/* Copyright 2002-2024 CS GROUP
    * Licensed to CS GROUP (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;
  
  
  import org.hipparchus.CalculusFieldElement;
  import org.hipparchus.Field;
  import org.hipparchus.exception.LocalizedCoreFormats;
  import org.hipparchus.exception.MathIllegalArgumentException;
  import org.hipparchus.exception.MathIllegalStateException;
  import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
  import org.hipparchus.util.FastMath;
  import org.orekit.attitudes.FieldAttitude;
  import org.orekit.errors.OrekitException;
  import org.orekit.errors.OrekitIllegalArgumentException;
  import org.orekit.errors.OrekitIllegalStateException;
  import org.orekit.errors.OrekitMessages;
  import org.orekit.frames.FieldStaticTransform;
  import org.orekit.frames.FieldTransform;
  import org.orekit.frames.Frame;
  import org.orekit.orbits.FieldOrbit;
  import org.orekit.orbits.Orbit;
  import org.orekit.time.FieldAbsoluteDate;
  import org.orekit.time.FieldTimeShiftable;
  import org.orekit.time.FieldTimeStamped;
  import org.orekit.utils.DoubleArrayDictionary;
  import org.orekit.utils.FieldArrayDictionary;
  import org.orekit.utils.FieldAbsolutePVCoordinates;
  import org.orekit.utils.FieldPVCoordinates;
  import org.orekit.utils.TimeStampedFieldPVCoordinates;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  /** This class is the representation of a complete state holding orbit, attitude
   * and mass information at a given date, meant primarily for propagation.
   *
   * <p>It contains an {@link FieldOrbit}, or a {@link FieldAbsolutePVCoordinates} if there
   * is no definite central body, plus the current mass and attitude at the intrinsic
   * {@link FieldAbsoluteDate}. Quantities are guaranteed to be consistent in terms
   * of date and reference frame. The spacecraft state may also contain additional
   * states, which are simply named double arrays which can hold any user-defined
   * data.
   * </p>
   * <p>
   * The state can be slightly shifted to close dates. This actual shift varies
   * between {@link FieldOrbit} and {@link FieldAbsolutePVCoordinates}.
   * For attitude it is a linear extrapolation taking the spin rate into account
   * and no mass change. It is <em>not</em> intended as a replacement for proper
   * orbit and attitude propagation but should be sufficient for either small
   * time shifts or coarse accuracy.
   * </p>
   * <p>
   * The instance {@code FieldSpacecraftState} is guaranteed to be immutable.
   * </p>
   * @see org.orekit.propagation.numerical.NumericalPropagator
   * @see SpacecraftState
   * @author Fabien Maussion
   * @author V&eacute;ronique Pommier-Maurussane
   * @author Luc Maisonobe
   * @author Vincent Mouraux
   * @param <T> type of the field elements
   */
  public class FieldSpacecraftState <T extends CalculusFieldElement<T>>
      implements FieldTimeStamped<T>, FieldTimeShiftable<FieldSpacecraftState<T>, T> {
  
      /** Default mass. */
      private static final double DEFAULT_MASS = 1000.0;
  
      /**
       * tolerance on date comparison in {@link #checkConsistency(FieldOrbit, FieldAttitude)}. 100 ns
       * corresponds to sub-mm accuracy at LEO orbital velocities.
       */
      private static final double DATE_INCONSISTENCY_THRESHOLD = 100e-9;
  
      /** Orbital state. */
      private final FieldOrbit<T> orbit;
  
      /** Trajectory state, when it is not an orbit. */
      private final FieldAbsolutePVCoordinates<T> absPva;
  
      /** FieldAttitude<T>. */
      private final FieldAttitude<T> attitude;
  
      /** Current mass (kg). */
      private final T mass;
  
     /** Additional states. */
     private final FieldArrayDictionary<T> additional;
 
     /** Additional states derivatives.
      * @since 11.1
      */
     private final FieldArrayDictionary<T> additionalDot;
 
     /** Build a spacecraft state from orbit only.
      * <p>FieldAttitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param orbit the orbit
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit) {
         this(orbit, SpacecraftState.getDefaultAttitudeProvider(orbit.getFrame())
                         .getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              orbit.getA().getField().getZero().newInstance(DEFAULT_MASS), (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit and attitude.
      * <p>Mass is set to an unspecified non-null arbitrary value.</p>
      * @param orbit the orbit
      * @param attitude attitude
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldAttitude<T> attitude)
         throws IllegalArgumentException {
         this(orbit, attitude, orbit.getA().getField().getZero().newInstance(DEFAULT_MASS), (FieldArrayDictionary<T>) null);
     }
 
