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TwoBodyPropagator Constructor (JulianDate, ReferenceFrame, MotionCartesian, 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 TwoBodyPropagator(
	JulianDate orbitEpoch,
	ReferenceFrame referenceFrame,
	Motion<Cartesian> initialConditions,
	double gravitationalParameter
)

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.FoundationMotionCartesian
The elements from which to propagate.
gravitationalParameter
Type: SystemDouble
The gravitational parameter for the central body around which to propagate.
Exceptions
ExceptionCondition
ArgumentException Thrown when the initialConditions do not contain velocity information.
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