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