Merge pull request suavecode#21 from suavecode/feature-2point3

Feature 2point3

Regional_Jet_Optimization/Analyses.py

@@ -8,6 +8,9 @@
 # ----------------------------------------------------------------------    
 
 import SUAVE
+from SUAVE.Core import Units
+
+import numpy as np
 
 # ----------------------------------------------------------------------        
 #   Setup Analyses
@@ -55,6 +58,10 @@ def base(vehicle):
     #  Aerodynamics Analysis
     aerodynamics = SUAVE.Analyses.Aerodynamics.Fidelity_Zero()
     aerodynamics.geometry = vehicle
+    aerodynamics.settings.number_spanwise_vortices  = 5 
+    aerodynamics.settings.number_chordwise_vortices = 1
+    aerodynamics.process.compute.lift.inviscid_wings.training.angle_of_attack = np.array([[-5., 0.0, 5.0, 10.0, 75.]]).T * Units.deg 
+    aerodynamics.process.compute.lift.inviscid_wings.training.Mach            = np.array([[0.0, 0.2, 0.5, 0.70, 0.80, 0.9, 1.3, 1.35, 1.5, 2.0]]).T         
     analyses.append(aerodynamics)
 
     # ------------------------------------------------------------------

Regional_Jet_Optimization/Optimize.py

@@ -23,26 +23,19 @@
 #   Run the whole thing
 # ----------------------------------------------------------------------  
 def main():
+
     problem = setup()
 
     ## Base Input Values
-    #output = problem.objective()
+    output = problem.objective()
 
     ## Uncomment to view contours of the design space
     #variable_sweep(problem)
 
-    ## Uncomment for the first optimization
+    # Uncomment for the first optimization
     output = scipy_setup.SciPy_Solve(problem,solver='SLSQP')
     print (output)    
-
-    ## Uncomment these lines when you want to start an optimization problem from a different initial guess
-    #inputs                                   = [1.28, 1.38]
-    #scaling                                  = problem.optimization_problem.inputs[:,3] #have to rescale inputs to start problem from here
-    #scaled_inputs                            = np.multiply(inputs,scaling)
-    #problem.optimization_problem.inputs[:,1] = scaled_inputs
-    #output = scipy_setup.SciPy_Solve(problem,solver='SLSQP')
-    #print output        
-
+
     print('fuel burn = ', problem.summary.base_mission_fuelburn)
     print('fuel margin = ', problem.all_constraints())
 
@@ -64,17 +57,16 @@ def setup():
     # Inputs
     # -------------------------------------------------------------------
 
-    #   [ tag                            , initial, (lb,ub)             , scaling , units ]
+    #   [ tag                   , initial,     (lb , ub)        , scaling , units ]
     problem.inputs = np.array([
-        [ 'wing_area'                    ,  100    , (   90. ,   130.   ) ,   100. , Units.meter**2],
-        [ 'cruise_altitude'              ,  11    , (   9   ,    14.   ) ,   10.  , Units.km],
+        [ 'wing_area'           ,  92    , (   50. ,   130.   ) ,   100.  , Units.meter**2],
+        [ 'cruise_altitude'     ,   8    , (    6. ,    12.   ) ,   10.   , Units.km],
     ])
 
     # -------------------------------------------------------------------
     # Objective
     # -------------------------------------------------------------------
 
-    # throw an error if the user isn't specific about wildcards
     # [ tag, scaling, units ]
     problem.objective = np.array([
         [ 'fuel_burn', 10000, Units.kg ]
@@ -137,19 +129,18 @@ def variable_sweep(problem):
     objective   = outputs.objective
     constraints = outputs.constraint_val
     plt.figure(0)
-    CS   = plt.contourf(inputs[0,:],inputs[1,:], objective, 20, linewidths=2)
+    CS   = plt.contourf(inputs[0,:],inputs[1,:], objective, 20, linewidths=2,cmap='jet')
     cbar = plt.colorbar(CS)
 
     cbar.ax.set_ylabel('fuel burn (kg)')
-    CS_const = plt.contour(inputs[0,:],inputs[1,:], constraints[0,:,:])
+    CS_const = plt.contour(inputs[0,:],inputs[1,:], constraints[0,:,:],cmap='jet')
     plt.clabel(CS_const, inline=1, fontsize=10)
     cbar = plt.colorbar(CS_const)
     cbar.ax.set_ylabel('fuel margin')
 
     plt.xlabel('Wing Area (m^2)')
     plt.ylabel('Cruise Altitude (km)')
 
