SingleBodyRelativeAttraction.java

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package org.orekit.forces.gravity;

import org.hipparchus.CalculusFieldElement;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.orekit.bodies.CelestialBodies;
import org.orekit.bodies.CelestialBody;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.SpacecraftState;
import org.orekit.utils.ExtendedPositionProvider;
import org.orekit.utils.FieldPVCoordinates;
import org.orekit.utils.PVCoordinates;

/** Body attraction force model computed as relative acceleration towards frame center.
 * @author Luc Maisonabe
 * @author Julio Hernanz
 */
public class SingleBodyRelativeAttraction extends AbstractBodyAttraction {

    /** Simple constructor.
     * @param positionProvider extended position provider for the body to consider
     * @param name name of the body
     * @param mu body gravitational constant
     * @since 13.0
     */
    public SingleBodyRelativeAttraction(final ExtendedPositionProvider positionProvider, final String name,
                                        final double mu) {
        super(positionProvider, name, mu);
    }

    /** Constructor.
     * @param body the body to consider
     * (ex: {@link CelestialBodies#getSun()} or
     * {@link CelestialBodies#getMoon()})
     */
    public SingleBodyRelativeAttraction(final CelestialBody body) {
        this(body, body.getName(), body.getGM());
    }

    /** {@inheritDoc} */
    public Vector3D acceleration(final SpacecraftState s, final double[] parameters) {

        // compute bodies separation vectors and squared norm
        final PVCoordinates bodyPV   = getBodyPVCoordinates(s.getDate(), s.getFrame());
        final Vector3D satToBody     = bodyPV.getPosition().subtract(s.getPosition());
        final double r2Sat           = satToBody.getNormSq();

        // compute relative acceleration
        final double gm = parameters[0];
        final double a = gm / r2Sat;
        return new Vector3D(a, satToBody.normalize()).add(bodyPV.getAcceleration());

    }

    /** {@inheritDoc} */
    public <T extends CalculusFieldElement<T>> FieldVector3D<T> acceleration(final FieldSpacecraftState<T> s,
                                                                         final T[] parameters) {

        // compute bodies separation vectors and squared norm
        final FieldPVCoordinates<T> bodyPV = getBodyPVCoordinates(s.getDate(), s.getFrame());
        final FieldVector3D<T> satToBody   = bodyPV.getPosition().subtract(s.getPosition());
        final T                r2Sat       = satToBody.getNormSq();

        // compute relative acceleration
        final T gm = parameters[0];
        final T a  = gm.divide(r2Sat);
        return new FieldVector3D<>(a, satToBody.normalize()).add(bodyPV.getAcceleration());

    }

}