def main():
#initialize the problem
nexus = Nexus()
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
nexus.missions = Missions.setup(nexus.analyses)
#problem = Data()
#nexus.optimization_problem = problem
nexus.procedure = setup()
nexus.sizing_loop = Sizing_Loop()
nexus.total_number_of_iterations = 0
evaluate_problem(nexus)
results = nexus.results
err = nexus.sizing_loop.norm_error
err_true = 0.00975078 #for 1E-2 tol
error = abs((err-err_true)/err)
print 'error = ', error
assert(error<1e-5), 'sizing loop regression failed'
#output=nexus._really_evaluate() #run; use optimization setup without inputs
return
def main():
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
analyses = mission_B737.analyses_setup(configs)
mission = mission_setup(configs,analyses)
configs.finalize()
analyses.finalize()
results = mission.evaluate()
results = results.merged()
plot_results(results)
distance_regression = 4317710.33719722
distance_calc = results.conditions.frames.inertial.position_vector[-1,0]
error_distance = abs((distance_regression - distance_calc )/distance_regression)
assert error_distance < 1e-6
error_weight = abs(mission.target_landing_weight - results.conditions.weights.total_mass[-1,0])
print('landing weight error' , error_weight)
assert error_weight < 1e-6
return
def main():
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
analyses = mission_B737.analyses_setup(configs)
mission = mission_setup(configs, analyses)
configs.finalize()
analyses.finalize()
results = mission.evaluate()
results = results.merged()
plot_results(results)
distance_regression = 4317710.33719722
distance_calc = results.conditions.frames.inertial.position_vector[-1, 0]
error_distance = abs(
(distance_regression - distance_calc) / distance_regression)
assert error_distance < 1e-6
error_weight = abs(mission.target_landing_weight -
results.conditions.weights.total_mass[-1, 0])
print('landing weight error', error_weight)
assert error_weight < 1e-6
return
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
stability = SUAVE.Analyses.Stability.AVL()
aerodynamics.geometry = copy.deepcopy(configs.cruise)
stability.geometry = copy.deepcopy(configs.cruise)
aerodynamics.process.compute.lift.inviscid.training_file = 'base_data_aerodynamics.txt'
stability.training_file = 'base_data_stability.txt'
configs_analyses.cruise.append(aerodynamics)
configs_analyses.cruise.append(stability)
# mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# lift coefficient check
lift_coefficient = results.conditions.cruise.aerodynamics.lift_coefficient[
0]
lift_coefficient_true = 0.59571034
print lift_coefficient
diff_CL = np.abs(lift_coefficient - lift_coefficient_true)
print 'CL difference'
print diff_CL
assert np.abs((lift_coefficient - lift_coefficient_true) /
lift_coefficient_true) < 1e-6
# moment coefficient check
moment_coefficient = results.conditions.cruise.stability.static.CM[0][0]
moment_coefficient_true = -0.62167644
print moment_coefficient
diff_CM = np.abs(moment_coefficient - moment_coefficient_true)
print 'CM difference'
print diff_CM
assert np.abs((moment_coefficient - moment_coefficient_true) /
moment_coefficient_true) < 1e-6
return
def main():
# Setup for converging on weight
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
analyses = mission_B737.analyses_setup(configs)
mission = mission_setup(configs, analyses)
configs.finalize()
analyses.finalize()
results = mission.evaluate()
results = results.merged()
plot_results(results)
distance_regression = 3804806.720225211
distance_calc = results.conditions.frames.inertial.position_vector[-1, 0]
print('distance_calc = ', distance_calc)
error_distance = abs(
(distance_regression - distance_calc) / distance_regression)
assert error_distance < 1e-6
error_weight = abs(mission.target_landing_weight -
results.conditions.weights.total_mass[-1, 0])
print('landing weight error', error_weight)
assert error_weight < 1e-6
# Setup for converging on SOC, using the stopped rotor vehicle
vehicle_SR, analyses_SR = full_setup_SR()
analyses_SR.finalize()
mission_SR = analyses_SR.mission
results_SR = mission_SR.evaluate()
results_SR = results_SR.merged()
distance_regression_SR = 101649.83535243798
distance_calc_SR = results_SR.conditions.frames.inertial.position_vector[
-1, 0]
print('distance_calc_SR = ', distance_calc_SR)
error_distance_SR = abs(
(distance_regression_SR - distance_calc_SR) / distance_regression_SR)
assert error_distance_SR < 1e-6
error_soc = abs(
mission_SR.target_state_of_charge -
results_SR.conditions.propulsion.battery_state_of_charge[-1, 0])
print('landing state of charge error', error_soc)
assert error_soc < 1e-6
return
def main():
#initialize the problem
nexus = Nexus()
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
nexus.missions = Missions.setup(nexus.analyses)
problem = Data()
problem_inputs = np.array([
['dummy', 1., (.1, 10.), 1., ' continuous', Units.less],
['dummy2', 2., (.1, 10.), 1., ' continuous', Units.less],
]) #create dummy inputs for optimization to test io
problem.inputs = problem_inputs
nexus.optimization_problem = problem
nexus.procedure = setup()
sizing_loop = Sizing_Loop()
sizing_loop.output_filename = 'sizing_outputs.txt'
nexus.sizing_loop = sizing_loop
#create a fake array of data to test outputs
write_sizing_outputs(sizing_loop, np.array([6.]), [5., 5.])
