various 2.5 fixes

Author: planes

B737_AVL_Tutorial/tut_mission_B737_AVL.py

@@ -113,23 +113,26 @@ def base_analysis(vehicle):
     # ------------------------------------------------------------------
     #  Aerodynamics Analysis
     aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
-    aerodynamics.process.compute.lift.inviscid.settings.filenames.avl_bin_name = 'CHANGE ME TO YOUR DIRECTORY'
+    #aerodynamics.process.compute.lift.inviscid.settings.filenames.avl_bin_name = 'CHANGE ME TO YOUR DIRECTORY'
+    aerodynamics.process.compute.lift.inviscid.settings.filenames.avl_bin_name = '/Users/emiliobotero/Research/avl3.35'
     #aerodynamics.process.compute.lift.inviscid.settings.spanwise_vortex_density    = 3 
     aerodynamics.geometry = vehicle
     analyses.append(aerodynamics)
 
     # ------------------------------------------------------------------
     #  Stability Analysis
     stability = SUAVE.Analyses.Stability.AVL()
-    stability.settings.filenames.avl_bin_name = 'CHANGE ME TO YOUR DIRECTORY'
+    #stability.settings.filenames.avl_bin_name = 'CHANGE ME TO YOUR DIRECTORY'
+    stability.settings.filenames.avl_bin_name = '/Users/emiliobotero/Research/avl3.35'
+    
     #stability.settings.spanwise_vortex_density                  = 3
     stability.geometry = vehicle
     analyses.append(stability)
 
     # ------------------------------------------------------------------
     #  Energy
     energy= SUAVE.Analyses.Energy.Energy()
-    energy.network = vehicle.propulsors 
+    energy.network = vehicle.networks
     analyses.append(energy)
 
     # ------------------------------------------------------------------
@@ -347,9 +350,6 @@ def vehicle_setup():
     turbofan.bypass_ratio      = 5.4
     turbofan.origin            = [[13.72, 4.86,-1.9],[13.72, -4.86,-1.9]]
 
-    #compute engine areas
-    turbofan.areas.wetted      = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
-    
     # working fluid
     turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
 

BWB_CFD/BWB.py

@@ -21,6 +21,7 @@
 
 from SUAVE.Methods.Propulsion.turbofan_sizing import turbofan_sizing
 from SUAVE.Methods.Geometry.Two_Dimensional.Cross_Section.Propulsion import compute_turbofan_geometry
+from SUAVE.Methods.Geometry.Two_Dimensional.Planform import segment_properties
 
 from SUAVE.Plots.Performance.Mission_Plots import *
 
@@ -156,7 +157,7 @@ def base_analysis(vehicle):
     # ------------------------------------------------------------------
     #  Energy
     energy= SUAVE.Analyses.Energy.Energy()
-    energy.network = vehicle.propulsors 
+    energy.network = vehicle.networks
     analyses.append(energy)
 
     # ------------------------------------------------------------------
@@ -330,6 +331,9 @@ def vehicle_setup():
     segment.sweeps.quarter_chord  = 0. * Units.degrees
     segment.thickness_to_chord    = 0.10
     wing.Segments.append(segment)  
+    
+    # Fill out more segment properties automatically
+    wing = segment_properties(wing)         
 
     # add to vehicle
     vehicle.append_component(wing)
@@ -341,20 +345,8 @@ def vehicle_setup():
     nacelle.diameter              = 3.96 * Units.meters 
     nacelle.length                = 289. * Units.inches
     nacelle.tag                   = 'nacelle' 
-    nacelle.origin                = [[133.0 *Units.feet, 25.0*Units.feet, 6.5*Units.feet]]
-    nacelle.areas.wetted          =  nacelle.length *(2*np.pi*nacelle.diameter/2.) 
-
-    nacelle_2                     = deepcopy(nacelle)
-    nacelle_2.tag                 = 'nacelle_2' 
-    nacelle_2.origin              = [[145.0 *Units.feet, 0.0*Units.feet, 6.5*Units.feet]]     
-     
-    nacelle_3                     = deepcopy(nacelle)
-    nacelle_3.tag                 = 'nacelle_3'
-    nacelle_3.origin              = [[133.0 *Units.feet, -25.0*Units.feet, 6.5*Units.feet]]   
-    
-    vehicle.append_component(nacelle) 
-    vehicle.append_component(nacelle_2) 
-    vehicle.append_component(nacelle_3) 
+    nacelle.origin                = [[123.0 *Units.feet, 25.0*Units.feet, 6.5*Units.feet]]
+    nacelle.Airfoil.naca_4_series_airfoil = '0012'
 
 
     # ------------------------------------------------------------------
@@ -506,19 +498,31 @@ def vehicle_setup():
     #design sizing conditions
     altitude      = 0. * Units.km
     mach_number   = 0.01
-    isa_deviation = 0.
 
