def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
['wing_area', 72.72, (65.0, 85.0), 100., Units.meter**2],
['aspect_ratio', 8.6, (7.6, 10.6), 100.0, Units.less],
# ['taper_ratio', 0.3275, (0.2875, 0.4275), 1., Units.less],
['t_c_ratio', 0.11, (0.09, 0.15), 1., Units.less],
['sweep_angle', 23., (18.0, 35.0), 100.0, Units.deg],
['cruise_range', 1109.0, (800., 1350.), 10000.0, Units.nautical_miles],
['beta', 1., (1., 1.), 1., Units.less],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
# ['fuel_burn', 10000., Units.kg],
['objective', 10000., Units.kg],
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
# CONSTRAINTS ARE SET TO BE BIGGER THAN ZERO, SEE PROCEDURE (SciPy's SLSQP optimization algorithm assumes this form)
problem.constraints = np.array([
# ['design_range_margin', '=', 0., 100., Units.nautical_miles], # Range consistency
['fuel_margin', '>', 0., 1000.,
Units.kg], #fuel margin defined here as fuel
['Throttle_min', '>', 0., 1., Units.less],
['Throttle_max', '>', 0., 1., Units.less],
['tofl_mtow_margin', '>', 0., 100., Units.m], # take-off field length
['mzfw_consistency', '>', 0., 1000., Units.kg], # MZFW consistency
['design_range_ub', '>', 0., 1.,
Units.nautical_miles], # Range consistency
['design_range_lb', '>', 0., 1.,
Units.nautical_miles], # Range consistency
['time_to_climb', '>', 0., 10.,
Units.min], # Time to climb consistency
['climb_gradient', '>', 0., 1.,
Units.less], # second segment climb gradient
['lfl_mlw_margin', '>', 0., 100., Units.m], # landing field length
['max_fuel_margin', '>', 0., 1000., Units.kg], # max fuel margin
# ['range_HH_margin', '>', 0., 1000., Units.nautical_miles], # Range for Hot and High
['TOW_HH_margin', '>', 0., 1000., Units.kg], # TOW for Hot and High
# ['MTOW', '>', 0., 100000., Units.kg], # TOW for Hot and High
# ['BOW', '>', 0., 1., Units.kg], # TOW for Hot and High
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[
'wing_area',
[
'vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area'
]
],
[
'aspect_ratio',
'vehicle_configurations.*.wings.main_wing.aspect_ratio'
],
# ['taper_ratio', 'vehicle_configurations.*.wings.main_wing.taper' ],
[
't_c_ratio',
'vehicle_configurations.*.wings.main_wing.thickness_to_chord'
],
[
'sweep_angle',
'vehicle_configurations.*.wings.main_wing.sweeps.quarter_chord'
],
['cruise_range', 'missions.base.segments.cruise.distance'],
# ['fuel_burn', 'summary.base_mission_fuelburn' ],
['fuel_margin', 'summary.fuel_margin'],
['Throttle_min', 'summary.throttle_min'],
['Throttle_max', 'summary.throttle_max'],
['tofl_mtow_margin', 'summary.takeoff_field_length_margin'],
['mzfw_consistency', 'summary.mzfw_consistency'],
# ['design_range_margin', 'summary.design_range_margin'],
['design_range_ub', 'summary.design_range_ub'],
['design_range_lb', 'summary.design_range_lb'],
['time_to_climb', 'summary.time_to_climb'],
['climb_gradient', 'summary.climb_gradient'],
['lfl_mlw_margin', 'summary.lfl_mlw_margin'],
['max_fuel_margin', 'summary.max_fuel_margin'],
# ['range_HH_margin', 'summary.range_HH_margin'],
['TOW_HH_margin', 'summary.TOW_HH_margin'],
# ['MTOW', 'summary.MTOW'],
# ['BOW', 'summary.BOW'],
['beta', 'vehicle_configurations.base.wings.main_wing.beta'],
['objective', 'summary.objective'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
[ 'wing_area' , 95 , ( 90. , 130. ) , 100. , Units.meter**2],
