rslt.ans.desc

多学科优化软件isight培训教程初级pdf有很详细的例子讲解

MDOLVersion: 6.0
CompilerOptions: warn

Task Airplane

    TaskHeader Airplane
        Version: 1.0
        Evaluation: taskplan
        ControlMode: user
        RunCounter: 1
        BoundsPolicy: adjustvalue
        CheckPoint: unknown
    End TaskHeader Airplane

    Inputs Airplane
        Parameter: WingSpan Type: real InitialValue: 22.72
        Parameter: WingArea Type: real InitialValue: 179.073
        Parameter: FuseLength Type: real InitialValue: 32.6
        Parameter: FuseDia Type: real InitialValue: 4.85
        Parameter: CruiseVel Type: real InitialValue: 200.0
        Parameter: WtFuel Type: real InitialValue: 296.0
        Parameter: WtEng Type: real InitialValue: 197.0
        Parameter: NumEng Type: integer InitialValue: 1
        Parameter: NumPass Type: integer InitialValue: 2
        Parameter: WtPayload Type: real InitialValue: 100.0
    End Inputs Airplane

    Outputs Airplane
        Parameter: SurfAreaFuse Type: real
        Parameter: WetArea Type: real
        Parameter: LoD Type: real
        Parameter: AR Type: real
        Parameter: WingChord Type: real
        Parameter: LoadedWt Type: real
        Parameter: AircraftRange Type: real
        Parameter: StallSpd Type: real
    End Outputs Airplane

    Calculations Airplane
        Calculation AspectRatioCalc
            Parameters
                WingSpan WingArea AR WingChord
            Tcl
                set AR(V) [expr $WingSpan(V)*$WingSpan(V)/$WingArea(V)]
                set WingChord(V) [expr $WingArea(V)/$WingSpan(V)]
            End Tcl
        End Calculation AspectRatioCalc
    End Calculations Airplane

    SimCode AeroCode
        InputFiles AeroCode
            FileDescription AeroIntxt
                FileType: standard
                TemplateFile: "AeroInTemp.dat"
                InputFile: "AeroIn.txt"
                Parameters
                    WingSpan WingArea FuseLength FuseDia
                Instructions
                    find "b     = " ignore 
                    write $WingSpan as "%7.3f"
                    find "Swing = " ignore 
                    replace word with $WingArea 
                    find "Lfuse = " ignore 
                    replace word with $FuseLength 
                    find "Dfuse = " ignore 
                    replace word with $FuseDia as "%9.5f"
                End Instructions
            End FileDescription AeroIntxt
        End InputFiles AeroCode

        OutputFiles AeroCode
            FileDescription AeroOuttxt
                FileType: standard
                OutputFile: "AeroOut.txt"
                Parameters
                    SurfAreaFuse WetArea LoD
                Instructions
                    find "Surface Area of the Fuselage = " ignore 
                    read SurfAreaFuse as "%g"
                    provide $SurfAreaFuse 
                    find "Wetted Area of the Aircraft  = " ignore 
                    read WetArea as "%g"
                    provide $WetArea 
                    find "Lift/Drag of the Aircraft    = " ignore 
                    read LoD as "%g"
                    provide $LoD
                End Instructions
            End FileDescription AeroOuttxt
        End OutputFiles AeroCode

        SimCodeProcess AeroCode
            Program: "../Programs/aero.exe"
            ElapseTime: 5m
            Prologue
                WriteInputSpecs: AeroIntxt
            Epilogue
                ReadOutputSpecs: AeroOuttxt
            Execution: "$Program"
        End SimCodeProcess AeroCode

    End SimCode AeroCode

    SimCode WeightsCode
        InputFiles WeightsCode
            FileDescription WeightsIntxt
                FileType: standard
                TemplateFile: "WeightsInTemp.dat"
                InputFile: "WeightsIn.txt"
                Parameters
                    CruiseVel WingArea AR FuseLength FuseDia WtFuel WtEng NumEng NumPass WtPayload
                Instructions
                    replace "velocity" with $CruiseVel ignore 
                    replace "wingarea" with $WingArea ignore 
                    replace "aspectratio" with $AR ignore 
                    replace "fuselength" with $FuseLength ignore 
                    replace "fusediameter" with $FuseDia ignore 
                    replace "weightfuel" with $WtFuel ignore 
                    replace "weightengine" with $WtEng ignore 
                    replace "numberofengines" with $NumEng ignore 
                    replace "numberofpassengers" with $NumPass ignore 
                    replace "weightofpayload" with $WtPayload ignore
                End Instructions
            End FileDescription WeightsIntxt
        End InputFiles WeightsCode

