81265e-05 - 0.0, 5000.0, 46.0, 23193.5, 0.0, 6708.4, 39.1314, 0.0001159675 - 0.0, 5000.0, 48.0, 24977.9, 0.0, 7391.9, 57.3145, 0.0001248895 - 0.0, 5000.0, 50.0, 26761.8, 0.0, 8104.6, 69.2582, 0.000133809 - 0.1, 0.0, 21.0, 2503.9, 1057.5, 905.8, 4.7726,1.2519500000000001e-05 - 0.1, 0.0, 22.0, 3575.1, 1260.9, 1088.1, 5.7209, 1.78755e-05 - 0.1, 0.0, 24.0, 5626.3, 1576.4, 1525.4, 7.6905, 2.81315e-05 - 0.1, 0.0, 26.0, 7615.0, 1829.5, 2001.1, 9.4545,3.8075000000000004e-05 - 0.1, 0.0, 30.0, 11922.9, 2280.3, 3129.8, 13.5965,5.9614499999999996e-05 - 0.1, 0.0, 34.0, 16145.2, 2645.4, 4326.3, 16.5878, 8.0726e-05 - 0.1, 0.0, 38.0, 20316.5, 2959.7, 5587.6, 19.1578, 0.0001015825 - 0.1, 0.0, 42.0, 24452.2, 3238.4, 6932.0, 26.8701, 0.000122261 - 0.1, 0.0, 46.0, 28560.1, 3489.2, 8389.7, 57.6579,0.00014280049999999998 - 0.1, 0.0, 48.0, 30603.9, 3604.5, 9194.3, 69.2477,0.00015301950000000001 - 0.1, 0.0, 50.0, 32642.3, 3714.3, 10032.8, 77.4403, 0.0001632115 - 0.1, 2000.0, 21.0, 2330.3, 984.5, 824.4, 4.924,1.1651500000000002e-05 - 0.1, 2000.0, 22.0, 3327.1, 1173.8, 991.2, 5.5336, 1.66355e-05 - 0.1, 2000.0, 24.0, 5235.7, 1467.4, 1391.5, 7.5234, 2.61785e-05 - 0.1, 2000.0, 26.0, 7086.3, 1702.9, 1826.8, 9.2983, 3.54315e-05 - 0.1, 2000.0, 30.0, 11094.9, 2122.6, 2859.5, 13.4284, 5.54745e-05 - 0.1, 2000.0, 34.0, 15023.5, 2462.3, 3960.7, 16.4467, 7.51175e-05 - 0.1, 2000.0, 38.0, 18904.9, 2754.8, 5117.1, 19.0209,9.452450000000001e-05 - 0.1, 2000.0, 42.0, 22752.9, 3013.8, 6361.1, 24.7835,0.00011376450000000001 - 0.1, 2000.0, 46.0, 26574.2, 3246.4, 7721.3, 56.6411, 0.000132871 - 0.1, 2000.0, 48.0, 28476.4, 3353.7, 8462.9, 68.5093, 0.000142382 - 0.1, 2000.0, 50.0, 30372.6, 3455.8, 9235.9, 77.0405, 0.000151863 - 0.1, 5000.0, 21.0, 2084.6, 880.6, 738.0, 6.5816, 1.0423e-05 - 0.1, 5000.0, 22.0, 2976.4, 1050.0, 884.8, 4.9156, 1.4882e-05 - 0.1, 5000.0, 24.0, 4684.1, 1312.8, 1237.6, 6.8861,2.3420500000000004e-05 - 0.1, 5000.0, 26.0, 6339.8, 1523.6, 1621.7, 8.6447, 3.1699e-05 - 0.1, 5000.0, 30.0, 9926.1, 1899.3, 2532.7, 12.6499,4.9630500000000005e-05 - 0.1, 5000.0, 34.0, 13440.9, 2203.3, 3503.2, 15.6314, 6.72045e-05 - 0.1, 5000.0, 38.0, 16913.5, 2465.1, 4524.4, 18.1789, 8.45675e-05 - 0.1, 5000.0, 42.0, 20356.6, 2696.9, 5621.1, 20.4797, 0.000101783 - 0.1, 5000.0, 46.0, 23775.6, 2905.2, 6820.1, 42.0756, 0.000118878 - 0.1, 5000.0, 48.0, 25476.8, 3001.2, 7474.2, 58.5348, 0.000127384 - 0.1, 5000.0, 50.0, 27173.2, 3092.6, 8156.2, 69.8119, 0.000135866 - 0.1, 10000.0, 21.0, 1721.9, 727.2, 612.6, 9.402,8.609500000000001e-06 - 0.1, 10000.0, 22.0, 2458.8, 867.2, 730.7, 7.2271,1.2294000000000001e-05 - 0.1, 10000.0, 24.0, 3869.8, 1084.5, 1014.8, 5.7309, 1.9349e-05 - 0.1, 10000.0, 26.0, 5237.7, 1258.8, 1324.4, 7.4445, 2.61885e-05 - 0.1, 10000.0, 30.0, 8200.9, 1569.4, 2059.1, 10.9423, 4.10045e-05 - 0.1, 10000.0, 34.0, 11104.9, 1820.8, 2841.8, 14.0989, 5.55245e-05 - 0.1, 10000.0, 38.0, 13974.0, 2037.3, 3665.3, 16.5692,6.987000000000001e-05 - 0.1, 10000.0, 42.0, 16818.6, 2229.1, 4548.6, 18.7998, 8.4093e-05 - 0.1, 10000.0, 46.0, 19643.6, 2401.3, 5515.6, 21.9454, 9.8218e-05 - 0.1, 10000.0, 48.0, 21049.0, 2480.6, 6042.3, 33.2727, 0.000105245 - 0.1, 10000.0, 50.0, 22450.7, 2556.3, 6592.6, 50.9804, 0.0001122535 - 0.2, 0.0, 21.0, 3984.0, 2660.5, 927.8, 4.88, 1.992e-05 - 0.2, 0.0, 22.0, 5132.8, 3015.2, 1158.3, 6.0773, 2.5664e-05 - 0.2, 0.0, 24.0, 7290.5, 3584.8, 1655.7, 8.2264,3.6452500000000004e-05 - 0.2, 0.0, 26.0, 9344.4, 4050.6, 2168.2, 10.048, 4.6722e-05 - 0.2, 0.0, 30.0, 13714.4, 4891.5, 3335.6, 14.1832, 6.8572e-05 - 0.2, 0.0, 34.0, 17928.1, 5575.9, 4564.4, 17.1365, 8.96405e-05 - 0.2, 0.0, 38.0, 22048.5, 6167.1, 5839.6, 19.6518, 0.0001102425 - 0.2, 0.0, 42.0, 26104.0, 6693.4, 7176.2, 31.254, 0.00013052 - 0.2, 0.0, 46.0, 30105.5, 7165.7, 8625.1, 60.8012, 0.0001505275 - 0.2, 0.0, 48.0, 32088.4, 7383.6, 9408.5, 71.4541, 0.000160442 - 0.2, 0.0, 50.0, 34059.1, 7590.1, 10231.7, 78.754, 0.0001702955 - 0.2, 2000.0, 21.0, 3705.8, 2475.9, 844.5, 4.8026, 1.8529e-05 - 0.2, 2000.0, 22.0, 4773.5, 2805.8, 1055.1, 5.8928, 2.38675e-05 - 0.2, 2000.0, 24.0, 6779.2, 3335.6, 1509.9, 8.0591, 3.3896e-05 - 0.2, 2000.0, 26.0, 8688.2, 3768.8, 1978.1, 9.8731,4.3441000000000006e-05 - 0.2, 2000.0, 30.0, 12750.0, 4551.0, 3045.6, 14.0129, 6.375e-05 - 0.2, 2000.0, 34.0, 16665.9, 5187.3, 4175.2, 16.9893,8.332950000000001e-05 - 0.2, 2000.0, 38.0, 20495.5, 5737.3, 5341.9, 19.5044, 0.0001024775 - 0.2, 2000.0, 42.0, 24264.1, 6226.1, 6575.1, 28.1727,0.00012132049999999999 - 0.2, 2000.0, 46.0, 27981.8, 6663.9, 7924.2, 59.5213, 0.000139909 - 0.2, 2000.0, 48.0, 29823.9, 6866.3, 8646.0, 70.5775, 0.0001491195 - 0.2, 2000.0, 50.0, 31655.3, 7058.3, 9403.9, 78.2786, 0.0001582765 - 0.2, 5000.0, 21.0, 3315.0, 2214.7, 755.5, 6.435, 1.6575e-05 - 0.2, 5000.0, 22.0, 4270.4, 2510.0, 941.0, 5.268,2.1351999999999998e-05 - 0.2, 5000.0, 24.0, 6064.9, 2984.3, 1342.0, 7.4149,3.0324499999999997e-05 - 0.2, 5000.0, 26.0, 7773.0, 3372.1, 1755.4, 9.2124, 3.8865e-05 - 0.2, 5000.0, 30.0, 11407.0, 4072.2, 2696.9, 13.2256, 5.7035e-05 - 0.2, 5000.0, 34.0, 14910.5, 4641.7, 3693.1, 16.1681,7.455250000000001e-05 - 0.2, 5000.0, 38.0, 18336.7, 5134.0, 4722.6, 18.6548, 9.16835e-05 - 0.2, 5000.0, 42.0, 21708.3, 5571.5, 5810.0, 20.9007, 0.0001085415 - 0.2, 5000.0, 46.0, 25034.4, 5963.4, 6999.7, 46.548, 0.000125172 - 0.2, 5000.0, 48.0, 26682.2, 6144.6, 7635.7, 60.7973, 0.000133411 - 0.2, 5000.0, 50.0, 28321.1, 6316.5, 8304.7, 71.4843, 0.0001416055 - 0.2, 10000.0, 21.0, 2738.0, 1829.0, 626.4, 9.2804,1.3690000000000001e-05 - 0.2, 10000.0, 22.0, 3527.6, 2073.3, 775.5, 6.4797, 1.7638e-05 - 0.2, 10000.0, 24.0, 5010.5, 2465.5, 1098.5, 6.2413, 2.50525e-05 - 0.2, 10000.0, 26.0, 6421.8, 2786.1, 1431.7, 7.9908, 3.2109e-05 - 0.2, 10000.0, 30.0, 9424.6, 3365.1, 2191.4, 11.7561, 4.7123e-05 - 0.2, 10000.0, 34.0, 12319.4, 3836.1, 2994.6, 14.6148, 6.1597e-05 - 0.2, 10000.0, 38.0, 15150.2, 4243.1, 3825.2, 17.0282, 7.5751e-05 - 0.2, 10000.0, 42.0, 17936.1, 4604.8, 4701.2, 19.1798,8.968049999999999e-05 - 0.2, 10000.0, 46.0, 20683.4, 4929.0, 5659.9, 23.6308, 0.000103417 - 0.2, 10000.0, 48.0, 22045.5, 5078.8, 6173.0, 36.4956,0.00011022750000000001 - 0.2, 10000.0, 50.0, 23399.5, 5221.0, 6712.2, 53.4919, 0.0001169975 - 0.25, 0.0, 21.0, 4982.9, 3711.0, 967.7, 5.1347, 2.49145e-05 - 0.25, 0.0, 22.0, 6155.9, 4120.9, 1221.5, 6.4157, 3.07795e-05 - 0.25, 0.0, 24.0, 8353.0, 4791.8, 1741.2, 8.5818,4.1765000000000004e-05 - 0.25, 0.0, 26.0, 10434.6, 5347.2, 2267.6, 10.7481,5.2173000000000003e-05 - 0.25, 0.0, 30.0, 14837.1, 6358.1, 3458.3, 14.5379, 7.41855e-05 - 0.25, 0.0, 34.0, 19055.8, 7185.2, 4700.4, 17.4532, 9.5279e-05 - 0.25, 0.0, 38.0, 23164.2, 7901.7, 5979.8, 19.9304, 0.000115821 - 0.25, 0.0, 42.0, 27194.4, 8540.4, 7318.7, 34.2788,0.00013597200000000002 - 0.25, 0.0, 46.0, 31158.1, 9112.7, 8772.0, 62.9527, 0.0001557905 - 0.25, 0.0, 48.0, 33119.2, 9377.6, 9547.4, 72.8167,0.00016559599999999998 - 0.25, 0.0, 50.0, 35064.8, 9627.7, 10368.8, 79.61,0.00017532400000000003 - 0.25, 2000.0, 21.0, 4635.4, 3453.6, 881.2, 4.9403, 2.3177e-05 - 0.25, 2000.0, 22.0, 5725.7, 3834.8, 1113.2, 6.2358, 2.86285e-05 - 0.25, 2000.0, 24.0, 7767.9, 4458.7, 1587.7, 8.4148, 3.88395e-05 - 0.25, 2000.0, 26.0, 9702.8, 4975.4, 2068.9, 10.3133, 4.8514e-05 - 0.25, 2000.0, 30.0, 13794.8, 5915.8, 3157.8, 14.3694, 6.8974e-05 - 0.25, 2000.0, 34.0, 17715.3, 6684.5, 4299.7, 17.3076, 8.85765e-05 - 0.25, 2000.0, 38.0, 21533.5, 7351.2, 5470.6, 19.7854, 0.0001076675 - 0.25, 2000.0, 42.0, 25278.1, 7944.4, 6705.3, 30.7493, 0.0001263905 - 0.25, 2000.0, 46.0, 28960.8, 8474.8, 8057.1, 61.504, 0.000144804 - 0.25, 2000.0, 48.0, 