write_sizing_outputs(sizing_loop, np.array([12.]), [4., 1.])
write_sizing_outputs(sizing_loop, np.array([11.]), [1., 3.])
nexus.total_number_of_iterations = 0
evaluate_problem(nexus)
results = nexus.results
err = nexus.sizing_loop.norm_error
err_true = 0.0008433474527249522 #for 1E-2 tol
error = abs((err - err_true) / err_true)
data_inputs, data_outputs, read_success = read_sizing_residuals(
sizing_loop, problem.inputs)
check_read_res = -0.06803060191281879
error_res = (data_outputs[1][0] - check_read_res) / check_read_res
#remove files for later
os.remove('sizing_outputs.txt')
os.remove('y_err_values.txt')
print('error = ', error)
print('error_res = ', error_res)
assert (error < 1e-4), 'sizing loop regression failed'
assert (error_res < 1e-4), 'sizing loop io failed'
return
def full_setup():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
return configs, analyses
def full_setup():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
return configs, analyses
def main():
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
analyses = mission_B737.analyses_setup(configs)
mission = mission_setup(configs,analyses)
vehicle.mass_properties.takeoff = 70000 * Units.kg
configs.finalize()
analyses.finalize()
results = mission.evaluate()
results = results.merged()
plot_results(results)
error = abs(mission.target_landing_weight - results.conditions.weights.total_mass[-1,0])
print 'landing weight error' , error
assert error < 1.
return
def main():
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
analyses = mission_B737.analyses_setup(configs)
mission = mission_setup(configs, analyses)
vehicle.mass_properties.takeoff = 70000 * Units.kg
configs.finalize()
analyses.finalize()
results = mission.evaluate()
results = results.merged()
plot_results(results)
error = abs(mission.target_landing_weight -
results.conditions.weights.total_mass[-1, 0])
print 'landing weight error', error
assert error < 1.