[ 'cruise_altitude' , 11 , ( 9 , 14. ) , 10. , Units.km],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
[ 'fuel_burn', 10000, Units.kg ]
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
[ 'design_range_fuel_margin' , '>', 0., 1E-1, Units.less], #fuel margin defined here as fuel
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[ 'wing_area' , ['vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area' ]],
[ 'cruise_altitude' , 'missions.base.segments.climb_5.altitude_end' ],
[ 'fuel_burn' , 'summary.base_mission_fuelburn' ],
[ 'design_range_fuel_margin' , 'summary.max_zero_fuel_margin' ],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
['wing_aspect_ratio', 2.7935, (1., 7.), 2.7935, Units.less],
['wing_area', 68.172, (50., 80.), 68.172, Units.meter**2],
['cruise_airspeed', 450., (40., 120.), 70., Units.knots],
['climb1_airspeed', 268.25, (100.0, 200.0), 268.25, Units.knots],
['climb2_airspeed', 326.56, (300.0, 400.0), 326.56, Units.knots],
['descent1_airspeed', 440.0, (400.0, 500.0), 440.0, Units.knots],
['descent2_airspeed', 250.0, (200.0, 300.0), 250.0, Units.knots],
['climb1_altitude', 3., (1., 5.), 3., Units.km],
['climb2_altitude', 11.28, (7., 15.), 11.28, Units.km],
['descent1_altitude', 3.657, (2., 7.), 3.657, Units.km],
['climb1_rate', 15.24, (5., 20.), 15.24, Units['m/s']],
['climb2_rate', 9.14, (3., 10.), 9.14, Units['m/s']],
['descent1_rate', 11.68, (3., 15.), 11.68, Units['m/s']],
['descent2_rate', 7.62, (2., 10.), 7.62, Units['m/s']],
['voltage', 461., (100., 700.), 461., Units.watts],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([['range', -10, Units.nautical_miles]])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
#[ 'energy_constraint', '=', 0.0, 1.0, Units.less],
['battery_mass', '>', 0.0, 1.0, Units.kg],
#[ 'CL' , '>', 0.0, 1.0, Units.less],
['Throttle_min', '>', 0.0, 1.0, Units.less],
['Throttle_max', '>', 0.0, 1.0, Units.less],
['HL_rpm', '>=', 0.0, 100, Units['rpm']],
['cruise_rpm', '>=', 0.0, 100, Units['rpm']],
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[
'wing_aspect_ratio',
'vehicle_configurations.*.wings.main_wing.aspect_ratio'
],
[
'wing_area',
'vehicle_configurations.*.wings.main_wing.areas.reference'
],
['cruise_airspeed', 'missions.mission.segments.cruise.air_speed'],
['climb1_airspeed', 'missions.mission.segments.climb_1.air_speed'],
['climb2_airspeed', 'missions.mission.segments.climb_2.air_speed'],
['descent1_airspeed', 'missions.mission.segments.descent_1.air_speed'],
['descent2_airspeed', 'missions.mission.segments.descent_2.air_speed'],
['climb1_altitude', 'missions.mission.segments.climb_1.altitude_end'],
['climb2_altitude', 'missions.mission.segments.climb_2.altitude_end'],
[
'descent1_altitude',
'missions.mission.segments.descent_1.altitude_end'
],
['climb1_rate', 'missions.mission.segments.climb_1.climb_rate'],
['climb2_rate', 'missions.mission.segments.climb_2.climb_rate'],
['descent1_rate', 'missions.mission.segments.descent_1.descent_rate'],
['descent2_rate', 'missions.mission.segments.descent_2.descent_rate'],
['voltage', 'vehicle_configurations.*.propulsors.propulsor.voltage'],
['range', 'nexus.missions.mission.total_range'],
[
'battery_mass',
'vehicle_configurations.base.propulsors.network.battery.mass_properties.mass'
],
['Throttle_min', 'summary.throttle_min'],