30782.4, 8720.7, 8773.3, 71.9783, 0.000153912 - 0.25, 2000.0, 50.0, 32590.3, 8953.2, 9529.4, 79.1712, 0.0001629515 - 0.25, 5000.0, 21.0, 4146.8, 3089.4, 787.7, 5.8398,2.0734000000000002e-05 - 0.25, 5000.0, 22.0, 5122.4, 3430.7, 992.0, 5.6074,2.5611999999999998e-05 - 0.25, 5000.0, 24.0, 6949.9, 3989.3, 1411.0, 7.7697,3.4749499999999997e-05 - 0.25, 5000.0, 26.0, 8681.0, 4451.7, 1835.5, 9.5548, 4.3405e-05 - 0.25, 5000.0, 30.0, 12342.2, 5293.4, 2795.6, 13.5758, 6.1711e-05 - 0.25, 5000.0, 34.0, 15850.1, 5981.6, 3803.0, 16.4816,7.925050000000001e-05 - 0.25, 5000.0, 38.0, 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10000.0, 48.0, 22754.0, 6450.6, 6263.1, 38.8691, 0.00011377 - 0.25, 10000.0, 50.0, 24090.7, 6622.7, 6801.4, 55.311, 0.0001204535 - 0.3, 0.0, 21.0, 6173.4, 4945.6, 1022.8, 5.4835, 3.0867e-05 - 0.3, 0.0, 22.0, 7364.1, 5399.7, 1289.1, 6.7761,3.6820500000000004e-05 - 0.3, 0.0, 24.0, 9594.3, 6156.5, 1828.9, 8.945, 4.79715e-05 - 0.3, 0.0, 26.0, 11702.0, 6790.9, 2370.2, 11.3695, 5.851e-05 - 0.3, 0.0, 30.0, 16141.2, 7956.0, 3586.7, 14.9079,8.070600000000001e-05 - 0.3, 0.0, 34.0, 20374.2, 8914.9, 4845.9, 17.7911, 0.000101871 - 0.3, 0.0, 38.0, 24482.0, 9748.6, 6136.4, 20.2415,0.00012241000000000002 - 0.3, 0.0, 42.0, 28498.9, 10491.9, 7487.2, 38.1853,0.00014249450000000002 - 0.3, 0.0, 46.0, 32440.2, 11158.6, 8946.6, 65.3539, 0.000162201 - 0.3, 0.0, 48.0, 34385.6, 11467.0, 9722.6, 74.4559,0.00017192799999999998 - 0.3, 0.0, 50.0, 36314.3, 11758.7, 10541.1, 80.6075, 0.0001815715 - 0.3, 2000.0, 21.0, 5743.4, 4602.6, 931.5, 5.2941, 2.8717e-05 - 0.3, 2000.0, 22.0, 6850.3, 5024.9, 1175.0, 6.6001, 3.42515e-05 - 0.3, 2000.0, 24.0, 8923.2, 5728.8, 1668.1, 8.7823,4.461600000000001e-05 - 0.3, 2000.0, 26.0, 10882.3, 6318.8, 2161.9, 11.0244, 5.44115e-05 - 0.3, 2000.0, 30.0, 15008.5, 7402.8, 3275.4, 14.742, 7.50425e-05 - 0.3, 2000.0, 34.0, 18942.1, 8294.0, 4433.1, 17.6473, 9.47105e-05 - 0.3, 2000.0, 38.0, 22759.9, 9069.6, 5614.1, 20.0977,0.00011379950000000001 - 0.3, 2000.0, 42.0, 26492.4, 9759.9, 6860.5, 34.3047,0.00013246200000000002 - 0.3, 2000.0, 46.0, 30152.8, 10377.9, 8215.0, 63.8559, 0.000150764 - 0.3, 2000.0, 48.0, 31959.4, 10663.8, 8934.3, 73.6791,0.00015979700000000002 - 0.3, 2000.0, 50.0, 33752.0, 10934.9, 9687.3, 80.2171, 0.00016876 - 0.3, 5000.0, 21.0, 5137.9, 4117.3, 832.0, 5.0092, 2.56895e-05 - 0.3, 5000.0, 22.0, 6128.4, 4495.5, 1046.5, 5.9682,3.0641999999999996e-05 - 0.3, 5000.0, 24.0, 7983.1, 5125.5, 1481.4, 8.1293, 3.99155e-05 - 0.3, 5000.0, 26.0, 9735.9, 5653.8, 1917.6, 9.9046, 4.86795e-05 - 0.3, 5000.0, 30.0, 13427.5, 6623.9, 2899.2, 13.9423, 6.71375e-05 - 0.3, 5000.0, 34.0, 16946.8, 7421.7, 3920.4, 16.8161,8.473399999999999e-05 - 0.3, 5000.0, 38.0, 20362.5, 8115.9, 4962.2, 19.2379, 0.0001018125 - 0.3, 5000.0, 42.0, 23701.7, 8733.8, 6061.4, 23.5209, 0.0001185085 - 0.3, 5000.0, 46.0, 26976.2, 9286.8, 7256.0, 52.5299, 0.000134881 - 0.3, 5000.0, 48.0, 28592.9, 9543.0, 7890.1, 64.7543,0.00014296450000000002 - 0.3, 5000.0, 50.0, 30196.6, 9785.7, 8554.4, 74.2115, 0.000150983 - 0.3, 10000.0, 21.0, 4243.8, 3400.8, 687.6, 7.8677, 2.1219e-05 - 0.3, 10000.0, 22.0, 5062.5, 3713.6, 860.4, 4.908,2.5312500000000002e-05 - 0.3, 10000.0, 24.0, 6595.3, 4234.8, 1211.0, 6.9375, 3.29765e-05 - 0.3, 10000.0, 26.0, 8043.8, 4671.6, 1563.1, 8.6667, 4.0219e-05 - 0.3, 10000.0, 30.0, 11094.2, 5473.9, 2354.8, 12.4504,5.5471000000000005e-05 - 0.3, 10000.0, 34.0, 14002.0, 6133.6, 3177.8, 15.2398, 7.001e-05 - 0.3, 10000.0, 38.0, 16824.1, 6707.5, 4018.5, 17.5905, 8.41205e-05 - 0.3, 10000.0, 42.0, 19583.3, 7218.6, 4904.6, 19.6927, 9.79165e-05 - 0.3, 10000.0, 46.0, 22288.8, 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0.35, 0.0, 22.0, 8770.7, 6863.1, 1379.4, 7.2407, 4.38535e-05 - 0.35, 0.0, 24.0, 11031.6, 7693.3, 1932.5, 9.3656, 5.5158e-05 - 0.35, 0.0, 26.0, 13168.6, 8399.6, 2472.9, 11.7648, 6.5843e-05 - 0.35, 0.0, 30.0, 17653.6, 9705.4, 3720.3, 15.2909,8.826799999999999e-05 - 0.35, 0.0, 34.0, 21914.4, 10786.9, 5002.2, 18.1525,0.00010957200000000001 - 0.35, 0.0, 38.0, 26037.3, 11730.5, 6310.8, 20.5849, 0.0001301865 - 0.35, 0.0, 42.0, 30057.1, 12571.0, 7691.3, 43.1208,0.00015028549999999998 - 0.35, 0.0, 46.0, 33993.9, 13328.4, 9155.7, 67.9905,0.00016996950000000002 - 0.35, 0.0, 48.0, 35932.2, 13677.3, 9939.7, 76.3155,0.00017966099999999999 - 0.35, 0.0, 50.0, 37853.7, 14009.0, 10755.8, 81.718,0.00018926849999999999 - 0.35, 2000.0, 21.0, 7039.8, 5932.0, 999.1, 5.7509, 3.5199e-05 - 0.35, 2000.0, 22.0, 8159.4, 6386.9, 1257.8, 7.0693,4.0796999999999996e-05 - 0.35, 2000.0, 24.0, 10260.8, 7159.0, 1763.3, 9.2076,5.1303999999999995e-05 - 0.35, 2000.0, 26.0, 12247.3, 7816.1, 2255.9, 11.5847, 6.12365e-05 - 0.35, 2000.0, 30.0, 16416.2, 9030.9, 3397.3, 15.1257, 8.2081e-05 - 0.35, 2000.0, 34.0, 20375.6, 10036.0, 4575.8, 18.0083,0.00010187799999999999 - 0.35, 2000.0, 38.0, 24207.3, 10913.7, 5773.4, 20.4408,0.00012103649999999999 - 0.35, 2000.0, 42.0, 27941.9, 11694.1, 7047.4, 39.005,0.00013970950000000002 - 0.35, 2000.0, 46.0, 31598.2, 12396.5, 8403.2, 66.4441, 0.000157991 - 0.35, 2000.0, 48.0, 33398.3, 12719.4, 9133.8, 75.6132,0.00016699150000000002 - 0.35, 2000.0, 50.0, 35183.5, 13027.6, 9884.0, 81.3882, 0.0001759175 - 0.35, 5000.0, 21.0, 6297.7, 5306.8, 891.4, 5.1268, 3.14885e-05 - 0.35, 5000.0, 22.0, 7299.6, 5714.1, 1119.5, 6.4339, 3.6498e-05 - 0.35, 5000.0, 24.0, 9179.9, 6405.3, 1565.3, 8.5499,4.5899499999999997e-05 - 0.35, 5000.0, 26.0, 10957.1, 6993.4, 2000.3, 10.2625,5.4785500000000006e-05 - 0.35, 5000.0, 30.0, 14686.9, 8080.8, 3006.9, 14.3212, 7.34345e-05 - 0.35, 5000.0, 34.0, 18229.2, 8980.4, 4046.1, 17.1706,9.114600000000001e-05 - 0.35, 5000.0, 38.0, 21657.4, 9766.2, 5102.9, 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35000.0, 38.0, 14418.8, 11005.1, 2142.8, 13.0965, 144.188 + 0.9, 35000.0, 42.0, 15682.3, 11509.9, 2543.0, 14.6396, 156.823 + 0.9, 35000.0, 46.0, 16909.5, 11978.5, 2959.3, 16.0593, 169.095 + 0.9, 35000.0, 48.0, 17506.0, 12195.7, 3179.8, 16.7568, 175.06 + 0.9, 35000.0, 50.0, 18098.7, 12409.1, 3401.9, 17.4262, 180.98700000000002 + 0.9, 37000.0, 21.0, 7891.3, 7632.9, 559.6, 6.0554, 78.913 + 0.9, 37000.0, 22.0, 8217.1, 7803.6, 621.9, 4.6273, 82.171 + 0.9, 37000.0, 24.0, 8834.9, 8111.3, 766.2, 5.2826, 88.349 + 0.9, 37000.0, 26.0, 9431.0, 8397.2, 908.7, 6.3254, 94.31 + 0.9, 37000.0, 30.0, 10705.5, 8982.6, 1239.4, 8.326, 107.055 + 0.9, 37000.0, 34.0, 11924.9, 9512.8, 1581.3, 10.6732, 119.249 + 0.9, 37000.0, 38.0, 13099.4, 9998.1, 1940.8, 12.3857, 130.994 + 0.9, 37000.0, 42.0, 14247.6, 10457.1, 2302.0, 13.878, 142.476 + 0.9, 37000.0, 46.0, 15363.1, 10883.5, 2678.2, 15.2518, 153.631 + 0.9, 37000.0, 48.0, 15905.5, 11081.3, 2876.5, 15.9229, 159.055 + 0.9, 37000.0, 50.0, 16443.8, 11275.0, 3076.2, 16.5691, 164.438 + 0.9, 39000.0, 21.0, 7163.6, 6928.7, 514.4, 5.8837, 71.63600000000001 + 0.9, 39000.0, 22.0, 7459.9, 7084.2, 570.9, 4.5067, 74.599 + 0.9, 39000.0, 24.0, 8021.6, 7364.1, 701.6, 5.0624, 80.21600000000001 + 0.9, 39000.0, 26.0, 8563.7, 7624.5, 831.4, 6.0727, 85.63700000000001 + 0.9, 39000.0, 30.0, 9722.3, 8156.9, 1131.6, 7.9996, 97.223 + 0.9, 39000.0, 34.0, 10830.8, 8639.2, 1442.2, 10.2576, 108.30799999999999 + 0.9, 39000.0, 38.0, 11898.0, 9080.3, 1768.2, 11.9058, 118.98 + 0.9, 39000.0, 42.0, 12941.4, 9497.6, 2096.6, 13.3448, 129.414 + 0.9, 39000.0, 46.0, 13955.2, 9885.2, 2438.2, 14.6669, 139.55200000000002 + 0.9, 39000.0, 48.0, 14447.9, 10064.9, 2618.2, 15.3126, 144.479 + 0.9, 39000.0, 50.0, 14937.5, 10241.3, 2799.5, 15.9332, 149.375 diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 1d758b02c..a54cf8c03 