/* Copyright 2010-2011 Centre National d'Études Spatiales
* 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.propagation.numerical;
import java.util.ArrayList;
import java.util.Arrays;
import java.util.HashMap;
import java.util.List;
import java.util.Map;
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.Rotation;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.FastMath;
import org.hipparchus.util.Precision;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.forces.ForceModel;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.integration.AdditionalEquations;
import org.orekit.utils.ParameterDriver;
import org.orekit.utils.ParameterDriversList;
/** Set of {@link AdditionalEquations additional equations} computing the partial derivatives
* of the state (orbit) with respect to initial state and force models parameters.
* <p>
* This set of equations are automatically added to a {@link NumericalPropagator numerical propagator}
* in order to compute partial derivatives of the orbit along with the orbit itself. This is
* useful for example in orbit determination applications.
* </p>
* <p>
* The partial derivatives with respect to initial state can be either dimension 6
* (orbit only) or 7 (orbit and mass).
* </p>
* <p>
* The partial derivatives with respect to force models parameters has a dimension
* equal to the number of selected parameters. Parameters selection is implemented at
* {@link ForceModel force models} level. Users must retrieve a {@link ParameterDriver
* parameter driver} using {@link ForceModel#getParameterDriver(String)} and then
* select it by calling {@link ParameterDriver#setSelected(boolean) setSelected(true)}.
* </p>
* <p>
* If several force models provide different {@link ParameterDriver drivers} for the
* same parameter name, selecting any of these drivers has the side effect of
* selecting all the drivers for this shared parameter. In this case, the partial
* derivatives will be the sum of the partial derivatives contributed by the
* corresponding force models. This case typically arises for central attraction
* coefficient, which has an influence on {@link org.orekit.forces.gravity.NewtonianAttraction
* Newtonian attraction}, {@link org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel
* gravity field}, and {@link org.orekit.forces.gravity.Relativity relativity}.
* </p>
* @author Véronique Pommier-Maurussane
*/
public class PartialDerivativesEquations implements AdditionalEquations {
/** Propagator computing state evolution. */
private final NumericalPropagator propagator;
/** Selected parameters for Jacobian computation. */
private ParameterDriversList selected;
/** Parameters map. */
private Map<ParameterDriver, ForceModel> map;
/** Name. */
private final String name;
/** State vector dimension without additional parameters
* (either 6 or 7 depending on mass derivatives being included or not). */
private int stateDim;
/** Step used for finite difference computation with respect to spacecraft position. */
private double hPos;
/** Jacobian of acceleration with respect to spacecraft position. */
private transient double[][] dAccdPos;
/** Jacobian of acceleration with respect to spacecraft velocity. */
private transient double[][] dAccdVel;
/** Jacobian of acceleration with respect to spacecraft mass. */
private transient double[] dAccdM;
/** Jacobian of acceleration with respect to one force model parameter (array reused for all parameters). */
private transient double[] dAccdParam;
/** Simple constructor.
* <p>
* Upon construction, this set of equations is <em>automatically</em> added to
* the propagator by calling its {@link
* NumericalPropagator#addAdditionalEquations(AdditionalEquations)} method. So
* there is no need to call this method explicitly for these equations.
* </p>
* @param name name of the partial derivatives equations
* @param propagator the propagator that will handle the orbit propagation
* @exception OrekitException if a set of equations with the same name is already present
*/
public PartialDerivativesEquations(final String name, final NumericalPropagator propagator)
throws OrekitException {
this.name = name;
this.selected = null;
this.map = null;
this.propagator = propagator;
this.stateDim = -1;
this.hPos = Double.NaN;
propagator.addAdditionalEquations(this);
}
/** {@inheritDoc} */
public String getName() {
return name;
}
/** Freeze the selected parameters from the force models.
