AbstractIntegratedPropagator.java
/* Copyright 2002-2015 CS Systèmes d'Information
* 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.integration;
import java.util.ArrayList;
import java.util.Collection;
import java.util.Collections;
import java.util.HashMap;
import java.util.List;
import java.util.Map;
import org.apache.commons.math3.exception.MathIllegalArgumentException;
import org.apache.commons.math3.exception.MathIllegalStateException;
import org.apache.commons.math3.ode.AbstractIntegrator;
import org.apache.commons.math3.ode.ContinuousOutputModel;
import org.apache.commons.math3.ode.EquationsMapper;
import org.apache.commons.math3.ode.ExpandableStatefulODE;
import org.apache.commons.math3.ode.FirstOrderDifferentialEquations;
import org.apache.commons.math3.ode.SecondaryEquations;
import org.apache.commons.math3.ode.sampling.StepHandler;
import org.apache.commons.math3.ode.sampling.StepInterpolator;
import org.apache.commons.math3.util.Precision;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitExceptionWrapper;
import org.orekit.errors.OrekitMessages;
import org.orekit.errors.PropagationException;
import org.orekit.frames.Frame;
import org.orekit.orbits.Orbit;
import org.orekit.orbits.OrbitType;
import org.orekit.orbits.PositionAngle;
import org.orekit.propagation.AbstractPropagator;
import org.orekit.propagation.BoundedPropagator;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
import org.orekit.propagation.events.handlers.EventHandler;
import org.orekit.propagation.sampling.OrekitStepHandler;
import org.orekit.propagation.sampling.OrekitStepInterpolator;
import org.orekit.time.AbsoluteDate;
/** Common handling of {@link org.orekit.propagation.Propagator Propagator}
* methods for both numerical and semi-analytical propagators.
* @author Luc Maisonobe
*/
public abstract class AbstractIntegratedPropagator extends AbstractPropagator {
/** Event detectors not related to force models. */
private final List<EventDetector> detectors;
/** Integrator selected by the user for the orbital extrapolation process. */
private final AbstractIntegrator integrator;
/** Mode handler. */
private ModeHandler modeHandler;
/** Additional equations. */
private List<AdditionalEquations> additionalEquations;
/** Counter for differential equations calls. */
private int calls;
/** Mapper between raw double components and space flight dynamics objects. */
private StateMapper stateMapper;
/** Complete equation to be integrated. */
private ExpandableStatefulODE mathODE;
/** Underlying raw rawInterpolator. */
private StepInterpolator mathInterpolator;
/** Output only the mean orbit. <br/>
* <p>
* This is used only in the case of semianalitical propagators where there is a clear separation between
* mean and short periodic elements. It is ignored by the Numerical propagator.
* </p>
*/
private boolean meanOrbit;
/** Build a new instance.
* @param integrator numerical integrator to use for propagation.
* @param meanOrbit output only the mean orbit.
*/
protected AbstractIntegratedPropagator(final AbstractIntegrator integrator, final boolean meanOrbit) {
detectors = new ArrayList<EventDetector>();
additionalEquations = new ArrayList<AdditionalEquations>();
this.integrator = integrator;
this.meanOrbit = meanOrbit;
}
/** Initialize the mapper. */
protected void initMapper() {
stateMapper = createMapper(null, Double.NaN, null, null, null, null);
}
/** {@inheritDoc} */
public void setAttitudeProvider(final AttitudeProvider attitudeProvider) {
super.setAttitudeProvider(attitudeProvider);
stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
attitudeProvider, stateMapper.getFrame());
}
/** Set propagation orbit type.
* @param orbitType orbit type to use for propagation
*/
protected void setOrbitType(final OrbitType orbitType) {
stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
orbitType, stateMapper.getPositionAngleType(),
stateMapper.getAttitudeProvider(), stateMapper.getFrame());
}
/** Get propagation parameter type.
* @return orbit type used for propagation
*/
protected OrbitType getOrbitType() {
return stateMapper.getOrbitType();
}
/** Check if only the mean elements should be used in a semianalitical propagation.