['Throttle_max', 'summary.throttle_max'],
['HL_rpm', 'state.conditions.propulsion.rpm_lift'],
['cruise_rpm', 'state.conditions.propulsion.rpm_forward'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses,
nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup(solver_name):
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
nexus.solver_name = solver_name
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
problem.inputs = np.array([
# [ tag , initial,( lb , ub ) , scaling , units ]
['x1', 1., (-2., 2.), 1., Units.less],
['x2', 1., (-2., 2.), 1., Units.less],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([['y', 1., Units.less]])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
['x1', '>', -10., 1., Units.less],
['x2', '>', -50., 1., Units.less],
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
# don't set wing_area for initial configuration so that values can be used later
problem.aliases = [
['x1', 'vehicle_configurations.base.x1'],
['x2', 'vehicle_configurations.base.x2'],
['y', 'obj'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = vehicle_opt_pack.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = None
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = None
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = procedure_opt_pack.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
problem.inputs = np.array([
# Variable inputs
['wing_area', 700., (650., 725.), 500., Units.meter**2],
['MTOW', 207e3, (207e3, 207e3), 200e3, Units.kg],
['alt_outgoing_cruise', 13.14, (9., 14.), 13.,
Units.km], # 13.15 #explain the physics behing the optimizer
['design_thrust', 110e3, (100e3, 120e3), 100e3, Units.N],
['outgoing_cruise_speed', 190., (180., 212.), 200.,
Units['m/s']], # 191
['spray_cruise_speed', 210., (205., 212.), 200, Units['m/s']],
['cruise1_distance', 1050., (1000., 1200.), 1075., Units.km],
['cruise2_distance', 1173., (1000., 1300.), 1225., Units.km],
['cruise3_distance', 1001., (900., 1200.), 1000., Units.km],
['cruise_outgoing_distance', 3393., (3200., 3500.), 3300., Units.km],
# climb throttle as input?
# "Set" inputs
['AR', 13., (12., 14.), 13.,
Units.less], # aerosol released per kg of fuel ratio max?
['payload', 35e3, (35e3, 35e3), 30e3, Units.kg],
# speeds???
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([['fuel_burn', 60000., Units.kg]])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
# ['min_throttle', '>', 0., 1e-1, Units.less],
['max_throttle', '<', 1., 1., Units.less],
# ['main_mission_time', '<', 11.1, 10, Units.h],
['design_range_fuel_margin', '>', 0.1, 1E-1, Units.less],
# ['take_off_field_length', '<', 2500., 2500, Units.m],
# ['landing_field_length', '<', 2500., 2500, Units.m],
['clmax', '<', 1.1, 1, Units.less],
['non_spraying_range', '>', 3500., 3500., Units.km],
['spraying_range', '>', 3500., 3500., Units.km]
# main mission range
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[
'wing_area',
[
'vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area'
]
],
[
'MTOW',
[
'vehicle_configurations.*.mass_properties.takeoff',
"vehicle_configurations.*.mass_properties.max_takeoff"
]
],
[
'alt_outgoing_cruise',
'missions.base.segments.final_outgoing.altitude_end'
],
[
'design_thrust',
'vehicle_configurations.*.propulsors.turbofan.thrust.total_design'
],
[
'spray_cruise_speed',
[
