def main():
vehicle = vehicle_setup()
weight = Tube_Wing.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 12977.803363592691 #includes cargo #22177.6377131 #without cargo
actual.empty = 38688.08848390731
actual.wing = 6649.709658738429
actual.fuselage = 6642.061164271899
actual.propulsion = 6838.185174956626
actual.landing_gear = 3160.632
actual.systems = 13479.10479056802
actual.wt_furnish = 6431.80372889
actual.horizontal_tail = 1037.7414196819743
actual.vertical_tail = 629.0387683502595
actual.rudder = 251.61550734010382
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload) / actual.payload
error.pax = (actual.pax - weight.pax) / actual.pax
error.bag = (actual.bag - weight.bag) / actual.bag
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage - weight.fuselage) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.landing_gear = (actual.landing_gear -
weight.landing_gear) / actual.landing_gear
error.systems = (actual.systems - weight.systems) / actual.systems
error.wt_furnish = (actual.wt_furnish -
weight.systems_breakdown.furnish) / actual.wt_furnish
error.horizontal_tail = (actual.horizontal_tail -
weight.horizontal_tail) / actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail -
weight.vertical_tail) / actual.vertical_tail
error.rudder = (actual.rudder - weight.rudder) / actual.rudder
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
#General Aviation weights; note that values are taken from Raymer,
#but there is a huge spread among the GA designs, so individual components
#differ a good deal from the actual design
vehicle = vehicle_setup_general_aviation()
GTOW = vehicle.mass_properties.max_takeoff
weight = General_Aviation.empty(vehicle)
weight.fuel = vehicle.fuel.mass_properties.mass
actual = Data()
actual.bag = 0.
actual.empty = 618.485310343
actual.fuel = 144.69596603
actual.wing = 124.673093906
actual.fuselage = 119.522072873
actual.propulsion = 194.477769922 #includes power plant and propeller, does not include fuel system
actual.landing_gear = 44.8033840543 + 5.27975390045
actual.furnishing = 37.8341395817
actual.electrical = 36.7532226254
actual.control_systems = 14.8331955546
actual.fuel_systems = 15.6859717453
actual.systems = 108.096549345
error = Data()
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage - weight.fuselage) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.landing_gear = (actual.landing_gear -
(weight.landing_gear_main +
weight.landing_gear_nose)) / actual.landing_gear
error.furnishing = (actual.furnishing -
weight.systems_breakdown.furnish) / actual.furnishing
error.electrical = (actual.electrical - weight.systems_breakdown.electrical
) / actual.electrical
error.control_systems = (
actual.control_systems -
weight.systems_breakdown.control_systems) / actual.control_systems
error.fuel_systems = (
actual.fuel_systems -
weight.systems_breakdown.fuel_system) / actual.fuel_systems
error.systems = (actual.systems - weight.systems) / actual.systems
print('actual.systems=', actual.systems)
print('General Aviation Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
# BWB WEIGHTS
vehicle = bwb_setup()
weight = BWB.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 24860.343951919327
actual.empty = 26805.547895580676
actual.wing = 6576.679767012152
actual.fuselage = 1.0
actual.propulsion = 1413.8593105126783
actual.landing_gear = 3160.632
actual.systems = 15654.376818055844
actual.wt_furnish = 8205.349895589
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload) / actual.payload
error.pax = (actual.pax - weight.pax) / actual.pax
error.bag = (actual.bag - weight.bag) / actual.bag
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.fuselage + 1.0)) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.systems = (actual.systems - weight.systems) / actual.systems
error.wt_furnish = (actual.wt_furnish -
weight.systems_breakdown.furnish) / actual.wt_furnish
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
# Human Powered Aircraft
vehicle = hp_setup()
weight = HP.empty(vehicle)
# regression values
actual = Data()
actual.empty = 138.02737768459374
actual.wing = 89.86286881794777
actual.fuselage = 1.0
actual.horizontal_tail = 31.749272074174737
actual.vertical_tail = 16.415236792471237
# error calculations
error = Data()
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.fuselage + 1.0)) / actual.fuselage
error.horizontal_tail = (actual.horizontal_tail -
weight.horizontal_tail) / actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail -
weight.vertical_tail) / actual.vertical_tail
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
return
def main():
vehicle = vehicle_setup()
weight = Transport.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 # includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 16504.32206450931 # includes cargo #22177.6377131 #without cargo
actual.empty = 35161.56978299069
actual.wing = 3461.869204335895
actual.fuselage = 6700.709511002648
actual.propulsion = 6838.185174956626
actual.landing_gear = 3160.632
actual.systems = 13390.723085494214
actual.wt_furnish = 6431.803728889001
actual.horizontal_tail = 728.7965315109458
actual.vertical_tail = 880.6542756903633
actual.rudder = 251.61550734010382
actual.nose_gear = 316.06320000000005
actual.main_gear = 2844.5688
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload) / actual.payload
error.pax = (actual.pax - weight.pax) / actual.pax
error.bag = (actual.bag - weight.bag) / actual.bag
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage - weight.fuselage) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.nose_gear = (actual.nose_gear - weight.nose_gear) / actual.nose_gear
error.main_gear = (actual.main_gear - weight.main_gear) / actual.main_gear
error.systems = (actual.systems - weight.systems) / actual.systems
error.wt_furnish = (actual.wt_furnish -
weight.systems_breakdown.furnish) / actual.wt_furnish
error.horizontal_tail = (actual.horizontal_tail -
weight.horizontal_tail) / actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail -
weight.vertical_tail) / actual.vertical_tail
error.rudder = (actual.rudder - weight.rudder) / actual.rudder
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
#General Aviation weights; note that values are taken from Raymer,
#but there is a huge spread among the GA designs, so individual components
#differ a good deal from the actual design
vehicle = vehicle_setup_general_aviation()
GTOW = vehicle.mass_properties.max_takeoff
weight = General_Aviation.empty(vehicle)
weight.fuel = vehicle.fuel.mass_properties.mass
actual = Data()
actual.bag = 0.
