TroposphericDSConverter.java
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* this work for additional information regarding copyright ownership.
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*
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package org.orekit.estimation.measurements.modifiers;
import java.util.ArrayList;
import java.util.List;
import org.hipparchus.analysis.differentiation.DSFactory;
import org.hipparchus.analysis.differentiation.DerivativeStructure;
import org.hipparchus.geometry.euclidean.threed.FieldRotation;
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.models.earth.troposphere.DiscreteTroposphericModel;
import org.orekit.orbits.FieldCartesianOrbit;
import org.orekit.orbits.FieldOrbit;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.SpacecraftState;
import org.orekit.utils.FieldAngularCoordinates;
import org.orekit.utils.FieldPVCoordinates;
import org.orekit.utils.ParameterDriver;
import org.orekit.utils.TimeStampedFieldAngularCoordinates;
import org.orekit.utils.TimeStampedFieldPVCoordinates;
/** Converter for states and parameters arrays.
* @author Luc Maisonobe
* @deprecated as of 10.2, replaced by {@link TroposphericGradientConverter}
*/
@Deprecated
public class TroposphericDSConverter {
/** Dimension of the state. */
private final int freeStateParameters;
/** States with various number of additional parameters for tropospheric models. */
private final List<FieldSpacecraftState<DerivativeStructure>> dsStates;
/** 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 TroposphericDSConverter(final SpacecraftState state, final int freeStateParameters, final AttitudeProvider provider) {
this.freeStateParameters = freeStateParameters;
// prepare derivation variables, position, optionally velocity
final DSFactory factory = new DSFactory(freeStateParameters, 1);
// position always has derivatives
final Vector3D pos = state.getPVCoordinates().getPosition();
final FieldVector3D<DerivativeStructure> posDS = new FieldVector3D<>(factory.variable(0, pos.getX()),
factory.variable(1, pos.getY()),
factory.variable(2, pos.getZ()));
// velocity may have derivatives or not
final Vector3D vel = state.getPVCoordinates().getVelocity();
final FieldVector3D<DerivativeStructure> velDS;
if (freeStateParameters > 3) {
velDS = new FieldVector3D<>(factory.variable(3, vel.getX()),
factory.variable(4, vel.getY()),
factory.variable(5, vel.getZ()));
} else {
velDS = new FieldVector3D<>(factory.constant(vel.getX()),
factory.constant(vel.getY()),
factory.constant(vel.getZ()));
}
// acceleration never has derivatives
final Vector3D acc = state.getPVCoordinates().getAcceleration();
final FieldVector3D<DerivativeStructure> accDS = new FieldVector3D<>(factory.constant(acc.getX()),
factory.constant(acc.getY()),
factory.constant(acc.getZ()));
// mass never has derivatives
final DerivativeStructure dsM = factory.constant(state.getMass());
final FieldOrbit<DerivativeStructure> dsOrbit =
new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(state.getDate(), posDS, velDS, accDS),
state.getFrame(),
factory.getDerivativeField().getZero().add(state.getMu()));
final FieldAttitude<DerivativeStructure> dsAttitude;
if (freeStateParameters > 3) {
// compute attitude partial derivatives with respect to position/velocity
dsAttitude = provider.getAttitude(dsOrbit, dsOrbit.getDate(), dsOrbit.getFrame());
} else {
// force model does not depend on attitude, don't bother recomputing it
dsAttitude = new FieldAttitude<>(factory.getDerivativeField(), state.getAttitude());
}
// initialize the list with the state having 0 formce model parameters
dsStates = new ArrayList<>();
dsStates.add(new FieldSpacecraftState<>(dsOrbit, dsAttitude, dsM));
}
/** Get the number of free state parameters.
* @return number of free state parameters
*/
public int getFreeStateParameters() {
return freeStateParameters;
}
/** Get the state with the number of parameters consistent with tropospheric model.
