Duration.java
/* Copyright 2002-2024 CS GROUP
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* 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
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* 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,
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package org.orekit.forces.maneuvers.jacobians;
import org.orekit.propagation.AdditionalStateProvider;
import org.orekit.propagation.SpacecraftState;
/** Generator for one column of a Jacobian matrix for special case of maneuver duration.
* <p>
* Typical use cases for this are estimation of maneuver duration during
* either orbit determination or maneuver optimization.
* </p>
* @author Luc Maisonobe
* @since 11.1
* @see MedianDate
* @see TriggerDate
*/
public class Duration implements AdditionalStateProvider {
/** Name of the parameter corresponding to the start date. */
private final String startName;
/** Name of the parameter corresponding to the stop date. */
private final String stopName;
/** Name of the parameter corresponding to the column. */
private final String columnName;
/** Simple constructor.
* @param startName name of the parameter corresponding to the start date
* @param stopName name of the parameter corresponding to the stop date
* @param columnName name of the parameter corresponding to the column
*/
public Duration(final String startName, final String stopName, final String columnName) {
this.startName = startName;
this.stopName = stopName;
this.columnName = columnName;
}
/** {@inheritDoc} */
@Override
public String getName() {
return columnName;
}
/** {@inheritDoc}
* <p>
* The column state can be computed only if the start and stop dates columns are available.
* </p>
*/
@Override
public boolean yields(final SpacecraftState state) {
return !(state.hasAdditionalState(startName) && state.hasAdditionalState(stopName));
}
/** {@inheritDoc} */
@Override
public double[] getAdditionalState(final SpacecraftState state) {
// compute partial derivatives with respect to start and stop dates
final double[] dYdT0 = state.getAdditionalState(startName);
final double[] dYdT1 = state.getAdditionalState(stopName);
// combine derivatives to get partials with respect to duration
final double[] dYdTm = new double[dYdT0.length];
for (int i = 0; i < dYdTm.length; ++i) {
dYdTm[i] = 0.5 * (dYdT1[i] - dYdT0[i]);
}
return dYdTm;
}
}