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Update tut_VSP_Import_Export_B737.py
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‎tut_VSP_Import_Export_B737.py‎

Lines changed: 259 additions & 21 deletions
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# tut_mission_B737.py
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# tut_VSP_Import_Export_B737.py
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#
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# Created: Aug 2014, SUAVE Team
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# Modified: Jun 2015, SUAVE Team
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""" setup file for a mission with a 737
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"""
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"""
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# ----------------------------------------------------------------------
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# Imports
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# ----------------------------------------------------------------------
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import SUAVE
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from SUAVE.Core import Units
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import numpy as np
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import pylab as plt
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import pickle
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import copy, time
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import os
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from SUAVE.Core import (
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Data, Container
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)
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import vsp
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from SUAVE.Input_Output.OpenVSP.vsp_write import write
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from SUAVE.Core import Units , Data, Container
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from SUAVE.Plots.Performance.Mission_Plots import *
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from SUAVE.Plots.Geometry import *
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from SUAVE.Methods.Propulsion.turbofan_sizing import turbofan_sizing
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from SUAVE.Methods.Propulsion.turbofan_sizing import turbofan_sizing
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from SUAVE.Methods.Geometry.Two_Dimensional.Planform import segment_properties
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from copy import deepcopy
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import vsp
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from SUAVE.Input_Output.OpenVSP.vsp_write import write
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import numpy as np
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import pylab as plt
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# ----------------------------------------------------------------------
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# Main
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# ----------------------------------------------------------------------
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def main():
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vehicle = vehicle_setup()
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write(vehicle, "B737-800")
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vehicle = vsp_export_vehicle_setup()
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write(vehicle, "B737-800")
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vehicle = vsp_import_vehicle_setup()
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return
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# ----------------------------------------------------------------------
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# Define the Vehicle
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# ----------------------------------------------------------------------
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def vehicle_setup():
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def vsp_export_vehicle_setup():
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# ------------------------------------------------------------------
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# Initialize the Vehicle
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# ------------------------------------------------------------------
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return vehicle
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def vsp_import_vehicle_setup():
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# ------------------------------------------------------------------
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# Turbofan Network
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# ------------------------------------------------------------------
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#instantiate the gas turbine network
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turbofan = SUAVE.Components.Energy.Networks.Turbofan()
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turbofan.tag = 'turbofan'
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# setup
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turbofan.number_of_engines = 2.0
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turbofan.bypass_ratio = 5.4
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turbofan.engine_length = 2.71
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# This origin is overwritten by compute_component_centers_of_gravity(base,compute_propulsor_origin=True)
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turbofan.origin = [[13.72, 4.86,-1.9],[13.72, -4.86,-1.9]]
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# working fluid
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turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
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# ------------------------------------------------------------------
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# Component 1 - Ram
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# to convert freestream static to stagnation quantities
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# instantiate
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ram = SUAVE.Components.Energy.Converters.Ram()
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ram.tag = 'ram'
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# add to the network
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turbofan.append(ram)
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# ------------------------------------------------------------------
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# Component 2 - Inlet Nozzle
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# instantiate
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inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
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inlet_nozzle.tag = 'inlet_nozzle'
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# setup
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inlet_nozzle.polytropic_efficiency = 0.98
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inlet_nozzle.pressure_ratio = 0.98
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# add to network
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turbofan.append(inlet_nozzle)
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# ------------------------------------------------------------------
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# Component 3 - Low Pressure Compressor
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# instantiate
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compressor = SUAVE.Components.Energy.Converters.Compressor()
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compressor.tag = 'low_pressure_compressor'
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# setup
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compressor.polytropic_efficiency = 0.91
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compressor.pressure_ratio = 1.14
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# add to network
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turbofan.append(compressor)
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# ------------------------------------------------------------------
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# Component 4 - High Pressure Compressor
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# instantiate
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compressor = SUAVE.Components.Energy.Converters.Compressor()
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compressor.tag = 'high_pressure_compressor'
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# setup
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compressor.polytropic_efficiency = 0.91
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compressor.pressure_ratio = 13.415
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# add to network
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turbofan.append(compressor)
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# ------------------------------------------------------------------
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# Component 5 - Low Pressure Turbine
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# instantiate
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turbine = SUAVE.Components.Energy.Converters.Turbine()
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turbine.tag='low_pressure_turbine'
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# setup
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turbine.mechanical_efficiency = 0.99