-    plt.legend(loc='upper left')  
     plt.show(block=True)    
 
     return

Regional_Jet_Optimization/Procedure.py

@@ -54,7 +54,6 @@ def setup():
 def find_target_range(nexus,mission):
 
     segments = mission.segments
-    cruise_altitude = mission.segments['climb_5'].altitude_end
     climb_1  = segments['climb_1']
     climb_2  = segments['climb_2']
     climb_3  = segments['climb_3']
@@ -139,55 +138,6 @@ def simple_sizing(nexus):
         turbofan_sizing(config.propulsors['turbofan'], mach_number = mach_number, altitude = altitude)
         compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
 
-
-    # ------------------------------------------------------------------
-    #   Landing Configuration
-    # ------------------------------------------------------------------
-    landing = nexus.vehicle_configurations.landing
-    state = Data()
-    state.conditions = Data()
-    state.conditions.freestream = Data()
-
-    # landing weight
-    landing.mass_properties.landing = 0.85 * config.mass_properties.takeoff
-
-    # Landing CL_max
-    altitude                                      = nexus.missions.base.segments[-1].altitude_end
-    atmosphere                                    = SUAVE.Analyses.Atmospheric.US_Standard_1976()
-    p, T, rho, a, mu                              = atmosphere.compute_values(altitude)
-    state.conditions.freestream.velocity          = nexus.missions.base.segments['descent_3'].air_speed
-    state.conditions.freestream.density           = rho
-    state.conditions.freestream.dynamic_viscosity = mu/rho
-    settings                                      = Data()
-    settings.maximum_lift_coefficient_factor      = 1.0
-    CL_max_landing, CDi                           = compute_max_lift_coeff(state,settings,landing)
-    landing.maximum_lift_coefficient              = CL_max_landing
-
-
-    #Takeoff CL_max
-    takeoff                                       = nexus.vehicle_configurations.takeoff
-    altitude                                      = nexus.missions.base.airport.altitude
-    atmosphere                                    = SUAVE.Analyses.Atmospheric.US_Standard_1976()
-    p, T, rho, a, mu                              = atmosphere.compute_values(altitude)
-    state.conditions.freestream.velocity          = nexus.missions.base.segments.climb_1.air_speed
-    state.conditions.freestream.density           = rho
-    state.conditions.freestream.dynamic_viscosity = mu/rho 
-    settings.maximum_lift_coefficient_factor      = 1.0    
-    max_CL_takeoff,CDi                            = compute_max_lift_coeff(state,settings,takeoff)
-    takeoff.maximum_lift_coefficient              = max_CL_takeoff
-
-    #Base config CL_max
-    base                                          = nexus.vehicle_configurations.base
-    altitude                                      = nexus.missions.base.airport.altitude
-    atmosphere                                    = SUAVE.Analyses.Atmospheric.US_Standard_1976()
-    p, T, rho, a, mu                              = atmosphere.compute_values(altitude)
-    state.conditions.freestream.velocity          = nexus.missions.base.segments.climb_1.air_speed
-    state.conditions.freestream.density           = rho
-    state.conditions.freestream.dynamic_viscosity = mu/rho 
-    settings.maximum_lift_coefficient_factor      = 1.0       
-    max_CL_base,CDi                               = compute_max_lift_coeff(state,settings,landing)
-    base.maximum_lift_coefficient                 = max_CL_base    
-
     return nexus
 
 # ----------------------------------------------------------------------        
@@ -198,17 +148,13 @@ def weight(nexus):
     vehicle=nexus.vehicle_configurations.base
 
     # weight analysis
-    weights = nexus.analyses.base.weights.evaluate()
-    weights = nexus.analyses.cruise.weights.evaluate()
+    weights = nexus.analyses.base.weights.evaluate(method="SUAVE")
+    weights = nexus.analyses.cruise.weights.evaluate(method="SUAVE")
     vehicle.mass_properties.breakdown = weights
-    weights = nexus.analyses.landing.weights.evaluate()
-    weights = nexus.analyses.takeoff.weights.evaluate()
-    weights = nexus.analyses.short_field_takeoff.weights.evaluate()
-
-    for config in nexus.vehicle_configurations:
-        config.mass_properties.zero_fuel_center_of_gravity  = vehicle.mass_properties.zero_fuel_center_of_gravity
-        config.fuel                                         = vehicle.fuel
-
+    weights = nexus.analyses.landing.weights.evaluate(method="SUAVE")
+    weights = nexus.analyses.takeoff.weights.evaluate(method="SUAVE")
+    weights = nexus.analyses.short_field_takeoff.weights.evaluate(method="SUAVE")
+
     return nexus
 
 # ----------------------------------------------------------------------
@@ -231,16 +177,7 @@ def post_process(nexus):
     vehicle                           = nexus.vehicle_configurations.base
     results                           = nexus.results
     summary                           = nexus.summary
-    missions                          = nexus.missions  
     nexus.total_number_of_iterations +=1
-    # Static stability calculations
-    CMA = -10.
-    for segment in results.base.segments.values():
-        max_CMA = np.max(segment.conditions.stability.static.Cm_alpha[:,0])
-        if max_CMA > CMA:
-            CMA = max_CMA
-
-    summary.static_stability = CMA
 
