ModifierGradientConverter.java

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package org.orekit.estimation.measurements.modifiers;

import org.hipparchus.Field;
import org.hipparchus.analysis.differentiation.Gradient;
import org.hipparchus.analysis.differentiation.GradientField;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.attitudes.FieldAttitude;
import org.orekit.orbits.FieldCartesianOrbit;
import org.orekit.orbits.FieldOrbit;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.integration.AbstractGradientConverter;
import org.orekit.utils.TimeStampedFieldPVCoordinates;

/**
 * Converter for states and parameters arrays.
 * @author Bryan Cazabonne
 * @since 11.2
 */
public class ModifierGradientConverter extends AbstractGradientConverter {

    /** Simple constructor.
     * @param state regular state
     * @param freeStateParameters number of free parameters, either 3 (position) or 6 (position-velocity)
     * @param provider provider to use if attitude needs to be recomputed
     */
    public ModifierGradientConverter(final SpacecraftState state, final int freeStateParameters,
                                     final AttitudeProvider provider) {

        super(freeStateParameters);

        // Derivative field
        final Field<Gradient> field =  GradientField.getField(freeStateParameters);

        // position always has derivatives
        final Vector3D pos = state.getPVCoordinates().getPosition();
        final FieldVector3D<Gradient> posG = new FieldVector3D<>(Gradient.variable(freeStateParameters, 0, pos.getX()),
                                                                 Gradient.variable(freeStateParameters, 1, pos.getY()),
                                                                 Gradient.variable(freeStateParameters, 2, pos.getZ()));

        // velocity may have derivatives or not
        final Vector3D vel = state.getPVCoordinates().getVelocity();
        final FieldVector3D<Gradient> velG;
        if (freeStateParameters > 3) {
            velG = new FieldVector3D<>(Gradient.variable(freeStateParameters, 3, vel.getX()),
                                       Gradient.variable(freeStateParameters, 4, vel.getY()),
                                       Gradient.variable(freeStateParameters, 5, vel.getZ()));
        } else {
            velG = new FieldVector3D<>(Gradient.constant(freeStateParameters, vel.getX()),
                                       Gradient.constant(freeStateParameters, vel.getY()),
                                       Gradient.constant(freeStateParameters, vel.getZ()));
        }

        // acceleration never has derivatives
        final Vector3D acc = state.getPVCoordinates().getAcceleration();
        final FieldVector3D<Gradient> accG = new FieldVector3D<>(Gradient.constant(freeStateParameters, acc.getX()),
                                                                 Gradient.constant(freeStateParameters, acc.getY()),
                                                                 Gradient.constant(freeStateParameters, acc.getZ()));

        // mass never has derivatives
        final Gradient dsM = Gradient.constant(freeStateParameters, state.getMass());

        final FieldOrbit<Gradient> gOrbit =
                        new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(state.getDate(), posG, velG, accG),
                                                  state.getFrame(),
                                                  field.getZero().add(state.getMu()));

        final FieldAttitude<Gradient> gAttitude;
        if (freeStateParameters > 3) {
            // compute attitude partial derivatives with respect to position/velocity
            gAttitude = provider.getAttitude(gOrbit, gOrbit.getDate(), gOrbit.getFrame());
        } else {
            // force model does not depend on attitude, don't bother recomputing it
            gAttitude = new FieldAttitude<>(field, state.getAttitude());
        }

        // initialize the list with the state having 0 force model parameters
        initStates(new FieldSpacecraftState<>(gOrbit, gAttitude, dsM));

    }

}