# ATR_72.py # Created: 2025, M. Clarke, M. Guidotti # ---------------------------------------------------------------------------------------------------------------------- # IMPORT # ---------------------------------------------------------------------------------------------------------------------- # RCAIDE imports import RCAIDE from RCAIDE.Framework.Core import Units from RCAIDE.Library.Plots import * from RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop import design_turboprop from RCAIDE.Library.Methods.Performance import * # python imports import numpy as np from copy import deepcopy import matplotlib.pyplot as plt import os import sys # ---------------------------------------------------------------------- # Main # ---------------------------------------------------------------------- def main(): # Step 1: design a vehicle vehicle = vehicle_setup() # Step 2: create aircraft configuration based on vehicle configs = configs_setup(vehicle) # Step 3: set up analysis analyses = analyses_setup(configs) # Step 4: set up a flight mission mission = mission_setup(analyses) missions = missions_setup(mission) # Step 5: execute flight profile results = missions.base_mission.evaluate() # Step 6: plot results plot_mission(results) return # ---------------------------------------------------------------------- # Define Vehicle # --------------------------------------------------------------------- def vehicle_setup(): # ------------------------------------------------------------------ # File Paths # ------------------------------------------------------------------ ospath = os.path.abspath(__file__) separator = os.path.sep local_path = os.path.dirname(ospath) + separator + '..' airfoil_file_path = local_path + separator + 'Airfoils_and_Polars' + separator polar_file_path = local_path + separator + 'Airfoils_and_Polars' + separator + 'Polars' + separator # ------------------------------------------------------------------ # Initialize the Vehicle # ------------------------------------------------------------------ vehicle = RCAIDE.Vehicle() vehicle.tag = 'ATR_72' vehicle.mass_properties.max_takeoff = 23000 vehicle.mass_properties.takeoff = 23000 vehicle.mass_properties.operating_empty = 13010 vehicle.mass_properties.max_zero_fuel = 20000 vehicle.mass_properties.max_payload = 7100 vehicle.mass_properties.center_of_gravity = [[13.00381052,0,1.026]] vehicle.mass_properties.max_fuel = 5450 # envelope properties vehicle.flight_envelope.design_mach_number = 0.43 vehicle.flight_envelope.design_range = 890 * Units.nmi vehicle.flight_envelope.design_cruise_altitude = 25000 * Units.feet vehicle.flight_envelope.ultimate_load = 3.75 vehicle.flight_envelope.positive_limit_load = 1.5 vehicle.flight_envelope.design_dynamic_pressure = 5e4 # basic parameters vehicle.reference_area = 61.0 vehicle.number_of_passengers = 72 vehicle.systems.control = "fully powered" vehicle.systems.accessories = "short range" # ################################################# Landing Gear ############################################################# main_gear = RCAIDE.Library.Components.Landing_Gear.Main_Landing_Gear() main_gear.tire_diameter = 34 * Units.inches main_gear.rim_diameter = 16 * Units.inches main_gear.tire_width = 10 * Units.inches main_gear.strut_length = 1 * Units.meter main_gear.wheels = 4 main_gear.number_of_gear_types_in_tandem = 1 main_gear.number_of_wheels_in_gear_type = 2 main_gear.xz_plane_symmetric = True vehicle.append_component(main_gear) nose_gear = RCAIDE.Library.Components.Landing_Gear.Nose_Landing_Gear() nose_gear.tire_diameter = 17 * Units.inches nose_gear.rim_diameter = 7 * Units.inches nose_gear.tire_width = 17 * Units.inches nose_gear.strut_length = 1 * Units.meter nose_gear.wheels = 2 nose_gear.number_of_gear_types_in_tandem = 1 nose_gear.number_of_wheels_in_gear_type = 2 vehicle.append_component(nose_gear) # ################################################# Wings ############################################################# # ------------------------------------------------------------------ # Main Wing # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Main_Wing() wing.tag = 'main_wing' wing.areas.reference = 61.0 wing.spans.projected = 27.12 wing.aspect_ratio = (wing.spans.projected**2) / wing.areas.reference wing.sweeps.quarter_chord = 0.0 wing.thickness_to_chord = 0.1 wing.chords.root = 2.7 wing.chords.tip = 1.35 wing.total_length = wing.chords.root wing.taper = wing.chords.tip/wing.chords.root wing.chords.mean_aerodynamic = wing.chords.root * 2/3 * (( 1 + wing.taper + wing.taper**2 )/( 1 + wing.taper )) wing.areas.exposed = 2 * wing.areas.reference wing.areas.wetted = 2 * wing.areas.reference wing.origin = [[11.52756129,0,2.009316366]] wing.aerodynamic_center = [11.52756129 + 0.25*wing.chords.root ,0,2.009316366] wing.vertical = False wing.xz_plane_symmetric = True wing.dynamic_pressure_ratio = 1.0 # Wing Segments segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'root' segment.percent_span_location = 0.0 segment.twist = 0.0 * Units.deg segment.root_chord_percent = 1. segment.dihedral_outboard = 0.0 * Units.degrees segment.sweeps.quarter_chord = 0.0 * Units.degrees segment.thickness_to_chord = .15 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'inboard' segment.percent_span_location = 0.324 segment.twist = 0.0 * Units.deg segment.root_chord_percent = 1.0 segment.dihedral_outboard = 0.0 * Units.degrees segment.sweeps.leading_edge = 4.7 * Units.degrees segment.thickness_to_chord = .13 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tip' segment.percent_span_location = 1. segment.twist = 0. * Units.degrees segment.root_chord_percent = wing.taper segment.thickness_to_chord = 0.12 segment.dihedral_outboard = 0. segment.sweeps.quarter_chord = 0. wing.append_segment(segment) flap = RCAIDE.Library.Components.Wings.Control_Surfaces.Flap() flap.tag = 'flap' flap.span_fraction_start = 0.1 flap.span_fraction_end = 0.727 flap.deflection = 0.0 * Units.degrees flap.configuration_type = 'double_slotted' flap.chord_fraction = 0.25 wing.append_control_surface(flap) aileron = RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron() aileron.tag = 'aileron' aileron.span_fraction_start = 0.727 aileron.span_fraction_end = 1 aileron.deflection = 0.0 * Units.degrees aileron.chord_fraction = 0.4 wing.append_control_surface(aileron) # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Horizontal Stabilizer # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Horizontal_Tail() wing.tag = 'horizontal_stabilizer' wing.spans.projected = 3.61*2 wing.areas.reference = 15.2 wing.aspect_ratio = (wing.spans.projected**2) / wing.areas.reference wing.sweeps.leading_edge = 11.56*Units.degrees wing.thickness_to_chord = 0.12 wing.chords.root = 2.078645129 wing.chords.tip = 0.953457347 wing.total_length = wing.chords.root wing.taper = wing.chords.tip/wing.chords.root wing.chords.mean_aerodynamic = wing.chords.root * 2/3 * (( 1 + wing.taper + wing.taper**2 )/( 1 + wing.taper )) wing.twists.root = 0 * Units.degrees wing.twists.tip = 0 * Units.degrees wing.origin = [[25.505088,0,5.510942426]] wing.aerodynamic_center = [25.505088+ 0.25*wing.chords.root,0,2.009316366] wing.vertical = False wing.xz_plane_symmetric = True wing.dynamic_pressure_ratio = 0.95 # Wing Segments segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'root_segment' segment.percent_span_location = 0.0 segment.twist = 4. * Units.deg segment.root_chord_percent = 1.0 segment.sweeps.leading_edge = wing.sweeps.leading_edge segment.thickness_to_chord = .12 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tip_segment' segment.percent_span_location = 1. segment.twist = 4. * Units.deg segment.root_chord_percent = wing.taper segment.thickness_to_chord = .12 wing.append_segment(segment) # control surfaces ------------------------------------------- elevator = RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator() elevator.tag = 'elevator' elevator.span_fraction_start = 0.1 elevator.span_fraction_end = 0.9 elevator.deflection = 0.0 * Units.deg elevator.chord_fraction = 0.3 wing.append_control_surface(elevator) # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Vertical Stabilizer # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Vertical_Tail() wing.tag = 'vertical_stabilizer' wing.spans.projected = 4.5 wing.areas.reference = 12.7 wing.sweeps.quarter_chord = 54 * Units.degrees wing.thickness_to_chord = 0.1 wing.aspect_ratio = (wing.spans.projected**2) / wing.areas.reference wing.chords.root = 8.75 wing.chords.tip = 1.738510759 wing.total_length = wing.chords.root wing.taper = wing.chords.tip/wing.chords.root wing.chords.mean_aerodynamic = wing.chords.root * 2/3 * (( 1 + wing.taper + wing.taper**2 )/( 1 + wing.taper )) wing.areas.exposed = 2 * wing.areas.reference wing.areas.wetted = 2 * wing.areas.reference wing.twists.root = 0 * Units.degrees wing.twists.tip = 0 * Units.degrees wing.origin = [[17.34807199,0,1.3]] wing.aerodynamic_center = [17.34807199,0,1.3+ 0.25*wing.chords.root] wing.vertical = True wing.xz_plane_symmetric = False wing.t_tail = True wing.dynamic_pressure_ratio = 1.0 # Wing Segments segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'segment_1' segment.percent_span_location = 0.0 segment.twist = 0.0 segment.root_chord_percent = 1.0 segment.dihedral_outboard = 0.0 segment.sweeps.leading_edge = 75 * Units.degrees segment.thickness_to_chord = 0.10 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'segment_2' segment.percent_span_location = 1.331360381/wing.spans.projected segment.twist = 0.0 segment.root_chord_percent = 4.25/wing.chords.root segment.dihedral_outboard = 0 segment.sweeps.leading_edge = 54 * Units.degrees segment.thickness_to_chord = 0.15 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'segment_3' segment.percent_span_location = 3.058629978/wing.spans.projected segment.twist = 0.0 segment.root_chord_percent = 2.35/wing.chords.root segment.dihedral_outboard = 0 segment.sweeps.leading_edge = 31 * Units.degrees segment.thickness_to_chord = 0.13 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'segment_4' segment.percent_span_location = 4.380739035/wing.spans.projected segment.twist = 0.0 segment.root_chord_percent = 2.190082795/wing.chords.root segment.dihedral_outboard = 0 segment.sweeps.leading_edge = 52 * Units.degrees segment.thickness_to_chord = 0.13 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'segment_5' segment.percent_span_location = 1.0 segment.twist = 0.0 segment.root_chord_percent = 1.3/wing.chords.root segment.dihedral_outboard = 0 segment.sweeps.leading_edge = 0 * Units.degrees segment.thickness_to_chord = 0.13 wing.append_segment(segment) # control surfaces ------------------------------------------- rudder = RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder() rudder.tag = 'rudder' rudder.span_fraction_start = 0.09 rudder.span_fraction_end = 1 rudder.deflection = 0.0 * Units.deg rudder.chord_fraction = 0.3 wing.append_control_surface(rudder) # add to vehicle vehicle.append_component(wing) ## ########################################################## Landing Gear Pods ################################################################ landing_gear_pod = RCAIDE.Library.Components.Fuselages.Fuselage() landing_gear_pod.tag = 'landing_gear_pod' landing_gear_pod.origin = [[ 10, 0, -0.082]] landing_gear_pod.lengths.total = 6 landing_gear_pod.width = 3.5 landing_gear_pod.heights.maximum = 1.30 landing_gear_pod.heights.at_quarter_length = 1.05 landing_gear_pod.heights.at_three_quarters_length = 1.05 landing_gear_pod.effective_diameter = 3.5 landing_gear_pod.areas.wetted = 8.6715 landing_gear_pod.areas.front_projected = np.pi *( 1.30 / 2)*( 3.5 / 2) landing_gear_pod.differential_pressure = 0. # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_1' segment.percent_x_location = 0 segment.percent_z_location = 0 segment.height = 0.01 segment.width = 2.35 landing_gear_pod.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_2' segment.percent_x_location = 0.2 segment.percent_z_location = -0.25 / landing_gear_pod.lengths.total segment.height = 1.05 segment.width = 3.15 landing_gear_pod.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_3' segment.percent_x_location = 0.5 segment.percent_z_location = -0.25 /landing_gear_pod.lengths.total segment.height = 1.30 segment.width = 3.5 landing_gear_pod.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_4' segment.percent_x_location = 0.8 segment.percent_z_location = -0.25 /landing_gear_pod.lengths.total segment.height = 1.05 segment.width = 3.15 landing_gear_pod.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_5' segment.percent_x_location = 1 segment.percent_z_location = 0 segment.height = 0.01 segment.width = 2.35 landing_gear_pod.append_segment(segment) # add to vehicle vehicle.append_component(landing_gear_pod) # ########################################################## Fuselage ################################################################ # ------------------------------------------------------------------ # Fuselage # ------------------------------------------------------------------ fuselage = RCAIDE.Library.Components.Fuselages.Fuselage() fuselage.tag = 'fuselage' fuselage.seats_abreast = 4 fuselage.seat_pitch = 18 fuselage.fineness.nose = 1.6 fuselage.fineness.tail = 2. fuselage.lengths.total = 27.12 fuselage.lengths.nose = 3.375147531 fuselage.lengths.tail = 9.2 fuselage.effective_diameter = 2.985093814 fuselage.lengths.cabin = fuselage.lengths.total- (fuselage.lengths.nose + fuselage.lengths.tail ) fuselage.width = 2.985093814 fuselage.heights.maximum = 2.755708426 fuselage.areas.side_projected = fuselage.heights.maximum * fuselage.lengths.total * Units['meters**2'] fuselage.areas.wetted = np.pi * fuselage.width * fuselage.lengths.total * Units['meters**2'] fuselage.areas.front_projected = np.pi * (fuselage.width/2) **2 fuselage.differential_pressure = 5.0e4 * Units.pascal fuselage.heights.at_quarter_length = fuselage.heights.maximum * Units.meter fuselage.heights.at_three_quarters_length = fuselage.heights.maximum * Units.meter fuselage.heights.at_wing_root_quarter_chord = fuselage.heights.maximum* Units.meter # define cabin cabin = RCAIDE.Library.Components.Fuselages.Cabins.Cabin() cabin.origin = [[2,0,0]] economy_class = RCAIDE.Library.Components.Fuselages.Cabins.Classes.Economy() economy_class.number_of_seats_abrest = 4 economy_class.number_of_rows = 18 economy_class.galley_lavatory_percent_x_locations = [0, 9] economy_class.emergency_exit_percent_x_locations = [] economy_class.type_A_exit_percent_x_locations = [0.01,1] economy_class.number_of_seats = economy_class.number_of_rows * economy_class.number_of_seats_abrest cabin.append_cabin_class(economy_class) fuselage.append_cabin(cabin) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_1' segment.percent_x_location = 0.0000 segment.percent_z_location = 0.0000 segment.height = 0.0 segment.width = 0.0 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_2' segment.percent_x_location = 0.08732056/fuselage.lengths.total segment.percent_z_location = 0.0000 segment.height = 0.459245202 segment.width = 0.401839552 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_3' segment.percent_x_location = 0.197094977/fuselage.lengths.total segment.percent_z_location = 0.001 segment.height = 0.688749197 segment.width = 0.918490404 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_4' segment.percent_x_location = 0.41997031/fuselage.lengths.total segment.percent_z_location = 0.0000 segment.height = 0.975896055 segment.width = 1.320329956 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_5' segment.percent_x_location = 0.753451685/fuselage.lengths.total segment.percent_z_location = 0.0014551442477876075 # this is given as a percentage of the fuselage length i.e. location of the center of the cross section/fuselage length segment.height = 1.320329956 segment.width = 1.664763858 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_6' segment.percent_x_location = 1.14389933/fuselage.lengths.total segment.percent_z_location = 0.0036330994100294946 segment.height = 1.607358208 segment.width = 2.009316366 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_7' segment.percent_x_location = 1.585491874/fuselage.lengths.total segment.percent_z_location = 0.008262262758112099 segment.height = 2.18141471 segment.width = 2.411155918 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_8' segment.percent_x_location = 2.031242539/fuselage.lengths.total segment.percent_z_location = 0.013612882669616513 segment.height = 2.468442962 segment.width = 2.698065563 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_9' segment.percent_x_location = 2.59009412/fuselage.lengths.total segment.percent_z_location = 0.01636321766224188 segment.height = 2.640659912 segment.width = 2.812876863 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_10' segment.percent_x_location = 3.375147531/fuselage.lengths.total segment.percent_z_location = 0.01860240047935103 segment.height = 2.755708426 segment.width = 2.985093814 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_11' segment.percent_x_location = 17.01420312/fuselage.lengths.total segment.percent_z_location = 0.01860240047935103 segment.height = 2.755708426 segment.width = 2.985093814 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_12' segment.percent_x_location = 18.64210783/fuselage.lengths.total segment.percent_z_location = 0.01860240047935103 segment.height = 2.698302776 segment.width = 2.927925377 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_13' segment.percent_x_location = 22.7416002/fuselage.lengths.total segment.percent_z_location = 0.043363795685840714 segment.height = 1.779575158 segment.width = 1.722050901 