     #throttle in design mission
     max_throttle = 0
@@ -252,18 +189,15 @@ def post_process(nexus):
     summary.max_throttle = max_throttle
 
     # Fuel margin and base fuel calculations
-    operating_empty          = vehicle.mass_properties.operating_empty
-    payload                  = vehicle.mass_properties.breakdown.payload
     design_landing_weight    = results.base.segments[-1].conditions.weights.total_mass[-1]
     design_takeoff_weight    = vehicle.mass_properties.takeoff
-    max_takeoff_weight       = nexus.vehicle_configurations.takeoff.mass_properties.max_takeoff
-    zero_fuel_weight         = payload+operating_empty
+    zero_fuel_weight         = vehicle.mass_properties.breakdown.zero_fuel_weight
 
-    summary.max_zero_fuel_margin    = (design_landing_weight - zero_fuel_weight)/zero_fuel_weight
-    summary.base_mission_fuelburn   = design_takeoff_weight - results.base.segments['descent_3'].conditions.weights.total_mass[-1]
+    summary.max_zero_fuel_margin  = (design_landing_weight - zero_fuel_weight)/zero_fuel_weight
+    summary.base_mission_fuelburn = design_takeoff_weight - results.base.segments['descent_3'].conditions.weights.total_mass[-1]
 
     #when you run want to output results to a file
     filename = 'results.txt'
     write_optimization_outputs(nexus, filename)
-    
+
     return nexus    

Regional_Jet_Optimization/Vehicles.py

@@ -38,7 +38,6 @@ def base_setup():
     #   Vehicle-level Properties
     # ------------------------------------------------------------------
 
-    # mass properties (http://www.embraercommercialaviation.com/AircraftPDF/E190_Weights.pdf)
     vehicle.mass_properties.max_takeoff               = 51800.   # kg
     vehicle.mass_properties.operating_empty           = 27837.   # kg
     vehicle.mass_properties.takeoff                   = 51800.   # kg
@@ -47,9 +46,6 @@ def base_setup():
     vehicle.mass_properties.max_fuel                  = 12971.   # kg
     vehicle.mass_properties.cargo                     =     0.0  # kg
 
-    vehicle.mass_properties.center_of_gravity         = [[16.8, 0, 1.6]]
-    vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] 
-
     # envelope properties
     vehicle.envelope.ultimate_load = 3.5
     vehicle.envelope.limit_load    = 1.5
@@ -217,10 +213,11 @@ def base_setup():
     gt_engine.inlet_diameter    = 2.0
 
     #compute engine areas)
-    Amax                        = (np.pi/4.)*gt_engine.nacelle_diameter**2.
     Awet                        = 1.1*np.pi*gt_engine.nacelle_diameter*gt_engine.engine_length # 1.1 is simple coefficient
+
     #Assign engine area
     gt_engine.areas.wetted      = Awet
+
     #set the working fluid for the network
     working_fluid               = SUAVE.Attributes.Gases.Air()
 
@@ -320,7 +317,7 @@ def base_setup():
     #design sizing conditions
     altitude         = 35000.0*Units.ft
     mach_number      = 0.78 
-    isa_deviation    = 0.
+
     # add thrust to the network
     gt_engine.thrust = thrust
 

Solar_UAV_Optimization/Analyses.py

@@ -8,6 +8,8 @@
 # ----------------------------------------------------------------------    
 
 import SUAVE
+from SUAVE.Core import Units
+import numpy as np
 
 # ----------------------------------------------------------------------        
 #   Setup Analyses
@@ -54,6 +56,10 @@ def base(vehicle):
     # ------------------------------------------------------------------ 
     aerodynamics = SUAVE.Analyses.Aerodynamics.Fidelity_Zero()
     aerodynamics.geometry = vehicle
+    aerodynamics.settings.number_spanwise_vortices  = 10 
+    aerodynamics.settings.number_chordwise_vortices = 2
+    aerodynamics.process.compute.lift.inviscid_wings.training.angle_of_attack = np.array([[-5., 0.0, 5.0, 10.0, 75.]]).T * Units.deg 
+    aerodynamics.process.compute.lift.inviscid_wings.training.Mach            = np.array([[0.0, 0.2, 0.3, 0.9, 1.3, 1.35, 1.5, 2.0]]).T          
     analyses.append(aerodynamics)
 
     # ------------------------------------------------------------------

Solar_UAV_Optimization/Missions.py

@@ -54,7 +54,7 @@ def mission(analyses,vehicle):
     # connect vehicle configuration
     segment.analyses.extend(analyses.base)
 
