Click or drag to resize

Sgp4PropagatorMeanElementsAtEpoch Method (JulianDate, Cartesian, Cartesian, Int32, Double)

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 use the specified value for BStar in the resulting element set. Also, note that this method may have difficulty converging for perfectly circular orbits.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.3.420.0 (24.3.420.0)
Syntax
Copy
public static Sgp4Elements MeanElementsAtEpoch(
	JulianDate date,
	Cartesian posInTEME,
	Cartesian velInTEME,
	int maximumIterations,
	double bStarValue
)

Parameters

date
Type: AGI.Foundation.TimeJulianDate
The epoch of the state.
posInTEME
Type: AGI.Foundation.CoordinatesCartesian
The position in the TrueEquatorMeanEquinoxFrame.
velInTEME
Type: AGI.Foundation.CoordinatesCartesian
The velocity in the TrueEquatorMeanEquinoxFrame.
maximumIterations
Type: SystemInt32
The maximum number of iterations to perform when trying to match the specified state.
bStarValue
Type: SystemDouble
Specifies the value of BStar to use when producing the set of SGP4 elements which match the given state.

Return Value

Type: Sgp4Elements
The mean SGP4 elements which will produce the given state when evaluated at the given time.
See Also