     /** Create a new instance from orbit and mass.
      * <p>FieldAttitude law is set to an unspecified default attitude.</p>
      * @param orbit the orbit
      * @param mass the mass (kg)
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final T mass) {
         this(orbit, SpacecraftState.getDefaultAttitudeProvider(orbit.getFrame())
                         .getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              mass, (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit, attitude and mass.
      * @param orbit the orbit
      * @param attitude attitude
      * @param mass the mass (kg)
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldAttitude<T> attitude, final T mass)
         throws IllegalArgumentException {
         this(orbit, attitude, mass, (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit and additional states.
      * <p>FieldAttitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param orbit the orbit
      * @param additional additional states
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldArrayDictionary<T> additional) {
         this(orbit, SpacecraftState.getDefaultAttitudeProvider(orbit.getFrame())
                         .getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              orbit.getA().getField().getZero().newInstance(DEFAULT_MASS), additional);
     }
 
     /** Build a spacecraft state from orbit attitude and additional states.
      * <p>Mass is set to an unspecified non-null arbitrary value.</p>
      * @param orbit the orbit
      * @param attitude attitude
      * @param additional additional states
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldAttitude<T> attitude, final FieldArrayDictionary<T> additional)
         throws IllegalArgumentException {
         this(orbit, attitude, orbit.getA().getField().getZero().newInstance(DEFAULT_MASS), additional);
     }
 
     /** Create a new instance from orbit, mass and additional states.
      * <p>FieldAttitude law is set to an unspecified default attitude.</p>
      * @param orbit the orbit
      * @param mass the mass (kg)
      * @param additional additional states
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final T mass, final FieldArrayDictionary<T> additional) {
         this(orbit, SpacecraftState.getDefaultAttitudeProvider(orbit.getFrame())
                         .getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              mass, additional);
     }
 
     /** Build a spacecraft state from orbit, attitude, mass and additional states.
      * @param orbit the orbit
      * @param attitude attitude
      * @param mass the mass (kg)
      * @param additional additional states (may be null if no additional states are available)
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldAttitude<T> attitude,
                                 final T mass, final FieldArrayDictionary<T> additional) {
         this(orbit, attitude, mass, additional, null);
     }
 
     /** Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
      * @param orbit the orbit
      * @param attitude attitude
      * @param mass the mass (kg)
      * @param additional additional states (may be null if no additional states are available)
      * @param additionalDot additional states derivatives(may be null if no additional states derivative sare available)
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldOrbit<T> orbit, final FieldAttitude<T> attitude, final T mass,
                                 final FieldArrayDictionary<T> additional,
                                 final FieldArrayDictionary<T> additionalDot)
         throws IllegalArgumentException {
         checkConsistency(orbit, attitude);
         this.orbit      = orbit;
         this.attitude   = attitude;
         this.mass       = mass;
         this.absPva     = null;
 
         if (additional == null) {
             this.additional = new FieldArrayDictionary<>(orbit.getDate().getField());
         } else {
             this.additional = new FieldArrayDictionary<>(additional);
         }
 
         if (additionalDot == null) {
             this.additionalDot = new FieldArrayDictionary<>(orbit.getDate().getField());
         } else {
 
             this.additionalDot = new FieldArrayDictionary<>(additionalDot);
         }
 
     }
 
     /** Convert a {@link FieldSpacecraftState}.
      * @param field field to which the elements belong
      * @param state state to convert
      */
     public FieldSpacecraftState(final Field<T> field, final SpacecraftState state) {
 
         if (state.isOrbitDefined()) {
 
             final Orbit nonFieldOrbit = state.getOrbit();
             this.orbit    = nonFieldOrbit.getType().convertToFieldOrbit(field, nonFieldOrbit);
             this.absPva   = null;
 
         } else {
             final TimeStampedPVCoordinates tspva = state.getPVCoordinates();
             final FieldVector3D<T> position = new FieldVector3D<>(field, tspva.getPosition());
             final FieldVector3D<T> velocity = new FieldVector3D<>(field, tspva.getVelocity());
             final FieldVector3D<T> acceleration = new FieldVector3D<>(field, tspva.getAcceleration());
             final FieldPVCoordinates<T> pva = new FieldPVCoordinates<>(position, velocity, acceleration);
             final FieldAbsoluteDate<T> dateF = new FieldAbsoluteDate<>(field, state.getDate());
             this.orbit  = null;
             this.absPva = new FieldAbsolutePVCoordinates<>(state.getFrame(), dateF, pva);
         }
 
         this.attitude = new FieldAttitude<>(field, state.getAttitude());
         this.mass     = field.getZero().newInstance(state.getMass());
 
         final DoubleArrayDictionary additionalD = state.getAdditionalStatesValues();
         if (additionalD.size() == 0) {
             this.additional = new FieldArrayDictionary<>(field);
         } else {
             this.additional = new FieldArrayDictionary<>(field, additionalD.size());
             for (final DoubleArrayDictionary.Entry entry : additionalD.getData()) {
                 this.additional.put(entry.getKey(), entry.getValue());
             }
         }
         final DoubleArrayDictionary additionalDotD = state.getAdditionalStatesDerivatives();
         if (additionalDotD.size() == 0) {
             this.additionalDot = new FieldArrayDictionary<>(field);
         } else {
             this.additionalDot = new FieldArrayDictionary<>(field, additionalDotD.size());
             for (final DoubleArrayDictionary.Entry entry : additionalDotD.getData()) {
                 this.additionalDot.put(entry.getKey(), entry.getValue());
             }
         }
 