* @return true if only mean elements have to be used
*/
protected boolean isMeanOrbit() {
return meanOrbit;
}
/** Set position angle type.
* <p>
* The position parameter type is meaningful only if {@link
* #getOrbitType() propagation orbit type}
* support it. As an example, it is not meaningful for propagation
* in {@link OrbitType#CARTESIAN Cartesian} parameters.
* </p>
* @param positionAngleType angle type to use for propagation
*/
protected void setPositionAngleType(final PositionAngle positionAngleType) {
stateMapper = createMapper(stateMapper.getReferenceDate(), stateMapper.getMu(),
stateMapper.getOrbitType(), positionAngleType,
stateMapper.getAttitudeProvider(), stateMapper.getFrame());
}
/** Get propagation parameter type.
* @return angle type to use for propagation
*/
protected PositionAngle getPositionAngleType() {
return stateMapper.getPositionAngleType();
}
/** Set the central attraction coefficient μ.
* @param mu central attraction coefficient (m³/s²)
*/
public void setMu(final double mu) {
stateMapper = createMapper(stateMapper.getReferenceDate(), mu,
stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
stateMapper.getAttitudeProvider(), stateMapper.getFrame());
}
/** Get the central attraction coefficient μ.
* @return mu central attraction coefficient (m³/s²)
* @see #setMu(double)
*/
public double getMu() {
return stateMapper.getMu();
}
/** Get the number of calls to the differential equations computation method.
* <p>The number of calls is reset each time the {@link #propagate(AbsoluteDate)}
* method is called.</p>
* @return number of calls to the differential equations computation method
*/
public int getCalls() {
return calls;
}
/** {@inheritDoc} */
@Override
public boolean isAdditionalStateManaged(final String name) {
// first look at already integrated states
if (super.isAdditionalStateManaged(name)) {
return true;
}
// then look at states we integrate ourselves
for (final AdditionalEquations equation : additionalEquations) {
if (equation.getName().equals(name)) {
return true;
}
}
return false;
}
/** {@inheritDoc} */
@Override
public String[] getManagedAdditionalStates() {
final String[] alreadyIntegrated = super.getManagedAdditionalStates();
final String[] managed = new String[alreadyIntegrated.length + additionalEquations.size()];
System.arraycopy(alreadyIntegrated, 0, managed, 0, alreadyIntegrated.length);
for (int i = 0; i < additionalEquations.size(); ++i) {
managed[i + alreadyIntegrated.length] = additionalEquations.get(i).getName();
}
return managed;
}
/** Add a set of user-specified equations to be integrated along with the orbit propagation.
* @param additional additional equations
* @exception OrekitException if a set of equations with the same name is already present
*/
public void addAdditionalEquations(final AdditionalEquations additional)
throws OrekitException {
// check if the name is already used
if (isAdditionalStateManaged(additional.getName())) {
// this set of equations is already registered, complain
throw new OrekitException(OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE,
additional.getName());
}
// this is really a new set of equations, add it
additionalEquations.add(additional);
}
/** {@inheritDoc} */
public void addEventDetector(final EventDetector detector) {
detectors.add(detector);
}
/** {@inheritDoc} */
public Collection<EventDetector> getEventsDetectors() {
return Collections.unmodifiableCollection(detectors);
}
/** {@inheritDoc} */
public void clearEventsDetectors() {
detectors.clear();
}
/** Set up all user defined event detectors.
*/
protected void setUpUserEventDetectors() {
for (final EventDetector detector : detectors) {
setUpEventDetector(integrator, detector);
}
}
/** Wrap an Orekit event detector and register it to the integrator.