return
def main():
#initialize the problem
nexus = Nexus()
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
nexus.missions = Missions.setup(nexus.analyses)
nexus.procedure = setup()
nexus.sizing_loop = Sizing_Loop()
nexus.total_number_of_iterations = 0
evaluate_problem(nexus)
results = nexus.results
err = nexus.sizing_loop.norm_error
err_true = 0.0096907307307155348#for 1E-2 tol
error = abs((err_true-err)/err_true)
print 'error = ', error
assert(error<1e-6), 'sizing loop regression failed'
return
def main():
#initialize the problem
nexus = Nexus()
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
nexus.missions = Missions.setup(nexus.analyses)
nexus.procedure = setup()
nexus.sizing_loop = Sizing_Loop()
nexus.total_number_of_iterations = 0
evaluate_problem(nexus)
results = nexus.results
err = nexus.sizing_loop.norm_error
err_true = 0.0096907307307155348 #for 1E-2 tol
error = abs((err_true - err) / err_true)
print 'error = ', error
assert (error < 1e-6), 'sizing loop regression failed'
return
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# append AVL aerodynamic analysis
aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
aerodynamics.process.compute.lift.inviscid.regression_flag = True
aerodynamics.process.compute.lift.inviscid.keep_files = True
aerodynamics.geometry = copy.deepcopy(configs.cruise)
aerodynamics.process.compute.lift.inviscid.training_file = 'cruise_data_aerodynamics.txt'
configs_analyses.cruise.append(aerodynamics)
# append AVL stability analysis
stability = SUAVE.Analyses.Stability.AVL()
stability.regression_flag = True
stability.keep_files = True
stability.geometry = copy.deepcopy(configs.cruise)
stability.training_file = 'cruise_data_stability.txt'
configs_analyses.cruise.append(stability)
# ------------------------------------------------------------------
# Initialize the Mission
# ------------------------------------------------------------------
mission = SUAVE.Analyses.Mission.Sequential_Segments()
mission.tag = 'the_mission'
#airport
airport = SUAVE.Attributes.Airports.Airport()
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
mission.airport = airport
# unpack Segments module
Segments = SUAVE.Analyses.Mission.Segments
# base segment
base_segment = Segments.Segment()
# ------------------------------------------------------------------
# Cruise Segment: constant speed, constant altitude
# ------------------------------------------------------------------
segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment)
segment.tag = "cruise"
segment.analyses.extend( configs_analyses.cruise )
segment.air_speed = 230. * Units['m/s']
segment.distance = 4000. * Units.km
segment.altitude = 10.668 * Units.km
segment.state.numerics.number_control_points = 4
# add to mission
mission.append_segment(segment)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# lift coefficient check
lift_coefficient = results.segments.cruise.conditions.aerodynamics.lift_coefficient[0][0]
lift_coefficient_true = 0.6118979131570086
print(lift_coefficient)
diff_CL = np.abs(lift_coefficient - lift_coefficient_true)
print('CL difference')
print(diff_CL)
assert np.abs((lift_coefficient - lift_coefficient_true)/lift_coefficient_true) < 1e-6
# moment coefficient check
moment_coefficient = results.segments.cruise.conditions.stability.static.CM[0][0]
moment_coefficient_true = -0.6267104237340391
print(moment_coefficient)
diff_CM = np.abs(moment_coefficient - moment_coefficient_true)
print('CM difference')
print(diff_CM)
assert np.abs((moment_coefficient - moment_coefficient_true)/moment_coefficient_true) < 1e-6
return
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, [lb,ub], scaling, units ]
problem.inputs = np.array([
['wing_area', 124.8, (70., 200.), 124.8, Units.meter**2],
['wing_aspect_ratio', 10.18, (5., 20.), 10.18, Units.less],
['wing_sweep', 25., (0., 35.), 25., Units.degrees],
['wing_thickness', 0.105, (0.07, 0.20), 0.105, Units.less],
['design_thrust', 52700., (10000., 70000.), 52700., Units.N],
