org.orekit.propagation
Class OsculatingToMeanElementsConverter

java.lang.Object
  org.orekit.propagation.OsculatingToMeanElementsConverter

public class OsculatingToMeanElementsConverter
extends Object

This class converts osculating orbital elements into mean elements. As this process depends on the force model used to average the orbit, a Propagator is given as input. The force model used will be the one contained into the propagator.

Author:

rdicosta

Nested Class Summary

class

OsculatingToMeanElementsConverter.NewtonSolverImp Specific implementation of the Newton solver.

Constructor Summary

OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator)
Constructor.

Method Summary

SpacecraftState

convert() Convert an osculating orbit into a mean orbit, in DSST sense.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

OsculatingToMeanElementsConverter

public OsculatingToMeanElementsConverter(SpacecraftState state,
                                         int satelliteRevolution,
                                         Propagator propagator)

Constructor.

Parameters:

state - initial orbit to convert

satelliteRevolution - number of satellite revolutions in the averaging interval

propagator - propagator used to compute mean orbit

Method Detail

convert

public final SpacecraftState convert()
                              throws IllegalArgumentException,
                                     OrekitException

Convert an osculating orbit into a mean orbit, in DSST sense.

Returns:

mean orbit state, in DSST sense

Throws:

OrekitException - if state cannot be propagated throughout range

IllegalArgumentException - if eccentricity is out of range