        OutputFiles WeightsCode
            FileDescription WeightsOuttxt
                FileType: standard
                OutputFile: "WeightsOut.txt"
                Parameters
                    LoadedWt
                Instructions
                    find "Total Weight of Loaded Aircraft (lbs.)       = " ignore 
                    read LoadedWt as "%g"
                    provide $LoadedWt
                End Instructions
            End FileDescription WeightsOuttxt
        End OutputFiles WeightsCode

        SimCodeProcess WeightsCode
            Program: "../Programs/weights.exe"
            ElapseTime: 5m
            Prologue
                WriteInputSpecs: WeightsIntxt
            Epilogue
                ReadOutputSpecs: WeightsOuttxt
            Execution: "$Program"
        End SimCodeProcess WeightsCode

    End SimCode WeightsCode

    Task PerfTask

        TaskHeader PerfTask
            Version: 1.0
            Evaluation: single
            ControlMode: user
            RunCounter: 1
            BoundsPolicy: adjustvalue
            CheckPoint: unknown
        End TaskHeader PerfTask

        Inputs PerfTask
            Parameter: DragRatio Type: real InitialValue: 8.42585
            Parameter: LoadedWeight Type: real InitialValue: 2312.94
            Parameter: WeightOfFuel Type: real InitialValue: 296.0
            Parameter: AreaOfWing Type: real InitialValue: 177.3
        End Inputs PerfTask

        Outputs PerfTask
            Parameter: AircraftRange Type: real
            Parameter: StallSpeed Type: real
        End Outputs PerfTask

        SimCode PerfCode
            InputFiles PerfCode
                FileDescription PerfInput
                    FileType: standard
                    TemplateFile: "PerfInTemp.dat"
                    InputFile: "PerfIn.txt"
                    Parameters
                        DragRatio LoadedWeight WeightOfFuel AreaOfWing
                    Instructions
                        find "LoverD =" ignore 
                        replace word with $DragRatio as "%10.5f" 
                        find "Wtot =" ignore 
                        replace word with $LoadedWeight as "%10.5f"
                        find "Wfueltot =" ignore 
                        replace word with $WeightOfFuel as "%10.5f" 
                        find "Swing =" ignore 
                        replace word with $AreaOfWing as "%10.5f"
                    End Instructions
                End FileDescription PerfInput
            End InputFiles PerfCode

            OutputFiles PerfCode
                FileDescription PerfOutput
                    FileType: standard
                    OutputFile: "PerfOut.txt"
                    Parameters
                        AircraftRange StallSpeed
                    Instructions
                        find "Max. Range (miles)                         = "
                        read AircraftRange as "%g"
                        provide $AircraftRange 
                        find "Stall Speed (miles/hr)                     = " ignore 
                        read StallSpeed as "%g"
                        provide $StallSpeed
                    End Instructions
                End FileDescription PerfOutput
            End OutputFiles PerfCode

            SimCodeProcess PerfCode
                Program: "../Programs/perf.exe"
                ElapseTime: 5m
                Prologue
                    WriteInputSpecs: PerfInput
                Epilogue
                    ReadOutputSpecs: PerfOutput
                Execution: "$Program"
            End SimCodeProcess PerfCode

        End SimCode PerfCode

        TaskProcess PerfTask
            Control: [
                PerfCode
            ]
        End TaskProcess PerfTask

        Optimization PerfTask
            PotentialVariables:
                DragRatio LoadedWeight WeightOfFuel AreaOfWing
            Variables:
                DragRatio LoadedWeight WeightOfFuel AreaOfWing
            VariableScaling
                Parameter: DragRatio ScaleFactor: 1.0
                Parameter: LoadedWeight ScaleFactor: 1.0
                Parameter: WeightOfFuel ScaleFactor: 1.0
                Parameter: AreaOfWing ScaleFactor: 1.0
            PotentialObjectives:
                DragRatio LoadedWeight WeightOfFuel AreaOfWing AircraftRange StallSpeed

            # PLAN TO BE CONFIGURED BY ADVISOR:
            OptimizePlan PriorityRankedPlan
                Control: [
                ]
        End Optimization PerfTask

        TaskPlan PerfTask
            Control: [
                PriorityRankedPlan
            ]
        End TaskPlan PerfTask

        DataStorage PerfTask
            Restore: no
            DataLog: "PerfTask.ans.db" Mode: overwrite
            DataLookUp: "PerfTask.ans.db"
            MatchMode: Exact
            Levels: all
            StoreGradRuns: yes
            StoreApproxRuns: yes
        End DataStorage PerfTask