['MTOW', 79090., (20000., 100000.), 79090., Units.kg],
['MZFW_ratio', 0.77, (0.6, 0.99), 0.77, Units.less],
['flap_takeoff_angle', 10., (0., 20.), 10., Units.degrees],
['flap_landing_angle', 40., (0., 50.), 40., Units.degrees],
['short_field_TOW', 64030., (20000., 100000.), 64030., Units.kg],
['design_TOW', 68520., (20000., 100000.), 68520., Units.kg],
['noise_takeoff_speed_increase', 10.0, (10., 20.), 10.0, Units.knots],
['noise_cutback_altitude', 304.8, (240., 400.), 304.8, Units.meter],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
problem.objective = np.array([
['noise_cumulative_margin', 17, Units.less],
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
['MZFW consistency', '>', 0., 10, Units.less],
['design_range_fuel_margin', '>', 0., 10, Units.less],
['short_field_fuel_margin', '>', 0., 10, Units.less],
['max_range_fuel_margin', '>', 0., 10, Units.less],
['wing_span', '<', 35.9664, 35.9664, Units.less],
['noise_flyover_margin', '>', 0., 10., Units.less],
['noise_sideline_margin', '>', 0., 10., Units.less],
['noise_approach_margin', '>', 0., 10., Units.less],
['takeoff_field_length', '<', 1985., 1985., Units.meters],
['landing_field_length', '<', 1385., 1385., Units.meters],
['2nd_segment_climb_max_range', '>', 0.024, 0.024, Units.less],
['2nd_segment_climb_short_field', '>', 0.024, 0.024, Units.less],
['max_throttle', '<', 1., 1., Units.less],
['short_takeoff_field_length', '<', 1330., 1330., Units.meters],
['noise_cumulative_margin', '>', 10., 10., Units.less],
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
problem.aliases = [
[
'wing_area',
[
'vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area'
]
],
[
'wing_aspect_ratio',
'vehicle_configurations.*.wings.main_wing.aspect_ratio'
],
[
'wing_incidence',
'vehicle_configurations.*.wings.main_wing.twists.root'
],
[
'wing_tip_twist',
'vehicle_configurations.*.wings.main_wing.twists.tip'
],
[
'wing_sweep',
'vehicle_configurations.*.wings.main_wing.sweeps.quarter_chord'
],
[
'wing_thickness',
'vehicle_configurations.*.wings.main_wing.thickness_to_chord'
],
['wing_taper', 'vehicle_configurations.*.wings.main_wing.taper'],
[
'wing_location',
'vehicle_configurations.*.wings.main_wing.origin[0]'
],
[
'horizontal_tail_area',
'vehicle_configurations.*.wings.horizontal_stabilizer.areas.reference'
],
[
'horizontal_tail_aspect_ratio',
'vehicle_configurations.*.wings.horizontal_stabilizer.aspect_ratio'
],
[
'vertical_tail_area',
'vehicle_configurations.*.wings.vertical_stabilizer.areas.reference'
],
[
'vertical_tail_aspect_ratio',
'vehicle_configurations.*.wings.vertical_stabilizer.aspect_ratio'
],
[
'design_thrust',
'vehicle_configurations.*.propulsors.turbofan.thrust.total_design'
],
[
'MTOW',
[
'vehicle_configurations.*.mass_properties.takeoff',
'vehicle_configurations.*.mass_properties.max_takeoff'
]
],
['design_TOW', 'vehicle_configurations.base.mass_properties.takeoff'],
[
'short_field_TOW',
'vehicle_configurations.short_field_takeoff.mass_properties.takeoff'
],
[
'flap_takeoff_angle',
[
'vehicle_configurations.takeoff.wings.main_wing.control_surfaces.flap.deflection',
'vehicle_configurations.short_field_takeoff.wings.main_wing.control_surfaces.flap.deflection'
]
],
[
'flap_landing_angle',
'vehicle_configurations.landing.wings.main_wing.control_surfaces.flap.deflection'
],
[
'slat_takeoff_angle',
[
'vehicle_configurations.takeoff.wings.main_wing.control_surfaces.slat.deflection',
'vehicle_configurations.short_field_takeoff.wings.main_wing.control_surfaces.slat.deflection'
]
],
[
'slat_landing_angle',
'vehicle_configurations.landing.wings.main_wing.control_surfaces.slat.deflection'
],
[
'wing_span',
'vehicle_configurations.base.wings.main_wing.spans.projected'
],
['noise_approach_margin', 'summary.noise_approach_margin'],
['noise_sideline_margin', 'summary.noise_sideline_margin'],
['noise_flyover_margin', 'summary.noise_flyover_margin'],
['static_stability', 'summary.static_stability'],
[
'vertical_tail_volume_coefficient',
'summary.vertical_tail_volume_coefficient'
],
[
