updates to regional jet opt script

Author: timdmacdo

Regional_Jet_Optimization/Analyses.py

@@ -20,8 +20,11 @@ def setup(configs):
     # build a base analysis for each config
     for tag,config in configs.items():
         analysis = base(config)
+        if tag == 'cruise_spoilers':
+            analysis.aerodynamics.settings.spoiler_drag_increment = 0.005       
         analyses[tag] = analysis
 
+
     return analyses
 
 # ----------------------------------------------------------------------        

Regional_Jet_Optimization/Missions.py

@@ -210,7 +210,7 @@ def base(analyses):
     segment.tag = "descent_2"
 
     # connect vehicle configuration
-    segment.analyses.extend( analyses.cruise )
+    segment.analyses.extend( analyses.cruise_spoilers )
 
     # segment attributes
     segment.atmosphere   = atmosphere

Regional_Jet_Optimization/Optimize.py

@@ -23,25 +23,27 @@
 # ----------------------------------------------------------------------  
 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
+    
+    ## 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
-  
+    #print output    
 
-    #variable_sweep(problem)  #uncomment this to view some contours of the problem
+    ## 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
+  
     print 'fuel burn = ', problem.summary.base_mission_fuelburn
     print 'fuel margin = ', problem.all_constraints()
 
-    #Plot_Mission.plot_mission(problem)
+    Plot_Mission.plot_mission(problem)
 
     return
 
@@ -126,34 +128,24 @@ def setup():
     return nexus
 
 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
+    number_of_points = 20
+    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
+    results   = nexus.results.base
     axis_font = {'fontname':'Arial', 'size':'14'}    
 
 
@@ -54,7 +54,7 @@ def plot_mission(nexus,line_style='bo-'):
     # ------------------------------------------------------------------
     fig = plt.figure("Drag Components",figsize=(8,10))
     axes = plt.gca()
-    for i, segment in enumerate(results.base.segments.values()):
+    for i, segment in enumerate(results.segments.values()):
 
         time   = segment.conditions.frames.inertial.time[:,0] / Units.min
         drag_breakdown = segment.conditions.aerodynamics.drag_breakdown

Regional_Jet_Optimization/Vehicles.py

@@ -367,6 +367,17 @@ def configs_setup(vehicle):
     configs.append(config)
 
     config.maximum_lift_coefficient = 1.2
+    
+    # ------------------------------------------------------------------
+    #   Cruise with Spoilers Configuration
+    # ------------------------------------------------------------------
+
+    config = SUAVE.Components.Configs.Config(base_config)
+    config.tag = 'cruise_spoilers'
+
+    configs.append(config)
+    
+    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