Description
J4 Perturbation 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. |
| InitialState | Get the initial state. |
| StartTime | This property is deprecated. Use EphemerisInterval to configure the propagation interval. Start time. Uses DateFomat 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
Configure the J4 Perturbation propagator to a circular orbit
| [C#] |  Copy Code |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ4Perturbation);
IAgVePropagatorJ4Perturbation prop = satellite.Propagator as IAgVePropagatorJ4Perturbation;
IAgOrbitStateClassical keplerian = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
keplerian.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude;
IAgClassicalSizeShapeAltitude size = keplerian.SizeShape as IAgClassicalSizeShapeAltitude;
size.ApogeeAltitude = altitude;
size.PerigeeAltitude = altitude;
keplerian.Orientation.Inclination = incl;
keplerian.Orientation.ArgOfPerigee = 0;
keplerian.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
(keplerian.Orientation.AscNode as IAgOrientationAscNodeRAAN).Value = 0;
keplerian.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
(keplerian.Location as IAgClassicalLocationTrueAnomaly).Value = 0;
prop.InitialState.Representation.Assign(keplerian);
prop.Propagate();
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Configure the J4 Perturbation propagator to a critically inclined orbit
| [C#] | Copy Code |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ4Perturbation);
IAgVePropagatorJ4Perturbation prop = satellite.Propagator as IAgVePropagatorJ4Perturbation;
IAgOrbitStateClassical keplerian = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
keplerian.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude;
IAgClassicalSizeShapeAltitude size = keplerian.SizeShape as IAgClassicalSizeShapeAltitude;
size.ApogeeAltitude = apogeeAlt;
size.PerigeeAltitude = perigeeAlt;
keplerian.Orientation.Inclination = 63.434949;
keplerian.Orientation.ArgOfPerigee = 270.000000;
keplerian.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
(keplerian.Orientation.AscNode as IAgOrientationAscNodeLAN).Value = ascNodeLon;
keplerian.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
(keplerian.Location as IAgClassicalLocationTrueAnomaly).Value = 90.000000;
prop.InitialState.Representation.Assign(keplerian);
prop.Propagate();
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Configure the J4 Perturbation propagator to a circular orbit
| [Visual Basic .NET] | Copy Code |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ4Perturbation)
Dim prop As IAgVePropagatorJ4Perturbation = TryCast(satellite.Propagator, IAgVePropagatorJ4Perturbation)
Dim keplerian As IAgOrbitStateClassical = TryCast(prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical), IAgOrbitStateClassical)
keplerian.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude
Dim size As IAgClassicalSizeShapeAltitude = TryCast(keplerian.SizeShape, IAgClassicalSizeShapeAltitude)
size.ApogeeAltitude = altitude
size.PerigeeAltitude = altitude
keplerian.Orientation.Inclination = incl
keplerian.Orientation.ArgOfPerigee = 0
keplerian.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN
TryCast(keplerian.Orientation.AscNode, IAgOrientationAscNodeRAAN).Value = 0
keplerian.LocationType = AgEClassicalLocation.eLocationTrueAnomaly
TryCast(keplerian.Location, IAgClassicalLocationTrueAnomaly).Value = 0
prop.InitialState.Representation.Assign(keplerian)
prop.Propagate()
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Configure the J4 Perturbation propagator to a critically inclined orbit
| [Visual Basic .NET] | Copy Code |
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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ4Perturbation)
Dim prop As IAgVePropagatorJ4Perturbation = TryCast(satellite.Propagator, IAgVePropagatorJ4Perturbation)
Dim keplerian As IAgOrbitStateClassical = TryCast(prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical), IAgOrbitStateClassical)
keplerian.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude
Dim size As IAgClassicalSizeShapeAltitude = TryCast(keplerian.SizeShape, IAgClassicalSizeShapeAltitude)
size.ApogeeAltitude = apogeeAlt
size.PerigeeAltitude = perigeeAlt
keplerian.Orientation.Inclination = 63.434949
keplerian.Orientation.ArgOfPerigee = 270
keplerian.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN
TryCast(keplerian.Orientation.AscNode, IAgOrientationAscNodeLAN).Value = ascNodeLon
keplerian.LocationType = AgEClassicalLocation.eLocationTrueAnomaly
TryCast(keplerian.Location, IAgClassicalLocationTrueAnomaly).Value = 90
prop.InitialState.Representation.Assign(keplerian)
prop.Propagate()
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Set satellite propagator to J4 and assign cartesian position
| [MATLAB] | Copy Code |
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% IAgSatellite satellite: Satellite object
satellite.SetPropagatorType('ePropagatorJ4Perturbation');
propagator = satellite.Propagator;
propagator.InitialState.Representation.AssignCartesian('eCoordinateSystemICRF',6678.14,0,0,0,6.78953,3.68641)
propagator.Propagate;
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Set satellite propagator to J4 and assign cartesian position
| [Python] | Copy Code |
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# IAgSatellite satellite: Satellite object
satellite.SetPropagatorType(2) # ePropagatorJ4Perturbation
propagator = satellite.Propagator
propagator.InitialState.Representation.AssignCartesian(11,6678.14,0,0,0,6.78953,3.68641) # eCoordinateSystemICRF
propagator.Propagate()
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CoClasses that Implement IAgVePropagatorJ4Perturbation
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