Description
LOP (Long-Range Orbit Predictor) propagator
interface.
Object Model
Public Methods
Propagate |
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. |
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. |
Interfaces
Example
Configure the LOP
propagator
[C#] |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP);
IAgVePropagatorLOP lopProp = satellite.Propagator as IAgVePropagatorLOP;
lopProp.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000");
lopProp.Step = 86400;
IAgOrbitState orbit = lopProp.InitialState.Representation;
orbit.Epoch = "1 Jan 2012 12:00:00.000";
orbit.AssignCartesian(
AgECoordinateSystem.eCoordinateSystemFixed,
-1120.32,
-9520.84,
0.129,
2.155,
-1.54416,
5.668412);
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;
lopProp.Propagate();
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Set the satellite to
use the LOP propagator
[C#] |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP);
IAgVePropagatorLOP propagator = satellite.Propagator as IAgVePropagatorLOP;
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Configure the LOP
propagator
[Visual Basic .NET] |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP)
Dim lopProp As IAgVePropagatorLOP =
TryCast(satellite.Propagator, IAgVePropagatorLOP)
lopProp.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2
Jan 2012 12:00:00.000")
lopProp.[Step] = 86400
Dim orbit As IAgOrbitState =
lopProp.InitialState.Representation
orbit.Epoch = "1 Jan 2012
12:00:00.000"
orbit.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed,
-1120.32, -9520.84, 0.129, 2.155, -1.54416, _
5.668412)
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
lopProp.Propagate()
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Set the satellite to
use the LOP propagator
[Visual Basic .NET] |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorLOP)
Dim propagator As IAgVePropagatorLOP =
TryCast(satellite.Propagator, IAgVePropagatorLOP)
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CoClasses that Implement
IAgVePropagatorLOP