def evaluate_field_length(vehicle):
# ---------------------------
# Check field performance
# ---------------------------
# define takeoff and landing configuration
#print ' Defining takeoff and landing configurations'
takeoff_config,landing_config = define_field_configs(vehicle)
# define airport to be evaluated
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()
# evaluate takeoff / landing
#print ' Estimating takeoff performance'
TOFL = estimate_take_off_field_length(vehicle,takeoff_config,airport)
#print ' Estimating landing performance'
LFL = estimate_landing_field_length(vehicle,landing_config,airport)
fldlength = Data()
fldlength.TOFL = TOFL
fldlength.LFL = LFL
return fldlength
def evaluate_field_length(interface):
configs=interface.configs
# unpack
configs=interface.configs
analyses=interface.analyses
mission=interface.analyses.missions.base
results=interface.results
airport = mission.airport
takeoff_config = configs.takeoff
landing_config = configs.landing
# evaluate
TOFL = estimate_take_off_field_length(takeoff_config,analyses,airport)
LFL = estimate_landing_field_length(landing_config, analyses,airport)
# pack
field_length = SUAVE.Core.Data()
field_length.takeoff = TOFL[0][0]
field_length.landing = LFL[0][0]
results.field_length = field_length
return results
def evaluate_field_length(vehicle):
# ---------------------------
# Check field performance
# ---------------------------
# define takeoff and landing configuration
#print ' Defining takeoff and landing configurations'
takeoff_config,landing_config = define_field_configs(vehicle)
# define airport to be evaluated
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()
# evaluate takeoff / landing
#print ' Estimating takeoff performance'
TOFL = estimate_take_off_field_length(vehicle,takeoff_config,airport)
#print ' Estimating landing performance'
LFL = estimate_landing_field_length(vehicle,landing_config,airport)
fldlength = Data()
fldlength.TOFL = TOFL
fldlength.LFL = LFL
return fldlength
def evaluate_field_length(configs, analyses, mission, results):
# unpack
airport = mission.airport
takeoff_config = configs.takeoff
landing_config = configs.landing
# evaluate
airport.atmosphere = analyses.base.atmosphere
TOFL = estimate_take_off_field_length(takeoff_config, analyses, airport)
LFL = estimate_landing_field_length(landing_config, analyses, airport) #FIXME
# pack
field_length = SUAVE.Core.Data()
field_length.takeoff = TOFL[0]
field_length.landing = LFL[0]
results.field_length = field_length
return results
def evaluate_field_length(configs,analyses,mission,results):
# unpack
airport = mission.airport
takeoff_config = configs.takeoff
landing_config = configs.landing
# evaluate
TOFL = estimate_take_off_field_length(takeoff_config,analyses.configs,airport)
LFL = estimate_landing_field_length (landing_config, analyses.configs,airport)
# pack
field_length = SUAVE.Core.Data()
field_length.takeoff = TOFL[0]
field_length.landing = LFL[0]
results.field_length = field_length
return results
def main():
# build the vehicle
vehicle = define_vehicle()
# define the mission
mission = define_mission(vehicle)
# evaluate the mission
results = evaluate_mission(vehicle, mission)
# define takeoff and landing configuration
takeoff_config, landing_config = define_field_configs(vehicle)
# define airport to be evaluated
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()
# evaluate takeoff
TOFL = estimate_take_off_field_length(vehicle, takeoff_config, airport)
# evaluate landing
LFL = estimate_landing_field_length(vehicle, landing_config, airport)
print 'Weigth: {:.0f} kg ; TOFL: {:.1f} m ; LFL: {:.1f} m'.format(
float(vehicle.Mass_Props.m_takeoff), float(TOFL), float(LFL))
# plot results
## post_process(vehicle,mission,results)
# compute payload range diagram
## cruise_segment_tag = 'CRUISE'
## payload_range(vehicle,mission,cruise_segment_tag)
plt.show(True)
return results, vehicle
def evaluate_field_length(vehicle,mission,results):
# unpack
airport = mission.airport
takeoff_config = vehicle.configs.takeoff
landing_config = vehicle.configs.landing
from SUAVE.Methods.Performance import estimate_take_off_field_length
from SUAVE.Methods.Performance import estimate_landing_field_length
# evaluate
TOFL = estimate_take_off_field_length(vehicle,takeoff_config,airport)
LFL = estimate_landing_field_length(vehicle,landing_config,airport)
# pack
field_length = Data()
field_length.takeoff = TOFL[0]
field_length.landing = LFL[0]
results.field_length = field_length
return results
def evaluate_field_length(vehicle, mission, results):
# unpack
airport = mission.airport
takeoff_config = vehicle.configs.takeoff
landing_config = vehicle.configs.landing
from SUAVE.Methods.Performance import estimate_take_off_field_length
from SUAVE.Methods.Performance import estimate_landing_field_length
# evaluate
TOFL = estimate_take_off_field_length(vehicle, takeoff_config, airport)
LFL = estimate_landing_field_length(vehicle, landing_config, airport)
# pack
field_length = Data()
field_length.takeoff = TOFL[0]
field_length.landing = LFL[0]
results.field_length = field_length
return results
def main():
# build the vehicle
vehicle = define_vehicle()
# define the mission
mission = define_mission(vehicle)
# evaluate the mission
results = evaluate_mission(vehicle,mission)
# define takeoff and landing configuration
takeoff_config,landing_config = define_field_configs(vehicle)
# define airport to be evaluated
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()
# evaluate takeoff
TOFL = estimate_take_off_field_length(vehicle,takeoff_config,airport)
# evaluate landing
LFL = estimate_landing_field_length(vehicle,landing_config,airport)
print 'Weigth: {:.0f} kg ; TOFL: {:.1f} m ; LFL: {:.1f} m'.format(float(vehicle.Mass_Props.m_takeoff),float(TOFL),float(LFL))
# plot results
## post_process(vehicle,mission,results)
# compute payload range diagram
## cruise_segment_tag = 'CRUISE'
## payload_range(vehicle,mission,cruise_segment_tag)
plt.show(True)
return results,vehicle