* @param integ integrator into which event detector should be registered
* @param detector event detector to wrap
*/
protected void setUpEventDetector(final AbstractIntegrator integ, final EventDetector detector) {
integ.addEventHandler(new AdaptedEventDetector(detector),
detector.getMaxCheckInterval(),
detector.getThreshold(),
detector.getMaxIterationCount());
}
/** {@inheritDoc}
* <p>Note that this method has the side effect of replacing the step handlers
* of the underlying integrator set up in the {@link
* #AbstractIntegratedPropagator(AbstractIntegrator, boolean) constructor}. So if a specific
* step handler is needed, it should be added after this method has been callled.</p>
*/
public void setSlaveMode() {
super.setSlaveMode();
if (integrator != null) {
integrator.clearStepHandlers();
}
modeHandler = null;
}
/** {@inheritDoc}
* <p>Note that this method has the side effect of replacing the step handlers
* of the underlying integrator set up in the {@link
* #AbstractIntegratedPropagator(AbstractIntegrator, boolean) constructor}. So if a specific
* step handler is needed, it should be added after this method has been callled.</p>
*/
public void setMasterMode(final OrekitStepHandler handler) {
super.setMasterMode(handler);
integrator.clearStepHandlers();
final AdaptedStepHandler wrapped = new AdaptedStepHandler(handler);
integrator.addStepHandler(wrapped);
modeHandler = wrapped;
}
/** {@inheritDoc}
* <p>Note that this method has the side effect of replacing the step handlers
* of the underlying integrator set up in the {@link
* #AbstractIntegratedPropagator(AbstractIntegrator, boolean) constructor}. So if a specific
* step handler is needed, it should be added after this method has been called.</p>
*/
public void setEphemerisMode() {
super.setEphemerisMode();
integrator.clearStepHandlers();
final EphemerisModeHandler ephemeris = new EphemerisModeHandler();
modeHandler = ephemeris;
integrator.addStepHandler(ephemeris);
}
/** {@inheritDoc} */
public BoundedPropagator getGeneratedEphemeris()
throws IllegalStateException {
if (getMode() != EPHEMERIS_GENERATION_MODE) {
throw OrekitException.createIllegalStateException(OrekitMessages.PROPAGATOR_NOT_IN_EPHEMERIS_GENERATION_MODE);
}
return ((EphemerisModeHandler) modeHandler).getEphemeris();
}
/** Create a mapper between raw double components and spacecraft state.
/** Simple constructor.
* <p>
* The position parameter type is meaningful only if {@link
* #getOrbitType() propagation orbit type}
* support it. As an example, it is not meaningful for propagation
* in {@link OrbitType#CARTESIAN Cartesian} parameters.
* </p>
* @param referenceDate reference date
* @param mu central attraction coefficient (m³/s²)
* @param orbitType orbit type to use for mapping
* @param positionAngleType angle type to use for propagation
* @param attitudeProvider attitude provider
* @param frame inertial frame
* @return new mapper
*/
protected abstract StateMapper createMapper(final AbsoluteDate referenceDate, final double mu,
final OrbitType orbitType, final PositionAngle positionAngleType,
final AttitudeProvider attitudeProvider, final Frame frame);
/** Get the differential equations to integrate (for main state only).
* @param integ numerical integrator to use for propagation.
* @return differential equations for main state
*/
protected abstract MainStateEquations getMainStateEquations(final AbstractIntegrator integ);
/** {@inheritDoc} */
public SpacecraftState propagate(final AbsoluteDate target) throws PropagationException {
try {
if (getStartDate() == null) {
if (getInitialState() == null) {
throw new PropagationException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
}
setStartDate(getInitialState().getDate());
}
return propagate(getStartDate(), target);
} catch (OrekitException oe) {
// recover a possible embedded PropagationException
for (Throwable t = oe; t != null; t = t.getCause()) {
if (t instanceof PropagationException) {
throw (PropagationException) t;
}
}
throw new PropagationException(oe);
}
}
/** {@inheritDoc} */
public SpacecraftState propagate(final AbsoluteDate tStart, final AbsoluteDate tEnd)
throws PropagationException {
try {
if (getInitialState() == null) {
throw new PropagationException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
}
if (!tStart.equals(getInitialState().getDate())) {
// if propagation start date is not initial date,
// propagate from initial to start date without event detection
propagate(tStart, false);
}
// propagate from start date to end date with event detection
return propagate(tEnd, true);
} catch (OrekitException oe) {
// recover a possible embedded PropagationException
for (Throwable t = oe; t != null; t = t.getCause()) {
if (t instanceof PropagationException) {
throw (PropagationException) t;
}
}
throw new PropagationException(oe);
}
}
/** Propagation with or without event detection.