'missions.base.segments.cruise_1.air_speed',
'missions.base.segments.cruise_2.air_speed',
'missions.base.segments.cruise_final.air_speed'
]
],
[
'outgoing_cruise_speed',
'missions.base.segments.cruise_outgoing.air_speed'
],
['AR', 'vehicle_configurations.*.wings.main_wing.aspect_ratio'],
[
'payload',
[
'vehicle_configurations.*.mass_properties.max_payload',
'vehicle_configurations.*.mass_properties.payload'
]
],
['fuel_burn', 'summary.base_mission_fuelburn'],
['min_throttle', 'summary.min_throttle'],
['max_throttle', 'summary.max_throttle'],
['main_mission_time', 'summary.main_mission_time'],
['mission_range', 'summary.mission_range'],
['clmax', 'summary.clmax'],
['design_range_fuel_margin', 'summary.max_zero_fuel_margin'],
['take_off_field_length', 'summary.field_length_takeoff'],
['landing_field_length', 'summary.field_length_landing'],
['MTOW_delta', 'summary.MTOW_delta'],
['cruise_speed', 'missions.base.segments.cruise_empty.air_speed'],
['cruise1_distance', 'missions.base.segments.cruise_1.distance'],
['cruise2_distance', 'missions.base.segments.cruise_2.distance'],
['cruise3_distance', 'missions.base.segments.cruise_final.distance'],
[
'cruise_outgoing_distance',
'missions.base.segments.cruise_outgoing.distance'
],
['non_spraying_range', 'summary.empty_range'],
['spraying_range', 'summary.spray_range'],
# [
# "missions.base.segments.cruise_highlift.air_speed",
#
# "missions.base.segments.cruise_2.air_speed"]],
# ['return_cruise_speed', "missions.base.segments.cruise_final.air_speed"],
['oswald', 'vehicle_configurations.*.wings.main_wing.span_efficiency'],
['cruise_altitude', "missions.base.segments.climb_8.altitude_end"],
['return_cruise_alt', 'missions.base.segments.descent_1.altitude_end'],
[
'bypass',
'vehicle_configurations.*.propulsors.turbofan.bypass_ratio'
],
['wing_sweep', 'vehicle_configurations.*.wings.main_wing.sweep'],
['oew', 'summary.op_empty'],
['Nothing', 'summary.nothing'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Mission.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
['wing_area', 72.72, (72.72, 72.72), 100., Units.meter**2],
['aspect_ratio', 8.6, (8.6, 8.6), 10.0, Units.less],
['taper_ratio', 0.3275, (0.3275, 0.3275), 1., Units.less],
['t_c_ratio', 0.11, (0.11, 0.11), 1., Units.less],
['sweep_angle', 23.0, (23.0, 23.0), 100.0, Units.deg],
['cruise_range', 1088., (1000., 1200.), 10000.0, Units.nautical_miles],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
['Nothing', 1., Units.kg],
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
# CONSTRAINTS ARE SET TO BE BIGGER THAN ZERO, SEE PROCEDURE (SciPy's SLSQP optimization algorithm assumes this form)
problem.constraints = np.array([
# ['design_range_fuel_margin', '>', 0., 1E-1, Units.less], #fuel margin defined here as fuel
['fuel_margin', '>', 0., 1000., Units.kg], # fuel tank volume capacity
# ['CL', '>', 0, 1., Units.less],
['Throttle_min', '>', 0., 1., Units.less],
['Throttle_max', '>', 0., 1., Units.less],
['tofl_mtow_margin', '>', 0., 100., Units.m], # take-off field length
['mzfw_consistency', '>', 0., 1000., Units.kg], # MZFW consistency
['design_range_ub', '>', 0., 1., Units.nautical_miles], # Range consistency
['design_range_lb', '>', 0., 1., Units.nautical_miles], # Range consistency
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