     }
 
     /** Build a spacecraft state from orbit only.
      * <p>Attitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param absPva position-velocity-acceleration
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva) {
         this(absPva,
              SpacecraftState.getDefaultAttitudeProvider(absPva.getFrame()).
                      getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
              absPva.getDate().getField().getZero().newInstance(DEFAULT_MASS), (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit and attitude.
      * <p>Mass is set to an unspecified non-null arbitrary value.</p>
      * @param absPva position-velocity-acceleration
      * @param attitude attitude
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude)
         throws IllegalArgumentException {
         this(absPva, attitude, absPva.getDate().getField().getZero().newInstance(DEFAULT_MASS), (FieldArrayDictionary<T>) null);
     }
 
     /** Create a new instance from orbit and mass.
      * <p>Attitude law is set to an unspecified default attitude.</p>
      * @param absPva position-velocity-acceleration
      * @param mass the mass (kg)
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final T mass) {
         this(absPva, SpacecraftState.getDefaultAttitudeProvider(absPva.getFrame())
                         .getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
              mass, (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit, attitude and mass.
      * @param absPva position-velocity-acceleration
      * @param attitude attitude
      * @param mass the mass (kg)
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude, final T mass)
         throws IllegalArgumentException {
         this(absPva, attitude, mass, (FieldArrayDictionary<T>) null);
     }
 
     /** Build a spacecraft state from orbit only.
      * <p>Attitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param absPva position-velocity-acceleration
      * @param additional additional states
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldArrayDictionary<T> additional) {
         this(absPva, SpacecraftState.getDefaultAttitudeProvider(absPva.getFrame())
                         .getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
              absPva.getDate().getField().getZero().newInstance(DEFAULT_MASS), additional);
     }
 
     /** Build a spacecraft state from orbit and attitude.
      * <p>Mass is set to an unspecified non-null arbitrary value.</p>
      * @param absPva position-velocity-acceleration
      * @param attitude attitude
      * @param additional additional states
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude,
                                 final FieldArrayDictionary<T> additional)
         throws IllegalArgumentException {
         this(absPva, attitude, absPva.getDate().getField().getZero().newInstance(DEFAULT_MASS), additional);
     }
 
     /** Create a new instance from orbit and mass.
      * <p>Attitude law is set to an unspecified default attitude.</p>
      * @param absPva position-velocity-acceleration
      * @param mass the mass (kg)
      * @param additional additional states
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final T mass, final FieldArrayDictionary<T> additional) {
         this(absPva, SpacecraftState.getDefaultAttitudeProvider(absPva.getFrame())
                         .getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
              mass, additional);
     }
 
     /** Build a spacecraft state from orbit, attitude and mass.
      * @param absPva position-velocity-acceleration
      * @param attitude attitude
      * @param mass the mass (kg)
      * @param additional additional states (may be null if no additional states are available)
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude,
                            final T mass, final FieldArrayDictionary<T> additional) {
         this(absPva, attitude, mass, additional, null);
     }
 
     /** Build a spacecraft state from orbit, attitude and mass.
      * @param absPva position-velocity-acceleration
      * @param attitude attitude
      * @param mass the mass (kg)
      * @param additional additional states (may be null if no additional states are available)
      * @param additionalDot additional states derivatives(may be null if no additional states derivatives are available)
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      * @since 11.1
      */
     public FieldSpacecraftState(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude, final T mass,
                                 final FieldArrayDictionary<T> additional, final FieldArrayDictionary<T> additionalDot)
         throws IllegalArgumentException {
         checkConsistency(absPva, attitude);
         this.orbit      = null;
         this.absPva     = absPva;
         this.attitude   = attitude;
         this.mass       = mass;
         if (additional == null) {
             this.additional = new FieldArrayDictionary<>(absPva.getDate().getField());
         } else {
             this.additional = new FieldArrayDictionary<>(additional);
         }
         if (additionalDot == null) {
             this.additionalDot = new FieldArrayDictionary<>(absPva.getDate().getField());
         } else {
             this.additionalDot = new FieldArrayDictionary<>(additionalDot);
         }
     }
 