* @param tEnd target date to which orbit should be propagated
* @param activateHandlers if true, step and event handlers should be activated
* @return state at end of propagation
* @exception PropagationException if orbit cannot be propagated
*/
protected SpacecraftState propagate(final AbsoluteDate tEnd, final boolean activateHandlers)
throws PropagationException {
try {
if (getInitialState().getDate().equals(tEnd)) {
// don't extrapolate
return getInitialState();
}
// space dynamics view
stateMapper = createMapper(getInitialState().getDate(), stateMapper.getMu(),
stateMapper.getOrbitType(), stateMapper.getPositionAngleType(),
stateMapper.getAttitudeProvider(), getInitialState().getFrame());
// set propagation orbit type
final Orbit initialOrbit = stateMapper.getOrbitType().convertType(getInitialState().getOrbit());
if (Double.isNaN(getMu())) {
setMu(initialOrbit.getMu());
}
if (getInitialState().getMass() <= 0.0) {
throw new PropagationException(OrekitMessages.SPACECRAFT_MASS_BECOMES_NEGATIVE,
getInitialState().getMass());
}
integrator.clearEventHandlers();
// set up events added by user
setUpUserEventDetectors();
// convert space flight dynamics API to math API
mathODE = createODE(integrator);
mathInterpolator = null;
// initialize mode handler
if (modeHandler != null) {
modeHandler.initialize(activateHandlers);
}
// mathematical integration
try {
beforeIntegration(getInitialState(), tEnd);
integrator.integrate(mathODE, tEnd.durationFrom(getInitialState().getDate()));
afterIntegration();
} catch (OrekitExceptionWrapper oew) {
throw oew.getException();
}
// get final state
SpacecraftState finalState =
stateMapper.mapArrayToState(mathODE.getTime(), mathODE.getPrimaryState(), meanOrbit);
finalState = updateAdditionalStates(finalState);
for (int i = 0; i < additionalEquations.size(); ++i) {
final double[] secondary = mathODE.getSecondaryState(i);
finalState = finalState.addAdditionalState(additionalEquations.get(i).getName(),
secondary);
}
resetInitialState(finalState);
setStartDate(finalState.getDate());
return finalState;
} catch (PropagationException pe) {
throw pe;
} catch (OrekitException oe) {
throw new PropagationException(oe);
} catch (MathIllegalArgumentException miae) {
throw PropagationException.unwrap(miae);
} catch (MathIllegalStateException mise) {
throw PropagationException.unwrap(mise);
}
}
/** Create an ODE with all equations.
* @param integ numerical integrator to use for propagation.
* @return a new ode
* @exception OrekitException if initial state cannot be mapped
*/
private ExpandableStatefulODE createODE(final AbstractIntegrator integ)
throws OrekitException {
// retrieve initial state
final double[] initialStateVector = new double[getBasicDimension()];
stateMapper.mapStateToArray(getInitialState(), initialStateVector);
// main part of the ODE
final ExpandableStatefulODE ode =
new ExpandableStatefulODE(new ConvertedMainStateEquations(getMainStateEquations(integ)));
ode.setTime(0.0);
ode.setPrimaryState(initialStateVector);
// secondary part of the ODE
for (int i = 0; i < additionalEquations.size(); ++i) {
final AdditionalEquations additional = additionalEquations.get(i);
final double[] data = getInitialState().getAdditionalState(additional.getName());
final SecondaryEquations secondary =
new ConvertedSecondaryStateEquations(additional, data.length);
ode.addSecondaryEquations(secondary);
ode.setSecondaryState(i, data);
}
return ode;
}
/** Method called just before integration.
* <p>
* The default implementation does nothing, it may be specialized in subclasses.
* </p>
* @param initialState initial state
* @param tEnd target date at which state should be propagated
* @exception OrekitException if hook cannot be run
*/
protected void beforeIntegration(final SpacecraftState initialState,
final AbsoluteDate tEnd)
throws OrekitException {
// do nothing by default
}
/** Method called just after integration.
* <p>
* The default implementation does nothing, it may be specialized in subclasses.
