OrbitType.java
/* Copyright 2002-2013 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.
*/
package org.orekit.orbits;
import org.apache.commons.math3.geometry.euclidean.threed.Vector3D;
import org.orekit.frames.Frame;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.PVCoordinates;
/** Enumerate for {@link Orbit orbital} parameters types.
*/
public enum OrbitType {
/** Type for propagation in {@link CartesianOrbit Cartesian parameters}. */
CARTESIAN {
/** {@inheritDoc} */
public Orbit convertType(final Orbit orbit) {
return (orbit.getType() == this) ? orbit : new CartesianOrbit(orbit);
}
/** {@inheritDoc} */
public void mapOrbitToArray(final Orbit orbit, final PositionAngle type,
final double[] stateVector) {
final PVCoordinates pv = orbit.getPVCoordinates();
final Vector3D p = pv.getPosition();
final Vector3D v = pv.getVelocity();
stateVector[0] = p.getX();
stateVector[1] = p.getY();
stateVector[2] = p.getZ();
stateVector[3] = v.getX();
stateVector[4] = v.getY();
stateVector[5] = v.getZ();
}
/** {@inheritDoc} */
public Orbit mapArrayToOrbit(final double[] stateVector, final PositionAngle type,
final AbsoluteDate date, final double mu, final Frame frame) {
final Vector3D p = new Vector3D(stateVector[0], stateVector[1], stateVector[2]);
final Vector3D v = new Vector3D(stateVector[3], stateVector[4], stateVector[5]);
return new CartesianOrbit(new PVCoordinates(p, v), frame, date, mu);
}
},
/** Type for propagation in {@link CircularOrbit circular parameters}. */
CIRCULAR {
/** {@inheritDoc} */
public Orbit convertType(final Orbit orbit) {
return (orbit.getType() == this) ? orbit : new CircularOrbit(orbit);
}
/** {@inheritDoc} */
public void mapOrbitToArray(final Orbit orbit, final PositionAngle type,
final double[] stateVector) {
final CircularOrbit circularOrbit = (CircularOrbit) OrbitType.CIRCULAR.convertType(orbit);
stateVector[0] = circularOrbit.getA();
stateVector[1] = circularOrbit.getCircularEx();
stateVector[2] = circularOrbit.getCircularEy();
stateVector[3] = circularOrbit.getI();
stateVector[4] = circularOrbit.getRightAscensionOfAscendingNode();
stateVector[5] = circularOrbit.getAlpha(type);
}
/** {@inheritDoc} */
public Orbit mapArrayToOrbit(final double[] stateVector, final PositionAngle type,
final AbsoluteDate date, final double mu, final Frame frame) {
return new CircularOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
stateVector[4], stateVector[5], type,
frame, date, mu);
}
},
/** Type for propagation in {@link EquinoctialOrbit equinoctial parameters}. */
EQUINOCTIAL {
/** {@inheritDoc} */
public Orbit convertType(final Orbit orbit) {
return (orbit.getType() == this) ? orbit : new EquinoctialOrbit(orbit);
}
/** {@inheritDoc} */
public void mapOrbitToArray(final Orbit orbit, final PositionAngle type,
final double[] stateVector) {
final EquinoctialOrbit equinoctialOrbit =
(EquinoctialOrbit) OrbitType.EQUINOCTIAL.convertType(orbit);
stateVector[0] = equinoctialOrbit.getA();
stateVector[1] = equinoctialOrbit.getEquinoctialEx();
stateVector[2] = equinoctialOrbit.getEquinoctialEy();
stateVector[3] = equinoctialOrbit.getHx();
stateVector[4] = equinoctialOrbit.getHy();
stateVector[5] = equinoctialOrbit.getL(type);
}
/** {@inheritDoc} */
public Orbit mapArrayToOrbit(final double[] stateVector, final PositionAngle type,
final AbsoluteDate date, final double mu, final Frame frame) {
return new EquinoctialOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
stateVector[4], stateVector[5], type,
frame, date, mu);
}
},
/** Type for propagation in {@link KeplerianOrbit Keplerian parameters}. */
KEPLERIAN {
/** {@inheritDoc} */
public Orbit convertType(final Orbit orbit) {
return (orbit.getType() == this) ? orbit : new KeplerianOrbit(orbit);
}
/** {@inheritDoc} */
public void mapOrbitToArray(final Orbit orbit, final PositionAngle type,
final double[] stateVector) {
final KeplerianOrbit keplerianOrbit =
(KeplerianOrbit) OrbitType.KEPLERIAN.convertType(orbit);
stateVector[0] = keplerianOrbit.getA();
stateVector[1] = keplerianOrbit.getE();
stateVector[2] = keplerianOrbit.getI();
stateVector[3] = keplerianOrbit.getPerigeeArgument();
stateVector[4] = keplerianOrbit.getRightAscensionOfAscendingNode();
stateVector[5] = keplerianOrbit.getAnomaly(type);
}
/** {@inheritDoc} */
public Orbit mapArrayToOrbit(final double[] stateVector, final PositionAngle type,
final AbsoluteDate date, final double mu, final Frame frame) {
return new KeplerianOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
stateVector[4], stateVector[5], type,
frame, date, mu);
}
};
/** Convert an orbit to the instance type.
* <p>
* The returned orbit is the specified instance itself if its type already matches,
* otherwise, a new orbit of the proper type created
* </p>
* @param orbit orbit to convert
* @return converted orbit with type guaranteed to match (so it can be cast safely)
*/
public abstract Orbit convertType(final Orbit orbit);
/** Convert orbit to state array.
* <p>
* Note that all implementations of this method <em>must</em> be consistent with the
* implementation of the {@link org.orekit.orbits.Orbit#getJacobianWrtCartesian(
* org.orekit.orbits.PositionAngle, double[][]) Orbit.getJacobianWrtCartesian}
* method for the corresponding orbit type in terms of parameters order and meaning.
* </p>
* @param orbit orbit to map
* @param type type of the angle
* @param stateVector flat array into which the state vector should be mapped */
public abstract void mapOrbitToArray(Orbit orbit, PositionAngle type, double[] stateVector);
/** Convert state array to orbital parameters.
* <p>
* Note that all implementations of this method <em>must</em> be consistent with the
* implementation of the {@link org.orekit.orbits.Orbit#getJacobianWrtCartesian(
* org.orekit.orbits.PositionAngle, double[][]) Orbit.getJacobianWrtCartesian}
* method for the corresponding orbit type in terms of parameters order and meaning.
* </p>
* @param array state as a flat array
* @param type type of the angle
* @param date integration date
* @param mu central attraction coefficient used for propagation (m<sup>3</sup>/s<sup>2</sup>)
* @param frame frame in which integration is performed
* @return orbit corresponding to the flat array as a space dynamics object
*/
public abstract Orbit mapArrayToOrbit(double[] array, PositionAngle type,
AbsoluteDate date, double mu, Frame frame);
}