'horizontal_tail_volume_coefficient',
'summary.horizontal_tail_volume_coefficient'
],
['wing_max_cl_norm', 'summary.maximum_cl_norm'],
['design_range_fuel_margin', 'summary.design_range_fuel_margin'],
['takeoff_field_length', 'summary.takeoff_field_length'],
['landing_field_length', 'summary.landing_field_length'],
['short_takeoff_field_length', 'summary.short_takeoff_field_length'],
[
'2nd_segment_climb_max_range',
'summary.second_segment_climb_gradient_takeoff'
],
[
'2nd_segment_climb_short_field',
'summary.second_segment_climb_gradient_short_field'
],
['max_throttle', 'summary.max_throttle'],
['short_field_fuel_margin', 'summary.short_field_fuel_margin'],
['max_range_fuel_margin', 'summary.max_range_fuel_margin'],
['max_range', 'missions.max_range_distance'],
['MZFW consistency', 'summary.MZFW_consistency'],
['MZFW_ratio', 'MZFW_ratio'],
['noise_takeoff_speed_increase', 'noise_V2_increase'],
[
'noise_cutback_altitude',
'missions.takeoff.segments.climb.altitude_end'
],
['noise_cumulative_margin', 'summary.noise_margin'],
['weighted_sum_objective', 'summary.weighted_sum_objective'],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
return nexus
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
run_new_regression = False
# append AVL aerodynamic analysis
aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
aerodynamics.settings.number_spanwise_vortices = 30
aerodynamics.settings.keep_files = True
aerodynamics.geometry = copy.deepcopy(configs.cruise)
configs_analyses.cruise.append(aerodynamics)
# append AVL stability analysis
stability = SUAVE.Analyses.Stability.AVL()
stability.settings.number_spanwise_vortices = 30
stability.settings.keep_files = True
stability.geometry = copy.deepcopy(configs.cruise)
if run_new_regression:
# append AVL aerodynamic analysis
aerodynamics.settings.regression_flag = False
aerodynamics.process.compute.lift.inviscid.settings.filenames.avl_bin_name = 'CHANGE/TO/AVL/PATH'
aerodynamics.settings.save_regression_results = True
stability.settings.regression_flag = False
stability.settings.save_regression_results = True
stability.settings.filenames.avl_bin_name = 'CHANGE/TO/AVL/PATH'
else:
aerodynamics.settings.regression_flag = True
aerodynamics.settings.save_regression_results = False
aerodynamics.settings.training_file = 'cruise_aero_data.txt'
stability.settings.regression_flag = True
stability.settings.save_regression_results = False
stability.training_file = 'cruise_stability_data.txt'
configs_analyses.cruise.append(aerodynamics)
configs_analyses.cruise.append(stability)
# ------------------------------------------------------------------
# Initialize the Mission
# ------------------------------------------------------------------
mission = SUAVE.Analyses.Mission.Sequential_Segments()
mission.tag = 'the_mission'
#airport
airport = SUAVE.Attributes.Airports.Airport()
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
mission.airport = airport
# unpack Segments module
Segments = SUAVE.Analyses.Mission.Segments
# base segment
base_segment = Segments.Segment()
# ------------------------------------------------------------------
# Cruise Segment: constant speed, constant altitude
# ------------------------------------------------------------------
segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment)
segment.tag = "cruise"
segment.analyses.extend(configs_analyses.cruise)
segment.air_speed = 230. * Units['m/s']
segment.distance = 4000. * Units.km
segment.altitude = 10.668 * Units.km
segment.state.numerics.number_control_points = 4
# add to mission
mission.append_segment(segment)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# lift coefficient check
lift_coefficient = results.segments.cruise.conditions.aerodynamics.lift_coefficient[
0][0]
lift_coefficient_true = 0.6124936427552575
print(lift_coefficient)
diff_CL = np.abs(lift_coefficient - lift_coefficient_true)
print('CL difference')
print(diff_CL)
assert np.abs((lift_coefficient - lift_coefficient_true) /
lift_coefficient_true) < 1e-6