* </p>
* @exception OrekitException if hook cannot be run
*/
protected void afterIntegration()
throws OrekitException {
// do nothing by default
}
/** Get state vector dimension without additional parameters.
* @return state vector dimension without additional parameters.
*/
public int getBasicDimension() {
return 7;
}
/** Get the integrator used by the propagator.
* @return the integrator.
*/
protected AbstractIntegrator getIntegrator() {
return integrator;
}
/** Get a complete state with all additional equations.
* @param t current value of the independent <I>time</I> variable
* @param y array containing the current value of the state vector
* @return complete state
* @exception OrekitException if state cannot be mapped
*/
private SpacecraftState getCompleteState(final double t, final double[] y)
throws OrekitException {
// main state
SpacecraftState state = stateMapper.mapArrayToState(t, y, true); //not sure of the mean orbit, should be true
// pre-integrated additional states
state = updateAdditionalStates(state);
// additional states integrated here
if (!additionalEquations.isEmpty()) {
final EquationsMapper[] em = mathODE.getSecondaryMappers();
for (int i = 0; i < additionalEquations.size(); ++i) {
final double[] secondary = new double[em[i].getDimension()];
System.arraycopy(y, em[i].getFirstIndex(), secondary, 0, secondary.length);
state = state.addAdditionalState(additionalEquations.get(i).getName(), secondary);
}
}
return state;
}
/** Differential equations for the main state (orbit, attitude and mass). */
public interface MainStateEquations {
/** Compute differential equations for main state.
* @param state current state
* @return derivatives of main state
* @throws OrekitException if differentials cannot be computed
*/
double[] computeDerivatives(final SpacecraftState state) throws OrekitException;
}
/** Differential equations for the main state (orbit, attitude and mass), with converted API. */
private class ConvertedMainStateEquations implements FirstOrderDifferentialEquations {
/** Main state equations. */
private final MainStateEquations main;
/** Simple constructor.
* @param main main state equations
*/
public ConvertedMainStateEquations(final MainStateEquations main) {
this.main = main;
calls = 0;
}
/** {@inheritDoc} */
public int getDimension() {
return getBasicDimension();
}
/** {@inheritDoc} */
public void computeDerivatives(final double t, final double[] y, final double[] yDot)
throws OrekitExceptionWrapper {
try {
// update space dynamics view
// use only ODE elements
SpacecraftState currentState = stateMapper.mapArrayToState(t, y, true);
currentState = updateAdditionalStates(currentState);
// compute main state differentials
final double[] mainDot = main.computeDerivatives(currentState);
System.arraycopy(mainDot, 0, yDot, 0, mainDot.length);
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
// increment calls counter
++calls;
}
}
/** Differential equations for the secondary state (Jacobians, user variables ...), with converted API. */
private class ConvertedSecondaryStateEquations implements SecondaryEquations {
/** Additional equations. */
private final AdditionalEquations equations;
/** Dimension of the additional state. */
private final int dimension;
/** Simple constructor.
* @param equations additional equations
* @param dimension dimension of the additional state
*/
public ConvertedSecondaryStateEquations(final AdditionalEquations equations,
final int dimension) {
this.equations = equations;
this.dimension = dimension;
}
/** {@inheritDoc} */
public int getDimension() {
return dimension;
}
/** {@inheritDoc} */
public void computeDerivatives(final double t, final double[] primary,
final double[] primaryDot, final double[] secondary,
final double[] secondaryDot)
throws OrekitExceptionWrapper {
try {
// update space dynamics view
// the state contains only the ODE elements
SpacecraftState currentState = stateMapper.mapArrayToState(t, primary, true);
currentState = updateAdditionalStates(currentState);
currentState = currentState.addAdditionalState(equations.getName(), secondary);
// compute additional derivatives
final double[] additionalMainDot =
equations.computeDerivatives(currentState, secondaryDot);
if (additionalMainDot != null) {
// the additional equations have an effect on main equations
for (int i = 0; i < additionalMainDot.length; ++i) {
primaryDot[i] += additionalMainDot[i];
}
}
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
}
/** Adapt an {@link org.orekit.propagation.events.EventDetector}
* to commons-math {@link org.apache.commons.math3.ode.events.EventHandler} interface.
