DSSTForceModel.java
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* this work for additional information regarding copyright ownership.
* CS licenses this file to You under the Apache License, Version 2.0
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* Unless required by applicable law or agreed to in writing, software
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package org.orekit.propagation.semianalytical.dsst.forces;
import org.hipparchus.CalculusFieldElement;
import org.hipparchus.Field;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.PropagationType;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
import org.orekit.propagation.events.EventDetectorsProvider;
import org.orekit.propagation.events.FieldEventDetector;
import org.orekit.propagation.AbstractGradientConverter;
import org.orekit.propagation.semianalytical.dsst.utilities.AuxiliaryElements;
import org.orekit.propagation.semianalytical.dsst.utilities.FieldAuxiliaryElements;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.FieldAbsoluteDate;
import org.orekit.utils.drivers.ParameterDriversProvider;
import java.util.List;
import java.util.stream.Stream;
/** This interface represents a force modifying spacecraft motion for a {@link
* org.orekit.propagation.semianalytical.dsst.DSSTPropagator DSSTPropagator}.
* <p>
* Objects implementing this interface are intended to be added to a {@link
* org.orekit.propagation.semianalytical.dsst.DSSTPropagator DSST propagator}
* before the propagation is started.
* </p>
* <p>
* The propagator will call at the very beginning of a propagation the {@link
* #initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[])} method allowing
* preliminary computation such as truncation if needed.
* </p>
* <p>
* Then the propagator will call at each step:
* <ol>
* <li>the {@link #getMeanElementRate(SpacecraftState, AuxiliaryElements, double[])} method.
* The force model instance will extract all the state data needed to compute
* the mean element rates that contribute to the mean state derivative.</li>
* <li>the {@link #updateShortPeriodTerms(double[], SpacecraftState...)} method,
* if osculating parameters are desired, on a sample of points within the
* last step.</li>
* </ol>
*
* @author Romain Di Constanzo
* @author Pascal Parraud
*/
public interface DSSTForceModel extends ParameterDriversProvider, EventDetectorsProvider {
/**
* Initialize the force model at the start of propagation.
* <p> The default implementation of this method does nothing.</p>
*
* @param initialState spacecraft state at the start of propagation.
* @param target date of propagation. Not equal to {@code initialState.getDate()}.
* @since 11.0
*/
default void init(final SpacecraftState initialState, final AbsoluteDate target) {
}
/**
* Initialize the force model at the start of propagation.
* <p> The default implementation of this method does nothing.</p>
*
* @param initialState spacecraft state at the start of propagation.
* @param target date of propagation. Not equal to {@code initialState.getDate()}.
* @param <T> type of the elements
* @since 11.1
*/
default <T extends CalculusFieldElement<T>> void init(final FieldSpacecraftState<T> initialState, final FieldAbsoluteDate<T> target) {
init(initialState.toSpacecraftState(), target.toAbsoluteDate());
}
/** {@inheritDoc}.*/
@Override
default Stream<EventDetector> getEventDetectors() {
return getEventDetectors(getParametersDrivers());
}
/** {@inheritDoc}.*/
@Override
default <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventDetectors(final Field<T> field) {
return getFieldEventDetectors(field, getParametersDrivers());
}
/** Performs initialization prior to propagation for the current force model.
* <p>
* This method aims at being called at the very beginning of a propagation.
* </p>
* @param auxiliaryElements auxiliary elements related to the current orbit
* @param type type of the elements used during the propagation
* @param parameters values of the force model parameters for specific date
* (1 value only per parameter driver) obtained for example by calling
* {@link #getParameters()} on force model.
* @return a list of objects that will hold short period terms (the objects
* are also retained by the force model, which will update them during propagation)
*/
List<ShortPeriodTerms> initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type, double[] parameters);
/** Performs initialization prior to propagation for the current force model.
* <p>
* This method aims at being called at the very beginning of a propagation.
* </p>
* @param <T> type of the elements
* @param auxiliaryElements auxiliary elements related to the current orbit
* @param type type of the elements used during the propagation
* @param parameters values of the force model parameters for specific date
* (1 value only per parameter driver) obtained for example by calling
* {@link #getParameters()} on force model or
* {@link AbstractGradientConverter#getParametersAtStateDate(FieldSpacecraftState, ParameterDriversProvider)}
* on gradient converter.
* @return a list of objects that will hold short period terms (the objects
* are also retained by the force model, which will update them during propagation)
*/
<T extends CalculusFieldElement<T>> List<FieldShortPeriodTerms<T>> initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type, T[] parameters);
/** Computes the mean equinoctial elements rates da<sub>i</sub> / dt.
*
* @param state current state information: date, kinematics, attitude
* @param auxiliaryElements auxiliary elements related to the current orbit
* @param parameters values of the force model parameters at state date (only 1 span for
* each parameter driver) obtained for example by calling {@link #getParameters()}
* on force model.
* @return the mean element rates dai/dt
*/
double[] getMeanElementRate(SpacecraftState state,
AuxiliaryElements auxiliaryElements, double[] parameters);
/** Computes the mean equinoctial elements rates da<sub>i</sub> / dt.
*
* @param <T> type of the elements
* @param state current state information: date, kinematics, attitude
* @param auxiliaryElements auxiliary elements related to the current orbit
* @param parameters values of the force model parameters at state date (only 1 span for
* each parameter driver) obtained for example by calling {@link #getParameters(Field)}
* on force model or
* {@link AbstractGradientConverter#getParametersAtStateDate(FieldSpacecraftState, ParameterDriversProvider)}
* on gradient converter.
* @return the mean element rates dai/dt
*/
<T extends CalculusFieldElement<T>> T[] getMeanElementRate(FieldSpacecraftState<T> state,
FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters);
/** Register an attitude provider.
* <p>
* Register an attitude provider that can be used by the force model.
* </p>
* @param provider the {@link AttitudeProvider}
*/
void registerAttitudeProvider(AttitudeProvider provider);
/** Update the short period terms.
* <p>
* The {@link ShortPeriodTerms short period terms} that will be updated
* are the ones that were returned during the call to {@link
* #initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[])}.
* </p>
* @param parameters values of the force model parameters (all span values for each parameters)
* obtained for example by calling {@link #getParameters()} on force model.
* @param meanStates mean states information: date, kinematics, attitude
*/
void updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates);
/** Update the short period terms.
* <p>
* The {@link ShortPeriodTerms short period terms} that will be updated
* are the ones that were returned during the call to {@link
* #initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[])}.
* </p>
* @param <T> type of the elements
* @param parameters values of the force model parameters (all span values for each parameters)
* obtained for example by calling {@link #getParameters(Field)} on force model or
* {@link AbstractGradientConverter#getParameters(FieldSpacecraftState, ParameterDriversProvider)}
* on gradient converter.
* @param meanStates mean states information: date, kinematics, attitude
*/
@SuppressWarnings("unchecked")
<T extends CalculusFieldElement<T>> void updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates);
}