TwoBodyStateTransitionMatrixPropagatorGetEvaluator Method

Gets an evaluator that can propagate the state transition matrix to individual dates.

This evaluator propagates the orbit state transition matrix. The result of evaluating will be a Motion<Matrix> corresponding to the orbital state transition matrix at the given JulianDate.

Note: when evaluating with this evaluator, it may be more efficient to specify times using an arithmetically safe TimeStandard to avoid the need to convert in order to perform the propagation. The length of a time step may be different in different TimeStandards. So be careful when specifying times.