* @param <T> class type for the generic version
* @author Fabien Maussion
*/
private class AdaptedEventDetector
implements org.apache.commons.math3.ode.events.EventHandler {
/** Underlying event detector. */
private final EventDetector detector;
/** Time of the previous call to g. */
private double lastT;
/** Value from the previous call to g. */
private double lastG;
/** Build a wrapped event detector.
* @param detector event detector to wrap
*/
public AdaptedEventDetector(final EventDetector detector) {
this.detector = detector;
this.lastT = Double.NaN;
this.lastG = Double.NaN;
}
/** {@inheritDoc} */
public void init(final double t0, final double[] y0, final double t) {
try {
detector.init(getCompleteState(t0, y0), stateMapper.mapDoubleToDate(t));
this.lastT = Double.NaN;
this.lastG = Double.NaN;
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
/** {@inheritDoc} */
public double g(final double t, final double[] y) {
try {
if (!Precision.equals(lastT, t, 1)) {
lastT = t;
lastG = detector.g(getCompleteState(t, y));
}
return lastG;
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
/** {@inheritDoc} */
public Action eventOccurred(final double t, final double[] y, final boolean increasing) {
try {
final EventHandler.Action whatNext = detector.eventOccurred(getCompleteState(t, y), increasing);
switch (whatNext) {
case STOP :
return Action.STOP;
case RESET_STATE :
return Action.RESET_STATE;
case RESET_DERIVATIVES :
return Action.RESET_DERIVATIVES;
default :
return Action.CONTINUE;
}
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
/** {@inheritDoc} */
public void resetState(final double t, final double[] y) {
try {
final SpacecraftState newState = detector.resetState(getCompleteState(t, y));
// main part
stateMapper.mapStateToArray(newState, y);
// secondary part
final EquationsMapper[] em = mathODE.getSecondaryMappers();
for (int i = 0; i < additionalEquations.size(); ++i) {
final double[] secondary =
newState.getAdditionalState(additionalEquations.get(i).getName());
System.arraycopy(secondary, 0, y, em[i].getFirstIndex(), secondary.length);
}
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
}
/** Adapt an {@link org.orekit.propagation.sampling.OrekitStepHandler}
* to commons-math {@link StepHandler} interface.
* @author Luc Maisonobe
*/
private class AdaptedStepHandler
implements OrekitStepInterpolator, StepHandler, ModeHandler {
/** Underlying handler. */
private final OrekitStepHandler handler;
/** Flag for handler . */
private boolean activate;
/** Build an instance.
* @param handler underlying handler to wrap
*/
public AdaptedStepHandler(final OrekitStepHandler handler) {
this.handler = handler;
}
/** {@inheritDoc} */
public void initialize(final boolean activateHandlers) {
this.activate = activateHandlers;
}
/** {@inheritDoc} */
public void init(final double t0, final double[] y0, final double t) {
try {
handler.init(getCompleteState(t0, y0), stateMapper.mapDoubleToDate(t));
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
/** {@inheritDoc} */
public void handleStep(final StepInterpolator interpolator, final boolean isLast) {
try {
mathInterpolator = interpolator;
if (activate) {
handler.handleStep(this, isLast);
}
} catch (PropagationException pe) {
throw new OrekitExceptionWrapper(pe);
}
}
/** Get the current grid date.
* @return current grid date
*/
public AbsoluteDate getCurrentDate() {
return stateMapper.mapDoubleToDate(mathInterpolator.getCurrentTime());
}
/** Get the previous grid date.
* @return previous grid date
*/
public AbsoluteDate getPreviousDate() {
return stateMapper.mapDoubleToDate(mathInterpolator.getPreviousTime());
}
/** Get the interpolated date.
* <p>If {@link #setInterpolatedDate(AbsoluteDate) setInterpolatedDate}
* has not been called, the date returned is the same as {@link
* #getCurrentDate() getCurrentDate}.</p>
* @return interpolated date
* @see #setInterpolatedDate(AbsoluteDate)
* @see #getInterpolatedState()
*/
public AbsoluteDate getInterpolatedDate() {
return stateMapper.mapDoubleToDate(mathInterpolator.getInterpolatedTime());
}
/** Set the interpolated date.