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_14' segment.percent_x_location = 1. segment.percent_z_location = 0.06630560070058995 segment.height = 0.401839552 segment.width = 0.401839552 fuselage.append_segment(segment) # add to vehicle vehicle.append_component(fuselage) # ######################################################## Energy Network ######################################################### net = RCAIDE.Framework.Networks.Fuel() #------------------------------------------------------------------------------------------------------------------------- # Fuel Distribution Line #------------------------------------------------------------------------------------------------------------------------- fuel_line = RCAIDE.Library.Components.Powertrain.Distributors.Fuel_Line() #------------------------------------------------------------------------------------------------------------------------------------ # Propulsor #------------------------------------------------------------------------------------------------------------------------------------ starboard_propulsor = RCAIDE.Library.Components.Powertrain.Propulsors.Turboprop() starboard_propulsor.tag = 'starboard_propulsor' starboard_propulsor.origin = [[ 9.559106394 ,4.219315295, 1.616135105]] starboard_propulsor.working_fluid = RCAIDE.Library.Attributes.Gases.Air() starboard_propulsor.gearbox.efficiency = 0.99 starboard_propulsor.design_thrust = 15000.0 * Units.N starboard_propulsor.design_altitude = 25000*Units.ft starboard_propulsor.design_freestream_velocity = 270 * Units.kts #Propeller Design propeller = RCAIDE.Library.Components.Powertrain.Converters.Propeller() propeller.tag = 'starboard_propulsor_propeller' propeller.origin = [[9.1,4.219315295, 1.616135105 ]] propeller.active = True propeller.tip_radius = 2.8/2 propeller.hub_radius = 0.1 propeller.number_of_blades = 3 propeller.design_efficiency = 0.83 propeller.design_angular_velocity = 3000.0 * Units.rpm propeller.design_thrust = starboard_propulsor.design_thrust propeller.design_altitude = starboard_propulsor.design_altitude propeller.design_freestream_velocity = starboard_propulsor.design_freestream_velocity starboard_propulsor.propeller = propeller # Ram inlet ram = RCAIDE.Library.Components.Powertrain.Converters.Ram() ram.tag = 'ram' starboard_propulsor.ram = ram # inlet nozzle inlet_nozzle = RCAIDE.Library.Components.Powertrain.Converters.Compression_Nozzle() inlet_nozzle.tag = 'inlet nozzle' inlet_nozzle.pressure_ratio = 0.98 inlet_nozzle.compressibility_effects = False starboard_propulsor.inlet_nozzle = inlet_nozzle # compressor compressor = RCAIDE.Library.Components.Powertrain.Converters.Compressor() compressor.tag = 'lpc' compressor.pressure_ratio = 10 starboard_propulsor.compressor = compressor # combustor combustor = RCAIDE.Library.Components.Powertrain.Converters.Combustor() combustor.tag = 'Comb' combustor.efficiency = 0.99 combustor.turbine_inlet_temperature = 1370 combustor.pressure_ratio = 0.96 combustor.fuel_data = RCAIDE.Library.Attributes.Propellants.Jet_A() starboard_propulsor.combustor = combustor # high pressure turbine high_pressure_turbine = RCAIDE.Library.Components.Powertrain.Converters.Turbine() high_pressure_turbine.tag ='hpt' high_pressure_turbine.mechanical_efficiency = 0.99 starboard_propulsor.high_pressure_turbine = high_pressure_turbine # low pressure turbine low_pressure_turbine = RCAIDE.Library.Components.Powertrain.Converters.Turbine() low_pressure_turbine.tag ='lpt' low_pressure_turbine.mechanical_efficiency = 0.99 starboard_propulsor.low_pressure_turbine = low_pressure_turbine # core nozzle core_nozzle = RCAIDE.Library.Components.Powertrain.Converters.Expansion_Nozzle() core_nozzle.tag = 'core nozzle' core_nozzle.pressure_ratio = 0.99 starboard_propulsor.core_nozzle = core_nozzle # design starboard_propulsor design_turboprop(starboard_propulsor) #------------------------------------------------------------------------------------------------------------------------------------ # Nacelles #------------------------------------------------------------------------------------------------------------------------------------ nacelle = RCAIDE.Library.Components.Nacelles.Stack_Nacelle() nacelle.tag = 'nacelle_1' nacelle.length = 5 nacelle.diameter = 0.85 nacelle.areas.wetted = 1.0 nacelle.origin = [[8.941625295,4.219315295, 1.616135105 ]] nacelle.flow_through = False nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_1' nac_segment.percent_x_location = 0.0 nac_segment.height = 0.0 nac_segment.width = 0.0 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_2' nac_segment.percent_x_location = 0.2 / nacelle.length nac_segment.percent_z_location = 0 nac_segment.height = 0.4 nac_segment.width = 0.4 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_3' nac_segment.percent_x_location = 0.6 / nacelle.length nac_segment.percent_z_location = 0 nac_segment.height = 0.52 nac_segment.width = 0.700 nac_segment.curvature = 3 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_4' nac_segment.percent_x_location = 0.754 / nacelle.length nac_segment.percent_z_location = -0.15 / nacelle.length nac_segment.height = 0.9 nac_segment.width = 0.85 nac_segment.curvature = 3 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_5' nac_segment.percent_x_location = 1.154 / nacelle.length nac_segment.percent_z_location = -0.1/ nacelle.length nac_segment.height = 1 nac_segment.width = 0.85 nac_segment.curvature = 4 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_6' nac_segment.percent_x_location = 3.414 / nacelle.length nac_segment.percent_z_location = -0.1 / nacelle.length nac_segment.height = 0.9 nac_segment.width = 0.85 nac_segment.curvature = 4 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_6' nac_segment.percent_x_location = 0.96 nac_segment.percent_z_location = 0.05/ nacelle.length nac_segment.height = 0.6 nac_segment.width = 0.5 nac_segment.curvature = 4 nacelle.append_segment(nac_segment) nac_segment = RCAIDE.Library.Components.Nacelles.Segments.Segment() nac_segment.tag = 'segment_7' nac_segment.percent_x_location = 1.0 nac_segment.percent_z_location = 0.15/ nacelle.length nac_segment.height = 0.4 nac_segment.width = 0.2 nac_segment.curvature = 4 nacelle.append_segment(nac_segment) starboard_propulsor.nacelle = nacelle net.propulsors.append(starboard_propulsor) #------------------------------------------------------------------------------------------------------------------------------------ # Propulsor: Port Propulsor #------------------------------------------------------------------------------------------------------------------------------------ port_propulsor = deepcopy(starboard_propulsor) port_propulsor.tag = 'port_propulsor' port_propulsor.origin = [[ 9.559106394 ,-4.219315295, 1.616135105]] # change origin port_propulsor.nacelle.tag = 'port_propulsor_nacelle' port_propulsor.nacelle.origin = [[8.941625295,-4.219315295, 1.616135105 ]] port_propulsor.propeller.tag = 'port_propulsor_propeller' port_propulsor.propeller.origin = [[9.1,-4.219315295, 1.616135105 ]] # append propulsor to distribution line net.propulsors.append(port_propulsor) #------------------------------------------------------------------------------------------------------------------------- # Energy Source: Fuel Tank #------------------------------------------------------------------------------------------------------------------------- inboard_tank = RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank(vehicle.wings.main_wing) inboard_tank.fuel = RCAIDE.Library.Attributes.Propellants.Jet_A() inboard_tank.segments_bounding_tank = ['root','inboard'] fuel_line.fuel_tanks.append(inboard_tank) outboard_tank = RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank(vehicle.wings.main_wing) outboard_tank.fuel = RCAIDE.Library.Attributes.Propellants.Jet_A() outboard_tank.segments_bounding_tank = ['inboard', 'tip'] fuel_line.fuel_tanks.append(outboard_tank) #------------------------------------------------------------------------------------------------------------------------------------ # Assign propulsors to fuel line fuel_line.assigned_propulsors = [[starboard_propulsor.tag, port_propulsor.tag]] # Append fuel line to Network net.fuel_lines.append(fuel_line) # Append energy network to aircraft vehicle.append_energy_network(net) return vehicle # ---------------------------------------------------------------------- # Define the Configurations # --------------------------------------------------------------------- def configs_setup(vehicle): # ------------------------------------------------------------------ # Initialize Configurations # ------------------------------------------------------------------ configs = RCAIDE.Library.Components.Configs.Config.Container() base_config = RCAIDE.Library.Components.Configs.Config(vehicle) base_config.tag = 'base' configs.append(base_config) return configs # ---------------------------------------------------------------------- # Define the Analyses # ---------------------------------------------------------------------- def analyses_setup(configs): analyses = RCAIDE.Framework.Analyses.Analysis.Container() # build a base analysis for each config for tag,config in configs.items(): analysis = base_analysis(config) analyses[tag] = analysis return analyses # ---------------------------------------------------------------------- # Define the Base Analysis # ---------------------------------------------------------------------- def base_analysis(vehicle): # ------------------------------------------------------------------ # Initialize the Analyses # ------------------------------------------------------------------ analyses = RCAIDE.Framework.Analyses.Vehicle() analyses.vehicle = vehicle analyses.vehicle = vehicle # Geometry geometry = RCAIDE.Framework.Analyses.Geometry.Geometry() geometry.settings.overwrite_reference = True geometry.settings.update_wing_properties = True analyses.append(geometry) # ------------------------------------------------------------------ # Weights # ------------------------------------------------------------------ weights = RCAIDE.Framework.Analyses.Weights.Conventional_Transport() weights.settings.update_moment_of_inertia = True weights.method = "Raymer" weights.settings.weight_correction_factors.empty.systems.apu = 0.0 weights.settings.weight_correction_factors.empty.systems.furnishings = 0.5 analyses.append(weights) # ------------------------------------------------------------------ # Aerodynamics Analysis # ------------------------------------------------------------------ aerodynamics = RCAIDE.Framework.Analyses.Aerodynamics.Vortex_Lattice_Method() analyses.append(aerodynamics) # ------------------------------------------------------------------ # Stability Analysis # ------------------------------------------------------------------ stability = RCAIDE.Framework.Analyses.Stability.Vortex_Lattice_Method() stability.settings.compute_neutral_point = True analyses.append(stability) # ------------------------------------------------------------------ # Energy # ------------------------------------------------------------------ energy= RCAIDE.Framework.Analyses.Energy.Energy() analyses.append(energy) # ------------------------------------------------------------------ # Planet Analysis # ------------------------------------------------------------------ planet = RCAIDE.Framework.Analyses.Planets.Earth() analyses.append(planet) # ------------------------------------------------------------------ # Atmosphere Analysis # ------------------------------------------------------------------ atmosphere = RCAIDE.Framework.Analyses.Atmospheric.US_Standard_1976() analyses.append(atmosphere) # done! return analyses # ---------------------------------------------------------------------- # Define the Missions # ---------------------------------------------------------------------- def missions_setup(mission): missions = RCAIDE.Framework.Mission.Missions() # base mission mission.tag = 'base_mission' missions.append(mission) return missions # ---------------------------------------------------------------------- # Define the Mission # ---------------------------------------------------------------------- def mission_setup(analyses): # ------------------------------------------------------------------ # Initialize the Mission # ------------------------------------------------------------------ mission = RCAIDE.Framework.Mission.Sequential_Segments() mission.tag = 'mission' # unpack Segments module Segments = RCAIDE.Framework.Mission.Segments base_segment = Segments.Segment() base_segment.state.numerics.solver.type = "root_finder" # ------------------------------------------------------------------ # Takeoff # ------------------------------------------------------------------ segment = Segments.Ground.Takeoff(base_segment) segment.tag = "Takeoff" segment.analyses.extend( analyses.base) segment.velocity_start = 10 * Units.knots segment.velocity_end = 120 * Units.knots segment.friction_coefficient = 0.04 segment.throttle = 0.8 mission.append_segment(segment) # ------------------------------------------------------------------ # Departure End of Runway Segment Flight 1 : # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = 'Departure_End_of_Runway' segment.analyses.extend( analyses.base ) segment.altitude_start = 0.0 * Units.feet