Feature sizing

Lithium_Air_Sizing/Analyses.py

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+# Analyses.py
+# 
+# Created:  May 2015, E. Botero
+# Modified: 
+
+# ----------------------------------------------------------------------        
+#   Imports
+# ----------------------------------------------------------------------    
+
+import SUAVE
+
+# ----------------------------------------------------------------------        
+#   Setup Analyses
+# ----------------------------------------------------------------------  
+
+def setup(configs):
+    #Ereq=configs.Ereq
+    #Preq=configs.Preq
+    analyses = SUAVE.Analyses.Analysis.Container()
+
+    # build a base analysis for each config
+    for tag,config in configs.items():
+        analysis = base(config)
+        analyses[tag] = analysis
+
+    # adjust analyses for configs
+
+    # takeoff_analysis
+    analyses.takeoff.aerodynamics.settings.drag_coefficient_increment = 0.0000
+
+    # landing analysis
+    aerodynamics = analyses.landing.aerodynamics
+
+    return analyses
+
+# ----------------------------------------------------------------------        
+#   Define Base Analysis
+# ----------------------------------------------------------------------  
+
+def base(vehicle):
+
+    # ------------------------------------------------------------------
+    #   Initialize the Analyses
+    # ------------------------------------------------------------------     
+    analyses = SUAVE.Analyses.Vehicle()
+
+    # ------------------------------------------------------------------
+    #  Basic Geometry Relations
+    sizing = SUAVE.Analyses.Sizing.Sizing()
+    sizing.features.vehicle = vehicle
+    analyses.append(sizing)
+
+    # ------------------------------------------------------------------
+    #  Weights
+    weights = SUAVE.Analyses.Weights.Weights()
+    weights.settings.empty_weight_method= \
+           SUAVE.Methods.Weights.Correlations.Tube_Wing.empty
+    weights.vehicle = vehicle
+    analyses.append(weights)
+
+    # ------------------------------------------------------------------
+    #  Aerodynamics Analysis
+    aerodynamics = SUAVE.Analyses.Aerodynamics.Fidelity_Zero()
+    aerodynamics.geometry = vehicle
+    aerodynamics.settings.drag_coefficient_increment = 0.0000
+    analyses.append(aerodynamics)
+
+    # ------------------------------------------------------------------
+    #  Stability Analysis
+    stability = SUAVE.Analyses.Stability.Fidelity_Zero()
+    stability.geometry = vehicle
+    analyses.append(stability)
+
+    # ------------------------------------------------------------------
+    #  Propulsion Analysis
+    energy= SUAVE.Analyses.Energy.Energy()
+    energy.network = vehicle.energy_network                              # SEE THIS
+    analyses.append(energy)
+
+    # ------------------------------------------------------------------
+    #  Planet Analysis
+    planet = SUAVE.Analyses.Planets.Planet()
+    analyses.append(planet)
+
+    # ------------------------------------------------------------------
+    #  Atmosphere Analysis
+    atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
+    atmosphere.features.planet = planet.features
+    analyses.append(atmosphere)   
+    # done!
+    return analyses 