['wing_area', ['vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area' ]],
['aspect_ratio', 'vehicle_configurations.*.wings.main_wing.aspect_ratio' ],
['taper_ratio', 'vehicle_configurations.*.wings.main_wing.taper' ],
['t_c_ratio', 'vehicle_configurations.*.wings.main_wing.thickness_to_chord' ],
['sweep_angle', 'vehicle_configurations.*.wings.main_wing.sweeps.quarter_chord'],
['cruise_range', 'missions.base.segments.cruise.distance' ],
# ['fuel_burn', 'summary.base_mission_fuelburn' ],
# ['design_range_fuel_margin', 'summary.max_zero_fuel_margin' ],
['fuel_margin', 'summary.fuel_margin' ],
# ['CL', 'summary.CL'],
['Throttle_min', 'summary.throttle_min' ],
['Throttle_max', 'summary.throttle_max' ],
['Nothing', 'summary.nothing' ],
['tofl_mtow_margin', 'summary.takeoff_field_length_margin' ],
['mzfw_consistency', 'summary.mzfw_consistency' ],
['design_range_ub', 'summary.design_range_ub' ],
['design_range_lb', 'summary.design_range_lb' ],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
[ 'wing_span' , 9.4 , ( 9.4 , 15. ) , 9.4 , Units.meter],
[ 'wing_root_chord' , 2. , ( 1. , 4. ) , 2. , Units.meter],
[ 'cruise_distance' , 150. , ( 50. , 300. ) , 150. , Units.nautical_miles],
[ 'cruise_airspeed' , 200. , ( 90. , 300. ) , 200. , Units['m/s']],
[ 'climb1_airspeed' , 125.0 , ( 50.0 , 150.0 ) , 125.0 , Units['m/s']],
[ 'climb2_airspeed' , 190.0 , ( 70.0 , 250.0 ) , 190.0 , Units['m/s']],
[ 'descent1_airspeed' , 180.0 , ( 100. , 270. ) , 180.0 , Units['m/s']],
[ 'descent2_airspeed' , 145.0 , ( 50. , 170.0 ) , 145.0 , Units['m/s']],
[ 'climb1_altitude' , 3. , ( 1. , 5. ) , 3. , Units.km],
[ 'climb2_altitude' , 8.0 , ( 7. , 15. ) , 8.0 , Units.km],
[ 'descent1_altitude' , 3.0 , ( 2. , 7. ) , 3.0 , Units.km],
[ 'climb1_rate' , 6.0 , ( 3. , 12. ) , 6.0 , Units['m/s']],
[ 'climb2_rate' , 3.0 , ( 2. , 6. ) , 3.0 , Units['m/s']],
[ 'descent1_rate' , 4.5 , ( 3. , 10. ) , 4.5 , Units['m/s']],
[ 'descent2_rate' , 3.0 , ( 2. , 7. ) , 3.0 , Units['m/s']],
[ 'voltage' , 461. , ( 100. , 700. ) , 461. , Units['volt']],
[ 'motor_kv_cruise' , 180. , ( 80. , 220. ) , 180. , Units['rpm/volt']],
[ 'motor_kv_HL' , 90. , ( 30. , 120. ) , 90. , Units['rpm/volt']],
#[ 'bat_spec_energy' , 4500. , ( 300. , 4600. ) , 4500. , Units.Wh/Units.kg],
#[ 'bat_spec_power' , 0.837 , ( 0.5 , 10. ) , 0.837 , Units.kW/Units.kg],
#[ 'bat_max_voltage' , 60000. , ( 0.5 , 100000 ) , 60000. , Units['volt']],
#[ 'bat_resistance' , 0.0153 , ( 0.0001 , 50. ) , 0.0153 , Units['ohm']],
#[ 'payload_draw' , 50. , ( 5. , 50000. ) , 50. , Units.watts],
#[ 'avionics_draw' , 50. , ( 5. , 50000. ) , 50. , Units.watts],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
[ 'range', -540.9079921321364, Units.nautical_miles ]
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
#[ 'energy_constraint', '=', 0.0, 1.0, Units.less],
[ 'battery_energy' , '>', -0.1, 1.0, Units.Wh ],
#[ 'battery_draw' , '>', -0.1, 1.0, Units.kW ],
#[ 'CL' , '>', 0.0, 1.0, Units.less],
[ 'Throttle_cruise' , '>', -0.1, 1.0, Units.less],
#[ 'Throttle_HL' , '>', -0.1, 1.0, Units.less],
[ 'HL_rpm' , '>', -0.1, 1.0, Units['rpm']],
[ 'cruise_rpm' , '>', -0.1, 1.0, Units['rpm']],
[ 'lift_coefficient' , '>', -0.1, 1.0, Units.less],
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[ 'wing_span' , 'vehicle_configurations.*.wings.main_wing.spans.projected' ],