-    # segment attributes     
+    # segment attributes
     segment.state.numerics.number_control_points = 50
     segment.dynamic_pressure = 115.0 * Units.pascals
     segment.start_time       = time.strptime("Tue, Jun 21  11:00:00  2020", "%a, %b %d %H:%M:%S %Y",)

Solar_UAV_Optimization/Optimize.py

@@ -17,6 +17,8 @@
 import SUAVE.Optimization.Package_Setups.scipy_setup as scipy_setup
 import SUAVE.Optimization.Package_Setups.pyopt_setup as pyopt_setup
 from SUAVE.Optimization.Nexus import Nexus
+import pylab as plt
+
 
 # ----------------------------------------------------------------------        
 #   Run the whole thing
@@ -48,11 +50,11 @@ def setup():
 
     # [ tag , initial, [lb,ub], scaling, units ]
     problem.inputs = np.array([
-        [ 'wing_area'       ,   0.62, (  0.1,    1.5 ),    0.5, Units.meter      ],
-        [ 'aspect_ratio'    ,   13.5, (  5.0,   20.0 ),   10.0, Units.less       ], 
-        [ 'dynamic_pressure',  115.0, (  1.0, 2000.0 ),  125.0, Units.pascals    ], 
-        [ 'solar_ratio'     ,    0.0, (  0.0,    0.97),    1.0, Units.less       ], 
-        [ 'kv'              ,  900.0, ( 10.0, 1500.0 ),  800.0, Units['rpm/volt']], 
+        [ 'wing_area'       ,    0.5, (  0.1,      1.5 ),    0.5, Units.meter      ],
+        [ 'aspect_ratio'    ,   10.0, (  5.0,     20.0 ),   10.0, Units.less       ], 
+        [ 'dynamic_pressure',  125.0, (  1.0,   2000.0 ),  125.0, Units.pascals    ], 
+        [ 'solar_ratio'     ,    0.0, (  0.0,      0.97),    1.0, Units.less       ], 
+        [ 'kv'              ,  800.0, ( 10.0,  10000.0 ),  800.0, Units['rpm/volt']], 
     ])
 
     # -------------------------------------------------------------------
@@ -120,4 +122,5 @@ def setup():
     return nexus
 
 if __name__ == '__main__':
-    main()
+    main()
+    plt.show()

Solar_UAV_Optimization/Vehicles.py

@@ -38,9 +38,9 @@ def base_setup():
     #   Vehicle-level Properties
     # ------------------------------------------------------------------    
     # mass properties
-    vehicle.mass_properties.takeoff         = 6.75 * Units.kg
-    vehicle.mass_properties.operating_empty = 6.75 * Units.kg
-    vehicle.mass_properties.max_takeoff     = 6.75 * Units.kg 
+    vehicle.mass_properties.takeoff         = 4.00 * Units.kg
+    vehicle.mass_properties.operating_empty = 4.00 * Units.kg
+    vehicle.mass_properties.max_takeoff     = 4.00 * Units.kg 
 
     # basic parameters
     vehicle.reference_area                    = 1.0       
@@ -171,24 +171,24 @@ def base_setup():
     esc.efficiency = 0.95 # Gundlach for brushless motors
     net.esc        = esc
 
-    # Component 5 the Propeller
+    # Component 4 the Propeller
     prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
     prop.propulsive_efficiency = 0.825
     net.propeller        = prop
 
-    # Component 4 the Motor
+    # Component 5 the Motor
     motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
-    motor.speed_constant       = 800. * Units['rpm/volt'] # RPM/volt is standard
+    motor.speed_constant       = 900. * Units['rpm/volt'] # RPM/volt is standard
     motor                      = size_from_kv(motor)    
     motor.gear_ratio           = 1. # Gear ratio, no gearbox
     motor.gearbox_efficiency   = 1. # Gear box efficiency, no gearbox
-    motor.motor_efficiency     = 0.825;
+    motor.motor_efficiency     = 0.8;
     net.motor                  = motor    
 
     # Component 6 the Payload
     payload = SUAVE.Components.Energy.Peripherals.Payload()
     payload.power_draw           = 0. #Watts 
-    payload.mass_properties.mass = 0.0 * Units.kg
+    payload.mass_properties.mass = 1.0 * Units.kg
     net.payload                  = payload
 
     # Component 7 the Avionics
@@ -198,8 +198,8 @@ def base_setup():
 
     # Component 8 the Battery
     bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
-    bat.mass_properties.mass = 5.0  * Units.kg
-    bat.specific_energy      = 250. *Units.Wh/Units.kg
+    bat.mass_properties.mass = 3.0  * Units.kg
+    bat.specific_energy      = 200. *Units.Wh/Units.kg
     bat.resistance           = 0.003
     initialize_from_mass(bat,bat.mass_properties.mass)
     net.battery              = bat