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Merge branch 'develop' of https://github.com/suavecode/Tutorials into develop
2 parents 42365d0 + 9157fdf commit 02780d0

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‎Solar_UAV_Optimization/Analyses.py‎

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# Analyses.py
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#
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# Created: Feb 2015, E. Botero
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# Modified:
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# ----------------------------------------------------------------------
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# Imports
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# ----------------------------------------------------------------------
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import SUAVE
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# ----------------------------------------------------------------------
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# Setup Analyses
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# ----------------------------------------------------------------------
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def setup(configs):
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analyses = SUAVE.Analyses.Analysis.Container()
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# build a base analysis for each config
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for tag,config in configs.items():
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analysis = base(config)
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analyses[tag] = analysis
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return analyses
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# ----------------------------------------------------------------------
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# Define Base Analysis
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# ----------------------------------------------------------------------
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def base(vehicle):
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# ------------------------------------------------------------------
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# Initialize the Analyses
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# ------------------------------------------------------------------
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analyses = SUAVE.Analyses.Vehicle()
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# ------------------------------------------------------------------
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# Basic Geometry Relations
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sizing = SUAVE.Analyses.Sizing.Sizing()
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sizing.features.vehicle = vehicle
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analyses.append(sizing)
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# ------------------------------------------------------------------
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# Weights
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# ------------------------------------------------------------------
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weights = SUAVE.Analyses.Weights.Weights()
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weights.settings.empty_weight_method = SUAVE.Methods.Weights.Correlations.UAV.Empty
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weights.vehicle = vehicle
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analyses.append(weights)
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# ------------------------------------------------------------------
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# Aerodynamics Analysis
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# ------------------------------------------------------------------
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aerodynamics = SUAVE.Analyses.Aerodynamics.Fidelity_Zero()
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aerodynamics.geometry = vehicle
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analyses.append(aerodynamics)
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# ------------------------------------------------------------------
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# Energy
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# ------------------------------------------------------------------
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energy = SUAVE.Analyses.Energy.Energy()
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energy.network = vehicle.propulsors
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analyses.append(energy)
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# ------------------------------------------------------------------
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# Planet Analysis
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# ------------------------------------------------------------------
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planet = SUAVE.Analyses.Planets.Planet()
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analyses.append(planet)
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# ------------------------------------------------------------------
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# Atmosphere Analysis
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# ------------------------------------------------------------------
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atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
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atmosphere.features.planet = planet.features
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analyses.append(atmosphere)
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return analyses

‎Solar_UAV_Optimization/Missions.py‎

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# Missions.py
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#
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# Created: Feb 2016, E. Botero
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# Modified:
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# ----------------------------------------------------------------------
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# Imports
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# ----------------------------------------------------------------------
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import SUAVE
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from SUAVE.Core import Units
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import time
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import numpy as np
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# ----------------------------------------------------------------------
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# Define the Mission
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# ----------------------------------------------------------------------
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def setup(analyses):
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# the mission container
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missions = SUAVE.Analyses.Mission.Mission.Container()
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missions.mission = mission(analyses)
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return missions
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def mission(analyses):
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# ------------------------------------------------------------------
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# Initialize the Mission
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# ------------------------------------------------------------------
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mission = SUAVE.Analyses.Mission.Sequential_Segments()
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mission.tag = 'mission'
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mission.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
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mission.planet = SUAVE.Attributes.Planets.Earth()
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# unpack Segments module
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Segments = SUAVE.Analyses.Mission.Segments
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# base segment
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base_segment = Segments.Segment()
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base_segment.process.iterate.initials.initialize_battery = SUAVE.Methods.Missions.Segments.Common.Energy.initialize_battery
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# ------------------------------------------------------------------
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# Cruise Segment: Constant Dynamic Pressure, Constant Altitude
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# ------------------------------------------------------------------
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segment = SUAVE.Analyses.Mission.Segments.Cruise.Constant_Dynamic_Pressure_Constant_Altitude(base_segment)
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segment.tag = "cruise"
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# connect vehicle configuration
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segment.analyses.extend(analyses.base)
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# segment attributes
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segment.state.numerics.number_control_points = 50
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segment.dynamic_pressure = 115.0 * Units.pascals
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segment.start_time = time.strptime("Tue, Jun 21 11:00:00 2016", "%a, %b %d %H:%M:%S %Y",)
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segment.altitude = 1000.0 * Units.feet
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segment.distance = 1000.0 * Units.km
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segment.charge_ratio = 1.0
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segment.latitude = 37.4
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segment.longitude = -122.15
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segment.state.conditions.frames.wind.body_rotations[:,2] = 125.* Units.degrees
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mission.append_segment(segment)
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return mission

