TrajectoryState.java
/* Copyright 2002-2024 CS GROUP
* Licensed to CS GROUP (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
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*/
package org.orekit.files.ccsds.ndm.odm.ocm;
import java.util.List;
import org.orekit.bodies.OneAxisEllipsoid;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.TimeStamped;
import org.orekit.utils.CartesianDerivativesFilter;
import org.orekit.utils.TimeStampedPVCoordinates;
import org.orekit.utils.units.Unit;
/** Trajectory state entry.
* @author Luc Maisonobe
* @since 11.0
*/
public class TrajectoryState implements TimeStamped {
/** Type of the elements. */
private final OrbitElementsType type;
/** Entry date. */
private final AbsoluteDate date;
/** Trajectory elements. */
private final double[] elements;
/** Simple constructor.
* @param type type of the elements
* @param date entry date
* @param fields trajectory elements
* @param first index of first field to consider when parsing
* @param units units to use for parsing
*/
public TrajectoryState(final OrbitElementsType type, final AbsoluteDate date,
final String[] fields, final int first, final List<Unit> units) {
this.type = type;
this.date = date;
this.elements = new double[units.size()];
for (int i = 0; i < elements.length; ++i) {
elements[i] = units.get(i).toSI(Double.parseDouble(fields[first + i]));
}
}
/** Simple constructor.
* @param type type of the elements
* @param date entry date
* @param elements trajectory elements in SI units
* @since 12.0
*/
public TrajectoryState(final OrbitElementsType type, final AbsoluteDate date,
final double[] elements) {
this.type = type;
this.date = date;
this.elements = elements.clone();
}
/** {@inheritDoc} */
@Override
public AbsoluteDate getDate() {
return date;
}
/** Get trajectory elements.
* @return trajectory elements
*/
public double[] getElements() {
return elements.clone();
}
/** Get the type of the elements.
* @return type of the elements
*/
public OrbitElementsType getType() {
return type;
}
/** Get which derivatives of position are available in this state.
* @return a value indicating if the file contains velocity and/or acceleration
*/
public CartesianDerivativesFilter getAvailableDerivatives() {
return type == OrbitElementsType.CARTP ?
CartesianDerivativesFilter.USE_P :
(type == OrbitElementsType.CARTPVA ?
CartesianDerivativesFilter.USE_PVA :
CartesianDerivativesFilter.USE_PV);
}
/** Convert to Cartesian coordinates.
* @param body central body
* (may be null if {@link #getType() type} is <em>not</em> {@link OrbitElementsType#GEODETIC})
* @param mu gravitational parameter in m³/s²
* @return Cartesian coordinates
*/
public TimeStampedPVCoordinates toCartesian(final OneAxisEllipsoid body, final double mu) {
return type.toCartesian(date, elements, body, mu);
}
}