* @exception OrekitException if an existing driver for a
* parameter throws one when its value is reset using the value
* from another driver managing the same parameter
*/
private void freezeParametersSelection()
throws OrekitException {
if (selected == null) {
// first pass: gather all parameters, binding similar names together
selected = new ParameterDriversList();
map = new HashMap<ParameterDriver, ForceModel>();
for (final ForceModel provider : propagator.getAllForceModels()) {
for (final ParameterDriver driver : provider.getParametersDrivers()) {
map.put(driver, provider);
selected.add(driver);
}
}
// second pass: now that shared parameter names are bound together,
// their selections status have been synchronized, we can filter them
selected.filter(true);
// third pass: sort parameters lexicographically
selected.sort();
}
}
/** Get the selected parameters, in Jacobian matrix column order.
* <p>
* The force models parameters for which partial derivatives are desired,
* <em>must</em> have been {@link ParameterDriver#setSelected(boolean) selected}
* before this method is called, so the proper list is returned.
* </p>
* @return selected parameters, in Jacobian matrix column order which
* is lexicographic order
* @exception OrekitException if an existing driver for a
* parameter throws one when its value is reset using the value
* from another driver managing the same parameter
*/
public ParameterDriversList getSelectedParameters()
throws OrekitException {
freezeParametersSelection();
return selected;
}
/** Get the names of the available parameters in the propagator.
* <p>
* The names returned depend on the force models set up in the propagator,
* including the Newtonian attraction from the central body.
* </p>
* @return available parameters
* @deprecated as of 8.0, this method is not needed anymore, as
* parameters selection is performed at force model level
*/
@Deprecated
public List<String> getAvailableParameters() {
final List<String> available = new ArrayList<String>();
for (final ForceModel model : propagator.getAllForceModels()) {
for (final ParameterDriver driver : model.getParametersDrivers()) {
available.add(driver.getName());
}
}
return available;
}
/** Select the parameters to consider for Jacobian processing.
* <p>This method is deprecated. Starting with version 8.0, parameters
* selection is implemented at {@link ForceModel force models} level.</p>
* @param parameters parameters to consider for Jacobian processing
* @see NumericalPropagator#addForceModel(ForceModel)
* @see #setInitialJacobians(SpacecraftState, double[][], double[][])
* @deprecated as of 8.0, this method is not needed anymore, as
* parameters selection is performed at force model level
*/
@Deprecated
public void selectParameters(final Iterable<String> parameters) {
// unselect everything
for (final ForceModel model : propagator.getAllForceModels()) {
for (final ParameterDriver driver : model.getParametersDrivers()) {
driver.setSelected(false);
}
}
// select the specified parameters
for (String param : parameters) {
for (final ForceModel model : propagator.getAllForceModels()) {
for (final ParameterDriver driver : model.getParametersDrivers()) {
if (param.equals(driver.getName())) {
driver.setSelected(true);
}
}
}
}
}
/** Select the parameters to consider for Jacobian processing.
* <p>This method is deprecated. Starting with version 8.0, parameters
* selection is implemented at {@link ForceModel force models} level.</p>
* @param parameters parameters to consider for Jacobian processing
* @see NumericalPropagator#addForceModel(ForceModel)
* @see #setInitialJacobians(SpacecraftState, double[][], double[][])
* @deprecated as of 8.0, this method is not needed anymore, as
* parameters selection is performed at force model level
*/
@Deprecated
public void selectParameters(final String... parameters) {
selectParameters(Arrays.asList(parameters));
}
/** Select the parameters to consider for Jacobian processing.
* <p>This method is deprecated. Starting with version 8.0, parameters
* selection is implemented at {@link ForceModel force models} level.</p>
* @param parameter parameter to consider for Jacobian processing
* @param ignored ignored parameter (used to be the step to use for
* computing Jacobian column using finite differences)
* @see NumericalPropagator#addForceModel(ForceModel)
* @see #setInitialJacobians(SpacecraftState, double[][], double[][])
* @deprecated as of 8.0, this method is not needed anymore, as
* parameters selection is performed at force model level
*/
@Deprecated
public void selectParamAndStep(final String parameter, final double ignored) {
for (final ForceModel model : propagator.getAllForceModels()) {
for (final ParameterDriver driver : model.getParametersDrivers()) {
if (parameter.equals(driver.getName())) {
driver.setSelected(true);
}
}
}
}
/** Set the initial value of the Jacobian with respect to state and parameter.
