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J2Propagator Constructor (JulianDate, ReferenceFrame, KeplerianElements, Double, Double)

Initializes a new instance.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.2.419.0 (24.2.419.0)
Syntax
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public J2Propagator(
	JulianDate orbitEpoch,
	ReferenceFrame referenceFrame,
	KeplerianElements initialConditions,
	double j2UnnormalizedValue,
	double referenceDistance
)

Parameters

orbitEpoch
Type: AGI.Foundation.TimeJulianDate
The Julian date at which the initial conditions are defined.
referenceFrame
Type: AGI.Foundation.GeometryReferenceFrame
The reference frame in which the initialConditions are defined. Generally this should be the InertialFrame of the central body around which you are propagating. See the Remarks section for more information.
initialConditions
Type: AGI.Foundation.CoordinatesKeplerianElements
The orbital elements from which to propagate.
j2UnnormalizedValue
Type: SystemDouble
The non-normalized J2 zonal harmonic coefficient of the central body around which to propagate.
referenceDistance
Type: SystemDouble
The reference distance (equatorial radius) associated with the J2 coefficient.
Exceptions
ExceptionCondition
ArgumentNullException Thrown if referenceFrame or initialConditions is .
Remarks
For correct results, referenceFrame generally must be an inertial reference frame. However, it is easy to obtain ephemeris in any desired ReferenceFrame (such as the FixedFrame) by transforming it after it has been produced by the propagator. To do so, call Propagate(JulianDate, JulianDate, Duration, Int32, ReferenceFrame). Or, call CreatePoint and then use ObservePoint(Point, ReferenceFrame) to get an evaluator that can be used to find the propagated position in the specified reference frame.
See Also