Sgp4PropagatorMeanElementsAtEpoch Method

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.

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.

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.