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -53,3 +53,7 @@ def get_constraints(self): {'type': 'path', 'lower': 0.2}} return constraint_dict + + def get_parameters(self): + return {Aircraft.Battery.ENERGY_CAPACITY: {'units': 'kJ', 'val': 1.e4}, + Aircraft.Battery.EFFICIENCY: {'units': 'unitless', 'val': 0.95}} diff --git a/aviary/subsystems/energy/battery_sizing.py b/aviary/subsystems/energy/battery_sizing.py index c16d6d72e..bb7ccaad6 100644 --- a/aviary/subsystems/energy/battery_sizing.py +++ b/aviary/subsystems/energy/battery_sizing.py @@ -1,10 +1,8 @@ import openmdao.api as om -from openmdao.utils.units import convert_units - from aviary.utils.aviary_values import AviaryValues from aviary.variable_info.functions import add_aviary_input, add_aviary_output -from aviary.variable_info.variables import Aircraft, Dynamic +from aviary.variable_info.variables import Aircraft class SizeBattery(om.ExplicitComponent): @@ -18,26 +16,25 @@ def initialize(self): desc='collection of Aircraft/Mission specific options') def setup(self): - add_aviary_input(self, Aircraft.Battery.PACK_MASS, val=0.0, units='lbm', + add_aviary_input(self, Aircraft.Battery.PACK_MASS, val=0.0, units='kg', desc='mass of energy-storing components of battery') - add_aviary_input(self, Aircraft.Battery.ADDITIONAL_MASS, val=0.0, units='lbm', + add_aviary_input(self, Aircraft.Battery.ADDITIONAL_MASS, val=0.0, units='kg', desc='mass of non energy-storing components of battery') - add_aviary_input(self, Aircraft.Battery.PACK_ENERGY_DENSITY, val=0.0, units='kW*h/kg', + add_aviary_input(self, Aircraft.Battery.PACK_ENERGY_DENSITY, val=0.0, units='kJ/kg', desc='energy density of battery pack') add_aviary_output(self, Aircraft.Battery.MASS, val=0.0, - units='lbm', desc='total battery mass') + units='kg', desc='total battery mass') add_aviary_output(self, Aircraft.Battery.ENERGY_CAPACITY, val=0.0, units='kJ', desc='total battery energy storage') def compute(self, inputs, outputs): - energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] * 3600 + energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] addtl_mass = inputs[Aircraft.Battery.ADDITIONAL_MASS] - pack_mass_lbm = inputs[Aircraft.Battery.PACK_MASS] - pack_mass_kg = convert_units(pack_mass_lbm, 'lbm', 'kg') + pack_mass = inputs[Aircraft.Battery.PACK_MASS] - total_mass = pack_mass_lbm + addtl_mass - total_energy = pack_mass_kg * energy_density_kj_kg + total_mass = pack_mass + addtl_mass + total_energy = pack_mass * energy_density_kj_kg outputs[Aircraft.Battery.MASS] = total_mass outputs[Aircraft.Battery.ENERGY_CAPACITY] = total_energy @@ -54,11 +51,10 @@ def setup_partials(self): Aircraft.Battery.PACK_MASS, val=1.0) def compute_partials(self, inputs, J): - energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] * 3600 - # addtl_mass = inputs[Aircraft.Battery.ADDITIONAL_MASS] - pack_mass_kg = convert_units(inputs[Aircraft.Battery.PACK_MASS], 'lbm', 'kg') + energy_density_kj_kg = inputs[Aircraft.Battery.PACK_ENERGY_DENSITY] + pack_mass = inputs[Aircraft.Battery.PACK_MASS] J[Aircraft.Battery.ENERGY_CAPACITY, - Aircraft.Battery.PACK_ENERGY_DENSITY] = pack_mass_kg * 3600 + Aircraft.Battery.PACK_ENERGY_DENSITY] = pack_mass J[Aircraft.Battery.ENERGY_CAPACITY, - Aircraft.Battery.PACK_MASS] = energy_density_kj_kg * convert_units(1, 'lbm', 'kg') + Aircraft.Battery.PACK_MASS] = energy_density_kj_kg diff --git a/aviary/subsystems/energy/test/test_battery_in_a_mission.py b/aviary/subsystems/energy/test/test_battery_in_a_mission.py index a65471bea..c03de0cef 100644 --- a/aviary/subsystems/energy/test/test_battery_in_a_mission.py +++ b/aviary/subsystems/energy/test/test_battery_in_a_mission.py @@ -54,7 +54,8 @@ def test_subsystems_in_a_mission(self): prob = av.AviaryProblem() - prob.load_inputs("models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv", phase_info) + prob.load_inputs( + "models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv", phase_info) # Preprocess inputs prob.check_and_preprocess_inputs() @@ -68,7 +69,7 @@ def test_subsystems_in_a_mission(self): # Link phases and variables prob.link_phases() - prob.add_driver("SLSQP", max_iter=100) + prob.add_driver('SLSQP') prob.add_design_variables() @@ -78,10 +79,9 @@ def test_subsystems_in_a_mission(self): prob.set_initial_guesses() - prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kW*h/kg') - prob.set_val(av.Aircraft.Battery.PACK_MASS, 1200, units='lbm') + prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kJ/kg') + prob.set_val(av.Aircraft.Battery.PACK_MASS, 1000, units='lbm') prob.set_val(av.Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') - prob.set_val("traj.cruise.rhs_all.engine_deck.electric_power", 2., units='kW') prob.run_aviary_problem() From 211b3c1d9bfc74546156928310e92e286aca25a1 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Fri, 7 Jun 2024 16:21:59 -0500 Subject: [PATCH 07/17] Moving battery test --- .../benchmark_tests}/test_battery_in_a_mission.py | 4 +--- 1 file changed, 1 insertion(+), 3 deletions(-) rename aviary/{subsystems/energy/test => validation_cases/benchmark_tests}/test_battery_in_a_mission.py (97%) diff --git a/aviary/subsystems/energy/test/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py similarity index 97% rename from aviary/subsystems/energy/test/test_battery_in_a_mission.py rename to aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index c03de0cef..88ffa47a1 100644 --- a/aviary/subsystems/energy/test/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -1,7 +1,5 @@ -import numpy as np import unittest -from numpy.testing import assert_almost_equal from openmdao.utils.testing_utils import use_tempdirs import aviary.api as av @@ -9,7 +7,7 @@ from aviary.subsystems.energy.battery_builder import BatteryBuilder -# @use_tempdirs +@use_tempdirs class TestSubsystemsMission(unittest.TestCase): def setUp(self): self.phase_info = { From 5e33b3f8fc7e203928a9b21f09dc65c393bf9a00 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 10 Jun 2024 15:44:30 -0500 Subject: [PATCH 08/17] Removed state of charge constraint --- aviary/interface/test/test_timeseries_report.py | 2 +- aviary/mission/flops_based/ode/mission_ODE.py | 6 ++---- aviary/subsystems/energy/battery_builder.py | 12 +++++------- .../benchmark_tests/test_battery_in_a_mission.py | 3 +-- 4 files changed, 9 insertions(+), 14 deletions(-) diff --git a/aviary/interface/test/test_timeseries_report.py b/aviary/interface/test/test_timeseries_report.py index 7cbcdfa1c..b444c405a 100644 --- a/aviary/interface/test/test_timeseries_report.py +++ b/aviary/interface/test/test_timeseries_report.py @@ -9,7 +9,7 @@ from aviary.interface.methods_for_level1 import run_aviary -# @use_tempdirs +@use_tempdirs class AviaryMissionTimeseries(unittest.TestCase): def setUp(self): om.clear_reports() diff --git a/aviary/mission/flops_based/ode/mission_ODE.py b/aviary/mission/flops_based/ode/mission_ODE.py index 20272afee..794e75ba1 100644 --- a/aviary/mission/flops_based/ode/mission_ODE.py +++ b/aviary/mission/flops_based/ode/mission_ODE.py @@ -142,7 +142,7 @@ def setup(self): # Create a lightly modified version of an OM group to add external subsystems # to the ODE with a special configure() method that promotes # all aircraft:* and mission:* variables to the ODE. - external_subsystem_group = om.Group() + external_subsystem_group = ExternalSubsystemGroup() add_subsystem_group = False for subsystem in self.options['external_subsystems']: @@ -151,9 +151,7 @@ def setup(self): if subsystem_mission is not None: add_subsystem_group = True