# moment coefficient check
moment_coefficient = results.segments.cruise.conditions.stability.static.CM[
0][0]
moment_coefficient_true = -0.5764235338199974
print(moment_coefficient)
diff_CM = np.abs(moment_coefficient - moment_coefficient_true)
print('CM difference')
print(diff_CM)
assert np.abs((moment_coefficient - moment_coefficient_true) /
moment_coefficient_true) < 1e-6
return
def setup():
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
# [ tag , initial, [lb,ub], scaling, units ]
problem.inputs = np.array([
[ 'wing_area' , 124.8 , ( 70. , 200. ) , 124.8 , Units.meter**2],
[ 'wing_aspect_ratio' , 10.18, ( 5. , 20. ) , 10.18, Units.less],
[ 'wing_sweep' , 25. , ( 0. , 35. ) , 25. , Units.degrees],
[ 'wing_thickness' , 0.105 , ( 0.07 , 0.20 ) , 0.105, Units.less],
[ 'design_thrust' , 52700. , ( 10000. , 70000. ) , 52700. , Units.N],
[ 'MTOW' , 79090. , ( 20000. ,100000. ) , 79090. , Units.kg],
[ 'MZFW_ratio' , 0.77 , ( 0.6 , 0.99 ) , 0.77 , Units.less],
[ 'flap_takeoff_angle' , 10. , ( 0. , 20. ) , 10. , Units.degrees],
[ 'flap_landing_angle' , 40. , ( 0. , 50. ) , 40. , Units.degrees],
[ 'short_field_TOW' , 64030. , ( 20000. ,100000. ) , 64030. , Units.kg],
[ 'design_TOW' , 68520. , ( 20000. ,100000. ) , 68520. , Units.kg],
[ 'noise_takeoff_speed_increase' , 10.0 , ( 10. , 20. ) , 10.0 , Units.knots],
[ 'noise_cutback_altitude' , 304.8 , ( 240. , 400. ) , 304.8 , Units.meter],
])
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
problem.objective = np.array([
[ 'noise_cumulative_margin', 17, Units.less ],
])
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
# [ tag, sense, edge, scaling, units ]
problem.constraints = np.array([
[ 'MZFW consistency' , '>' , 0. , 10 , Units.less],
[ 'design_range_fuel_margin' , '>', 0., 10, Units.less],
[ 'short_field_fuel_margin' , '>' , 0. , 10, Units.less],
[ 'max_range_fuel_margin' , '>' , 0. , 10, Units.less],
[ 'wing_span' , '<', 35.9664, 35.9664, Units.less],
[ 'noise_flyover_margin' , '>', 0. , 10., Units.less],
[ 'noise_sideline_margin' , '>', 0. , 10. , Units.less],
[ 'noise_approach_margin' , '>', 0., 10., Units.less],
[ 'takeoff_field_length' , '<', 1985., 1985., Units.meters],
[ 'landing_field_length' , '<', 1385., 1385., Units.meters],
[ '2nd_segment_climb_max_range' , '>', 0.024, 0.024, Units.less],
[ '2nd_segment_climb_short_field' , '>', 0.024, 0.024, Units.less],
[ 'max_throttle' , '<', 1., 1., Units.less],
[ 'short_takeoff_field_length' , '<', 1330., 1330., Units.meters],
[ 'noise_cumulative_margin' , '>', 10., 10., Units.less],
])
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
problem.aliases = [
[ 'wing_area' , ['vehicle_configurations.*.wings.main_wing.areas.reference',
'vehicle_configurations.*.reference_area' ]],
[ 'wing_aspect_ratio' , 'vehicle_configurations.*.wings.main_wing.aspect_ratio' ],
[ 'wing_incidence' , 'vehicle_configurations.*.wings.main_wing.twists.root' ],
[ 'wing_tip_twist' , 'vehicle_configurations.*.wings.main_wing.twists.tip' ],
[ 'wing_sweep' , 'vehicle_configurations.*.wings.main_wing.sweeps.quarter_chord' ],
[ 'wing_thickness' , 'vehicle_configurations.*.wings.main_wing.thickness_to_chord' ],
[ 'wing_taper' , 'vehicle_configurations.*.wings.main_wing.taper' ],
[ 'wing_location' , 'vehicle_configurations.*.wings.main_wing.origin[0]' ],
[ 'horizontal_tail_area' , 'vehicle_configurations.*.wings.horizontal_stabilizer.areas.reference'],
[ 'horizontal_tail_aspect_ratio' , 'vehicle_configurations.*.wings.horizontal_stabilizer.aspect_ratio' ],
[ 'vertical_tail_area' , 'vehicle_configurations.*.wings.vertical_stabilizer.areas.reference' ],
[ 'vertical_tail_aspect_ratio' , 'vehicle_configurations.*.wings.vertical_stabilizer.aspect_ratio' ],
[ 'design_thrust' , 'vehicle_configurations.*.propulsors.turbofan.thrust.total_design' ],
[ 'MTOW' , ['vehicle_configurations.*.mass_properties.takeoff' ,
'vehicle_configurations.*.mass_properties.max_takeoff' ]],
[ 'design_TOW' , 'vehicle_configurations.base.mass_properties.takeoff' ],