[ 'wing_root_chord' , 'vehicle_configurations.*.wings.main_wing.chords.root' ],
[ 'cruise_distance' , 'missions.mission.segments.cruise.distance' ],
[ 'cruise_airspeed' , 'missions.mission.segments.cruise.air_speed' ],
[ 'climb1_airspeed' , 'missions.mission.segments.climb_1.air_speed' ],
[ 'climb2_airspeed' , 'missions.mission.segments.climb_2.air_speed' ],
[ 'descent1_airspeed' , 'missions.mission.segments.descent_1.air_speed' ],
[ 'descent2_airspeed' , 'missions.mission.segments.descent_2.air_speed' ],
[ 'climb1_altitude' , 'missions.mission.segments.climb_1.altitude_end' ],
[ 'climb2_altitude' , 'missions.mission.segments.climb_2.altitude_end' ],
[ 'descent1_altitude' , 'missions.mission.segments.descent_1.altitude_end' ],
[ 'climb1_rate' , 'missions.mission.segments.climb_1.climb_rate' ],
[ 'climb2_rate' , 'missions.mission.segments.climb_2.climb_rate' ],
[ 'descent1_rate' , 'missions.mission.segments.descent_1.descent_rate' ],
[ 'descent2_rate' , 'missions.mission.segments.descent_2.descent_rate' ],
[ 'voltage' , 'vehicle_configurations.*.propulsors.propulsor.voltage' ],
[ 'motor_kv_cruise' , 'vehicle_configurations.*.propulsors.propulsor.motor_forward.kv' ],
[ 'motor_kv_HL' , 'vehicle_configurations.*.propulsors.propulsor.motor_lift.kv' ],
#[ 'bat_spec_energy' , 'vehicle_configurations.*.propulsors.propulsor.battery.specific_energy' ],
#[ 'bat_spec_power' , 'vehicle_configurations.*.propulsors.propulsor.battery.specific_power' ],
#[ 'bat_max_voltage' , 'vehicle_configurations.*.propulsors.propulsor.battery.max_voltage' ],
#[ 'bat_resistance' , 'vehicle_configurations.*.propulsors.propulsor.battery.resistance' ],
#[ 'payload_draw' , 'vehicle_configurations.*.propulsors.propulsor.payload.power_draw' ],
#[ 'avionics_draw' , 'vehicle_configurations.*.propulsors.propulsor.avionics.power_draw' ],
[ 'range' , 'missions.mission.total_range' ],
[ 'battery_energy' , 'results.base.conditions.battery_energy_all_segments' ],
#[ 'battery_draw' , 'results.base.conditions.battery_charging_power_all_segments' ],
[ 'Throttle_cruise' , 'results.base.conditions.throttle_all_segments' ],
#[ 'Throttle_HL' , 'results.base.conditions.lift_throttle_all_segments' ],
[ 'HL_rpm' , 'results.base.conditions.rpm_lift_all_segments' ],
[ 'cruise_rpm' , 'results.base.conditions.rpm_forward_all_segments' ],
[ 'lift_coefficient' , 'results.base.conditions.lift_coefficient_all_segments' ],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses,nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
problem.inputs = np.array([
# Variable inputs
['wing_area', 700., (650., 725.), 500., Units.meter ** 2],
['MTOW', 207e3, (207e3, 207e3), 200e3, Units.kg],
['alt_outgoing_cruise', 13.14, (9., 14.), 13., Units.km], # 13.15 #explain the physics behing the optimizer
['design_thrust', 110e3, (100e3, 120e3), 100e3, Units.N],
['outgoing_cruise_speed', 190., (180., 212.), 200., Units['m/s']], # 191
['spray_cruise_speed', 210., (205., 212.), 200, Units['m/s']],
['cruise1_distance', 1050., (1000., 1200.), 1075., Units.km],
['cruise2_distance', 1173., (1000., 1300.), 1225., Units.km],
['cruise3_distance', 1001., (900., 1200.), 1000., Units.km],
['cruise_outgoing_distance', 3393., (3200., 3500.), 3300., Units.km],
# climb throttle as input?
# "Set" inputs
['AR', 13., (12., 14.), 13., Units.less], # aerosol released per kg of fuel ratio max?
