def main():
vehicle = vehicle_setup()
analyses = SUAVE.Analyses.Vehicle()
sizing = SUAVE.Analyses.Sizing.Sizing()
sizing.features.vehicle = vehicle
analyses.append(sizing)
weights = SUAVE.Analyses.Weights.Weights_Transport()
weights.vehicle = vehicle
analyses.append(weights)
aerodynamics = SUAVE.Analyses.Aerodynamics.AERODAS()
aerodynamics.geometry = vehicle
aerodynamics.settings.drag_coefficient_increment = 0.0000
analyses.append(aerodynamics)
stability = SUAVE.Analyses.Stability.Fidelity_Zero()
stability.geometry = vehicle
analyses.append(stability)
energy = SUAVE.Analyses.Energy.Energy()
energy.network = vehicle.networks
analyses.append(energy)
planet = SUAVE.Analyses.Planets.Planet()
analyses.append(planet)
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = planet.features
analyses.append(atmosphere)
analyses.finalize()
climb_rate = electric_V_h_diagram(vehicle,
analyses,
CL_max=1.4,
delta_isa=0.,
grid_points=5,
altitude_ceiling=1e4 * Units.ft,
max_speed=150 * Units.knots,
test_omega=2400 * Units.rpm,
display_plot=True)
climb_rate_r = [
[0., 0., 0., 0., 0.], [0., 0., 0., 0., 0.],
[365.28164616, 0., 0., 0., 0.],
[671.06501573, 565.12568368, 462.33970468, 362.03685772, 263.49032629],
[677.20427984, 577.26538105, 483.80816586, 395.7082193, 311.81340271]
]
assert (np.all(
np.nan_to_num(np.abs(climb_rate - climb_rate_r) / climb_rate_r) < 1e-6)
), "Electric V_h Diagram Regression Failed"
return
def main():
vehicle = vehicle_setup()
analyses = SUAVE.Analyses.Vehicle()
sizing = SUAVE.Analyses.Sizing.Sizing()
sizing.features.vehicle = vehicle
analyses.append(sizing)
weights = SUAVE.Analyses.Weights.Weights_Transport()
weights.vehicle = vehicle
analyses.append(weights)
aerodynamics = SUAVE.Analyses.Aerodynamics.AERODAS()
aerodynamics.geometry = vehicle
aerodynamics.settings.drag_coefficient_increment = 0.0000
analyses.append(aerodynamics)
stability = SUAVE.Analyses.Stability.Fidelity_Zero()
stability.geometry = vehicle
analyses.append(stability)
energy = SUAVE.Analyses.Energy.Energy()
energy.network = vehicle.networks
analyses.append(energy)
planet = SUAVE.Analyses.Planets.Planet()
analyses.append(planet)
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = planet.features
analyses.append(atmosphere)
analyses.finalize()
climb_rate = electric_V_h_diagram(vehicle,
analyses,
CL_max=1.4,
delta_isa=0.,
grid_points=5,
altitude_ceiling= 2e4 * Units.ft,
max_speed=130 * Units['m/s'],
test_omega= 1000 * Units.rpm,
display_plot=True)
climb_rate_r = [[ 0. , 0. , 0. , 0. , 0. ],
[ 0. , 0. , 0. , 0. , 0. ],
[719.7179757 , 582.17272069, 452.68248026, 329.12481042, 212.19190451],
[ 0. , 0. , 0. , 0. , 0. ],
[ 0. , 0. , 0. , 0. , 0. ]]
assert (np.all(np.nan_to_num(np.abs(climb_rate-climb_rate_r)/climb_rate_r) < 1e-6)), "Electric V_h Diagram Regression Failed"
return
def test_2():
"""
This tests the propeller_single_point function using the Fidelity One rotor inflow model.
"""
vehicle = vehicle_setup()
# update the wake method used for each prop
for p in vehicle.networks.battery_propeller.propellers:
p.Wake = Rotor_Wake_Fidelity_One()
analyses = SUAVE.Analyses.Vehicle()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = SUAVE.Analyses.Planets.Planet()
analyses.append(atmosphere)
results = propeller_single_point(vehicle.networks.battery_propeller,
analyses,
pitch=0.,
omega=2200. * Units.rpm,
altitude=5000. * Units.ft,
delta_isa=0.,
speed=10 * Units['m/s'],
plots=True,
print_results=True)
thrust = results.thrust
torque = results.torque
power = results.power
Cp = results.power_coefficient
etap = results.efficiency
thrust_r = 637.9402297052759
torque_r = 129.07946679553763
power_r = 29737.7743383709
Cp_r = 0.03796285858728355
etap_r = 0.21452184768317925
assert (np.abs(thrust - thrust_r) / thrust_r <
1e-6), "Propeller Single Point Regression Failed at Thrust Test"
assert (np.abs(torque - torque_r) / torque_r <
1e-6), "Propeller Single Point Regression Failed at Torque Test"
assert (np.abs(power - power_r) / power_r <
1e-6), "Propeller Single Point Regression Failed at Power Test"
assert (
np.abs(Cp - Cp_r) / Cp_r < 1e-6
), "Propeller Single Point Regression Failed at Power Coefficient Test"
assert (np.abs(etap - etap_r) / etap_r < 1e-6
), "Propeller Single Point Regression Failed at Efficiency Test"
return
def test_2():
"""
This tests the propeller_single_point function using the helical fixed wake (HFW) + BET model.