segment.altitude_end = 50.0 * Units.feet segment.air_speed_start = 120 * Units.knots segment.air_speed_end = 125 * Units.knots # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Initial Climb Area Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = 'Initial_CLimb_Area' segment.analyses.extend( analyses.base ) segment.altitude_start = 50.0 * Units.feet segment.altitude_end = 500.0 * Units.feet segment.air_speed_end = 130 * Units.knots segment.climb_rate = 600 * Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Climb Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = 'Climb_1' segment.analyses.extend( analyses.base) segment.altitude_start = 500.0 * Units.feet segment.altitude_end = 2500 * Units.feet segment.air_speed_end = 200 * Units.kts segment.climb_rate = 500* Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Climb 1 : constant Speed, constant rate segment # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = "Climb_2" segment.analyses.extend( analyses.base) segment.altitude_start = 2500.0 * Units.feet segment.altitude_end = 22000 * Units.feet segment.air_speed_end = 270 * Units.kts segment.climb_rate = 500.034 * Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Cruise Segment: constant Speed, constant altitude # ------------------------------------------------------------------ segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment) segment.tag = "Cruise" segment.analyses.extend(analyses.base) segment.altitude = 22000 * Units.feet segment.air_speed = 270 * Units.kts segment.distance = 862. * Units.nautical_mile # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.throttle.initial_guess_values = [[0.74]] segment.assigned_control_variables.pitch_angle.active = True segment.assigned_control_variables.pitch_angle.initial_guess_values = [[4.2 * Units.degree]] mission.append_segment(segment) # ------------------------------------------------------------------ # Descent Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = "Descent" segment.analyses.extend( analyses.base) segment.altitude_start = 22000 * Units.feet segment.altitude_end = 1000 * Units.feet segment.air_speed_end = 200 * Units.kts segment.climb_rate = -2000 * Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Downleg_Altitude Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment) segment.tag = 'Downleg' segment.analyses.extend(analyses.base) segment.distance = 6000 * Units.feet # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Baseleg Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = 'Baseleg' segment.analyses.extend( analyses.base) segment.altitude_start = 1000 * Units.feet segment.altitude_end = 500.0 * Units.feet segment.air_speed_end = 120 * Units.knots segment.climb_rate = -350 * Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True # ------------------------------------------------------------------ # Final Approach Segment Flight 1 # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment_name = 'Final_Approach' segment.tag = segment_name segment.analyses.extend( analyses.base) segment.altitude_start = 500.0 * Units.feet segment.altitude_end = 0.0 * Units.feet segment.air_speed_end = 110 * Units.knots segment.climb_rate = -300 * Units['ft/min'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Landing # ------------------------------------------------------------------ segment = Segments.Ground.Landing(base_segment) segment.tag = "Landing" segment.analyses.extend( analyses.base) segment.velocity_end = 120 * Units.knots * 0.1 segment.friction_coefficient = 0.4 segment.altitude = 0.0 segment.assigned_control_variables.elapsed_time.active = True segment.assigned_control_variables.elapsed_time.initial_guess_values = [[30.]] mission.append_segment(segment) return mission # ---------------------------------------------------------------------- # Plot Mission # ---------------------------------------------------------------------- def plot_mission(results): # Plot Flight Conditions plot_flight_conditions(results) # Plot Aerodynamic Forces plot_aerodynamic_forces(results) # Plot Aerodynamic Coefficients plot_aerodynamic_coefficients(results) # Drag Components plot_drag_components(results) # Plot Altitude, sfc, vehicle weight plot_altitude_sfc_weight(results) # Plot Velocities plot_aircraft_velocities(results) # Plot Trajectory plot_flight_trajectory(results) # Plot throttles plot_propulsor_throttles(results) return if __name__ == '__main__': main() plt.show()