ImpulseManeuver.java
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package org.orekit.forces.maneuvers;
import org.hipparchus.geometry.euclidean.threed.Rotation;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.ode.events.Action;
import org.hipparchus.util.FastMath;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.orbits.CartesianOrbit;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.AbstractDetector;
import org.orekit.propagation.events.AdaptableInterval;
import org.orekit.propagation.events.EventDetector;
import org.orekit.propagation.events.handlers.EventHandler;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.Constants;
import org.orekit.utils.DoubleArrayDictionary;
import org.orekit.utils.PVCoordinates;
/** Impulse maneuver model.
* <p>This class implements an impulse maneuver as a discrete event
* that can be provided to any {@link org.orekit.propagation.Propagator
* Propagator}.</p>
* <p>The maneuver is triggered when an underlying event generates a
* {@link Action#STOP STOP} event, in which case this class will generate a {@link
* Action#RESET_STATE RESET_STATE}
* event (the stop event from the underlying object is therefore filtered out).
* In the simple cases, the underlying event detector may be a basic
* {@link org.orekit.propagation.events.DateDetector date event}, but it
* can also be a more elaborate {@link
* org.orekit.propagation.events.ApsideDetector apside event} for apogee
* maneuvers for example.</p>
* <p>The maneuver is defined by a single velocity increment.
* If no AttitudeProvider is given, the current attitude of the spacecraft,
* defined by the current spacecraft state, will be used as the
* {@link AttitudeProvider} so the velocity increment should be given in
* the same pseudoinertial frame as the {@link SpacecraftState} used to
* construct the propagator that will handle the maneuver.
* If an AttitudeProvider is given, the velocity increment given should be
* defined appropriately in consideration of that provider. So, a typical
* case for tangential maneuvers is to provide a {@link org.orekit.attitudes.LofOffset LOF aligned}
* attitude provider along with a velocity increment defined in accordance with
* that LOF aligned attitude provider; e.g. if the LOF aligned attitude provider
* was constructed using LOFType.VNC the velocity increment should be
* provided in VNC coordinates.</p>
* <p>The norm through which the delta-V maps to the mass consumption is chosen via the
* enum {@link Control3DVectorCostType}. Default is Euclidean. </p>
* <p>Beware that the triggering event detector must behave properly both
* before and after maneuver. If for example a node detector is used to trigger
* an inclination maneuver and the maneuver change the orbit to an equatorial one,
* the node detector will fail just after the maneuver, being unable to find a
* node on an equatorial orbit! This is a real case that has been encountered
* during validation ...</p>
* @see org.orekit.propagation.Propagator#addEventDetector(EventDetector)
* @author Luc Maisonobe
*/
public class ImpulseManeuver extends AbstractDetector<ImpulseManeuver> {
/** The attitude to override during the maneuver, if set. */
private final AttitudeProvider attitudeOverride;
/** Triggering event. */
private final EventDetector trigger;
/** Velocity increment in satellite frame. */
private final Vector3D deltaVSat;
/** Specific impulse. */
private final double isp;
/** Engine exhaust velocity. */
private final double vExhaust;
/** Indicator for forward propagation. */
private boolean forward;
/** Type of norm linking delta-V to mass consumption. */
private final Control3DVectorCostType control3DVectorCostType;
/** Build a new instance.
* @param trigger triggering event
* @param deltaVSat velocity increment in satellite frame
* @param isp engine specific impulse (s)
*/
public ImpulseManeuver(final EventDetector trigger, final Vector3D deltaVSat, final double isp) {
this(trigger, null, deltaVSat, isp);
}
/** Build a new instance.
* @param trigger triggering event
* @param attitudeOverride the attitude provider to use for the maneuver
* @param deltaVSat velocity increment in satellite frame
* @param isp engine specific impulse (s)
*/
public ImpulseManeuver(final EventDetector trigger, final AttitudeProvider attitudeOverride,
final Vector3D deltaVSat, final double isp) {
this(trigger.getMaxCheckInterval(), trigger.getThreshold(),
trigger.getMaxIterationCount(), new Handler(),
trigger, attitudeOverride, deltaVSat, isp, Control3DVectorCostType.TWO_NORM);
}
/** Build a new instance.
* @param trigger triggering event
* @param attitudeOverride the attitude provider to use for the maneuver
* @param deltaVSat velocity increment in satellite frame
* @param isp engine specific impulse (s)
* @param control3DVectorCostType increment's norm for mass consumption
*/
public ImpulseManeuver(final EventDetector trigger, final AttitudeProvider attitudeOverride,
final Vector3D deltaVSat, final double isp, final Control3DVectorCostType control3DVectorCostType) {
this(trigger.getMaxCheckInterval(), trigger.getThreshold(),
trigger.getMaxIterationCount(), new Handler(),
trigger, attitudeOverride, deltaVSat, isp, control3DVectorCostType);
}
/** Protected constructor with full parameters.
* <p>
* This constructor is not public as users are expected to use the builder
* API with the various {@code withXxx()} methods to set up the instance
* in a readable manner without using a huge amount of parameters.