external_subsystem_group.add_subsystem(subsystem.name, - subsystem_mission, - promotes_inputs=['*'], - promotes_outputs=['*']) + subsystem_mission) # Only add the external subsystem group if it has at least one subsystem. # Without this logic there'd be an empty OM group added to the ODE. diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 57be44fda..92f5d9a01 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -49,11 +49,9 @@ def get_constraints(self): # constraint_dict = {f'path_{Dynamic.Mission.BATTERY_STATE_OF_CHARGE} = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE} - {Aircraft.Battery.DISCHARGE_LIMIT}': # {'type': 'path', # 'lower': 0.0}} - constraint_dict = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE: - {'type': 'path', - 'lower': 0.2}} + constraint_dict = { + # Dynamic.Mission.BATTERY_STATE_OF_CHARGE: + # {'type': 'path', + # 'lower': 0.2}, + } return constraint_dict - - def get_parameters(self, aviary_inputs=None, phase_info=None): - return {Aircraft.Battery.ENERGY_CAPACITY: {'units': 'kJ', 'val': 1.e4}, - Aircraft.Battery.EFFICIENCY: {'units': 'unitless', 'val': 0.95}} diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index 88ffa47a1..ba01ebc32 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -7,7 +7,7 @@ from aviary.subsystems.energy.battery_builder import BatteryBuilder -@use_tempdirs +# @use_tempdirs class TestSubsystemsMission(unittest.TestCase): def setUp(self): self.phase_info = { @@ -39,7 +39,6 @@ def setUp(self): "initial_bounds": ((0.0, 0.0), "min"), "duration_bounds": ((10., 30.), "min"), }, - "initial_guesses": {"times": ([0, 30], "min")}, }, 'post_mission': { 'include_landing': False, From 3dd14dea82d6cfffe2df7546adba78146d43cba9 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 10 Jun 2024 20:09:36 -0500 Subject: [PATCH 09/17] Cleaning up for PR --- .../battery/battery_variables.py | 2 +- aviary/models/engines/process_deck.py | 23 ------------------- aviary/models/engines/turbofan_28k.deck | 2 ++ 3 files changed, 3 insertions(+), 24 deletions(-) delete mode 100644 aviary/models/engines/process_deck.py diff --git a/aviary/examples/external_subsystems/battery/battery_variables.py b/aviary/examples/external_subsystems/battery/battery_variables.py index 5198ac736..551220281 100644 --- a/aviary/examples/external_subsystems/battery/battery_variables.py +++ b/aviary/examples/external_subsystems/battery/battery_variables.py @@ -41,7 +41,7 @@ class Cell: class Mission(AviaryMission): - class Battery(): + class Battery: CURRENT = "mission:battery:current" HEAT_OUT = "mission:battery:heat_out" STATE_OF_CHARGE = "mission:battery:state_of_charge" diff --git a/aviary/models/engines/process_deck.py b/aviary/models/engines/process_deck.py deleted file mode 100644 index d10787c11..000000000 --- a/aviary/models/engines/process_deck.py +++ /dev/null @@ -1,23 +0,0 @@ -import pandas as pd -import csv - - -# Read the CSV data into a DataFrame -df = pd.read_csv('turbofan_28k.deck') - -# Calculate the electric_power column -df['electric_power (kW)'] = df[' Gross_Thrust (lbf)'] * 1.e-2 - -# Define the output file name -output_file = 'turbofan_28k_with_electric.deck' - -# Write the DataFrame to a CSV file with the desired formatting -with open(output_file, mode='w', newline='') as file: - writer = csv.writer(file) - - # Write the header - writer.writerow(df.columns) - - # Write the data with formatted spacing - for index, row in df.iterrows(): - writer.writerow(['{:>20}'.format(item) for item in row]) diff --git a/aviary/models/engines/turbofan_28k.deck b/aviary/models/engines/turbofan_28k.deck index b3fe01619..4af2acf7c 100644 --- a/aviary/models/engines/turbofan_28k.deck +++ b/aviary/models/engines/turbofan_28k.deck @@ -1,3 +1,5 @@ +# FLOPS-derived engine deck converted from turbofan_28_ENGDEK + Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h) 0.0, 0.0, 21.0, 1446.4, 0.0, 842.2, 4.7876 0.0, 0.0, 22.0, 2314.3, 0.0, 976.0, 5.1926 From d6cdc09e8576891896631fbeb76c7e6b1a217dd8 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 24 Jun 2024 14:50:01 -0500 Subject: [PATCH 10/17] Addressing PR comments --- .../engine_NPSS/table_engine_builder.py | 2 +- .../interface/test/test_timeseries_report.py | 2 +- aviary/mission/flight_phase_builder.py | 4 +-- .../engines/turbofan_28k_with_electric.deck | 2 +- aviary/subsystems/energy/battery_builder.py | 31 +++++++++---------- aviary/subsystems/energy/test/test_battery.py | 6 ++-- aviary/subsystems/propulsion/engine_deck.py | 16 +++++----- .../subsystems/propulsion/engine_scaling.py | 28 ++++++++--------- .../propulsion/propulsion_mission.py | 18 +++++------ .../test/test_custom_engine_model.py | 2 +- .../test/test_propulsion_mission.py | 10 +++--- aviary/subsystems/propulsion/utils.py | 4 +-- aviary/utils/engine_deck_conversion.py | 2 +- .../test_battery_in_a_mission.py | 11 ++++++- aviary/variable_info/variable_meta_data.py | 23 +++++++------- aviary/variable_info/variables.py | 6 ++-- 16 files changed, 88 insertions(+), 79 deletions(-) diff --git a/aviary/examples/external_subsystems/engine_NPSS/table_engine_builder.py b/aviary/examples/external_subsystems/engine_NPSS/table_engine_builder.py index 0e3deab5d..1aaad993f 100644 --- a/aviary/examples/external_subsystems/engine_NPSS/table_engine_builder.py +++ b/aviary/examples/external_subsystems/engine_NPSS/table_engine_builder.py @@ -107,7 +107,7 @@ def build_mission(self, num_nodes, aviary_inputs): -engine_data[:, 4], units='lbm/s', desc='Current fuel flow rate ') - engine.add_output(Dynamic.Mission.ELECTRIC_POWER, + engine.add_output(Dynamic.Mission.ELECTRIC_POWER_IN, zeros_array, units='kW', desc='Current electric energy rate') diff --git a/aviary/interface/test/test_timeseries_report.py b/aviary/interface/test/test_timeseries_report.py index b444c405a..71a1cf94c 100644 --- a/aviary/interface/test/test_timeseries_report.py +++ b/aviary/interface/test/test_timeseries_report.py @@ -23,7 +23,7 @@ def test_timeseries_report(self): max_iter=0) expected_header = [ - "time (s)", "altitude (ft)", "altitude_rate (ft/s)", "distance (m)", "drag (lbf)", "electric_power_total (kW)", + "time (s)", "altitude (ft)", "altitude_rate (ft/s)", "distance (m)", "drag (lbf)", "electric_power_in_total (kW)", "fuel_flow_rate_negative_total (lbm/h)", "mach (unitless)", "mach_rate (unitless/s)", "mass (kg)", "specific_energy_rate_excess (m/s)", "throttle (unitless)", "thrust_net_total (lbf)", "velocity (m/s)" diff --git a/aviary/mission/flight_phase_builder.py b/aviary/mission/flight_phase_builder.py index 9c9b706b6..df2fbb9d7 100644 --- a/aviary/mission/flight_phase_builder.py +++ b/aviary/mission/flight_phase_builder.py @@ -257,8 +257,8 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO ) phase.add_timeseries_output( - Dynamic.Mission.ELECTRIC_POWER_TOTAL, - output_name=Dynamic.Mission.ELECTRIC_POWER_TOTAL, units='kW' + Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, + output_name=Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, units='kW' ) phase.add_timeseries_output( diff --git a/aviary/models/engines/turbofan_28k_with_electric.deck b/aviary/models/engines/turbofan_28k_with_electric.deck index 6c151d5a3..3ccbebe77 100644 --- a/aviary/models/engines/turbofan_28k_with_electric.deck +++ b/aviary/models/engines/turbofan_28k_with_electric.deck @@ -1,4 +1,4 @@ -Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h),electric_power (kW) +Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h),electric_power_in (kW) 0.0, 0.0, 21.0, 1446.4, 0.0, 842.2, 4.7876, 14.464 0.0, 0.0, 22.0, 2314.3, 0.0, 976.0, 5.1926, 23.143 