Package org.orekit.propagation.conversion

Interface PropagatorConverter

All Known Implementing Classes:
AbstractPropagatorConverter, FiniteDifferencePropagatorConverter, JacobianPropagatorConverter
public interface PropagatorConverter
This interface is the top-level abstraction for propagators conversions.

It provides a way to convert a given propagator or a set of SpacecraftState into a wanted propagator that minimize the mean square error over a time span.

Since:
6.0
Author:
Pascal Parraud

  • Method Details

    • convert

      Propagator convert(Propagator source, double timeSpan, int nbPoints, List<String> freeParameters)
      Convert a propagator into another one.
      Parameters:
      source - propagator to convert
      timeSpan - time span considered for conversion
      nbPoints - number of points for sampling over the time span
      freeParameters - names of the free parameters
      Returns:
      adapted propagator

    • convert

      Propagator convert(Propagator source, double timeSpan, int nbPoints, String... freeParameters)
      Convert a propagator into another one.
      Parameters:
      source - propagator to convert
      timeSpan - time span considered for conversion
      nbPoints - number of points for sampling over the time span
      freeParameters - names of the free parameters
      Returns:
      adapted propagator

    • convert

      Propagator convert(List<SpacecraftState> states, boolean positionOnly, List<String> freeParameters)
      Find the propagator that minimize the mean square error for a sample of states.
      Parameters:
      states - spacecraft states sample to fit
      positionOnly - if true, consider only position data otherwise both position and velocity are used
      freeParameters - names of the free parameters
      Returns:
      adapted propagator

    • convert

      Propagator convert(List<SpacecraftState> states, boolean positionOnly, String... freeParameters)
      Find the propagator that minimize the mean square error for a sample of states.
      Parameters:
      states - spacecraft states sample to fit
      positionOnly - if true, consider only position data otherwise both position and velocity are used
      freeParameters - names of the free parameters
      Returns:
      adapted propagator