Merge branch 'develop' of https://github.com/suavecode/Tutorials into develop

# Conflicts:
#	Regional_Jet_Optimization/Analyses.py
#	Regional_Jet_Optimization/Optimize.py
#	Regional_Jet_Optimization/Plot_Mission.py
#	Regional_Jet_Optimization/Vehicles.py

Author: timdmacdo

Regional_Jet_Optimization/Analyses.py

@@ -21,9 +21,11 @@ def setup(configs):
     for tag,config in configs.items():
         analysis = base(config)
         if tag == 'cruise_spoilers':
-            analysis.aerodynamics.settings.spoiler_drag_increment = 0.005           
+            # this is done since drag is not sufficient for the desired profile
+            analysis.aerodynamics.settings.spoiler_drag_increment = 0.005       
         analyses[tag] = analysis
 
+
     return analyses
 
 # ----------------------------------------------------------------------        

Regional_Jet_Optimization/Optimize.py

@@ -1,6 +1,7 @@
 # Optimize.py
 # Created:  Feb 2016, M. Vegh
 # Modified: Aug 2017, E. Botero
+#           Aug 2018, T. MacDonald
 
 # ----------------------------------------------------------------------        
 #   Imports
@@ -23,19 +24,25 @@
 # ----------------------------------------------------------------------  
 def main():
     problem = setup()
-    #output = problem.objective()
-    #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
-    
-    #optimize
-    output = scipy_setup.SciPy_Solve(problem,solver='SLSQP')
-    print output
-  
 
-    #variable_sweep(problem)  #uncomment this to view some contours of the problem
+    ## Base Input Values
+    output = problem.objective()
+    
+    ## Uncomment to view contours of the design space
+    #variable_sweep(problem)
+    
+    ## 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()
 
@@ -125,33 +132,23 @@ def setup():
 
 def variable_sweep(problem):    
     number_of_points = 5
-    outputs=carpet_plot(problem, number_of_points, 0, 0)  #run carpet plot, suppressing default plots
-    inputs =outputs.inputs
-    objective=outputs.objective
-    constraints=outputs.constraint_val
+    outputs     = carpet_plot(problem, number_of_points, 0, 0)  #run carpet plot, suppressing default plots
+    inputs      = outputs.inputs
+    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)
     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,:,:])
     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)')
-    
-    #now plot optimization path (note that these data points were post-processed into a plottable format)
-    '''
-    opt_1   = plt.plot(wing_1, alt_1, label='optimization path 1')
-    init_1  = plt.plot(wing_1[0], alt_1[0], 'ko')
-    final_1 = plt.plot(wing_1[-1], alt_1[-1], 'kx')
+    plt.xlabel('Wing Area (m^2)')
+    plt.ylabel('Cruise Altitude (km)')
 
-    opt_2   = plt.plot(wing_2, alt_2, 'k--', label='optimization path 2')
-    init_2  = plt.plot(wing_2[0], alt_2[0], 'ko', label= 'initial points')
-    final_2 = plt.plot(wing_2[-1], alt_2[-1], 'kx', label= 'final points')
-    '''
     plt.legend(loc='upper left')  
     plt.show(block=True)    
 

Regional_Jet_Optimization/Plot_Mission.py

@@ -17,7 +17,7 @@
 # ----------------------------------------------------------------------
 
 def plot_mission(nexus,line_style='bo-'):
-    results=nexus.results.base
+    results   = nexus.results.base
     axis_font = {'fontname':'Arial', 'size':'14'}    
 
 

Regional_Jet_Optimization/Procedure.py

@@ -53,30 +53,30 @@ 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']
-    climb_4=segments['climb_4']
-    climb_5=segments['climb_5']
+    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']
+    climb_4  = segments['climb_4']
+    climb_5  = segments['climb_5']
 
-    descent_1=segments['descent_1']
-    descent_2=segments['descent_2']
-    descent_3=segments['descent_3']
+    descent_1 = segments['descent_1']
+    descent_2 = segments['descent_2']
+    descent_3 = segments['descent_3']
 
