Updated tutorial scripts

Author: rachealerhard

Regional_Jet_Optimization/Optimize.py

@@ -23,22 +23,22 @@
 #   Run the whole thing
 # ----------------------------------------------------------------------  
 def main():
+    import time
+    t = time.time()
+    
     problem = setup()
 
     ## Base Input Values
     #output = problem.objective()
-    import time
-    t = time.time()
 
-    # Uncomment to view contours of the design space
-    variable_sweep(problem)
+    ## Uncomment to view contours of the design space
+    #variable_sweep(problem)
 
-    t_elapsed = time.time() - t
-    
-    ## Uncomment for the first optimization
-    #output = scipy_setup.SciPy_Solve(problem,solver='SLSQP')
-    #print (output)    
+    # Uncomment for the first optimization
+    output = scipy_setup.SciPy_Solve(problem,solver='SLSQP')
+    print (output)    
 
+    t_elapsed = time.time() - t
     ## 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
@@ -70,8 +70,8 @@ def setup():
 
     #   [ 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'           ,  90   , (   90. ,   130.   ) ,   100.  , Units.meter**2],
+        [ 'cruise_altitude'     ,  10    , (   9   ,    14.   ) ,   10.   , Units.km],
     ])
 
     # -------------------------------------------------------------------

Regional_Jet_Optimization/Procedure.py

@@ -253,11 +253,11 @@ def post_process(nexus):
 
     # Fuel margin and base fuel calculations
     operating_empty          = vehicle.mass_properties.operating_empty
-    payload                  = vehicle.mass_properties.breakdown.payload
+    payload                  = vehicle.mass_properties.breakdown.payload_breakdown
     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]

Solar_UAV_Optimization/Vehicles.py

@@ -171,12 +171,12 @@ 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                      = size_from_kv(motor)    

tut_solar_uav.py

@@ -242,7 +242,7 @@ def vehicle_setup():
     motor.no_load_current      = 4.5  * Units.ampere
     motor.speed_constant       = 120. * Units['rpm'] # RPM/volt converted to (rad/s)/volt    
     motor.propeller_radius     = prop.tip_radius
-    motor.propeller_Cp         = prop.power_coefficient
+    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
@@ -396,7 +396,7 @@ def mission_setup(analyses,vehicle):
     base_segment.process.iterate.unknowns.network            = vehicle.propulsors.solar.unpack_unknowns
     base_segment.process.iterate.residuals.network           = vehicle.propulsors.solar.residuals    
     base_segment.process.iterate.initials.initialize_battery = SUAVE.Methods.Missions.Segments.Common.Energy.initialize_battery
-    base_segment.state.unknowns.propeller_power_coefficient  = vehicle.propulsors.solar.propeller.power_coefficient  * ones_row(1)/15.
+    base_segment.state.unknowns.propeller_power_coefficient  = vehicle.propulsors.solar.propeller.design_power_coefficient  * ones_row(1)/15.
     base_segment.state.residuals.network                     = 0. * ones_row(1)      
 
     # ------------------------------------------------------------------