0.0, 0.0, 24.0, 4049.9, 0.0, 1281.0, 6.6532, 40.499 diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 92f5d9a01..4d3a037d7 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -15,41 +15,40 @@ def get_mass_names(self): def build_mission(self, num_nodes, aviary_inputs=None) -> om.Group: battery_group = om.Group() - soc = om.ExecComp('state_of_charge = (energy_capacity - (electric_energy/efficiency)) / energy_capacity', + # Here, the efficiency variable is used as an overall efficiency for the battery + soc = om.ExecComp('state_of_charge = (energy_capacity - (cumulative_electric_energy_used/efficiency)) / energy_capacity', state_of_charge={'val': np.zeros( num_nodes), 'units': 'unitless'}, energy_capacity={'val': 10.0, 'units': 'kJ'}, - electric_energy={'val': np.zeros(num_nodes), 'units': 'kJ'}, + cumulative_electric_energy_used={ + 'val': np.zeros(num_nodes), 'units': 'kJ'}, efficiency={'val': 0.95, 'units': 'unitless'}) battery_group.add_subsystem('state_of_charge', subsys=soc, promotes_inputs=[('energy_capacity', Aircraft.Battery.ENERGY_CAPACITY), - ('electric_energy', - Dynamic.Mission.ELECTRIC_ENERGY), + ('cumulative_electric_energy_used', + Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED), ('efficiency', Aircraft.Battery.EFFICIENCY)], promotes_outputs=[('state_of_charge', Dynamic.Mission.BATTERY_STATE_OF_CHARGE)]) return battery_group def get_states(self): - state_dict = {Dynamic.Mission.ELECTRIC_ENERGY: {'fix_initial': True, - 'fix_final': False, - 'lower': 0.0, - 'ref': 1e4, - 'defect_ref': 1e6, - 'units': 'kJ', - 'rate_source': Dynamic.Mission.ELECTRIC_POWER_TOTAL, - 'input_initial': 0.0}} + state_dict = {Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED: {'fix_initial': True, + 'fix_final': False, + 'lower': 0.0, + 'ref': 1e4, + 'defect_ref': 1e6, + 'units': 'kJ', + 'rate_source': Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, + 'input_initial': 0.0}} return state_dict def get_constraints(self): - # discharge_limit = aviary_options.get_val(Aircraft.Battery.DISCHARGE_LIMIT) - # constraint_dict = {f'path_{Dynamic.Mission.BATTERY_STATE_OF_CHARGE} = {Dynamic.Mission.BATTERY_STATE_OF_CHARGE} - {Aircraft.Battery.DISCHARGE_LIMIT}': - # {'type': 'path', - # 'lower': 0.0}} constraint_dict = { + # Can add constraints here; state of charge is a common one in other battery applications # Dynamic.Mission.BATTERY_STATE_OF_CHARGE: # {'type': 'path', # 'lower': 0.2}, diff --git a/aviary/subsystems/energy/test/test_battery.py b/aviary/subsystems/energy/test/test_battery.py index e7510defb..356be1ae3 100644 --- a/aviary/subsystems/energy/test/test_battery.py +++ b/aviary/subsystems/energy/test/test_battery.py @@ -32,10 +32,10 @@ def test_battery_premission(self): prob.run_model() mass_expected = 1_315 - energy_expected = 1_077_735_471.12 + energy_expected = 1_077_735.47112 mass = prob.get_val(av.Aircraft.Battery.MASS, 'lbm') - energy = prob.get_val(av.Aircraft.Battery.ENERGY_CAPACITY, 'kJ') + energy = prob.get_val(av.Aircraft.Battery.ENERGY_CAPACITY, 'MJ') assert_near_equal(mass, mass_expected, tolerance=1e-10) assert_near_equal(energy, energy_expected, tolerance=1e-10) @@ -54,7 +54,7 @@ def test_battery_mission(self): av.Aircraft.Battery.ENERGY_CAPACITY, 10_000, units='kJ') prob.model.set_input_defaults( av.Aircraft.Battery.EFFICIENCY, efficiency, units='unitless') - prob.model.set_input_defaults(av.Dynamic.Mission.ELECTRIC_ENERGY, [ + prob.model.set_input_defaults(av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED, [ 0, 2_000, 5_000, 9_500], units='kJ') prob.setup(force_alloc_complex=True) diff --git a/aviary/subsystems/propulsion/engine_deck.py b/aviary/subsystems/propulsion/engine_deck.py index 9937662d4..fc5ca7dc4 100644 --- a/aviary/subsystems/propulsion/engine_deck.py +++ b/aviary/subsystems/propulsion/engine_deck.py @@ -54,7 +54,7 @@ SHAFT_POWER_CORRECTED = EngineModelVariables.SHAFT_POWER_CORRECTED RAM_DRAG = EngineModelVariables.RAM_DRAG FUEL_FLOW = EngineModelVariables.FUEL_FLOW -ELECTRIC_POWER = EngineModelVariables.ELECTRIC_POWER +ELECTRIC_POWER_IN = EngineModelVariables.ELECTRIC_POWER_IN NOX_RATE = EngineModelVariables.NOX_RATE TEMPERATURE = EngineModelVariables.TEMPERATURE_ENGINE_T4 # EXIT_AREA = EngineModelVariables.EXIT_AREA @@ -71,7 +71,7 @@ GROSS_THRUST: ['gross_thrust'], RAM_DRAG: ['ram_drag'], FUEL_FLOW: ['fuel', 'fuel_flow', 'fuel_flow_rate'], - ELECTRIC_POWER: 'electric_power', + ELECTRIC_POWER_IN: ['electric_power_in', 'electric_power'], NOX_RATE: ['nox', 'nox_rate'], TEMPERATURE: ['t4', 'temp', 'temperature'], SHAFT_POWER: ['shaft_power', 'shp'], @@ -286,7 +286,7 @@ def _set_variable_flags(self): # requires importing EngineModelVariables) self.use_thrust = THRUST in engine_variables or TAILPIPE_THRUST in engine_variables self.use_fuel = FUEL_FLOW in engine_variables - self.use_electricity = ELECTRIC_POWER in engine_variables + self.use_electricity = ELECTRIC_POWER_IN in engine_variables self.use_hybrid_throttle = HYBRID_THROTTLE in engine_variables self.use_nox = NOX_RATE in engine_variables self.use_t4 = TEMPERATURE in engine_variables @@ -785,9 +785,9 @@ def _build_engine_interpolator(self, num_nodes, aviary_inputs): self.data[FUEL_FLOW], units=units[FUEL_FLOW], desc='Current fuel flow rate (unscaled)') - engine.add_output('electric_power_unscaled', - self.data[ELECTRIC_POWER], - units=units[ELECTRIC_POWER], + engine.add_output('electric_power_in_unscaled', + self.data[ELECTRIC_POWER_IN], + units=units[ELECTRIC_POWER_IN], desc='Current electric energy rate (unscaled)') engine.add_output('nox_rate_unscaled', self.data[NOX_RATE], @@ -990,8 +990,8 @@ def build_mission(self, num_nodes, aviary_inputs) -> om.Group: 'engine_scaling.thrust_net_unscaled') engine_group.connect('interpolation.fuel_flow_rate_unscaled', 'engine_scaling.fuel_flow_rate_unscaled') - engine_group.connect('interpolation.electric_power_unscaled', - 'engine_scaling.electric_power_unscaled') + engine_group.connect('interpolation.electric_power_in_unscaled', + 'engine_scaling.electric_power_in_unscaled') engine_group.connect('interpolation.nox_rate_unscaled', 'engine_scaling.nox_rate_unscaled') if self.use_thrust: diff --git a/aviary/subsystems/propulsion/engine_scaling.py b/aviary/subsystems/propulsion/engine_scaling.py index 7c3cf72dd..2e93162c3 100644 --- a/aviary/subsystems/propulsion/engine_scaling.py +++ b/aviary/subsystems/propulsion/engine_scaling.py @@ -41,7 +41,7 @@ def setup(self): self.add_input('fuel_flow_rate_unscaled', val=np.zeros(nn), units='lbm/h', desc='Current fuel flow rate (unscaled)') - self.add_input('electric_power_unscaled', val=np.zeros(nn), + self.add_input('electric_power_in_unscaled', val=np.zeros(nn), units='kW', desc='Current electric power consumption (unscaled)') self.add_input('nox_rate_unscaled', val=np.zeros(nn), units='lbm/h', @@ -65,7 +65,7 @@ def setup(self): self.add_output(Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, val=np.zeros(nn), units='lbm/h', desc='Current fuel flow rate (negative)') - self.add_output(Dynamic.Mission.ELECTRIC_POWER, val=np.zeros(nn), + self.add_output(Dynamic.Mission.ELECTRIC_POWER_IN, val=np.zeros(nn), units='kW', desc='Current electric power consumption') self.add_output(Dynamic.Mission.NOX_RATE, val=np.zeros(nn), @@ -103,7 +103,7 @@ def compute(self, inputs, outputs): unscaled_net_thrust = inputs['thrust_net_unscaled'] unscaled_max_thrust = inputs['thrust_net_max_unscaled'] unscaled_fuel_flow_rate = inputs['fuel_flow_rate_unscaled'] - unscaled_electric_power = inputs['electric_power_unscaled'] + unscaled_electric_power_in = inputs['electric_power_in_unscaled'] unscaled_nox_rate = inputs['nox_rate_unscaled'] unscaled_shaft_power = inputs['shaft_power_unscaled'] unscaled_shaft_power_corrected = inputs['shaft_power_corrected_unscaled'] @@ -140,7 +140,7 @@ def compute(self, inputs, outputs): (unscaled_fuel_flow_rate * fuel_flow_scale_factor) - constant_fuel_flow # all other variables are just linearly scaled - outputs[Dynamic.Mission.ELECTRIC_POWER] = unscaled_electric_power * scale_factor + outputs[Dynamic.Mission.ELECTRIC_POWER_IN] = unscaled_electric_power_in * scale_factor outputs[Dynamic.Mission.NOX_RATE] = unscaled_nox_rate * scale_factor outputs[Dynamic.Mission.SHAFT_POWER] = unscaled_shaft_power * scale_factor outputs[Dynamic.Mission.SHAFT_POWER_CORRECTED] = unscaled_shaft_power_corrected * scale_factor @@ -187,13 +187,13 @@ def setup_partials(self): val=1.0) self.declare_partials( - Dynamic.Mission.ELECTRIC_POWER, + Dynamic.Mission.ELECTRIC_POWER_IN, Aircraft.Engine.SCALE_FACTOR, rows=r, cols=c, val=1.0) self.declare_partials( - Dynamic.Mission.ELECTRIC_POWER, - 'electric_power_unscaled', + Dynamic.Mission.ELECTRIC_POWER_IN, + 'electric_power_in_unscaled', rows=r, cols=r, val=1.0) @@ -260,7 +260,7 @@ def compute_partials(self, inputs, J): unscaled_net_thrust = inputs['thrust_net_unscaled'] unscaled_max_thrust = inputs['thrust_net_max_unscaled'] unscaled_fuel_flow_rate = inputs['fuel_flow_rate_unscaled'] - unscaled_electric_power = inputs['electric_power_unscaled'] + unscaled_electric_power_in = inputs['electric_power_in_unscaled'] unscaled_nox_rate = inputs['nox_rate_unscaled'] unscaled_shaft_power = inputs['shaft_power_unscaled'] unscaled_shaft_power_corrected = inputs['shaft_power_corrected_unscaled'] @@ -331,10 +331,10 @@ def compute_partials(self, inputs, J): # J[Dynamic.FUEL_FLOW_RATE_NEGATIVE, Aircraft.Engine.SCALE_FACTOR] = -np.ravel( # fuel_flow_scale_deriv) - # J[Dynamic.ELECTRIC_POWER, 'electric_power_unscaled'] = np.tile( + # J[Dynamic.ELECTRIC_POWER_IN, 'electric_power_in_unscaled'] = np.tile( # scale_factor, nn) - # J[Dynamic.ELECTRIC_POWER, Aircraft.Engine.SCALE_FACTOR] = np.ravel( - # unscaled_electric_power * deriv_factor) + # J[Dynamic.ELECTRIC_POWER_IN, Aircraft.Engine.SCALE_FACTOR] = np.ravel( + # unscaled_electric_power_in * deriv_factor) # J[Dynamic.NOX_RATE, 'nox_rate_unscaled'] = np.tile( # scale_factor, nn) @@ -358,9 +358,9 @@ def compute_partials(self, inputs, J): J[Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, Aircraft.Engine.SCALE_FACTOR] = fuel_flow_scale_deriv - J[Dynamic.Mission.ELECTRIC_POWER, 'electric_power_unscaled'] = scale_factor - J[Dynamic.Mission.ELECTRIC_POWER, - Aircraft.Engine.SCALE_FACTOR] = unscaled_electric_power * deriv_factor + J[Dynamic.Mission.ELECTRIC_POWER_IN, 'electric_power_in_unscaled'] = scale_factor + J[Dynamic.Mission.ELECTRIC_POWER_IN, + Aircraft.Engine.SCALE_FACTOR] = unscaled_electric_power_in * deriv_factor J[Dynamic.Mission.NOX_RATE, 'nox_rate_unscaled'] = scale_factor J[Dynamic.Mission.NOX_RATE, Aircraft.Engine.SCALE_FACTOR] = unscaled_nox_rate * deriv_factor diff --git a/aviary/subsystems/propulsion/propulsion_mission.py b/aviary/subsystems/propulsion/propulsion_mission.py index 610403bb7..503cef166 100644 --- a/aviary/subsystems/propulsion/propulsion_mission.py +++ b/aviary/subsystems/propulsion/propulsion_mission.py @@ -116,7 +116,7 @@ def setup(self): axis=1, units='lbm/h') perf_mux.add_var( - Dynamic.Mission.ELECTRIC_POWER, + Dynamic.Mission.ELECTRIC_POWER_IN, shape=(nn,), axis=1, units='kW') @@ -161,8 +161,8 @@ def setup(self): 'vectorize_performance.' + Dynamic.Mission.THRUST_MAX + '_' + str(i)) self.connect(engine.name + '.' + Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, 'vectorize_performance.' + Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE + '_' + str(i)) - self.connect(engine.name + '.' + Dynamic.Mission.ELECTRIC_POWER, - 'vectorize_performance.' + Dynamic.Mission.ELECTRIC_POWER + '_' + str(i)) + self.connect(engine.name + '.' + Dynamic.Mission.ELECTRIC_POWER_IN, + 'vectorize_performance.' + Dynamic.Mission.ELECTRIC_POWER_IN + '_' + str(i)) self.connect(engine.name + '.' + Dynamic.Mission.NOX_RATE, 'vectorize_performance.' + Dynamic.Mission.NOX_RATE + '_' + str(i)) @@ -219,7 +219,7 @@ def setup(self): val=np.zeros((nn, num_engine_type)), units='lbf') self.add_input(Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, val=np.zeros((nn, num_engine_type)), units='lbm/h') - self.add_input(Dynamic.Mission.ELECTRIC_POWER, + self.add_input(Dynamic.Mission.ELECTRIC_POWER_IN, val=np.zeros((nn, num_engine_type)), units='kW') self.add_input(Dynamic.Mission.NOX_RATE, val=np.zeros((nn, num_engine_type)), units='lbm/h') @@ -228,7 +228,7 @@ def setup(self): self.add_output(Dynamic.Mission.THRUST_MAX_TOTAL, val=np.zeros(nn), units='lbf') self.add_output(Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL, val=np.zeros(nn), units='lbm/h') - self.add_output(Dynamic.Mission.ELECTRIC_POWER_TOTAL, + self.add_output(Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, val=np.zeros(nn), units='kW') self.add_output(Dynamic.Mission.NOX_RATE_TOTAL, val=np.zeros(nn), units='lbm/h') @@ -252,8 +252,8 @@ def setup_partials(self): Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL, Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, val=deriv, rows=r, cols=c) self.declare_partials( - Dynamic.Mission.ELECTRIC_POWER_TOTAL, - Dynamic.Mission.ELECTRIC_POWER, val=deriv, rows=r, cols=c) + Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, + Dynamic.Mission.ELECTRIC_POWER_IN, val=deriv, rows=r, cols=c) self.declare_partials( Dynamic.Mission.NOX_RATE_TOTAL, Dynamic.Mission.NOX_RATE, @@ -265,12 +265,12 @@ def compute(self, inputs, outputs): thrust = inputs[Dynamic.Mission.THRUST] thrust_max = inputs[Dynamic.Mission.THRUST_MAX] fuel_flow = inputs[Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE] - electric = inputs[Dynamic.Mission.ELECTRIC_POWER] + electric = inputs[Dynamic.Mission.ELECTRIC_POWER_IN] nox = inputs[Dynamic.Mission.NOX_RATE] outputs[Dynamic.Mission.THRUST_TOTAL] = np.dot(thrust, num_engines) outputs[Dynamic.Mission.THRUST_MAX_TOTAL] = np.dot(thrust_max, num_engines) outputs[Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL] = np.dot( fuel_flow, num_engines) - outputs[Dynamic.Mission.ELECTRIC_POWER_TOTAL] = np.dot(electric, num_engines) + outputs[Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL] = np.dot(electric, num_engines) outputs[Dynamic.Mission.NOX_RATE_TOTAL] = np.dot(nox, num_engines) diff --git a/aviary/subsystems/propulsion/test/test_custom_engine_model.py b/aviary/subsystems/propulsion/test/test_custom_engine_model.py index d682914bc..8a7c365f5 100644 --- a/aviary/subsystems/propulsion/test/test_custom_engine_model.py +++ b/aviary/subsystems/propulsion/test/test_custom_engine_model.py @@ -61,7 +61,7 @@ def setup(self): shape=nn, units='lbm/s', desc='Current fuel flow rate (scaled)') - self.add_output(Dynamic.Mission.ELECTRIC_POWER, + self.add_output(Dynamic.Mission.ELECTRIC_POWER_IN, shape=nn, units='W', desc='Current electric energy rate (scaled)') diff --git a/aviary/subsystems/propulsion/test/test_propulsion_mission.py b/aviary/subsystems/propulsion/test/test_propulsion_mission.py index 1ad3d82f2..0ea367c4b 100644 --- a/aviary/subsystems/propulsion/test/test_propulsion_mission.py +++ b/aviary/subsystems/propulsion/test/test_propulsion_mission.py @@ -115,7 +115,7 @@ def test_propulsion_sum(self): np.array([[602.11, 3554], [100, 