* @param tropoModel tropospheric model
* @return state with the number of parameters consistent with tropospheric model
*/
public FieldSpacecraftState<DerivativeStructure> getState(final DiscreteTroposphericModel tropoModel) {
// count the required number of parameters
int nbParams = 0;
for (final ParameterDriver driver : tropoModel.getParametersDrivers()) {
if (driver.isSelected()) {
++nbParams;
}
}
// fill in intermediate slots
while (dsStates.size() < nbParams + 1) {
dsStates.add(null);
}
if (dsStates.get(nbParams) == null) {
// it is the first time we need this number of parameters
// we need to create the state
final DSFactory factory = new DSFactory(freeStateParameters + nbParams, 1);
final FieldSpacecraftState<DerivativeStructure> s0 = dsStates.get(0);
// orbit
final FieldPVCoordinates<DerivativeStructure> pv0 = s0.getPVCoordinates();
final FieldOrbit<DerivativeStructure> dsOrbit =
new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(s0.getDate().toAbsoluteDate(),
extend(pv0.getPosition(), factory),
extend(pv0.getVelocity(), factory),
extend(pv0.getAcceleration(), factory)),
s0.getFrame(), extend(s0.getMu(), factory));
// attitude
final FieldAngularCoordinates<DerivativeStructure> ac0 = s0.getAttitude().getOrientation();
final FieldAttitude<DerivativeStructure> dsAttitude =
new FieldAttitude<>(s0.getAttitude().getReferenceFrame(),
new TimeStampedFieldAngularCoordinates<>(dsOrbit.getDate(),
extend(ac0.getRotation(), factory),
extend(ac0.getRotationRate(), factory),
extend(ac0.getRotationAcceleration(), factory)));
// mass
final DerivativeStructure dsM = extend(s0.getMass(), factory);
dsStates.set(nbParams, new FieldSpacecraftState<>(dsOrbit, dsAttitude, dsM));
}
return dsStates.get(nbParams);
}
/** Add zero derivatives.
* @param original original scalar
* @param factory factory for the extended derivatives
* @return extended scalar
*/
private DerivativeStructure extend(final DerivativeStructure original, final DSFactory factory) {
final double[] originalDerivatives = original.getAllDerivatives();
final double[] extendedDerivatives = new double[factory.getCompiler().getSize()];
System.arraycopy(originalDerivatives, 0, extendedDerivatives, 0, originalDerivatives.length);
return factory.build(extendedDerivatives);
}
/** Add zero derivatives.
* @param original original vector
* @param factory factory for the extended derivatives
* @return extended vector
*/
private FieldVector3D<DerivativeStructure> extend(final FieldVector3D<DerivativeStructure> original, final DSFactory factory) {
return new FieldVector3D<>(extend(original.getX(), factory),
extend(original.getY(), factory),
extend(original.getZ(), factory));
}
/** Add zero derivatives.
* @param original original rotation
* @param factory factory for the extended derivatives
* @return extended rotation
*/
private FieldRotation<DerivativeStructure> extend(final FieldRotation<DerivativeStructure> original, final DSFactory factory) {
return new FieldRotation<>(extend(original.getQ0(), factory),
extend(original.getQ1(), factory),
extend(original.getQ2(), factory),
extend(original.getQ3(), factory),
false);
}
/** Get the tropospheric model parameters.
* @param state state as returned by {@link #getState(DiscreteTroposphericModel)}
* @param tropoModel tropospheric model associated with the parameters
* @return tropospheric model parameters
*/
public DerivativeStructure[] getParameters(final FieldSpacecraftState<DerivativeStructure> state,
final DiscreteTroposphericModel tropoModel) {
final DSFactory factory = state.getMass().getFactory();
final List<ParameterDriver> drivers = tropoModel.getParametersDrivers();
final DerivativeStructure[] parameters = new DerivativeStructure[drivers.size()];
int index = freeStateParameters;
for (int i = 0; i < drivers.size(); ++i) {
parameters[i] = drivers.get(i).isSelected() ?
factory.variable(index++, drivers.get(i).getValue()) :
factory.constant(drivers.get(i).getValue());
}
return parameters;
}
}