-    x_climb_1=climb_1.altitude_end/np.tan(np.arcsin(climb_1.climb_rate/climb_1.air_speed))
-    x_climb_2=(climb_2.altitude_end-climb_1.altitude_end)/np.tan(np.arcsin(climb_2.climb_rate/climb_2.air_speed))
-    x_climb_3=(climb_3.altitude_end-climb_2.altitude_end)/np.tan(np.arcsin(climb_3.climb_rate/climb_3.air_speed))
-    x_climb_4=(climb_4.altitude_end-climb_3.altitude_end)/np.tan(np.arcsin(climb_4.climb_rate/climb_4.air_speed))
-    x_climb_5=(climb_5.altitude_end-climb_4.altitude_end)/np.tan(np.arcsin(climb_5.climb_rate/climb_5.air_speed))
-    x_descent_1=(climb_5.altitude_end-descent_1.altitude_end)/np.tan(np.arcsin(descent_1.descent_rate/descent_1.air_speed))
-    x_descent_2=(descent_1.altitude_end-descent_2.altitude_end)/np.tan(np.arcsin(descent_2.descent_rate/descent_2.air_speed))
-    x_descent_3=(descent_2.altitude_end-descent_3.altitude_end)/np.tan(np.arcsin(descent_3.descent_rate/descent_3.air_speed))
-    
-    cruise_range=mission.design_range-(x_climb_1+x_climb_2+x_climb_3+x_climb_4+x_climb_5+x_descent_1+x_descent_2+x_descent_3)
+    x_climb_1   = climb_1.altitude_end/np.tan(np.arcsin(climb_1.climb_rate/climb_1.air_speed))
+    x_climb_2   = (climb_2.altitude_end-climb_1.altitude_end)/np.tan(np.arcsin(climb_2.climb_rate/climb_2.air_speed))
+    x_climb_3   = (climb_3.altitude_end-climb_2.altitude_end)/np.tan(np.arcsin(climb_3.climb_rate/climb_3.air_speed))
+    x_climb_4   = (climb_4.altitude_end-climb_3.altitude_end)/np.tan(np.arcsin(climb_4.climb_rate/climb_4.air_speed))
+    x_climb_5   = (climb_5.altitude_end-climb_4.altitude_end)/np.tan(np.arcsin(climb_5.climb_rate/climb_5.air_speed))
+    x_descent_1 = (climb_5.altitude_end-descent_1.altitude_end)/np.tan(np.arcsin(descent_1.descent_rate/descent_1.air_speed))
+    x_descent_2 = (descent_1.altitude_end-descent_2.altitude_end)/np.tan(np.arcsin(descent_2.descent_rate/descent_2.air_speed))
+    x_descent_3 = (descent_2.altitude_end-descent_3.altitude_end)/np.tan(np.arcsin(descent_3.descent_rate/descent_3.air_speed))
+    
+    cruise_range = mission.design_range-(x_climb_1+x_climb_2+x_climb_3+x_climb_4+x_climb_5+x_descent_1+x_descent_2+x_descent_3)
 
-    segments['cruise'].distance=cruise_range
+    segments['cruise'].distance = cruise_range
 
     return nexus
 
@@ -151,9 +151,9 @@ def simple_sizing(nexus):
     landing.mass_properties.landing = 0.85 * config.mass_properties.takeoff
 
     # Landing CL_max
-    altitude = nexus.missions.base.segments[-1].altitude_end
+    altitude   = nexus.missions.base.segments[-1].altitude_end
     atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
-    freestream_landing  = atmosphere.compute_values(0.)
+    freestream_landing = atmosphere.compute_values(0.)
     landing_conditions.freestream.velocity           = nexus.missions.base.segments['descent_3'].air_speed
     landing_conditions.freestream.density            = freestream_landing.density
     landing_conditions.freestream.dynamic_viscosity  = freestream_landing.dynamic_viscosity
@@ -165,19 +165,19 @@ def simple_sizing(nexus):
     takeoff_conditions = Data()
     takeoff_conditions.freestream = Data()    
     altitude = nexus.missions.base.airport.altitude
-    freestream_takeoff  = atmosphere.compute_values(altitude)
+    freestream_takeoff = atmosphere.compute_values(altitude)
 
     takeoff_conditions.freestream.velocity           = nexus.missions.base.segments.climb_1.air_speed
     takeoff_conditions.freestream.density            = freestream_takeoff.density
     takeoff_conditions.freestream.dynamic_viscosity  = freestream_takeoff.dynamic_viscosity 
-    max_CL_takeoff,CDi = compute_max_lift_coeff(takeoff,takeoff_conditions) 
+    max_CL_takeoff, CDi = compute_max_lift_coeff(takeoff,takeoff_conditions) 
     takeoff.maximum_lift_coefficient = max_CL_takeoff
 