     # add to network
     turbofan.thrust = thrust
 
     #size the turbofan
     turbofan_sizing(turbofan,mach_number,altitude)
-    #turbofan.size(mach_number,altitude)
 
     #computing the engine length and diameter
-    compute_turbofan_geometry(turbofan,None)
+    compute_turbofan_geometry(turbofan,nacelle)
 
     vehicle.append_component(turbofan)  
+    
+    # Finish adding all the nacelles
+    
+    nacelle_2                     = deepcopy(nacelle)
+    nacelle_2.tag                 = 'nacelle_2' 
+    nacelle_2.origin              = [[135.0 *Units.feet, 0.0*Units.feet, 6.5*Units.feet]]     
+     
+    nacelle_3                     = deepcopy(nacelle)
+    nacelle_3.tag                 = 'nacelle_3'
+    nacelle_3.origin              = [[123.0 *Units.feet, -25.0*Units.feet, 6.5*Units.feet]]   
+    
+    vehicle.append_component(nacelle) 
+    vehicle.append_component(nacelle_2) 
+    vehicle.append_component(nacelle_3)     
 
 
     # ------------------------------------------------------------------

tut_solar_uav.py

@@ -9,7 +9,7 @@
 import SUAVE
 #if not SUAVE.__version__=='2.5.0':
     #assert('These tutorials only work with the SUAVE 2.5.0 release')
-from SUAVE.Core import Units, Data
+from SUAVE.Core import Units
 
 import numpy as np
 import pylab as plt
@@ -240,23 +240,23 @@ def vehicle_setup():
     prop.tip_radius          = 4.25 * Units.meters
     prop.hub_radius          = 0.05 * Units.meters
     prop.design_Cl           = 0.7
-    prop.design_altitude     = 14.0 * Units.km
-    prop.design_thrust       = None
-    prop.design_power        = 3500.0 * Units.watts
+    prop.design_altitude     = 15.0 * Units.km
+    prop.design_power        = None
+    prop.design_thrust       = 120.
     prop                     = propeller_design(prop)
 
     net.propellers.append(prop)
 
     # Component 4 the Motor
     motor = SUAVE.Components.Energy.Converters.Motor()
-    motor.resistance           = 0.008
-    motor.no_load_current      = 4.5  * Units.ampere
-    motor.speed_constant       = 120. * Units['rpm'] # RPM/volt converted to (rad/s)/volt    
+    motor.resistance           = 0.006
+    motor.no_load_current      = 2.5  * Units.ampere
+    motor.speed_constant       = 30. * Units['rpm'] # RPM/volt converted to (rad/s)/volt    
     motor.propeller_radius     = prop.tip_radius
     motor.propeller_Cp         = prop.design_power_coefficient
     motor.gear_ratio           = 12. # Gear ratio
     motor.gearbox_efficiency   = .98 # Gear box efficiency
-    motor.expected_current     = 160. # Expected current
+    motor.expected_current     = 60. # Expected current
     motor.mass_properties.mass = 2.0  * Units.kg
     net.motors.append(motor)
 
@@ -274,15 +274,14 @@ def vehicle_setup():
     # Component 8 the Battery
     bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
     bat.mass_properties.mass = 90.0 * Units.kg
-    bat.specific_energy      = 700. * Units.Wh/Units.kg
-    bat.resistance           = 0.05
-    bat.max_voltage          = 45.0
-    initialize_from_mass(bat,bat.mass_properties.mass)
+    bat.specific_energy      = 600. * Units.Wh/Units.kg
+    bat.max_voltage          = 130.0
+    initialize_from_mass(bat)
     net.battery              = bat
 
     #Component 9 the system logic controller and MPPT
     logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
-    logic.system_voltage  = 40.0
+    logic.system_voltage  = 120.0
     logic.MPPT_efficiency = 0.95
     net.solar_logic       = logic
 
@@ -403,6 +402,7 @@ def mission_setup(analyses,vehicle):
 
     # base segment
     base_segment = Segments.Segment()   
+    base_segment.process.iterate.initials.initialize_battery = SUAVE.Methods.Missions.Segments.Common.Energy.initialize_battery
 
     # ------------------------------------------------------------------    
     #   Cruise Segment: constant speed, constant altitude
@@ -420,7 +420,7 @@ def mission_setup(analyses,vehicle):
     segment.altitude       = 15.0  * Units.km 
     segment.mach           = 0.12
     segment.distance       = 3050.0 * Units.km
-    segment.battery_energy = vehicle.networks.solar.battery.max_energy*0.2 #Charge the battery to start
+    segment.battery_energy = vehicle.networks.solar.battery.max_energy*0.3 #Charge the battery to start
     segment.latitude       = 37.4300   # this defaults to degrees (do not use Units.degrees)
     segment.longitude      = -122.1700 # this defaults to degrees
 
@@ -461,6 +461,9 @@ def plot_mission(results):
 
     # Plot Aerodynamic Coefficients
     plot_aerodynamic_coefficients(results)  
+    
+    # Drag Components
+    plot_drag_components(results)    
 
     # Plot Aircraft Flight Speed
     plot_aircraft_velocities(results)