Description

Object Model

Public Methods

Propagate

Propagates the satellite's path using the specified time interval.

Public Properties

EphemerisInterval	The propagator's ephemeris interval.
InitialState	Get the initial state.
StartTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Start time. Uses DateFormat Dimension.
Step	Step size. Uses Time Dimension.
StopTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Stop time. Uses DateFormat Dimension.
UseScenarioAnalysisTime	This property is deprecated. Use the new Timeline API components to configure the propagator's analysis time. Whether the scenario analysis start/stop times shall be used.

Interfaces

Example

Set the satellite to use the J2 propagator

[C#]	Copy Code
// Set propagator to J2 Perturbation  satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);    // Get the J2 Perturbation propagator  IAgVePropagatorJ2Perturbation propagator = satellite.Propagator as IAgVePropagatorJ2Perturbation;

Configure the J2 Perturbation propagator

[C#]

Copy Code

// Set propagator to SGP4  satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);    // J2 Perturbation propagator  IAgVePropagatorJ2Perturbation j2prop = satellite.Propagator as IAgVePropagatorJ2Perturbation;    // Configure time period  j2prop.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000");  j2prop.Step = 60.0;    // Configure propagator initial state  IAgVeJxInitialState initial = j2prop.InitialState;  initial.Representation.Epoch = "1 Jan 2012 12:00:00.000";  initial.Representation.AssignCartesian(      AgECoordinateSystem.eCoordinateSystemFixed,      -1514.4,       // in km (assuming unit preferences set to km)      -6790.1,       // in km      -1.25,         // in km      4.8151,        // in km/sec (assuming unit preferences set to km/sec)      1.7710,        // in km/sec      5.6414);       // in km/sec  initial.EllipseOptions = AgEVeEllipseOptions.eSecularlyPrecessing;    // Propagate  j2prop.Propagate();

Configure the J2 Perturbation propagator

[Visual Basic .NET]

Copy Code

' Set propagator to SGP4 satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation) ' J2 Perturbation propagator Dim j2prop As IAgVePropagatorJ2Perturbation = TryCast(satellite.Propagator, IAgVePropagatorJ2Perturbation) ' Configure time period j2prop.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000") j2prop.[Step] = 60 ' Configure propagator initial state Dim initial As IAgVeJxInitialState = j2prop.InitialState initial.Representation.Epoch = "1 Jan 2012 12:00:00.000" ' in km (assuming unit preferences set to km) ' in km ' in km ' in km/sec (assuming unit preferences set to km/sec) ' in km/sec initial.Representation.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, -1514.4, -6790.1, -1.25, 4.8151, 1.771, _     5.6414) ' in km/sec initial.EllipseOptions = AgEVeEllipseOptions.eSecularlyPrecessing ' Propagate j2prop.Propagate()

Set the satellite to use the J2 propagator

[Visual Basic .NET]	Copy Code
' Set propagator to J2 Perturbation satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation) ' Get the J2 Perturbation propagator Dim propagator As IAgVePropagatorJ2Perturbation = TryCast(satellite.Propagator, IAgVePropagatorJ2Perturbation)

CoClasses that Implement IAgVePropagatorJ2Perturbation