9000]])) self.prob.set_val(Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, np.array([[123, -221.44], [-765.2, -1]])) - self.prob.set_val(Dynamic.Mission.ELECTRIC_POWER, + self.prob.set_val(Dynamic.Mission.ELECTRIC_POWER_IN, np.array([[3.01, -12], [484.2, 8123]])) self.prob.set_val(Dynamic.Mission.NOX_RATE, np.array([[322, 4610], [1.54, 2.844]])) @@ -126,20 +126,20 @@ def test_propulsion_sum(self): thrust_max = self.prob.get_val(Dynamic.Mission.THRUST_MAX_TOTAL, units='lbf') fuel_flow = self.prob.get_val( Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL, units='lb/h') - electric_power = self.prob.get_val( - Dynamic.Mission.ELECTRIC_POWER_TOTAL, units='kW') + electric_power_in = self.prob.get_val( + Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, units='kW') nox = self.prob.get_val(Dynamic.Mission.NOX_RATE_TOTAL, units='lb/h') expected_thrust = np.array([2347.202, 14535]) expected_thrust_max = np.array([8914.33, 18300]) expected_fuel_flow = np.array([-73.88, -2297.6]) - expected_electric_power = np.array([-14.97, 17698.6]) + expected_electric_power_in = np.array([-14.97, 17698.6]) expected_nox = np.array([10186, 10.308]) assert_near_equal(thrust, expected_thrust, tolerance=1e-12) assert_near_equal(thrust_max, expected_thrust_max, tolerance=1e-12) assert_near_equal(fuel_flow, expected_fuel_flow, tolerance=1e-12) - assert_near_equal(electric_power, expected_electric_power, tolerance=1e-12) + assert_near_equal(electric_power_in, expected_electric_power_in, tolerance=1e-12) assert_near_equal(nox, expected_nox, tolerance=1e-12) partial_data = self.prob.check_partials(out_stream=None, method="cs") diff --git a/aviary/subsystems/propulsion/utils.py b/aviary/subsystems/propulsion/utils.py index 41485c87e..ba3949b9b 100644 --- a/aviary/subsystems/propulsion/utils.py +++ b/aviary/subsystems/propulsion/utils.py @@ -33,7 +33,7 @@ class EngineModelVariables(Enum): SHAFT_POWER_CORRECTED = auto() RAM_DRAG = auto() FUEL_FLOW = auto() - ELECTRIC_POWER = auto() + ELECTRIC_POWER_IN = auto() NOX_RATE = auto() TEMPERATURE_ENGINE_T4 = auto() # EXIT_AREA = auto() @@ -51,7 +51,7 @@ class EngineModelVariables(Enum): EngineModelVariables.SHAFT_POWER_CORRECTED: 'hp', EngineModelVariables.RAM_DRAG: 'lbf', EngineModelVariables.FUEL_FLOW: 'lb/h', - EngineModelVariables.ELECTRIC_POWER: 'kW', + EngineModelVariables.ELECTRIC_POWER_IN: 'kW', EngineModelVariables.NOX_RATE: 'lb/h', EngineModelVariables.TEMPERATURE_ENGINE_T4: 'degR' # EngineModelVariables.EXIT_AREA: 'ft**2', diff --git a/aviary/utils/engine_deck_conversion.py b/aviary/utils/engine_deck_conversion.py index 7faa40259..596a2086a 100644 --- a/aviary/utils/engine_deck_conversion.py +++ b/aviary/utils/engine_deck_conversion.py @@ -38,7 +38,7 @@ def __str__(self): SHAFT_POWER_CORRECTED = EngineModelVariables.SHAFT_POWER_CORRECTED RAM_DRAG = EngineModelVariables.RAM_DRAG FUEL_FLOW = EngineModelVariables.FUEL_FLOW -ELECTRIC_POWER = EngineModelVariables.ELECTRIC_POWER +ELECTRIC_POWER_IN = EngineModelVariables.ELECTRIC_POWER_IN NOX_RATE = EngineModelVariables.NOX_RATE TEMPERATURE = EngineModelVariables.TEMPERATURE_ENGINE_T4 # EXIT_AREA = EngineModelVariables.EXIT_AREA diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index ba01ebc32..3ffe0c2e7 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -1,13 +1,14 @@ import unittest from openmdao.utils.testing_utils import use_tempdirs +from openmdao.utils.assert_utils import assert_near_equal import aviary.api as av from aviary.subsystems.energy.battery_builder import BatteryBuilder -# @use_tempdirs +@use_tempdirs class TestSubsystemsMission(unittest.TestCase): def setUp(self): self.phase_info = { @@ -82,6 +83,14 @@ def test_subsystems_in_a_mission(self): prob.run_aviary_problem() + electric_energy_used = prob.get_val( + f'traj.cruise.timeseries.{av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', units='kW*h') + fuel_burned = prob.get_val(av.Mission.Summary.FUEL_BURNED, units='lbm') + + # Check outputs + assert_near_equal(electric_energy_used[-1], 42.5594728, 1.e-7) + assert_near_equal(fuel_burned, 805.8963261, 1.e-7) + if __name__ == "__main__": unittest.main() diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 56bd8efac..cd1d2bc77 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -227,19 +227,20 @@ add_meta_data( Aircraft.Battery.DISCHARGE_LIMIT, meta_data=_MetaData, - historical_name={"GASP": None, + historical_name={"GASP": 'INGASP.SOCMIN', "FLOPS": None, "LEAPS1": 'aircraft.inputs.L0_battery.depth_of_discharge' }, units='unitless', - desc='default constraint on how far the battery can discharge, as a percentage of ' - 'total energy capacity' + desc='default constraint on how far the battery can discharge, as a proportion of ' + 'total energy capacity', + default_value=0.2, ) add_meta_data( Aircraft.Battery.EFFICIENCY, meta_data=_MetaData, - historical_name={"GASP": None, + historical_name={"GASP": 'INGASP.EFF_BAT', "FLOPS": None, "LEAPS1": None }, @@ -250,7 +251,7 @@ add_meta_data( Aircraft.Battery.ENERGY_CAPACITY, meta_data=_MetaData, - historical_name={"GASP": None, + historical_name={"GASP": 'EBATTAVL', "FLOPS": None, "LEAPS1": None }, @@ -261,7 +262,7 @@ add_meta_data( Aircraft.Battery.MASS, meta_data=_MetaData, - historical_name={"GASP": None, + historical_name={"GASP": 'INGASP.WBATTIN', "FLOPS": None, "LEAPS1": 'aircraft.inputs.L0_battery.weight' }, @@ -273,7 +274,7 @@ add_meta_data( Aircraft.Battery.PACK_ENERGY_DENSITY, meta_data=_MetaData, - historical_name={"GASP": None, + historical_name={"GASP": 'INGASP.ENGYDEN', "FLOPS": None, "LEAPS1": 'aircraft.inputs.L0_battery.energy_density' }, @@ -6213,18 +6214,18 @@ ) add_meta_data( - Dynamic.Mission.ELECTRIC_ENERGY, + Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED, meta_data=_MetaData, historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None }, units='kJ', - desc='Total amount of electric energy consumed by the vehicle across the mission', + desc='Total amount of electric energy consumed by the vehicle up until this point in the mission', ) add_meta_data( - Dynamic.Mission.ELECTRIC_POWER, + Dynamic.Mission.ELECTRIC_POWER_IN, meta_data=_MetaData, historical_name={"GASP": None, "FLOPS": None, @@ -6236,7 +6237,7 @@ ) add_meta_data( - Dynamic.Mission.ELECTRIC_POWER_TOTAL, + Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, meta_data=_MetaData, historical_name={"GASP": None, "FLOPS": None, diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 75185dba2..13945e0bb 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -600,9 +600,9 @@ class Mission: DISTANCE_RATE = 'distance_rate' DRAG = 'drag' DYNAMIC_PRESSURE = 'dynamic_pressure' - ELECTRIC_ENERGY = 'electric_energy' - ELECTRIC_POWER = 'electric_power' - ELECTRIC_POWER_TOTAL = 'electric_power_total' + CUMULATIVE_ELECTRIC_ENERGY_USED = 'cumulative_electric_energy_used' + ELECTRIC_POWER_IN = 'electric_power_in' + ELECTRIC_POWER_IN_TOTAL = 'electric_power_in_total' # EXIT_AREA = 'exit_area' FLIGHT_PATH_ANGLE = 'flight_path_angle' FLIGHT_PATH_ANGLE_RATE = 'flight_path_angle_rate' From df84b0177717edc27165f852bc6e7c2674db8325 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 24 Jun 2024 15:26:36 -0500 Subject: [PATCH 11/17] Added in state of charge constraint --- aviary/subsystems/energy/battery_builder.py | 9 ++++++--- 1 file changed, 6 insertions(+), 3 deletions(-) diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 4d3a037d7..010c79a7b 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -7,6 +7,8 @@ class BatteryBuilder(SubsystemBuilderBase): + default_name = 'battery' + def build_pre_mission(self, aviary_inputs=None): return SizeBattery(aviary_inputs=aviary_inputs) @@ -49,8 +51,9 @@ def get_states(self): def get_constraints(self): constraint_dict = { # Can add constraints here; state of charge is a common one in other battery applications - # Dynamic.Mission.BATTERY_STATE_OF_CHARGE: - # {'type': 'path', - # 'lower': 0.2}, + f'battery.