‎Solar_UAV_Optimization/Optimize.py‎

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# Optimize.py
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#
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# Created: Feb 2016, E. Botero
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# Modified:
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# ----------------------------------------------------------------------
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# Imports
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# ----------------------------------------------------------------------
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from SUAVE.Core import Units, Data
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import numpy as np
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import Vehicles
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import Analyses
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import Missions
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import Procedure
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import Plot_Mission
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import SUAVE.Optimization.Package_Setups.scipy_setup as scipy_setup
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import SUAVE.Optimization.Package_Setups.pyopt_setup as pyopt_setup
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from SUAVE.Optimization.Nexus import Nexus
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# ----------------------------------------------------------------------
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# Run the whole thing
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# ----------------------------------------------------------------------
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def main():
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problem = setup()
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output = scipy_setup.SciPy_Solve(problem)
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problem.translate(output)
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Plot_Mission.plot_mission(problem.results.mission)
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return
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# ----------------------------------------------------------------------
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# Inputs, Objective, & Constraints
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# ----------------------------------------------------------------------
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def setup():
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nexus = Nexus()
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problem = Data()
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nexus.optimization_problem = problem
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# -------------------------------------------------------------------
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# Inputs
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# -------------------------------------------------------------------
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# [ tag , initial, [lb,ub], scaling, units ]
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problem.inputs = np.array([
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[ 'wing_area' , 0.5, ( 0.1, 1.5 ), 0.5, Units.meter ],
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[ 'aspect_ratio' , 10.0, ( 5.0, 20.0 ), 10.0, Units.less ],
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[ 'dynamic_pressure', 125.0, ( 1.0, 2000.0 ), 125.0, Units.pascals ],
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[ 'solar_ratio' , 0.0, ( 0.0, 0.97), 1.0, Units.less ],
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[ 'kv' , 800.0, ( 10.0, 1500.0 ), 800.0, Units['rpm/volt']],
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])
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# -------------------------------------------------------------------
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# Objective
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# -------------------------------------------------------------------
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# [ tag, scaling, units ]
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problem.objective = np.array([
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[ 'Nothing', 1. , Units.kg],####Optimize.py:
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])
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# -------------------------------------------------------------------
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# Constraints
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# -------------------------------------------------------------------
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# [ tag, sense, edge, scaling, units ]
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problem.constraints = np.array([
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[ 'energy_constraint', '=', 0.0, 1.0, Units.less],
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[ 'battery_mass' , '>', 0.0, 1.0, Units.kg ],
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[ 'CL' , '>', 0.0, 1.0, Units.less],
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[ 'Throttle_min' , '>', 0.0, 1.0, Units.less],
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[ 'Throttle_max' , '>', 0.0, 1.0, Units.less],
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])
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# -------------------------------------------------------------------
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# Aliases
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# -------------------------------------------------------------------
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# [ 'alias' , ['data.path1.name','data.path2.name'] ]
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problem.aliases = [
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[ 'wing_area' ,['vehicle_configurations.*.wings.main_wing.areas.reference',
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'vehicle_configurations.base.reference_area'] ],
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[ 'aspect_ratio' , 'vehicle_configurations.*.wings.main_wing.aspect_ratio' ],
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[ 'kv' , 'vehicle_configurations.*.propulsors.network.motor.speed_constant' ],
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[ 'battery_mass' , 'vehicle_configurations.base.propulsors.network.battery.mass_properties.mass'],
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[ 'solar_ratio' , 'vehicle_configurations.*.propulsors.network.solar_panel.ratio' ],
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[ 'dynamic_pressure' , 'missions.mission.segments.cruise.dynamic_pressure' ],
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[ 'Nothing' , 'summary.nothing' ],
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[ 'energy_constraint', 'summary.energy_constraint' ],
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[ 'CL' , 'summary.CL' ],
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[ 'Throttle_min' , 'summary.throttle_min' ],
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[ 'Throttle_max' , 'summary.throttle_max' ],
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]
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# -------------------------------------------------------------------
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# Vehicles
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# -------------------------------------------------------------------
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nexus.vehicle_configurations = Vehicles.setup()
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# -------------------------------------------------------------------
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# Analyses
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# -------------------------------------------------------------------
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nexus.analyses = Analyses.setup(nexus.vehicle_configurations)
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# -------------------------------------------------------------------
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# Missions
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# -------------------------------------------------------------------
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nexus.missions = Missions.setup(nexus.analyses)
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# -------------------------------------------------------------------
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# Procedure
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# -------------------------------------------------------------------
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nexus.procedure = Procedure.setup()
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return nexus
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if __name__ == '__main__':
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main()