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turbine.polytropic_efficiency = 0.93
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# add to network
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turbofan.append(turbine)
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# ------------------------------------------------------------------
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# Component 6 - High Pressure Turbine
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# instantiate
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turbine = SUAVE.Components.Energy.Converters.Turbine()
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turbine.tag='high_pressure_turbine'
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# setup
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turbine.mechanical_efficiency = 0.99
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turbine.polytropic_efficiency = 0.93
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# add to network
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turbofan.append(turbine)
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# ------------------------------------------------------------------
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# Component 7 - Combustor
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# instantiate
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combustor = SUAVE.Components.Energy.Converters.Combustor()
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combustor.tag = 'combustor'
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# setup
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combustor.efficiency = 0.99
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combustor.alphac = 1.0
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combustor.turbine_inlet_temperature = 1450
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combustor.pressure_ratio = 0.95
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combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
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# add to network
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turbofan.append(combustor)
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# ------------------------------------------------------------------
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# Component 8 - Core Nozzle
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# instantiate
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nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
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nozzle.tag = 'core_nozzle'
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# setup
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nozzle.polytropic_efficiency = 0.95
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nozzle.pressure_ratio = 0.99
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# add to network
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turbofan.append(nozzle)
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# ------------------------------------------------------------------
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# Component 9 - Fan Nozzle
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# instantiate
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nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
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nozzle.tag = 'fan_nozzle'
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# setup
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nozzle.polytropic_efficiency = 0.95
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nozzle.pressure_ratio = 0.99
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# add to network
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turbofan.append(nozzle)
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# ------------------------------------------------------------------
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# Component 10 - Fan
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# instantiate
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fan = SUAVE.Components.Energy.Converters.Fan()
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fan.tag = 'fan'
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# setup
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fan.polytropic_efficiency = 0.93
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fan.pressure_ratio = 1.7
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# add to network
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turbofan.append(fan)
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# ------------------------------------------------------------------
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#Component 10 : thrust (to compute the thrust)
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thrust = SUAVE.Components.Energy.Processes.Thrust()
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thrust.tag ='compute_thrust'
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#total design thrust (includes all the engines)
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thrust.total_design = 2*24000. * Units.N #Newtons
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#design sizing conditions
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altitude = 35000.0*Units.ft
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mach_number = 0.78
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isa_deviation = 0.
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#Engine setup for noise module
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# add to network
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turbofan.thrust = thrust
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turbofan.core_nozzle_diameter = 0.92
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turbofan.fan_nozzle_diameter = 1.659
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turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
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turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
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turbofan.plug_diameter = 0.1 #dimater of the engine plug
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turbofan.geometry_xe = 1. # Geometry information for the installation effects function
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turbofan.geometry_ye = 1. # Geometry information for the installation effects function
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turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
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#size the turbofan
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turbofan_sizing(turbofan,mach_number,altitude)
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# add gas turbine network turbofan to the vehicle
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vehicle.append_component(turbofan)
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# ------------------------------------------------------------------
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# Fuel
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# ------------------------------------------------------------------
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fuel = SUAVE.Components.Physical_Component()
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vehicle.fuel = fuel
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fuel.mass_properties.mass = vehicle.mass_properties.max_takeoff-vehicle.mass_properties.max_fuel
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fuel.origin = vehicle.wings.main_wing.mass_properties.center_of_gravity
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fuel.mass_properties.center_of_gravity= vehicle.wings.main_wing.aerodynamic_center
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# ------------------------------------------------------------------
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# Landing Gear
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# ------------------------------------------------------------------
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landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
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landing_gear.tag = "main_landing_gear"
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landing_gear.main_tire_diameter = 1.12000 * Units.m
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landing_gear.nose_tire_diameter = 0.6858 * Units.m
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landing_gear.main_strut_length = 1.8 * Units.m
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landing_gear.nose_strut_length = 1.3 * Units.m
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landing_gear.main_units = 1 #number of nose landing gear
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landing_gear.nose_units = 1 #number of nose landing gear
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landing_gear.main_wheels = 2 #number of wheels on the main landing gear
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landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
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vehicle.landing_gear = landing_gear
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# ------------------------------------------------------------------
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# Vehicle Definition Complete
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# ------------------------------------------------------------------
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return vehicle
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if __name__ == '__main__':
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main()
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plt.show()

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