actual.empty = 720.1834370409678
actual.fuel = 144.69596603
actual.wing = 152.25407206578896
actual.fuselage = 126.7421108234472
actual.propulsion = 224.40728553408732
actual.landing_gear = 67.81320006645151
actual.furnishing = 37.8341395817
actual.electrical = 41.28649399649684
actual.control_systems = 20.51671046011007
actual.fuel_systems = 20.173688786768366
actual.systems = 122.8010526627288
error = Data()
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage - weight.fuselage) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.landing_gear = (actual.landing_gear -
(weight.landing_gear_main +
weight.landing_gear_nose)) / actual.landing_gear
error.furnishing = (actual.furnishing -
weight.systems_breakdown.furnish) / actual.furnishing
error.electrical = (actual.electrical - weight.systems_breakdown.electrical
) / actual.electrical
error.control_systems = (
actual.control_systems -
weight.systems_breakdown.control_systems) / actual.control_systems
error.fuel_systems = (
actual.fuel_systems -
weight.systems_breakdown.fuel_system) / actual.fuel_systems
error.systems = (actual.systems - weight.systems) / actual.systems
print('actual.systems=', actual.systems)
print('General Aviation Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
# BWB WEIGHTS
vehicle = bwb_setup()
weight = BWB.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 26119.117465169547
actual.empty = 25546.774382330455
actual.wing = 5317.906253761935
actual.fuselage = 1.0
actual.propulsion = 1413.8593105126783
actual.landing_gear = 3160.632
actual.systems = 15654.376818055844
actual.wt_furnish = 8205.349895589
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload) / actual.payload
error.pax = (actual.pax - weight.pax) / actual.pax
error.bag = (actual.bag - weight.bag) / actual.bag
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.fuselage + 1.0)) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion) / actual.propulsion
error.systems = (actual.systems - weight.systems) / actual.systems
error.wt_furnish = (actual.wt_furnish -
weight.systems_breakdown.furnish) / actual.wt_furnish
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
# Human Powered Aircraft
vehicle = hp_setup()
weight = HP.empty(vehicle)
# regression values
actual = Data()
actual.empty = 143.59737768459374
actual.wing = 95.43286881794776
actual.fuselage = 1.0
actual.horizontal_tail = 31.749272074174737
actual.vertical_tail = 16.415236792471237
# error calculations
error = Data()
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.fuselage + 1.0)) / actual.fuselage
error.horizontal_tail = (actual.horizontal_tail -
weight.horizontal_tail) / actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail -
weight.vertical_tail) / actual.vertical_tail
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1E-6)
return
def main():
vehicle = vehicle_setup()
weight = Tube_Wing.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 12977.803363592691 #includes cargo #22177.6377131 #without cargo
actual.empty = 38688.08848390731
actual.wing = 6649.709658738429
actual.fuselage = 6642.061164271899
actual.propulsion = 6838.185174956626
actual.landing_gear = 3160.632
actual.systems = 13479.10479056802
actual.wt_furnish = 6431.80372889
actual.horizontal_tail = 1037.7414196819743
actual.vertical_tail = 629.0387683502595
actual.rudder = 251.61550734010382
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload)/actual.payload
error.pax = (actual.pax - weight.pax)/actual.pax
error.bag = (actual.bag - weight.bag)/actual.bag
error.fuel = (actual.fuel - weight.fuel)/actual.fuel
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - weight.fuselage)/actual.fuselage
error.propulsion = (actual.propulsion - weight.propulsion)/actual.propulsion
error.landing_gear = (actual.landing_gear - weight.landing_gear)/actual.landing_gear
error.systems = (actual.systems - weight.systems)/actual.systems
error.wt_furnish = (actual.wt_furnish - weight.systems_breakdown.furnish)/actual.wt_furnish
error.horizontal_tail = (actual.horizontal_tail - weight.horizontal_tail)/actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail - weight.vertical_tail)/actual.vertical_tail
error.rudder = (actual.rudder - weight.rudder)/actual.rudder
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1E-6)
#General Aviation weights; note that values are taken from Raymer,
#but there is a huge spread among the GA designs, so individual components
#differ a good deal from the actual design
vehicle = vehicle_setup_general_aviation()
GTOW = vehicle.mass_properties.max_takeoff
weight = General_Aviation.empty(vehicle)
weight.fuel = vehicle.fuel.mass_properties.mass
actual = Data()
actual.bag = 0.