     #Base config CL_max
     base = nexus.vehicle_configurations.base
     base_conditions = Data()
     base_conditions.freestream = takeoff_conditions.freestream   
-    max_CL_base,CDi = compute_max_lift_coeff(base,base_conditions) 
+    max_CL_base, CDi = compute_max_lift_coeff(base,base_conditions) 
     base.maximum_lift_coefficient = max_CL_base    
 
     return nexus
@@ -191,21 +191,14 @@ def weight(nexus):
 
     # weight analysis
     weights = nexus.analyses.base.weights.evaluate()
-   
-    '''
-    compute_component_centers_of_gravity(vehicle)
-    nose_load_fraction=.06
-    compute_aircraft_center_of_gravity(vehicle,nose_load_fraction)
-    '''
-    
     weights = nexus.analyses.cruise.weights.evaluate()
     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()
 
-    empty_weight    =vehicle.mass_properties.operating_empty
-    passenger_weight=vehicle.passenger_weights.mass_properties.mass 
+    empty_weight     = vehicle.mass_properties.operating_empty
+    passenger_weight = vehicle.passenger_weights.mass_properties.mass 
     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
@@ -230,27 +223,21 @@ def post_process(nexus):
 
     # Unpack data
     vehicle                           = nexus.vehicle_configurations.base
-    
-    '''
-    print 'base.mass_properties.takeoff = ', vehicle.mass_properties.takeoff
-    print 'takeoff.mass_properties.takeoff = ',  nexus.vehicle_configurations.takeoff.mass_properties.takeoff
-    print 'vehicle.mass_properties.empty = ', vehicle.mass_properties.operating_empty
-    '''
     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
+        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
+    max_throttle = 0
     for segment in results.base.segments.values():
         max_segment_throttle = np.max(segment.conditions.propulsion.throttle[:,0])
         if max_segment_throttle > max_throttle:
@@ -272,25 +259,5 @@ def post_process(nexus):
     #when you run want to output results to a file
     filename = 'results.txt'
     write_optimization_outputs(nexus, filename)
-    '''
-    unscaled_inputs = nexus.optimization_problem.inputs[:,1] #use optimization problem inputs here
-    input_scaling   = nexus.optimization_problem.inputs[:,3]
-    scaled_inputs   = unscaled_inputs/input_scaling
-    problem_inputs=[]
-    
-    for value in unscaled_inputs:
-        problem_inputs.append(value) 
-    file=open('results.txt' , 'ab')
-    file.write('iteration = ')
-    file.write(str(nexus.iteration_number))
-    file.write('fuel weight = ')
-    file.write(str( summary.base_mission_fuelburn))
-  
-    file.write(', inputs = ')
-    file.write(str(problem_inputs))
-    
-    file.write('\n') 
-    file.close()
-    '''
 
     return nexus    

Regional_Jet_Optimization/Vehicles.py

@@ -44,8 +44,8 @@ def base_setup():
     vehicle.mass_properties.max_payload               = 13063. * Units.kg
     vehicle.mass_properties.max_fuel                  = 12971. * Units.kg
 
-    vehicle.mass_properties.center_of_gravity         = [18. , 0, 0]
-    vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
+    vehicle.mass_properties.center_of_gravity         = [18., 0, 0]
+    #vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
 
     # envelope properties
     vehicle.envelope.ultimate_load = 3.5
@@ -368,7 +368,6 @@ def configs_setup(vehicle):
 
     config.maximum_lift_coefficient = 1.2
 
-    
     # ------------------------------------------------------------------
     #   Cruise with Spoilers Configuration
     # ------------------------------------------------------------------
@@ -378,7 +377,7 @@ def configs_setup(vehicle):
 
     configs.append(config)
 
-    config.maximum_lift_coefficient = 1.2    
+    config.maximum_lift_coefficient = 1.2
 
 
     # ------------------------------------------------------------------

Solar_UAV_Optimization/Vehicles.py

@@ -71,7 +71,6 @@ def base_setup():
     wing.twists.tip              = 0.0 * Units.degrees
     wing.highlift                = False  
     wing.vertical                = False 
-    wing.eta                     = 1.0
     wing.number_ribs             = 26.
     wing.number_end_ribs         = 2.
     wing.transition_x_upper      = 0.6