* <p>
* This method is equivalent to call {@link #setInitialJacobians(SpacecraftState,
* double[][], double[][])} with dYdY0 set to the identity matrix and dYdP set
* to a zero matrix.
* </p>
* <p>
* The force models parameters for which partial derivatives are desired,
* <em>must</em> have been {@link ParameterDriver#setSelected(boolean) selected}
* before this method is called, so proper matrices dimensions are used.
* </p>
* @param s0 initial state
* @param stateDimension state dimension, must be either 6 for orbit only or 7 for orbit and mass
* @return state with initial Jacobians added
* @exception OrekitException if the partial equation has not been registered in
* the propagator or if matrices dimensions are incorrect
* @see #getSelectedParameters()
*/
public SpacecraftState setInitialJacobians(final SpacecraftState s0, final int stateDimension)
throws OrekitException {
freezeParametersSelection();
final double[][] dYdY0 = new double[stateDimension][stateDimension];
final double[][] dYdP = new double[stateDimension][selected.getNbParams()];
for (int i = 0; i < stateDimension; ++i) {
dYdY0[i][i] = 1.0;
}
return setInitialJacobians(s0, dYdY0, dYdP);
}
/** Set the initial value of the Jacobian with respect to state and parameter.
* <p>
* The returned state must be added to the propagator (it is not done
* automatically, as the user may need to add more states to it).
* </p>
* <p>
* The force models parameters for which partial derivatives are desired,
* <em>must</em> have been {@link ParameterDriver#setSelected(boolean) selected}
* before this method is called, and the {@code dY1dP} matrix dimension <em>must</em>
* be consistent with the selection.
* </p>
* @param s1 current state
* @param dY1dY0 Jacobian of current state at time t₁ with respect
* to state at some previous time t₀ (may be either 6x6 for orbit
* only or 7x7 for orbit and mass)
* @param dY1dP Jacobian of current state at time t₁ with respect
* to parameters (may be null if no parameters are selected)
* @return state with initial Jacobians added
* @exception OrekitException if the partial equation has not been registered in
* the propagator or if matrices dimensions are incorrect
* @see #getSelectedParameters()
*/
public SpacecraftState setInitialJacobians(final SpacecraftState s1,
final double[][] dY1dY0, final double[][] dY1dP)
throws OrekitException {
freezeParametersSelection();
// Check dimensions
stateDim = dY1dY0.length;
if (stateDim < 6 || stateDim > 7 || stateDim != dY1dY0[0].length) {
throw new OrekitException(OrekitMessages.STATE_JACOBIAN_NEITHER_6X6_NOR_7X7,
stateDim, dY1dY0[0].length);
}
if (dY1dP != null && stateDim != dY1dP.length) {
throw new OrekitException(OrekitMessages.STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH,
stateDim, dY1dP.length);
}
if ((dY1dP == null && selected.getNbParams() != 0) ||
(dY1dP != null && selected.getNbParams() != dY1dP[0].length)) {
throw new OrekitException(new OrekitException(OrekitMessages.INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH,
dY1dP == null ? 0 : dY1dP[0].length, selected.getNbParams()));
}
final int dim = 3;
dAccdParam = new double[dim];
dAccdPos = new double[dim][dim];
dAccdVel = new double[dim][dim];
dAccdM = (stateDim > 6) ? new double[dim] : null;
// store the matrices as a single dimension array
final JacobiansMapper mapper = getMapper();
final double[] p = new double[mapper.getAdditionalStateDimension()];
mapper.setInitialJacobians(s1, dY1dY0, dY1dP, p);
// set value in propagator
return s1.addAdditionalState(name, p);
}
/** Get a mapper between two-dimensional Jacobians and one-dimensional additional state.
