MassDepletionDelay.java

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 *
 *   http://www.apache.org/licenses/LICENSE-2.0
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package org.orekit.forces.maneuvers.jacobians;

import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.orekit.forces.maneuvers.Maneuver;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.integration.AdditionalDerivativesProvider;
import org.orekit.propagation.integration.CombinedDerivatives;
import org.orekit.time.AbsoluteDate;

/** Generator for effect of delaying mass depletion when delaying a maneuver.
 * @author Luc Maisonobe
 * @since 11.1
 */
public class MassDepletionDelay implements AdditionalDerivativesProvider {

    /** Prefix for state name. */
    public static final String PREFIX = "Orekit-depletion-";

    /** Name of the mass depletion additional state. */
    private final String depletionName;

    /** Start/stop management flag. */
    private final boolean manageStart;

    /** Maneuver that is delayed. */
    private final Maneuver maneuver;

    /** Indicator for forward propagation. */
    private boolean forward;

    /** Simple constructor.
     * <p>
     * The generated additional state and derivatives will be named by prepending
     * the {@link #PREFIX} to the name of the date trigger parameter.
     * </p>
     * @param triggerName name of the date trigger parameter
     * @param manageStart if true, we compute derivatives with respect to maneuver start
     * @param maneuver maneuver that is delayed
     */
    public MassDepletionDelay(final String triggerName, final boolean manageStart, final Maneuver maneuver) {
        this.depletionName = PREFIX + triggerName;
        this.manageStart   = manageStart;
        this.maneuver      = maneuver;
    }

    /** {@inheritDoc} */
    @Override
    public String getName() {
        return depletionName;
    }

    /** Get the dimension of the generated column.
     * @return dimension of the generated column
     */
    public int getDimension() {
        return 6;
    }

    /** {@inheritDoc} */
    @Override
    public void init(final SpacecraftState initialState, final AbsoluteDate target) {
        forward = target.isAfterOrEqualTo(initialState);
    }

    /** {@inheritDoc} */
    @Override
    public CombinedDerivatives combinedDerivatives(final SpacecraftState state) {

        // retrieve current Jacobian column
        final double[] p = state.getAdditionalState(getName());
        final double[] pDot = new double[6];

        if (forward == manageStart) {

            // current acceleration
            final double[] parameters   = maneuver.getParameters(state.getDate());
            // for the acceleration method we need all the span values of all the parameters driver
            // as in the acceleration method an exctractParameter method is called
            final Vector3D acceleration = maneuver.acceleration(state, parameters);

            // we have acceleration Γ = F/m and m = m₀ - q (t - tₛ)
            // where m is current mass, m₀ is initial mass and tₛ is maneuver trigger time
            // a delay dtₛ on trigger time induces delaying mass depletion
            // we get: dΓ = -F/m² dm = -F/m² q dtₛ = -Γ q/m dtₛ
            final double minusQ = maneuver.getPropulsionModel().getMassDerivatives(state, maneuver.getParameters(state.getDate()));
            final double m      = state.getMass();
            final double ratio  = minusQ / m;

            pDot[0] = p[3];
            pDot[1] = p[4];
            pDot[2] = p[5];
            pDot[3] = ratio * acceleration.getX();
            pDot[4] = ratio * acceleration.getY();
            pDot[5] = ratio * acceleration.getZ();

        }

        return new CombinedDerivatives(pDot, null);

    }

}