Sgp4PropagatorMeanElementsAtEpoch Method (JulianDate, Cartesian, Cartesian)

Produces an element set from a given Cartesian state at a given time. Since SGP4 uses perturbations, the classical orbital elements produced by ModifiedKeplerianElements may not correspond to the specified position and velocity when propagated as SGP4 elements. This method performs a simple iteration to correct the classical elements so that the resulting SGP4 elements will represent the specified position and velocity at the given time as accurately as possible. This will assume that the BStar value is zero.

public static Sgp4Elements MeanElementsAtEpoch(
	JulianDate date,
	Cartesian posInTEME,
	Cartesian velInTEME
)

Public Shared Function MeanElementsAtEpoch ( 
	date As JulianDate,
	posInTEME As Cartesian,
	velInTEME As Cartesian
) As Sgp4Elements

public:
static Sgp4Elements^ MeanElementsAtEpoch(
	JulianDate date, 
	Cartesian posInTEME, 
	Cartesian velInTEME
)

static member MeanElementsAtEpoch : 
        date : JulianDate * 
        posInTEME : Cartesian * 
        velInTEME : Cartesian -> Sgp4Elements