* <p>It is possible to set the interpolation date outside of the current
* step range, but accuracy will decrease as date is farther.</p>
* @param date interpolated date to set
* @see #getInterpolatedDate()
* @see #getInterpolatedState()
*/
public void setInterpolatedDate(final AbsoluteDate date) {
mathInterpolator.setInterpolatedTime(stateMapper.mapDateToDouble(date));
}
/** Get the interpolated state.
* @return interpolated state at the current interpolation date
* @exception OrekitException if state cannot be interpolated or converted
* @see #getInterpolatedDate()
* @see #setInterpolatedDate(AbsoluteDate)
*/
public SpacecraftState getInterpolatedState() throws OrekitException {
try {
SpacecraftState s =
stateMapper.mapArrayToState(mathInterpolator.getInterpolatedTime(),
mathInterpolator.getInterpolatedState(),
meanOrbit);
s = updateAdditionalStates(s);
for (int i = 0; i < additionalEquations.size(); ++i) {
final double[] secondary = mathInterpolator.getInterpolatedSecondaryState(i);
s = s.addAdditionalState(additionalEquations.get(i).getName(), secondary);
}
return s;
} catch (OrekitExceptionWrapper oew) {
throw oew.getException();
}
}
/** Check is integration direction is forward in date.
* @return true if integration is forward in date
*/
public boolean isForward() {
return mathInterpolator.isForward();
}
}
private class EphemerisModeHandler implements ModeHandler, StepHandler {
/** Underlying raw mathematical model. */
private ContinuousOutputModel model;
/** Generated ephemeris. */
private BoundedPropagator ephemeris;
/** Flag for handler . */
private boolean activate;
/** Creates a new instance of EphemerisModeHandler which must be
* filled by the propagator.
*/
public EphemerisModeHandler() {
}
/** {@inheritDoc} */
public void initialize(final boolean activateHandlers) {
this.activate = activateHandlers;
this.model = new ContinuousOutputModel();
// ephemeris will be generated when last step is processed
this.ephemeris = null;
}
/** Get the generated ephemeris.
* @return a new instance of the generated ephemeris
*/
public BoundedPropagator getEphemeris() {
return ephemeris;
}
/** {@inheritDoc} */
public void handleStep(final StepInterpolator interpolator, final boolean isLast)
throws OrekitExceptionWrapper {
try {
if (activate) {
model.handleStep(interpolator, isLast);
if (isLast) {
// set up the boundary dates
final double tI = model.getInitialTime();
final double tF = model.getFinalTime();
final AbsoluteDate startDate = stateMapper.mapDoubleToDate(tI);
final AbsoluteDate minDate;
final AbsoluteDate maxDate;
if (tF < tI) {
minDate = stateMapper.mapDoubleToDate(tF);
maxDate = startDate;
} else {
minDate = startDate;
maxDate = stateMapper.mapDoubleToDate(tF);
}
// get the initial additional states that are not managed
final Map<String, double[]> unmanaged = new HashMap<String, double[]>();
for (final Map.Entry<String, double[]> initial : getInitialState().getAdditionalStates().entrySet()) {
if (!isAdditionalStateManaged(initial.getKey())) {
// this additional state was in the initial state, but is unknown to the propagator
// we simply copy its initial value as is
unmanaged.put(initial.getKey(), initial.getValue());
}
}
// get the names of additional states managed by differential equations
final String[] names = new String[additionalEquations.size()];
for (int i = 0; i < names.length; ++i) {
names[i] = additionalEquations.get(i).getName();
}
// create the ephemeris
ephemeris = new IntegratedEphemeris(startDate, minDate, maxDate,
stateMapper, meanOrbit, model, unmanaged,
getAdditionalStateProviders(), names);
}
}
} catch (OrekitException oe) {
throw new OrekitExceptionWrapper(oe);
}
}
/** {@inheritDoc} */
public void init(final double t0, final double[] y0, final double t) {
model.init(t0, y0, t);
}
}
}