* @return a mapper between two-dimensional Jacobians and one-dimensional additional state,
* with the same name as the instance
* @exception OrekitException if the initial Jacobians have not been initialized yet
* @see #setInitialJacobians(SpacecraftState, int)
* @see #setInitialJacobians(SpacecraftState, double[][], double[][])
*/
public JacobiansMapper getMapper() throws OrekitException {
if (stateDim < 0) {
throw new OrekitException(OrekitMessages.STATE_JACOBIAN_NOT_INITIALIZED);
}
return new JacobiansMapper(name, stateDim, selected,
propagator.getOrbitType(),
propagator.getPositionAngleType());
}
/** {@inheritDoc} */
public double[] computeDerivatives(final SpacecraftState s, final double[] pDot)
throws OrekitException {
// if step has not been set by user, set a default value
if (Double.isNaN(hPos)) {
hPos = FastMath.sqrt(Precision.EPSILON) * s.getPVCoordinates().getPosition().getNorm();
}
// initialize acceleration Jacobians to zero
for (final double[] row : dAccdPos) {
Arrays.fill(row, 0.0);
}
for (final double[] row : dAccdVel) {
Arrays.fill(row, 0.0);
}
if (dAccdM != null) {
Arrays.fill(dAccdM, 0.0);
}
// prepare derivation variables, 3 for position, 3 for velocity and optionally 1 for mass
final DSFactory factory = new DSFactory((dAccdM == null) ? 6 : 7, 1);
// position corresponds three free parameters
final Vector3D position = s.getPVCoordinates().getPosition();
final FieldVector3D<DerivativeStructure> dsP =
new FieldVector3D<DerivativeStructure>(factory.variable(0, position.getX()),
factory.variable(1, position.getY()),
factory.variable(2, position.getZ()));
// velocity corresponds three free parameters
final Vector3D velocity = s.getPVCoordinates().getVelocity();
final FieldVector3D<DerivativeStructure> dsV =
new FieldVector3D<DerivativeStructure>(factory.variable(3, velocity.getX()),
factory.variable(4, velocity.getY()),
factory.variable(5, velocity.getZ()));
// mass corresponds either to a constant or to one free parameter
final DerivativeStructure dsM = (dAccdM == null) ?
factory.constant(s.getMass()) :
factory.variable(6, s.getMass());
// we should compute attitude partial derivatives with respect to position/velocity
// see issue #200
final Rotation rotation = s.getAttitude().getRotation();
final FieldRotation<DerivativeStructure> dsR =
new FieldRotation<DerivativeStructure>(factory.constant(rotation.getQ0()),
factory.constant(rotation.getQ1()),
factory.constant(rotation.getQ2()),
factory.constant(rotation.getQ3()),
false);
// compute acceleration Jacobians, finishing with the largest force: Newtonian attraction
for (final ForceModel forceModel : propagator.getAllForceModels()) {
final FieldVector3D<DerivativeStructure> acceleration =
forceModel.accelerationDerivatives(s.getDate(), s.getFrame(),
dsP, dsV, dsR, dsM);
addToRow(acceleration.getX(), 0);
addToRow(acceleration.getY(), 1);
addToRow(acceleration.getZ(), 2);
}
// the variational equations of the complete state Jacobian matrix have the
// following form for 7x7, i.e. when mass partial derivatives are also considered
// (when mass is not considered, only the A, B, D and E matrices are used along
// with their derivatives):
// [ | | ] [ | | ] [ | | ]
// [ Adot | Bdot | Cdot ] [ dVel/dPos = 0 | dVel/dVel = Id | dVel/dm = 0 ] [ A | B | C ]
// [ | | ] [ | | ] [ | | ]
// --------+--------+--- ---- ------------------+------------------+---------------- -----+-----+-----
// [ | | ] [ | | ] [ | | ]
// [ Ddot | Edot | Fdot ] = [ dAcc/dPos | dAcc/dVel | dAcc/dm ] * [ D | E | F ]
// [ | | ] [ | | ] [ | | ]
// --------+--------+--- ---- ------------------+------------------+---------------- -----+-----+-----
// [ Gdot | Hdot | Idot ] [ dmDot/dPos = 0 | dmDot/dVel = 0 | dmDot/dm = 0 ] [ G | H | I ]
// The A, B, D and E sub-matrices and their derivatives (Adot ...) are 3x3 matrices,
// the C and F sub-matrices and their derivatives (Cdot ...) are 3x1 matrices,
// the G and H sub-matrices and their derivatives (Gdot ...) are 1x3 matrices,
// the I sub-matrix and its derivative (Idot) is a 1x1 matrix.