    End Task PerfTask


    Approximations Airplane
        Approximation GenericApproximationModel
            Type: "Response Surface Model"
            Inputs
                WingSpan 0.25  WingArea 0.25  FuseLength 0.25  FuseDia 0.25  CruiseVel 0.25  WtFuel 0.25
            End Inputs
            Outputs
                SurfAreaFuse WetArea LoD AR WingChord LoadedWt AircraftRange StallSpd
            End Outputs
            Initialization
                Mode: process
            End Initialization
            Options
                InitialDesignCount: 7
        End Approximation GenericApproximationModel
    End Approximations Airplane

    TaskProcess Airplane
        Control: [
            AeroCode
            AspectRatioCalc
            WeightsCode
            PerfTask
        ]

        SubTask PerfTask
            ParameterMap
                LoD = DragRatio
                LoadedWt = LoadedWeight
                WtFuel = WeightOfFuel
                WingArea = AreaOfWing
                AircraftRange = AircraftRange
                StallSpd = StallSpeed
            InputToSubtask
                Send:
                    LoD LoadedWt WtFuel WingArea
            OutputFromSubtask
                Receive:
                    LoD LoadedWt WtFuel WingArea AircraftRange StallSpd
        End SubTask PerfTask

    End TaskProcess Airplane

    Optimization Airplane
        PotentialVariables:
            WingSpan WingArea FuseLength FuseDia CruiseVel WtFuel WtEng NumEng NumPass WtPayload
        Variables:
            WingSpan WingArea FuseLength FuseDia CruiseVel WtFuel
        VariableScaling
            Parameter: WingSpan ScaleFactor: 1.0
            Parameter: WingArea ScaleFactor: 1.0
            Parameter: FuseLength ScaleFactor: 1.0
            Parameter: FuseDia ScaleFactor: 1.0
            Parameter: CruiseVel ScaleFactor: 1.0
            Parameter: WtFuel ScaleFactor: 1.0
            Parameter: WtEng ScaleFactor: 1.0
            Parameter: NumEng ScaleFactor: 1.0
            Parameter: NumPass ScaleFactor: 1.0
            Parameter: WtPayload ScaleFactor: 1.0
        InputConstraints
            Parameter: FuseDia LowerBound: 3.5 UpperBound: 10.0
            Parameter: FuseLength LowerBound: 22.0 UpperBound: 50.0
            Parameter: NumEng LowerBound: 1
            Parameter: CruiseVel LowerBound: 175.0 UpperBound: 375.0
            Parameter: WingArea LowerBound: 50.0 UpperBound: 500.0
            Parameter: NumPass LowerBound: 1
            Parameter: WtFuel LowerBound: 1.0 UpperBound: 500.0
            Parameter: WingSpan LowerBound: 15.0 UpperBound: 55.0
        PotentialObjectives:
            WingSpan WingArea FuseLength FuseDia CruiseVel WtFuel WtEng NumEng NumPass WtPayload
            SurfAreaFuse WetArea LoD AR WingChord LoadedWt AircraftRange StallSpd
        Objectives
            Parameter: LoadedWt Direction: minimize Weight: 1.0 ScaleFactor: 1.0
            Parameter: AircraftRange Direction: maximize Weight: 1.0 ScaleFactor: 1.0
            Parameter: CruiseVel Direction: maximize Weight: 1.0 ScaleFactor: 1.0
        OutputConstraints
            Parameter: StallSpd UpperBound: 70 Weight: 1.0 ScaleFactor: 1.0
            Parameter: AR LowerBound: 4.5 Weight: 1.0 ScaleFactor: 1.0
            Parameter: AircraftRange LowerBound: 565 Weight: 1.0 ScaleFactor: 1.0

        AdvisorCriteria
            DiscontinuousSpace: no
            InitialDesignPoint: infeasible
            AnalysisType: nonlinear
            ExecutionTime: 1s 
            IORelationships: no
            GradientsAvailable: no
        End AdvisorCriteria

        # PLAN TO BE CONFIGURED BY ADVISOR:
        OptimizePlan PriorityRankedPlan
            Control: [
            ]
    End Optimization Airplane

    TaskPlan Airplane
        Control: [
            PriorityRankedPlan
        ]
    End TaskPlan Airplane

    DataStorage Airplane
        Restore: no
        DataLog: "Airplane.ans.db" Mode: overwrite
        DataLookUp: "Airplane.ans.db"
        MatchMode: Exact
        Levels: all
        StoreGradRuns: yes
        StoreApproxRuns: yes
    End DataStorage Airplane

End Task Airplane