{Dynamic.Mission.BATTERY_STATE_OF_CHARGE}': + {'type': 'boundary', + 'loc': 'final', + 'lower': 0.2}, } return constraint_dict From d5582b6dc1a9940e1b6b63e8ddcdff49b58f5f5f Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 24 Jun 2024 15:28:32 -0500 Subject: [PATCH 12/17] Better ordering of variables --- aviary/variable_info/variable_meta_data.py | 25 +++++++++++----------- aviary/variable_info/variables.py | 2 +- 2 files changed, 13 insertions(+), 14 deletions(-) diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index cd1d2bc77..d36b0a20d 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -6158,6 +6158,17 @@ desc="battery's current state of charge" ) +add_meta_data( + Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='kJ', + desc='Total amount of electric energy consumed by the vehicle up until this point in the mission', +) + add_meta_data( Dynamic.Mission.DENSITY, meta_data=_MetaData, @@ -6213,17 +6224,6 @@ desc="Atmospheric dynamic pressure at the vehicle's current flight condition" ) -add_meta_data( - Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units='kJ', - desc='Total amount of electric energy consumed by the vehicle up until this point in the mission', -) - add_meta_data( Dynamic.Mission.ELECTRIC_POWER_IN, meta_data=_MetaData, @@ -6232,8 +6232,7 @@ "LEAPS1": None }, units='kW', - desc='Current electric power consumption of the vehicle, per single instance of ' - 'each engine model' + desc='Current electric power consumption of each engine', ) add_meta_data( diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 13945e0bb..31e3cae43 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -595,12 +595,12 @@ class Mission: ALTITUDE_RATE = 'altitude_rate' ALTITUDE_RATE_MAX = 'altitude_rate_max' BATTERY_STATE_OF_CHARGE = 'battery_state_of_charge' + CUMULATIVE_ELECTRIC_ENERGY_USED = 'cumulative_electric_energy_used' DENSITY = 'density' DISTANCE = 'distance' DISTANCE_RATE = 'distance_rate' DRAG = 'drag' DYNAMIC_PRESSURE = 'dynamic_pressure' - CUMULATIVE_ELECTRIC_ENERGY_USED = 'cumulative_electric_energy_used' ELECTRIC_POWER_IN = 'electric_power_in' ELECTRIC_POWER_IN_TOTAL = 'electric_power_in_total' # EXIT_AREA = 'exit_area' From db020acc2c155b3dec4c3d7266bc2d610658b21e Mon Sep 17 00:00:00 2001 From: johnjasa Date: Mon, 24 Jun 2024 16:52:17 -0500 Subject: [PATCH 13/17] Fixed battery test --- aviary/subsystems/test/subsystem_tester.py | 3 ++- 1 file changed, 2 insertions(+), 1 deletion(-) diff --git a/aviary/subsystems/test/subsystem_tester.py b/aviary/subsystems/test/subsystem_tester.py index 860ec6eca..771ceb003 100644 --- a/aviary/subsystems/test/subsystem_tester.py +++ b/aviary/subsystems/test/subsystem_tester.py @@ -335,11 +335,12 @@ def test_check_constraints(self): inputs = prob.model.list_inputs(out_stream=None, prom_name=True) outputs = prob.model.list_outputs(out_stream=None, prom_name=True) + name = self.subsystem_builder.default_name for key, value in constraints.items(): # Check constraint existence constraint_exists = (any(key == output[1]['prom_name'] for output in outputs) or any( - key == input[1]['prom_name'] for input in inputs)) + key == input[1]['prom_name'] for input in inputs) or any(key == f'{name}.{output[1]["prom_name"]}' for output in outputs) or any(key == f'{name}.{input[1]["prom_name"]}' for input in inputs)) self.assertTrue(constraint_exists, f"Constraint '{key}' not found in the model.") From 1fa83a96437c0e7ac08e7a34b8b6e7634e7e64a2 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Tue, 25 Jun 2024 10:52:43 -0500 Subject: [PATCH 14/17] More PR feedback --- aviary/subsystems/propulsion/engine_model.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/subsystems/propulsion/engine_model.py b/aviary/subsystems/propulsion/engine_model.py index cf6301b5e..f0dc330b5 100644 --- a/aviary/subsystems/propulsion/engine_model.py +++ b/aviary/subsystems/propulsion/engine_model.py @@ -40,7 +40,7 @@ class EngineModel(SubsystemBuilderBase): default_name = 'engine_model' def __init__( - self, name: str = None, options: AviaryValues = AviaryValues(), meta_data: dict = None, + self, name: str = None, options: AviaryValues = None, meta_data: dict = None, ): super().__init__(name, meta_data=meta_data) if options is not None: From c0a6ed2e00b2e068b0e3af2418b0cdf803437f47 Mon Sep 17 00:00:00 2001 From: crecine <51181861+crecine@users.noreply.github.com> Date: Tue, 25 Jun 2024 10:44:30 -0700 Subject: [PATCH 15/17] Update aviary/variable_info/variable_meta_data.py fixed units for volume Co-authored-by: Jason Kirk <110835404+jkirk5@users.noreply.github.com> --- aviary/variable_info/variable_meta_data.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index d36b0a20d..84ffd6814 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -303,7 +303,7 @@ "FLOPS": None, "LEAPS1": None }, - units='kW*h/kg', + units='kW*h/L', desc='volumetric density of the battery pack', default_value=0, ) From 8616a0268bedf5d6f143e59ca364066613051b0f Mon Sep 17 00:00:00 2001 From: John Jasa Date: Tue, 25 Jun 2024 12:57:01 -0500 Subject: [PATCH 16/17] Apply suggestions from code review Co-authored-by: crecine <51181861+crecine@users.noreply.github.com> --- aviary/subsystems/energy/battery_builder.py | 2 +- aviary/subsystems/energy/test/test_battery.py | 1 + .../benchmark_tests/test_battery_in_a_mission.py | 1 + 3 files changed, 3 insertions(+), 1 deletion(-) diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 010c79a7b..635063ec9 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -50,7 +50,7 @@ def get_states(self): def get_constraints(self): constraint_dict = { - # Can add constraints here; state of charge is a common one in other battery applications + # Can add constraints here; state of charge is a common one in many battery applications f'battery.{Dynamic.Mission.BATTERY_STATE_OF_CHARGE}': {'type': 'boundary', 'loc': 'final', diff --git a/aviary/subsystems/energy/test/test_battery.py b/aviary/subsystems/energy/test/test_battery.py index 356be1ae3..22b528aab 100644 --- a/aviary/subsystems/energy/test/test_battery.py +++ b/aviary/subsystems/energy/test/test_battery.py @@ -79,3 +79,4 @@ def setUp(self): if __name__ == '__main__': unittest.main() + diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index 3ffe0c2e7..3c84b8a59 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -94,3 +94,4 @@ def test_subsystems_in_a_mission(self): if __name__ == "__main__": unittest.main() + From 155c8b2701c4ab35f707ec455593d88aab437248 Mon Sep 17 00:00:00 2001 From: johnjasa Date: Tue, 25 Jun 2024 13:10:09 -0500 Subject: [PATCH 17/17] Removing EOF lines --- aviary/subsystems/energy/test/test_battery.py | 1 - .../benchmark_tests/test_battery_in_a_mission.py | 1 - 2 files changed, 2 deletions(-) diff --git a/aviary/subsystems/energy/test/test_battery.py b/aviary/subsystems/energy/test/test_battery.py index 22b528aab..356be1ae3 100644 --- a/aviary/subsystems/energy/test/test_battery.py +++ b/aviary/subsystems/energy/test/test_battery.py @@ -79,4 +79,3 @@ def setUp(self): if __name__ == '__main__': unittest.main() - diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index 3c84b8a59..3ffe0c2e7 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -94,4 +94,3 @@ def test_subsystems_in_a_mission(self): if __name__ == "__main__": unittest.main() -