actual.empty = 618.485310343
actual.fuel = 144.69596603
actual.wing = 124.673093906
actual.fuselage = 119.522072873
actual.propulsion = 194.477769922 #includes power plant and propeller, does not include fuel system
actual.landing_gear = 44.8033840543+5.27975390045
actual.furnishing = 37.8341395817
actual.electrical = 36.7532226254
actual.control_systems = 14.8331955546
actual.fuel_systems = 15.6859717453
actual.systems = 108.096549345
error = Data()
error.fuel = (actual.fuel - weight.fuel)/actual.fuel
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - weight.fuselage)/actual.fuselage
error.propulsion = (actual.propulsion - weight.propulsion)/actual.propulsion
error.landing_gear = (actual.landing_gear - (weight.landing_gear_main+weight.landing_gear_nose))/actual.landing_gear
error.furnishing = (actual.furnishing-weight.systems_breakdown.furnish)/actual.furnishing
error.electrical = (actual.electrical-weight.systems_breakdown.electrical)/actual.electrical
error.control_systems = (actual.control_systems-weight.systems_breakdown.control_systems)/actual.control_systems
error.fuel_systems = (actual.fuel_systems-weight.systems_breakdown.fuel_system)/actual.fuel_systems
error.systems = (actual.systems - weight.systems)/actual.systems
print('actual.systems=', actual.systems)
print('General Aviation Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1e-6)
# BWB WEIGHTS
vehicle = bwb_setup()
weight = BWB.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 24860.343951919327
actual.empty = 26805.547895580676
actual.wing = 6576.679767012152
actual.fuselage = 1.0
actual.propulsion = 1413.8593105126783
actual.landing_gear = 3160.632
actual.systems = 15654.376818055844
actual.wt_furnish = 8205.349895589
# error calculations
error = Data()
error.payload = (actual.payload - weight.payload)/actual.payload
error.pax = (actual.pax - weight.pax)/actual.pax
error.bag = (actual.bag - weight.bag)/actual.bag
error.fuel = (actual.fuel - weight.fuel)/actual.fuel
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - (weight.fuselage+1.0))/actual.fuselage
error.propulsion = (actual.propulsion - weight.propulsion)/actual.propulsion
error.systems = (actual.systems - weight.systems)/actual.systems
error.wt_furnish = (actual.wt_furnish - weight.systems_breakdown.furnish)/actual.wt_furnish
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1E-6)
# Human Powered Aircraft
vehicle = hp_setup()
weight = HP.empty(vehicle)
# regression values
actual = Data()
actual.empty = 138.02737768459374
actual.wing = 89.86286881794777
actual.fuselage = 1.0
actual.horizontal_tail = 31.749272074174737
actual.vertical_tail = 16.415236792471237
# error calculations
error = Data()
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - (weight.fuselage+1.0))/actual.fuselage
error.horizontal_tail = (actual.horizontal_tail - weight.horizontal_tail)/actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail - weight.vertical_tail)/actual.vertical_tail
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1E-6)
return
def main():
# Transport Weights
vehicle = vehicle_setup()
method_types = [
'SUAVE', 'New SUAVE', 'FLOPS Simple', 'FLOPS Complex', 'Raymer'
]
for method_type in method_types:
print('Testing Method: ' + method_type)
if 'FLOPS' in method_type:
settings = Data()
settings.FLOPS = Data()
settings.FLOPS.aeroelastic_tailoring_factor = 0.
settings.FLOPS.strut_braced_wing_factor = 0.
settings.FLOPS.composite_utilization_factor = 0.5
settings.FLOPS.variable_sweep_factor = 1.
elif 'Raymer' in method_type:
settings = Data()
settings.Raymer = Data()
settings.Raymer.fuselage_mounted_landing_gear_factor = 1.
