/* Copyright 2002-2017 CS Systèmes d'Information
* Licensed to CS Systèmes d'Information (CS) under one or more
* contributor license agreements. See the NOTICE file distributed with
* this work for additional information regarding copyright ownership.
* CS licenses this file to You under the Apache License, Version 2.0
* (the "License"); you may not use this file except in compliance with
* the License. You may obtain a copy of the License at
*
* http://www.apache.org/licenses/LICENSE-2.0
*
* Unless required by applicable law or agreed to in writing, software
* distributed under the License is distributed on an "AS IS" BASIS,
* WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
* See the License for the specific language governing permissions and
* limitations under the License.
*/
/**
* This package provides tools to convert a given propagator or a set of
* {@link org.orekit.propagation.SpacecraftState} into another propagator.
* The conversion principle is to minimize the mean square error for positions
* and velocities over a given time span.
* <p>
* The conversion from osculating to mean elements appears as a side effect of
* propagation models conversion.
* </p>
* <p>
* These package extends an original contribution from Telespazio for TLE
* (Orbit Converter for Two-Lines Elements) to all propagators.
* </p>
*
* @author Pascal Parraud
*/
package org.orekit.propagation.conversion;