def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
['wing_area', 61., (50.0, 72.0), 61., Units.meter**2],
['aspect_ratio', 12., (10., 14.), 12.0, Units.less],
['t_c_ratio', 0.15, (0.11, 0.18), 0.15, Units.less],
# ['sweep_angle', 3., (0., 10.0), 3.0, Units.deg],
# ['taper_ratio', 0.53, (0.53, 0.53), 1., Units.less],
['cruise_range', 331.3, (310., 350.), 331.3, Units.nautical_miles],
['delta_fuel', 8.8, (0., 80.), 40., Units.kg], # MTOW consistency
# ['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([
# ['Nothing', 1., Units.kg],
['objective', 10., Units.less],
])
# -------------------------------------------------------------------
# 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_ub', '>', 0., 1000., Units.kg], # MTOW consistency
['fuel_margin_lb', '>', 0., 1000., Units.kg], # MTOW consistency
['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' ],
['delta_fuel', 'vehicle_configurations.base.delta_fuel' ],
['Nothing', 'summary.nothing' ],
# ['fuel_burn', 'summary.base_mission_fuelburn' ],
['fuel_margin_ub', 'summary.fuel_margin_ub' ],
['fuel_margin_lb', 'summary.fuel_margin_lb' ],
['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)
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
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, (lb,ub) , scaling , units ]
problem.inputs = np.array([
['wing_area', 68.35899318, (65.0, 80.0), 75., Units.meter**2],
['aspect_ratio', 9.423509209, (7.6, 9.8), 9.8, Units.less],
['t_c_ratio', 0.139063312, (0.09, 0.15), 0.13, Units.less],
['sweep_angle', 30., (18.0, 30.0), 30.0, Units.deg],
[
'cruise_range', 1114.55358764, (1000., 1160.), 1130.0,
Units.nautical_miles
],
['MTOW', 36777.7116079, (35000., 39000.), 37200., Units.kg],
['MZFW_ratio', 0.812216071, (0.7, 0.9), 0.9, 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', 1., Units.less],
])
# -------------------------------------------------------------------
# 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., 100., Units.kg], # MZFW consistency
['fuel_margin', '=', 0., 100.,
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)
# -------------------------------------------------------------------
# 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
