solar UAVs

Author: planes

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 +54,8 @@ def mission(analyses,vehicle):
     # connect vehicle configuration
     segment.analyses.extend(analyses.base)
 
-    # segment attributes     
+    # segment attributes
+    ones_row = segment.state.numerics.ones_row
     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

@@ -48,11 +48,11 @@ 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']], 
     ])
 
     # -------------------------------------------------------------------

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       
@@ -178,17 +178,17 @@ def base_setup():
 
     # 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

tut_solar_uav.py

@@ -16,7 +16,7 @@
 from SUAVE.Plots.Mission_Plots import *
 from SUAVE.Components.Energy.Networks.Solar import Solar
 from SUAVE.Methods.Propulsion import propeller_design
-from SUAVE.Methods.Power.Battery.Sizing import initialize_from_energy_and_power, initialize_from_mass
+from SUAVE.Methods.Power.Battery.Sizing import initialize_from_mass
 
 # ----------------------------------------------------------------------
 #   Main