Description

J2 Perturbation propagator interface.

Public Methods

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

Public Properties

EphemerisInterval	The propagator's ephemeris interval.
InitialState	Get the initial state.
PropagationFrame	The propagation frame
Step	Step size. Uses Time Dimension.
SupportedPropagationFrames	Returns supported propagation frames

Interfaces

Implemented Interface
IAgVePropagator

CoClasses that Implement IAgVePropagatorJ2Perturbation

Name
AgVePropagatorJ2Perturbation

Example

Set the satellite to use the J2 propagator

[C#]

// 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#]

// 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]

' 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]

' Set propagator to J2 Perturbation
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation)

' Get the J2 Perturbation propagator
Dim propagator As IAgVePropagatorJ2Perturbation = TryCast(satellite.Propagator, IAgVePropagatorJ2Perturbation)

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IAgVePropagatorJ2Perturbation Interface