else:
settings = None
weight = Common.empty_weight(vehicle,
settings=settings,
method_type=method_type)
#save_results(weight, 'weights_'+method_type.replace(' ','_')+'.res')
old_weight = load_results('weights_' + method_type.replace(' ', '_') +
'.res')
check_list = [
'payload_breakdown.total', 'payload_breakdown.passengers',
'payload_breakdown.baggage', 'structures.wing',
'structures.fuselage', 'propulsion_breakdown.total',
'structures.nose_landing_gear', 'structures.main_landing_gear',
'systems_breakdown.total', 'systems_breakdown.furnish',
'structures.horizontal_tail', 'structures.vertical_tail', 'empty',
'fuel'
]
# do the check
for k in check_list:
print(k)
old_val = old_weight.deep_get(k)
new_val = weight.deep_get(k)
err = (new_val - old_val) / old_val
print('Error:', err)
assert np.abs(err) < 1e-6, 'Check Failed : %s' % k
print('')
#General Aviation weights; note that values are taken from Raymer,
#but there is a huge spread among the GA designs, so individual components
#differ a good deal from the actual design
vehicle = vehicle_setup_general_aviation()
weight = General_Aviation.empty(vehicle)
weight.fuel = vehicle.fuel.mass_properties.mass
actual = Data()
actual.bag = 0.
actual.empty = 700.0097482541994
actual.fuel = 48.417662245800784
actual.wing = 152.25407206578896
actual.fuselage = 126.7421108234472
actual.propulsion = 224.40728553408732
actual.landing_gear = 67.81320006645151
actual.furnishing = 37.8341395817
actual.electrical = 41.28649399649684
actual.control_systems = 20.51671046011007
actual.fuel_systems = 20.173688786768366
actual.systems = 102.62736387596043
error = Data()
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.structures.wing) / actual.wing
error.fuselage = (actual.fuselage -
weight.structures.fuselage) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion_breakdown.total) / actual.propulsion
error.landing_gear = (
actual.landing_gear -
(weight.structures.main_landing_gear +
weight.structures.nose_landing_gear)) / actual.landing_gear
error.furnishing = (actual.furnishing -
weight.systems_breakdown.furnish) / actual.furnishing
error.electrical = (actual.electrical - weight.systems_breakdown.electrical
) / actual.electrical
error.control_systems = (
actual.control_systems -
weight.systems_breakdown.control_systems) / actual.control_systems
error.fuel_systems = (
actual.fuel_systems -
weight.propulsion_breakdown.fuel_system) / actual.fuel_systems
error.systems = (actual.systems -
weight.systems_breakdown.total) / actual.systems
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in error.items():
assert (np.abs(v) < 1E-6)
# BWB WEIGHTS
vehicle = bwb_setup()
weight = BWB.empty(vehicle)
# regression values
actual = Data()
actual.payload = 27349.9081525 #includes cargo #17349.9081525 #without cargo
actual.pax = 15036.587065500002
actual.bag = 2313.3210870000003
actual.fuel = 23361.42500371662
actual.empty = 24417.180232883387
actual.wing = 7272.740220314861
actual.fuselage = 1.0
actual.propulsion = 1413.8593105126783
actual.landing_gear = 3160.632
actual.systems = 12569.948702055846
actual.wt_furnish = 8205.349895589
# error calculations
error = Data()
error.payload = (actual.payload -
weight.payload_breakdown.total) / actual.payload
error.pax = (actual.pax - weight.payload_breakdown.passengers) / actual.pax
error.bag = (actual.bag - weight.payload_breakdown.baggage) / actual.bag
error.fuel = (actual.fuel - weight.fuel) / actual.fuel
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.structures.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.structures.fuselage + 1.0)) / actual.fuselage
error.propulsion = (actual.propulsion -
weight.propulsion_breakdown.total) / actual.propulsion
error.systems = (actual.systems -
weight.systems_breakdown.total) / actual.systems
error.wt_furnish = (actual.wt_furnish -
weight.systems_breakdown.furnish) / actual.wt_furnish
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in error.items():
assert (np.abs(v) < 1E-6)
# Human Powered Aircraft
vehicle = hp_setup()
weight = HP.empty(vehicle)
# regression values
actual = Data()
actual.empty = 143.59737768459374
actual.wing = 95.43286881794776
actual.fuselage = 1.0
actual.horizontal_tail = 31.749272074174737
actual.vertical_tail = 16.415236792471237
# error calculations
error = Data()
error.empty = (actual.empty - weight.empty) / actual.empty
error.wing = (actual.wing - weight.wing) / actual.wing
error.fuselage = (actual.fuselage -
(weight.fuselage + 1.0)) / actual.fuselage
error.horizontal_tail = (actual.horizontal_tail -
weight.horizontal_tail) / actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail -
weight.vertical_tail) / actual.vertical_tail
print('Results (kg)')
print(weight)
print('Relative Errors')
print(error)
for k, v in error.items():
assert (np.abs(v) < 1E-6)
return