‎Solar_UAV_Optimization/Plot_Mission.py‎

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# Plot_Mission.py
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#
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# Created: Feb 2016, E. Botero
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# Modified:
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# ----------------------------------------------------------------------
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# Imports
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# ----------------------------------------------------------------------
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from SUAVE.Core import Units
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import pylab as plt
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# ----------------------------------------------------------------------
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# Plot Mission
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# ----------------------------------------------------------------------
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def plot_mission(results,line_style='bo-'):
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axis_font = {'fontname':'Arial', 'size':'14'}
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# ------------------------------------------------------------------
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# Battery Energy
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# ------------------------------------------------------------------
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plt.figure("Battery Energy")
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axes = plt.gca()
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for i in range(len(results.segments)):
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time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min
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energy = results.segments[i].conditions.propulsion.battery_energy[:,0]
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axes.plot(time, energy, 'bo-')
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axes.set_xlabel('Time (mins)')
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axes.set_ylabel('Battery Energy (J)')
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axes.get_yaxis().get_major_formatter().set_scientific(False)
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axes.get_yaxis().get_major_formatter().set_useOffset(False)
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axes.grid(True)
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plt.savefig("opt_battery_energy.png")
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# ------------------------------------------------------------------
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# Solar Flux
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# ------------------------------------------------------------------
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plt.figure("Solar Flux")
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axes = plt.gca()
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for i in range(len(results.segments)):
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time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min
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energy = results.segments[i].conditions.propulsion.solar_flux[:,0]
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axes.plot(time, energy, 'bo-')
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axes.set_xlabel('Time (mins)')
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axes.set_ylabel('Solar Flux ($W/m^{2}$)')
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axes.get_yaxis().get_major_formatter().set_scientific(False)
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axes.get_yaxis().get_major_formatter().set_useOffset(False)
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axes.grid(True)
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plt.savefig("opt_solar_flux.png")
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# ------------------------------------------------------------------
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# Battery Draw
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# ------------------------------------------------------------------
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plt.figure("Battery Charging")
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axes = plt.gca()
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for i in range(len(results.segments)):
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time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min
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energy = results.segments[i].conditions.propulsion.battery_draw[:,0]
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axes.plot(time, energy, 'bo-')
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axes.set_xlabel('Time (mins)')
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axes.set_ylabel('Battery Charging (Watts)')
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axes.get_yaxis().get_major_formatter().set_scientific(False)
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axes.get_yaxis().get_major_formatter().set_useOffset(False)
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axes.grid(True)
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plt.savefig("opt_battery_draw.png")
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plt.show()
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return
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if __name__ == '__main__':
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main()
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plt.show()

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