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

Initializes a new instance.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 20.3.405.0 (20.3.405.0)
public J2Propagator(
	JulianDate orbitEpoch,
	ReferenceFrame referenceFrame,
	ModifiedKeplerianElements initialConditions,
	double j2UnnormalizedValue,
	double referenceDistance


Type: AGI.Foundation.TimeJulianDate
The Julian date at which the initial conditions are defined.
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.
Type: AGI.Foundation.CoordinatesModifiedKeplerianElements
The orbital elements from which to propagate.
Type: SystemDouble
The non-normalized J2 zonal harmonic coefficient of the central body around which to propagate.
Type: SystemDouble
The reference distance (equatorial radius) associated with the J2 coefficient.
ArgumentNullException Thrown if referenceFrame or initialConditions is .
ArgumentException Thrown if the initialConditions represent an open orbit (i.e. if the eccentricity is greater than or equal to unity).
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