Lithium_Air_Sizing/Mission.py

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+# Missions.py
+# 
+# Created:  Jan 2017, M. Vegh
+# Modified: 
+
+
+# ----------------------------------------------------------------------        
+#   Imports
+# ----------------------------------------------------------------------    
+
+import SUAVE
+from SUAVE.Core import Units
+
+import numpy as np
+
+# ----------------------------------------------------------------------
+#   Define the Mission
+# ----------------------------------------------------------------------
+
+def setup(analyses):
+
+    # the mission container
+    missions = SUAVE.Analyses.Mission.Mission.Container()
+
+    # ------------------------------------------------------------------
+    #   Base Mission
+    # ------------------------------------------------------------------
+    base_mission = base(analyses)
+    missions.base = base_mission
+
+
+    return missions  
+
+
+def base(analyses):
+
+    # ------------------------------------------------------------------
+    #   Initialize the Mission
+    # ------------------------------------------------------------------
+    sol_tol = 1E-12
+    mission = SUAVE.Analyses.Mission.Sequential_Segments()
+    mission.tag = 'embraer_e190ar test mission'
+
+    # atmospheric model
+    atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
+    planet = SUAVE.Attributes.Planets.Earth()
+
+    #airport
+    airport = SUAVE.Attributes.Airports.Airport()
+    airport.altitude   =  0.0  * Units.ft
+    airport.delta_isa  =  0.0
+    airport.atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
+    mission.airport = airport
+
+    # unpack Segments module
+    Segments = SUAVE.Analyses.Mission.Segments    
+
+
+    # ------------------------------------------------------------------
+    #   First Climb Segment: constant Mach, constant segment angle 
+    # ------------------------------------------------------------------
+
+    segment = Segments.Climb.Constant_Speed_Constant_Rate()
+    segment.tag = "climb_1"
+
+    segment.analyses.extend( analyses.takeoff )
+
+    segment.altitude_start = 0.0   * Units.km
+    segment.altitude_end   = 1.0   * Units.km
+    segment.air_speed      = 80. * Units['m/s']
+    segment.climb_rate     = 6.0   * Units['m/s']
+    segment.state.numerics.tolerance_solution = sol_tol
+    # add to misison
+    mission.append_segment(segment)
+
+
+    # ------------------------------------------------------------------
+    #   Second Climb Segment: constant Speed, constant segment angle 
+    # ------------------------------------------------------------------    
+
+    segment = Segments.Climb.Constant_Speed_Constant_Rate()
+    segment.tag = "climb_2"
+
+    segment.analyses.extend( analyses.cruise )
+
+    segment.altitude_end   = 2.0   * Units.km
+    segment.air_speed      = 100.* Units['m/s']
+    segment.climb_rate     = 6.0   * Units['m/s']
+    segment.state.numerics.tolerance_solution = sol_tol
+    # add to mission
+    mission.append_segment(segment)
+
+
+    # ------------------------------------------------------------------
+    #   Third Climb Segment: constant Mach, constant segment angle 
+    # ------------------------------------------------------------------    
+
+    segment = Segments.Climb.Constant_Speed_Constant_Rate()
+    segment.tag = "climb_3"
+
+    segment.analyses.extend( analyses.cruise )
+
+    segment.altitude_end = 10. * Units.km
+    segment.air_speed    =140* Units['m/s']
+    segment.climb_rate   = 3.0    * Units['m/s']
+    segment.state.numerics.tolerance_solution = sol_tol
+    # add to mission
+    mission.append_segment(segment)
+
+
+    # ------------------------------------------------------------------    
+    #   Cruise Segment: constant speed, constant altitude
+    # ------------------------------------------------------------------    
+
+    segment = Segments.Cruise.Constant_Speed_Constant_Altitude()
+    segment.tag = "cruise"
+
+    segment.analyses.extend( analyses.cruise )
+
+    segment.air_speed  = 230 * Units['m/s']
+    segment.distance   = 2000 * Units.nautical_miles
+    segment.state.numerics.tolerance_solution = sol_tol
+    mission.append_segment(segment)
+
+
+    # ------------------------------------------------------------------    
+    #   First Descent Segment: consant speed, constant segment rate
+    # ------------------------------------------------------------------    
+
+    segment = Segments.Descent.Constant_Speed_Constant_Rate()
+    segment.tag = "descent_1"
+
+    segment.analyses.extend( analyses.cruise )
+
+    segment.altitude_end = 2.   * Units.km
+    segment.air_speed    = 120.0 * Units['m/s']
+    segment.descent_rate = 5.0   * Units['m/s']
+    segment.state.numerics.tolerance_solution = sol_tol
+
+    # add to mission
+    mission.append_segment(segment)
+
+
+    # ------------------------------------------------------------------    
+    #   Second Descent Segment: consant speed, constant segment rate
+    # ------------------------------------------------------------------    
+
+    segment = Segments.Descent.Constant_Speed_Constant_Rate()
+    segment.tag = "descent_2"
+
+    segment.analyses.extend( analyses.cruise )
+
+    segment.altitude_end = 0.0   * Units.km
+    segment.air_speed    = 100.0 * Units['m/s']
+    segment.descent_rate = 5.0   * Units['m/s']
+    segment.state.numerics.tolerance_solution = sol_tol
+
+    # append to mission
+    mission.append_segment(segment)
+
+    # ------------------------------------------------------------------    
+    #   Mission definition complete    
+    # ------------------------------------------------------------------
+
+
+    return mission
+
+# ----------------------------------------------------------------------        
+#   Call Main
+# ----------------------------------------------------------------------    
+
+if __name__ == '__main__':
+    import vehicles
+    import analyses
+
+    vehicles = vehicles.setup()
+    analyses = analyses.setup(vehicles)
+    missions = setup(analyses)
+
+    vehicles.finalize()
+    analyses.finalize()
+    missions.finalize()
+
+    missions.base.evaluate()