"""
HFW = True
vehicle = vehicle_setup()
analyses = SUAVE.Analyses.Vehicle()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = SUAVE.Analyses.Planets.Planet()
analyses.append(atmosphere)
results = propeller_single_point(vehicle.networks.battery_propeller,
analyses,
pitch=0.,
omega=1500. * Units.rpm,
altitude=5000. * Units.ft,
delta_isa=0.,
speed=10 * Units['m/s'],
plots=True,
HFW=HFW,
print_results=True)
thrust = results.thrust
torque = results.torque
power = results.power
Cp = results.power_coefficient
etap = results.efficiency
thrust_r = 2393.728639733924
torque_r = 855.298865633124
power_r = 134350.0316448353
Cp_r = 0.3038702436194616
etap_r = 0.17817105142646564
assert (np.abs(thrust - thrust_r) / thrust_r <
1e-6), "Propeller Single Point Regression Failed at Thrust Test"
assert (np.abs(torque - torque_r) / torque_r <
1e-6), "Propeller Single Point Regression Failed at Torque Test"
assert (np.abs(power - power_r) / power_r <
1e-6), "Propeller Single Point Regression Failed at Power Test"
assert (
np.abs(Cp - Cp_r) / Cp_r < 1e-6
), "Propeller Single Point Regression Failed at Power Coefficient Test"
assert (np.abs(etap - etap_r) / etap_r < 1e-6
), "Propeller Single Point Regression Failed at Efficiency Test"
return
def test_1():
"""
This tests the propeller_single_point function using the BEMT model.
"""
HFW = False
vehicle = vehicle_setup()
analyses = SUAVE.Analyses.Vehicle()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = SUAVE.Analyses.Planets.Planet()
analyses.append(atmosphere)
results = propeller_single_point(vehicle.networks.battery_propeller,
analyses,
pitch=0.,
omega=1500. * Units.rpm,
altitude=5000. * Units.ft,
delta_isa=0.,
speed=10 * Units['m/s'],
plots=True,
HFW=HFW,
print_results=True)
thrust = results.thrust
torque = results.torque
power = results.power
Cp = results.power_coefficient
etap = results.efficiency
thrust_r = 2301.918639576478
torque_r = 827.0007491838651
power_r = 129904.97390746429
Cp_r = 0.29381649996923126
etap_r = 0.17720005086702875
assert (np.abs(thrust - thrust_r) / thrust_r <
1e-6), "Propeller Single Point Regression Failed at Thrust Test"
assert (np.abs(torque - torque_r) / torque_r <
1e-6), "Propeller Single Point Regression Failed at Torque Test"
assert (np.abs(power - power_r) / power_r <
1e-6), "Propeller Single Point Regression Failed at Power Test"
assert (
np.abs(Cp - Cp_r) / Cp_r < 1e-6
), "Propeller Single Point Regression Failed at Power Coefficient Test"
assert (np.abs(etap - etap_r) / etap_r < 1e-6
), "Propeller Single Point Regression Failed at Efficiency Test"
return
def test_1():
"""
This tests the propeller_single_point function using the Fidelity Zero rotor wake inflow model.
"""
vehicle = vehicle_setup()
analyses = SUAVE.Analyses.Vehicle()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = SUAVE.Analyses.Planets.Planet()
analyses.append(atmosphere)
results = propeller_single_point(vehicle.networks.battery_propeller,
analyses,
pitch=0.,
omega=2200. * Units.rpm,
altitude=5000. * Units.ft,
delta_isa=0.,
speed=10 * Units['m/s'],
plots=True,
print_results=True)
thrust = results.thrust
torque = results.torque
power = results.power
Cp = results.power_coefficient
etap = results.efficiency
thrust_r = 643.4365612076354
torque_r = 130.6985065893255
power_r = 30110.77432998669
Cp_r = 0.03843902555841082
etap_r = 0.21368980888905617
assert (np.abs(thrust - thrust_r) / thrust_r <
1e-6), "Propeller Single Point Regression Failed at Thrust Test"
assert (np.abs(torque - torque_r) / torque_r <
1e-6), "Propeller Single Point Regression Failed at Torque Test"
assert (np.abs(power - power_r) / power_r <
1e-6), "Propeller Single Point Regression Failed at Power Test"
assert (
np.abs(Cp - Cp_r) / Cp_r < 1e-6
), "Propeller Single Point Regression Failed at Power Coefficient Test"
assert (np.abs(etap - etap_r) / etap_r < 1e-6
), "Propeller Single Point Regression Failed at Efficiency Test"
return
def full_setup(bemt_wake, fixed_helical_wake, identical_props):
# vehicle data
vehicle = vehicle_setup()
# test for non-identical propellers
if not identical_props:
vehicle.networks.battery_propeller.identical_propellers = False
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs, bemt_wake, fixed_helical_wake)
# mission analyses
mission = mission_setup(configs_analyses, vehicle)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
return configs, analyses