Description

LOP (Long-Range Orbit Predictor) propagator interface.

Public Methods

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

Public Properties

EphemerisInterval	The propagator's ephemeris interval.
ForceModel	Get the force model parameters.
InitialState	Get the initial state.
Step	Step size. Uses Time Dimension.

Interfaces

Implemented Interface
IAgVePropagator

CoClasses that Implement IAgVePropagatorLOP

Name
AgVePropagatorLOP

Example

Set the satellite to use the LOP propagator

[C#]

// Set satellite propagator to LOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP);

// Get the LOP propagator
IAgVePropagatorLOP propagator = satellite.Propagator as IAgVePropagatorLOP;

Configure the LOP propagator

[C#]

// Set satellite propagator to LOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP);

// Get IAgVePropagatorLOP interface
IAgVePropagatorLOP lopProp = satellite.Propagator as IAgVePropagatorLOP;

// Configure time period
lopProp.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000");
lopProp.Step = 86400;

// Configure propagator initial state
IAgOrbitState orbit = lopProp.InitialState.Representation;
orbit.Epoch = "1 Jan 2012 12:00:00.000";
orbit.AssignCartesian(
    AgECoordinateSystem.eCoordinateSystemFixed,
    -1120.32,          // in km (assuming unit preferences set to km)
    -9520.84,         // in km
    0.129,      // in km
    2.155,      // in km/sec (assuming unit preferences set to km/sec)
    -1.54416,      // in km/sec
    5.668412);     // in km/sec

// Configure force model
IAgVeLOPForceModel lopForceModel = lopProp.ForceModel;
lopForceModel.CentralBodyGravity.MaxDegree = 15;
lopForceModel.CentralBodyGravity.MaxOrder = 8;
lopForceModel.Drag.Use = true;
lopForceModel.Drag.Cd = 3.55;
lopForceModel.SolarRadiationPressure.Use = true;
lopForceModel.SolarRadiationPressure.Cp = 1.1250;
lopForceModel.SolarRadiationPressure.AtmosHeight = 125;
lopForceModel.PhysicalData.DragCrossSectionalArea = 0.001555512;
lopForceModel.PhysicalData.SRPCrossSectionalArea = 0.001810026;
lopForceModel.PhysicalData.SatelliteMass = 1505.001;

// Propagate
lopProp.Propagate();

Configure the LOP propagator

[Visual Basic .NET]

' Set satellite propagator to LOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP)

' Get IAgVePropagatorLOP interface
Dim lopProp As IAgVePropagatorLOP = TryCast(satellite.Propagator, IAgVePropagatorLOP)

' Configure time period
lopProp.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000")
lopProp.[Step] = 86400

' Configure propagator initial state
Dim orbit As IAgOrbitState = lopProp.InitialState.Representation
orbit.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
orbit.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, -1120.32, -9520.84, 0.129, 2.155, -1.54416, _
	5.668412)
' in km/sec
' Configure force model
Dim lopForceModel As IAgVeLOPForceModel = lopProp.ForceModel
lopForceModel.CentralBodyGravity.MaxDegree = 15
lopForceModel.CentralBodyGravity.MaxOrder = 8
lopForceModel.Drag.Use = True
lopForceModel.Drag.Cd = 3.55
lopForceModel.SolarRadiationPressure.Use = True
lopForceModel.SolarRadiationPressure.Cp = 1.125
lopForceModel.SolarRadiationPressure.AtmosHeight = 125
lopForceModel.PhysicalData.DragCrossSectionalArea = 0.001555512
lopForceModel.PhysicalData.SRPCrossSectionalArea = 0.001810026
lopForceModel.PhysicalData.SatelliteMass = 1505.001

' Propagate
lopProp.Propagate()

Set the satellite to use the LOP propagator

[Visual Basic .NET]

' Set satellite propagator to LOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP)

' Get the LOP propagator
Dim propagator As IAgVePropagatorLOP = TryCast(satellite.Propagator, IAgVePropagatorLOP)

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IAgVePropagatorLOP Interface