// The expanded multiplication above can be rewritten to take into account
// the fixed values found in the sub-matrices in the left factor. This leads to:
// [ Adot ] = [ D ]
// [ Bdot ] = [ E ]
// [ Cdot ] = [ F ]
// [ Ddot ] = [ dAcc/dPos ] * [ A ] + [ dAcc/dVel ] * [ D ] + [ dAcc/dm ] * [ G ]
// [ Edot ] = [ dAcc/dPos ] * [ B ] + [ dAcc/dVel ] * [ E ] + [ dAcc/dm ] * [ H ]
// [ Fdot ] = [ dAcc/dPos ] * [ C ] + [ dAcc/dVel ] * [ F ] + [ dAcc/dm ] * [ I ]
// [ Gdot ] = [ 0 ]
// [ Hdot ] = [ 0 ]
// [ Idot ] = [ 0 ]
// The following loops compute these expressions taking care of the mapping of the
// (A, B, ... I) matrices into the single dimension array p and of the mapping of the
// (Adot, Bdot, ... Idot) matrices into the single dimension array pDot.
final int dim = 3;
// copy D, E and F into Adot, Bdot and Cdot
final double[] p = s.getAdditionalState(getName());
System.arraycopy(p, dim * stateDim, pDot, 0, dim * stateDim);
// compute Ddot, Edot and Fdot
for (int i = 0; i < dim; ++i) {
final double[] dAdPi = dAccdPos[i];
final double[] dAdVi = dAccdVel[i];
for (int j = 0; j < stateDim; ++j) {
pDot[(dim + i) * stateDim + j] =
dAdPi[0] * p[j] + dAdPi[1] * p[j + stateDim] + dAdPi[2] * p[j + 2 * stateDim] +
dAdVi[0] * p[j + 3 * stateDim] + dAdVi[1] * p[j + 4 * stateDim] + dAdVi[2] * p[j + 5 * stateDim] +
((dAccdM == null) ? 0.0 : dAccdM[i] * p[j + 6 * stateDim]);
}
}
if (dAccdM != null) {
// set Gdot, Hdot and Idot to 0
Arrays.fill(pDot, 6 * stateDim, 7 * stateDim, 0.0);
}
final int paramDim = selected.getNbParams();
for (int k = 0; k < paramDim; ++k) {
// compute the acceleration gradient with respect to current parameter
final ParameterDriversList.DelegatingDriver delegating = selected.getDrivers().get(k);
dAccdParam[0] = 0.0;
dAccdParam[1] = 0.0;
dAccdParam[2] = 0.0;
for (final ParameterDriver driver : delegating.getRawDrivers()) {
final FieldVector3D<DerivativeStructure> accDer = map.get(driver).accelerationDerivatives(s, driver.getName());
dAccdParam[0] += accDer.getX().getPartialDerivative(1);
dAccdParam[1] += accDer.getY().getPartialDerivative(1);
dAccdParam[2] += accDer.getZ().getPartialDerivative(1);
}
// the variational equations of the parameters Jacobian matrix are computed
// one column at a time, they have the following form:
// [ ] [ | | ] [ ] [ ]
// [ Jdot ] [ dVel/dPos = 0 | dVel/dVel = Id | dVel/dm = 0 ] [ J ] [ dVel/dParam = 0 ]
// [ ] [ | | ] [ ] [ ]
// -------- ------------------+------------------+---------------- ----- --------------------
// [ ] [ | | ] [ ] [ ]
// [ Kdot ] = [ dAcc/dPos | dAcc/dVel | dAcc/dm ] * [ K ] + [ dAcc/dParam ]
// [ ] [ | | ] [ ] [ ]
// -------- ------------------+------------------+---------------- ----- --------------------
// [ Ldot ] [ dmDot/dPos = 0 | dmDot/dVel = 0 | dmDot/dm = 0 ] [ L ] [ dmDot/dParam = 0 ]
// The J and K sub-columns and their derivatives (Jdot ...) are 3 elements columns,
// the L sub-colums and its derivative (Ldot) are 1 elements columns.