* </p>
* @param maxCheck maximum checking interval
* @param threshold convergence threshold (s)
* @param maxIter maximum number of iterations in the event time search
* @param handler event handler to call at event occurrences
* @param trigger triggering event
* @param attitudeOverride the attitude provider to use for the maneuver
* @param deltaVSat velocity increment in satellite frame
* @param isp engine specific impulse (s)
* @param control3DVectorCostType increment's norm for mass consumption
* @since 6.1
*/
protected ImpulseManeuver(final AdaptableInterval maxCheck, final double threshold,
final int maxIter, final EventHandler handler,
final EventDetector trigger, final AttitudeProvider attitudeOverride, final Vector3D deltaVSat,
final double isp, final Control3DVectorCostType control3DVectorCostType) {
super(maxCheck, threshold, maxIter, handler);
this.attitudeOverride = attitudeOverride;
this.trigger = trigger;
this.deltaVSat = deltaVSat;
this.isp = isp;
this.vExhaust = Constants.G0_STANDARD_GRAVITY * isp;
this.control3DVectorCostType = control3DVectorCostType;
}
/** {@inheritDoc} */
@Override
protected ImpulseManeuver create(final AdaptableInterval newMaxCheck, final double newThreshold,
final int newMaxIter, final EventHandler newHandler) {
return new ImpulseManeuver(newMaxCheck, newThreshold, newMaxIter, newHandler,
trigger, attitudeOverride, deltaVSat, isp, control3DVectorCostType);
}
/** {@inheritDoc} */
public void init(final SpacecraftState s0, final AbsoluteDate t) {
forward = t.durationFrom(s0.getDate()) >= 0;
// Initialize the triggering event
trigger.init(s0, t);
}
/** {@inheritDoc} */
public double g(final SpacecraftState s) {
return trigger.g(s);
}
/**
* Get the Attitude Provider to use during maneuver.
* @return the attitude provider
*/
public AttitudeProvider getAttitudeOverride() {
return attitudeOverride;
}
/** Get the triggering event.
* @return triggering event
*/
public EventDetector getTrigger() {
return trigger;
}
/** Get the velocity increment in satellite frame.
* @return velocity increment in satellite frame
*/
public Vector3D getDeltaVSat() {
return deltaVSat;
}
/** Get the specific impulse.
* @return specific impulse
*/
public double getIsp() {
return isp;
}
/** Get the control vector's cost type.
* @return control cost type
* @since 12.0
*/
public Control3DVectorCostType getControl3DVectorCostType() {
return control3DVectorCostType;
}
/** Local handler. */
private static class Handler implements EventHandler {
/** {@inheritDoc} */
public Action eventOccurred(final SpacecraftState s, final EventDetector detector,
final boolean increasing) {
// filter underlying event
final ImpulseManeuver im = (ImpulseManeuver) detector;
final Action underlyingAction = im.trigger.getHandler().eventOccurred(s, im.trigger, increasing);
return (underlyingAction == Action.STOP) ? Action.RESET_STATE : Action.CONTINUE;
}
/** {@inheritDoc} */
@Override
public SpacecraftState resetState(final EventDetector detector, final SpacecraftState oldState) {
final ImpulseManeuver im = (ImpulseManeuver) detector;
final AbsoluteDate date = oldState.getDate();
final AttitudeProvider override = im.getAttitudeOverride();
final Rotation rotation;
if (override == null) {
rotation = oldState.getAttitude().getRotation();
} else {
rotation = override.getAttitudeRotation(oldState.getOrbit(), date, oldState.getFrame());
}
// convert velocity increment in inertial frame
final Vector3D deltaV = rotation.applyInverseTo(im.deltaVSat);
final double sign = im.forward ? +1 : -1;
// apply increment to position/velocity
final PVCoordinates oldPV = oldState.getPVCoordinates();
final PVCoordinates newPV =
new PVCoordinates(oldPV.getPosition(),
new Vector3D(1, oldPV.getVelocity(), sign, deltaV));
final CartesianOrbit newOrbit =
new CartesianOrbit(newPV, oldState.getFrame(), date, oldState.getMu());
// compute new mass
final double normDeltaV = im.control3DVectorCostType.evaluate(im.deltaVSat);
final double newMass = oldState.getMass() * FastMath.exp(-sign * normDeltaV / im.vExhaust);
// pack everything in a new state
SpacecraftState newState = new SpacecraftState(oldState.getOrbit().getType().normalize(newOrbit, oldState.getOrbit()),
oldState.getAttitude(), newMass);
for (final DoubleArrayDictionary.Entry entry : oldState.getAdditionalStatesValues().getData()) {
newState = newState.addAdditionalState(entry.getKey(), entry.getValue());
}
for (final DoubleArrayDictionary.Entry entry : oldState.getAdditionalStatesDerivatives().getData()) {
newState = newState.addAdditionalStateDerivative(entry.getKey(), entry.getValue());
}
return newState;
}
}
}