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():
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 = mission_B737.vehicle_setup()
configs = mission_B737.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 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 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 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