[ 'short_field_TOW' , 'vehicle_configurations.short_field_takeoff.mass_properties.takeoff' ],
[ 'flap_takeoff_angle' , ['vehicle_configurations.takeoff.wings.main_wing.flaps.angle',
'vehicle_configurations.short_field_takeoff.wings.main_wing.flaps.angle']],
[ 'flap_landing_angle' , 'vehicle_configurations.landing.wings.main_wing.flaps.angle' ],
[ 'slat_takeoff_angle' , ['vehicle_configurations.takeoff.wings.main_wing.slats.angle',
'vehicle_configurations.short_field_takeoff.wings.main_wing.slats.angle']],
[ 'slat_landing_angle' , 'vehicle_configurations.landing.wings.main_wing.slats.angle' ],
[ 'wing_span' , 'vehicle_configurations.base.wings.main_wing.spans.projected' ],
[ 'noise_approach_margin' , 'summary.noise_approach_margin' ],
[ 'noise_sideline_margin' , 'summary.noise_sideline_margin' ],
[ 'noise_flyover_margin' , 'summary.noise_flyover_margin' ],
[ 'static_stability' , 'summary.static_stability' ],
[ 'vertical_tail_volume_coefficient' , 'summary.vertical_tail_volume_coefficient' ],
[ 'horizontal_tail_volume_coefficient', 'summary.horizontal_tail_volume_coefficient' ],
[ 'wing_max_cl_norm' , 'summary.maximum_cl_norm' ],
[ 'design_range_fuel_margin' , 'summary.design_range_fuel_margin' ],
[ 'takeoff_field_length' , 'summary.takeoff_field_length' ],
[ 'landing_field_length' , 'summary.landing_field_length' ],
[ 'short_takeoff_field_length' , 'summary.short_takeoff_field_length' ],
[ '2nd_segment_climb_max_range' , 'summary.second_segment_climb_gradient_takeoff' ],
[ '2nd_segment_climb_short_field' , 'summary.second_segment_climb_gradient_short_field' ],
[ 'max_throttle' , 'summary.max_throttle' ],
[ 'short_field_fuel_margin' , 'summary.short_field_fuel_margin' ],
[ 'max_range_fuel_margin' , 'summary.max_range_fuel_margin' ],
[ 'max_range' , 'missions.max_range_distance' ],
[ 'MZFW consistency' , 'summary.MZFW_consistency' ],
[ 'MZFW_ratio' , 'MZFW_ratio' ],
[ 'noise_takeoff_speed_increase' , 'noise_V2_increase' ],
[ 'noise_cutback_altitude' , 'missions.takeoff.segments.climb.altitude_end' ],
[ 'noise_cumulative_margin' , 'summary.noise_margin' ],
[ 'weighted_sum_objective' , 'summary.weighted_sum_objective' ],
]
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
vehicle = vehicle_setup()
nexus.vehicle_configurations = configs_setup(vehicle)
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = Missions.setup(nexus.analyses)
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.procedure = Procedure.setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
return nexus
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# append AVL aerodynamic analysis
aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
aerodynamics.process.compute.lift.inviscid.regression_flag = True
aerodynamics.process.compute.lift.inviscid.keep_files = True
aerodynamics.geometry = copy.deepcopy(configs.cruise)
aerodynamics.process.compute.lift.inviscid.training_file = 'cruise_data_aerodynamics.txt'
configs_analyses.cruise.append(aerodynamics)
# append AVL stability analysis
stability = SUAVE.Analyses.Stability.AVL()
stability.regression_flag = True
stability.keep_files = True
stability.geometry = copy.deepcopy(configs.cruise)
stability.training_file = 'cruise_data_stability.txt'
configs_analyses.cruise.append(stability)
# mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# lift coefficient check
lift_coefficient = results.conditions.cruise.aerodynamics.lift_coefficient[0]
lift_coefficient_true = 0.59495841
print lift_coefficient
diff_CL = np.abs(lift_coefficient - lift_coefficient_true)
print 'CL difference'
print diff_CL
assert np.abs((lift_coefficient - lift_coefficient_true)/lift_coefficient_true) < 1e-3
# moment coefficient check
moment_coefficient = results.conditions.cruise.stability.static.CM[0][0]
moment_coefficient_true = -0.620326644
print moment_coefficient
diff_CM = np.abs(moment_coefficient - moment_coefficient_true)
print 'CM difference'
print diff_CM
assert np.abs((moment_coefficient - moment_coefficient_true)/moment_coefficient_true) < 1e-3
return