// The expanded multiplication and addition above can be rewritten to take into
// account the fixed values found in the sub-matrices in the left factor. This leads to:
// [ Jdot ] = [ K ]
// [ Kdot ] = [ dAcc/dPos ] * [ J ] + [ dAcc/dVel ] * [ K ] + [ dAcc/dm ] * [ L ] + [ dAcc/dParam ]
// [ Ldot ] = [ 0 ]
// The following loops compute these expressions taking care of the mapping of the
// (J, K, L) columns into the single dimension array p and of the mapping of the
// (Jdot, Kdot, Ldot) columns into the single dimension array pDot.
// copy K into Jdot
final int columnTop = stateDim * stateDim + k;
pDot[columnTop] = p[columnTop + 3 * paramDim];
pDot[columnTop + paramDim] = p[columnTop + 4 * paramDim];
pDot[columnTop + 2 * paramDim] = p[columnTop + 5 * paramDim];
// compute Kdot
for (int i = 0; i < dim; ++i) {
final double[] dAdPi = dAccdPos[i];
final double[] dAdVi = dAccdVel[i];
pDot[columnTop + (dim + i) * paramDim] =
dAccdParam[i] +
dAdPi[0] * p[columnTop] + dAdPi[1] * p[columnTop + paramDim] + dAdPi[2] * p[columnTop + 2 * paramDim] +
dAdVi[0] * p[columnTop + 3 * paramDim] + dAdVi[1] * p[columnTop + 4 * paramDim] + dAdVi[2] * p[columnTop + 5 * paramDim] +
((dAccdM == null) ? 0.0 : dAccdM[i] * p[columnTop + 6 * paramDim]);
}
if (dAccdM != null) {
// set Ldot to 0
pDot[columnTop + 6 * paramDim] = 0;
}
}
// these equations have no effect on the main state itself
return null;
}
/** Fill Jacobians rows when mass is needed.
* @param accelerationComponent component of acceleration (along either x, y or z)
* @param index component index (0 for x, 1 for y, 2 for z)
*/
private void addToRow(final DerivativeStructure accelerationComponent, final int index) {
if (dAccdM == null) {
// free parameters 0, 1, 2 are for position
dAccdPos[index][0] += accelerationComponent.getPartialDerivative(1, 0, 0, 0, 0, 0);
dAccdPos[index][1] += accelerationComponent.getPartialDerivative(0, 1, 0, 0, 0, 0);
dAccdPos[index][2] += accelerationComponent.getPartialDerivative(0, 0, 1, 0, 0, 0);
// free parameters 3, 4, 5 are for velocity
dAccdVel[index][0] += accelerationComponent.getPartialDerivative(0, 0, 0, 1, 0, 0);
dAccdVel[index][1] += accelerationComponent.getPartialDerivative(0, 0, 0, 0, 1, 0);
dAccdVel[index][2] += accelerationComponent.getPartialDerivative(0, 0, 0, 0, 0, 1);
} else {
// free parameters 0, 1, 2 are for position
dAccdPos[index][0] += accelerationComponent.getPartialDerivative(1, 0, 0, 0, 0, 0, 0);
dAccdPos[index][1] += accelerationComponent.getPartialDerivative(0, 1, 0, 0, 0, 0, 0);
dAccdPos[index][2] += accelerationComponent.getPartialDerivative(0, 0, 1, 0, 0, 0, 0);
// free parameters 3, 4, 5 are for velocity
dAccdVel[index][0] += accelerationComponent.getPartialDerivative(0, 0, 0, 1, 0, 0, 0);
dAccdVel[index][1] += accelerationComponent.getPartialDerivative(0, 0, 0, 0, 1, 0, 0);
dAccdVel[index][2] += accelerationComponent.getPartialDerivative(0, 0, 0, 0, 0, 1, 0);
// free parameter 6 is for mass
dAccdM[index] += accelerationComponent.getPartialDerivative(0, 0, 0, 0, 0, 0, 1);
}
}
}