['payload', 35e3, (35e3, 35e3), 30e3, Units.kg],
# speeds???
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
['fuel_burn', 60000., Units.kg]
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
# ['min_throttle', '>', 0., 1e-1, Units.less],
['max_throttle', '<', 1., 1., Units.less],
# ['main_mission_time', '<', 11.1, 10, Units.h],
['design_range_fuel_margin', '>', 0.1, 1E-1, Units.less],
# ['take_off_field_length', '<', 2500., 2500, Units.m],
# ['landing_field_length', '<', 2500., 2500, Units.m],
['clmax', '<', 1.1, 1, Units.less],
['non_spraying_range', '>', 3500., 3500., Units.km],
['spraying_range', '>', 3500., 3500., Units.km]
# main mission range
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
['wing_area', ['vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area']],
['MTOW', ['vehicle_configurations.*.mass_properties.takeoff',
"vehicle_configurations.*.mass_properties.max_takeoff"]],
['alt_outgoing_cruise', 'missions.base.segments.final_outgoing.altitude_end'],
['design_thrust', 'vehicle_configurations.*.propulsors.turbofan.thrust.total_design'],
['spray_cruise_speed', ['missions.base.segments.cruise_1.air_speed',
'missions.base.segments.cruise_2.air_speed',
'missions.base.segments.cruise_final.air_speed']],
['outgoing_cruise_speed', 'missions.base.segments.cruise_outgoing.air_speed'],
['AR', 'vehicle_configurations.*.wings.main_wing.aspect_ratio'],
['payload', ['vehicle_configurations.*.mass_properties.max_payload',
'vehicle_configurations.*.mass_properties.payload']],
['fuel_burn', 'summary.base_mission_fuelburn'],
['min_throttle', 'summary.min_throttle'],
['max_throttle', 'summary.max_throttle'],
['main_mission_time', 'summary.main_mission_time'],
['mission_range', 'summary.mission_range'],
['clmax', 'summary.clmax'],
['design_range_fuel_margin', 'summary.max_zero_fuel_margin'],
['take_off_field_length', 'summary.field_length_takeoff'],
['landing_field_length', 'summary.field_length_landing'],
['MTOW_delta', 'summary.MTOW_delta'],
['cruise_speed', 'missions.base.segments.cruise_empty.air_speed'],
['cruise1_distance', 'missions.base.segments.cruise_1.distance'],
['cruise2_distance', 'missions.base.segments.cruise_2.distance'],
['cruise3_distance', 'missions.base.segments.cruise_final.distance'],
['cruise_outgoing_distance', 'missions.base.segments.cruise_outgoing.distance'],
['non_spraying_range', 'summary.empty_range'],
['spraying_range', 'summary.spray_range'],
# [
# "missions.base.segments.cruise_highlift.air_speed",
#
# "missions.base.segments.cruise_2.air_speed"]],
# ['return_cruise_speed', "missions.base.segments.cruise_final.air_speed"],
['oswald', 'vehicle_configurations.*.wings.main_wing.span_efficiency'],
['cruise_altitude', "missions.base.segments.climb_8.altitude_end"],
['return_cruise_alt', 'missions.base.segments.descent_1.altitude_end'],
['bypass', 'vehicle_configurations.*.propulsors.turbofan.bypass_ratio'],
['wing_sweep', 'vehicle_configurations.*.wings.main_wing.sweep'],
['oew', 'summary.op_empty'],
['Nothing', 'summary.nothing'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Mission.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
return nexus
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units]
problem.inputs = np.array([
