Description

Object Model

Public Methods

ApplyScript

Apply the script.

Public Properties

GenerateEphemeris	If true, the sequence generates ephemeris and displays it in the 2D and 3D Graphics windows.
RepeatCount	The number of times that the sequence will be executed. A sequence that is repeated is executed immediately subsequent to the previous execution of the sequence. Dimensionless.
ScriptingTool	Returns the Scripting tool for the sequence.
Segments	The list of segments defined for the sequence.
SequenceStateToPass	State To Pass To Next Segment - the state of the sequence to pass.

Example

Configure sequence segment with scripting tool

[C#]

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// Add launch sequence and retrieve the  IAgVAMCSSegment segment = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypeSequence, "MySequence", "-");  IAgVAMCSSequence sequence = segment as IAgVAMCSSequence;    IAgVAScriptingTool scriptTool = sequence.ScriptingTool;  scriptTool.Enable = true;  scriptTool.LanguageType = AgEVALanguage.eVALanguageVBScript;  scriptTool.ScriptText(  @"  DeltaArg = dArg    REM  Set the optimizers desired results  DEOdArgUB = DeltaArg  DEOdArgLB = DeltaArg      REM  Initial guess tool:  REM  Assume transfer orbit is something like a circular orbit linking apoapse of initial orbit to apoapse of final orbit  REM  Constants:  mu = 398600  pi = 3.14159265358979    REM  Step 1:  propagate to apoapsis  Prop1Dur = Period_0/2    REM  Step 2:  conditions at end of initial orbit:  SMA_0 = 0.5*(RadApo_0 + RadPeri_0)  VelApo_0 = sqr( (RadPeri_0*mu) / (RadApo_0*SMA_0) )    REM  Step 3:  evaluate properties of the circular transfer orbit  Rcirc = RadApo_0  Vcirc = sqr(mu/Rcirc)  PeriodCirc = 2*pi*Sqr( Rcirc*Rcirc*Rcirc / mu)    REM  Step 4:  set first maneuver to enter transfer orbit  Burn1X = Vcirc - VelApo_0  Burn1Z = 0    REM  Step 5:  propagate along transfer orbit the desired change in argument of periapse  If DeltaArg >= 0 Then   TransferDur = PeriodCirc*(DeltaArg/360)  Else   TransferDur = PeriodCirc*(360+DeltaArg)/360  End If    REM Step 6:  set second maneuver to enter desired final orbit  Burn2X = -Burn1X  Burn2Z = 0  ");    // Configure the script tool's segments    IAgVAScriptingSegment burn1X = scriptTool.SegmentProperties.Add("Burn1X");    if (Array.IndexOf(burn1X.AvailableObjectNames, "Optimize_Delta_w.Burn1") != -1)  {      burn1X.ObjectName = "Optimize_Delta_w.Burn1";      burn1X.Attribute = "ImpulsiveMnvr.Cartesian.X";      burn1X.Unit = "km/sec";  }    IAgVAScriptingCalcObject period0 = scriptTool.CalcObjects.Add("Period_0");  period0.CalcObjectName = "Segments/Value At Segment";  IAgVAStateCalcValueAtSegment valAtSeg = period0.CalcObject as IAgVAStateCalcValueAtSegment;  valAtSeg.CalcObjectName = "Keplerian Elems/Orbit Period";

Configure sequence segment with scripting tool

[Visual Basic .NET]

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' Add launch sequence and retrieve the Dim segment As IAgVAMCSSegment = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypeSequence, "MySequence", "-") Dim sequence As IAgVAMCSSequence = TryCast(segment, IAgVAMCSSequence) Dim scriptTool As IAgVAScriptingTool = sequence.ScriptingTool scriptTool.Enable = True scriptTool.LanguageType = AgEVALanguage.eVALanguageVBScript scriptTool.ScriptText(vbCr & vbLf & " DeltaArg = dArg" & vbCr & vbLf & vbCr & vbLf & " REM Set the optimizers desired results" & vbCr & vbLf & " DEOdArgUB = DeltaArg" & vbCr & vbLf & " DEOdArgLB = DeltaArg" & vbCr & vbLf & vbCr & vbLf & vbCr & vbLf & " REM Initial guess tool:" & vbCr & vbLf & " REM Assume transfer orbit is something like a circular orbit linking apoapse of initial orbit to apoapse of final orbit" & vbCr & vbLf & " REM Constants: " & vbCr & vbLf & " mu = 398600" & vbCr & vbLf & " pi = 3.14159265358979" & vbCr & vbLf & vbCr & vbLf & " REM Step 1: propagate to apoapsis" & vbCr & vbLf & " Prop1Dur = Period_0/2" & vbCr & vbLf & vbCr & vbLf & " REM Step 2: conditions at end of initial orbit:" & vbCr & vbLf & " SMA_0 = 0.5*(RadApo_0 + RadPeri_0)" & vbCr & vbLf & " VelApo_0 = sqr( (RadPeri_0*mu) / (RadApo_0*SMA_0) )" & vbCr & vbLf & vbCr & vbLf & " REM Step 3: evaluate properties of the circular transfer orbit" & vbCr & vbLf & " Rcirc = RadApo_0" & vbCr & vbLf & " Vcirc = sqr(mu/Rcirc)" & vbCr & vbLf & " PeriodCirc = 2*pi*Sqr( Rcirc*Rcirc*Rcirc / mu)" & vbCr & vbLf & vbCr & vbLf & " REM Step 4: set first maneuver to enter transfer orbit" & vbCr & vbLf & " Burn1X = Vcirc - VelApo_0" & vbCr & vbLf & " Burn1Z = 0" & vbCr & vbLf & vbCr & vbLf & " REM Step 5: propagate along transfer orbit the desired change in argument of periapse" & vbCr & vbLf & " If DeltaArg >= 0 Then" & vbCr & vbLf & " TransferDur = PeriodCirc*(DeltaArg/360)" & vbCr & vbLf & " Else " & vbCr & vbLf & " TransferDur = PeriodCirc*(360+DeltaArg)/360" & vbCr & vbLf & " End If" & vbCr & vbLf & vbCr & vbLf & " REM Step 6: set second maneuver to enter desired final orbit" & vbCr & vbLf & " Burn2X = -Burn1X" & vbCr & vbLf & " Burn2Z = 0" & vbCr & vbLf & " ") ' Configure the script tool's segments Dim burn1X As IAgVAScriptingSegment = scriptTool.SegmentProperties.Add("Burn1X") If Array.IndexOf(burn1X.AvailableObjectNames, "Optimize_Delta_w.Burn1") <> -1 Then     burn1X.ObjectName = "Optimize_Delta_w.Burn1"     burn1X.Attribute = "ImpulsiveMnvr.Cartesian.X"     burn1X.Unit = "km/sec" End If Dim period0 As IAgVAScriptingCalcObject = scriptTool.CalcObjects.Add("Period_0") period0.CalcObjectName = "Segments/Value At Segment" Dim valAtSeg As IAgVAStateCalcValueAtSegment = TryCast(period0.CalcObject, IAgVAStateCalcValueAtSegment) valAtSeg.CalcObjectName = "Keplerian Elems/Orbit Period"

CoClasses that Implement IAgVAMCSSequence