['wing_area', 61.10657012722955, (50.0, 72.0), 61., Units.meter**2],
['aspect_ratio', 12.088302121797874, (10., 14.), 12.0, Units.less],
['t_c_ratio', 0.15015861116831478, (0.11, 0.18), 0.15, Units.less],
[
'cruise_range', 331.5017418, (310., 350.), 331.3,
Units.nautical_miles
],
['MTOW', 23029.880482, (21000., 25000.), 23000., Units.kg],
['MZFW_ratio', 0.912817661, (0.8, 0.98), 0.92, Units.less],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
# throw an error if the user isn't specific about wildcards
# [ tag, scaling, units ]
problem.objective = np.array([
['objective', 23000., Units.kg],
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
# CONSTRAINTS ARE SET TO BE BIGGER THAN ZERO, SEE PROCEDURE (SciPy's SLSQP optimization algorithm assumes this form)
problem.constraints = np.array([
['mzfw_consistency', '=', 0., 1000., Units.kg], # MZFW consistency
['fuel_margin', '=', 0., 1000.,
Units.kg], # fuel margin defined here as fuel
['Throttle_min', '>', 0., 1., Units.less],
['Throttle_max', '>', 0., 1., Units.less],
['tofl_mtow_margin', '>', 0., 100., Units.m], # take-off field length
['design_range_ub', '>', 0., 10.,
Units.nautical_miles], # Range consistency
['design_range_lb', '>', 0., 10.,
Units.nautical_miles], # Range consistency
['time_to_climb', '>', 0., 10.,
Units.min], # Time to climb consistency
['climb_gradient', '>', 0., 1.,
Units.less], # second segment climb gradient
['lfl_mlw_margin', '>', 0., 100., Units.m], # landing field length
['max_fuel_margin', '>', 0., 100., Units.kg], # max fuel margin
['TOW_HH_margin', '>', 0., 100., Units.kg], # TOW for Hot and High
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
# [ 'alias' , ['data.path1.name','data.path2.name'] ]
problem.aliases = [
[
'wing_area',
[
'vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area'
]
],
[
'aspect_ratio',
'vehicle_configurations.*.wings.main_wing.aspect_ratio'
],
[
't_c_ratio',
'vehicle_configurations.*.wings.main_wing.thickness_to_chord'
],
[
'sweep_angle',
'vehicle_configurations.*.wings.main_wing.sweeps.quarter_chord'
],
['cruise_range', 'missions.base.segments.cruise.distance'],
['fuel_margin', 'summary.fuel_margin'],
['Throttle_min', 'summary.throttle_min'],
['Throttle_max', 'summary.throttle_max'],
['tofl_mtow_margin', 'summary.takeoff_field_length_margin'],
['mzfw_consistency', 'summary.mzfw_consistency'],
['design_range_ub', 'summary.design_range_ub'],
['design_range_lb', 'summary.design_range_lb'],
['time_to_climb', 'summary.time_to_climb'],
['climb_gradient', 'summary.climb_gradient'],
['lfl_mlw_margin', 'summary.lfl_mlw_margin'],
['max_fuel_margin', 'summary.max_fuel_margin'],
['TOW_HH_margin', 'summary.TOW_HH_margin'],
[
'MTOW',
[
'vehicle_configurations.*.mass_properties.max_takeoff',
'vehicle_configurations.*.mass_properties.takeoff'
]
],
['MZFW_ratio', 'summary.MZFW_ratio'],
['beta', 'vehicle_configurations.base.wings.main_wing.beta'],
['objective', 'summary.objective'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = Vehicles.setup()
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
nexus.analyses.vehicle = Data()
nexus.analyses.vehicle = nexus.vehicle_configurations.base
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.total_number_of_iterations = 0
nexus.beta = Data()
nexus.beta = 1.
return nexus