     /** Add an additional state.
      * <p>
      * {@link FieldSpacecraftState SpacecraftState} instances are immutable,
      * so this method does <em>not</em> change the instance, but rather
      * creates a new instance, which has the same orbit, attitude, mass
      * and additional states as the original instance, except it also
      * has the specified state. If the original instance already had an
      * additional state with the same name, it will be overridden. If it
      * did not have any additional state with that name, the new instance
      * will have one more additional state than the original instance.
      * </p>
      * @param name name of the additional state
      * @param value value of the additional state
      * @return a new instance, with the additional state added
      * @see #hasAdditionalState(String)
      * @see #getAdditionalState(String)
      * @see #getAdditionalStatesValues()
      */
     @SafeVarargs
     public final FieldSpacecraftState<T> addAdditionalState(final String name, final T... value) {
         final FieldArrayDictionary<T> newDict = new FieldArrayDictionary<>(additional);
         newDict.put(name, value.clone());
         if (isOrbitDefined()) {
             return new FieldSpacecraftState<>(orbit, attitude, mass, newDict, additionalDot);
         } else {
             return new FieldSpacecraftState<>(absPva, attitude, mass, newDict, additionalDot);
         }
     }
 
     /** Add an additional state derivative.
     * {@link FieldSpacecraftState FieldSpacecraftState} instances are immutable,
      * so this method does <em>not</em> change the instance, but rather
      * creates a new instance, which has the same components as the original
      * instance, except it also has the specified state derivative. If the
      * original instance already had an additional state derivative with the
      * same name, it will be overridden. If it did not have any additional
      * state derivative with that name, the new instance will have one more
      * additional state derivative than the original instance.
      * @param name name of the additional state derivative
      * @param value value of the additional state derivative
      * @return a new instance, with the additional state derivative added
      * @see #hasAdditionalStateDerivative(String)
      * @see #getAdditionalStateDerivative(String)
      * @see #getAdditionalStatesDerivatives()
      */
     @SafeVarargs
     public final FieldSpacecraftState<T> addAdditionalStateDerivative(final String name, final T... value) {
         final FieldArrayDictionary<T> newDict = new FieldArrayDictionary<>(additionalDot);
         newDict.put(name, value.clone());
         if (isOrbitDefined()) {
             return new FieldSpacecraftState<>(orbit, attitude, mass, additional, newDict);
         } else {
             return new FieldSpacecraftState<>(absPva, attitude, mass, additional, newDict);
         }
     }
 
     /** Check orbit and attitude dates are equal.
      * @param orbitN the orbit
      * @param attitudeN attitude
      * @exception IllegalArgumentException if orbit and attitude dates
      * are not equal
      */
     private void checkConsistency(final FieldOrbit<T> orbitN, final FieldAttitude<T> attitudeN)
         throws IllegalArgumentException {
         if (orbitN.getDate().durationFrom(attitudeN.getDate()).abs().getReal() >
             DATE_INCONSISTENCY_THRESHOLD) {
 
             throw new OrekitIllegalArgumentException(OrekitMessages.ORBIT_AND_ATTITUDE_DATES_MISMATCH,
                                                      orbitN.getDate(), attitudeN.getDate());
         }
 
         if (orbitN.getFrame() != attitudeN.getReferenceFrame()) {
             throw new OrekitIllegalArgumentException(OrekitMessages.FRAMES_MISMATCH,
                                                      orbitN.getFrame().getName(),
                                                      attitudeN.getReferenceFrame().getName());
         }
     }
 
     /** Check if the state contains an orbit part.
      * <p>
      * A state contains either an {@link FieldAbsolutePVCoordinates absolute
      * position-velocity-acceleration} or an {@link FieldOrbit orbit}.
      * </p>
      * @return true if state contains an orbit (in which case {@link #getOrbit()}
      * will not throw an exception), or false if the state contains an
      * absolut position-velocity-acceleration (in which case {@link #getAbsPVA()}
      * will not throw an exception)
      */
     public boolean isOrbitDefined() {
         return orbit != null;
     }
 
     /**
      * Check FieldAbsolutePVCoordinates and attitude dates are equal.
      * @param absPva   position-velocity-acceleration
      * @param attitude attitude
      * @param <T>      the type of the field elements
      * @exception IllegalArgumentException if orbit and attitude dates are not equal
      */
     private static <T extends CalculusFieldElement<T>> void checkConsistency(final FieldAbsolutePVCoordinates<T> absPva, final FieldAttitude<T> attitude)
         throws IllegalArgumentException {
         if (FastMath.abs(absPva.getDate().durationFrom(attitude.getDate())).getReal() >
             DATE_INCONSISTENCY_THRESHOLD) {
             throw new OrekitIllegalArgumentException(OrekitMessages.ORBIT_AND_ATTITUDE_DATES_MISMATCH,
                                                      absPva.getDate(), attitude.getDate());
         }
         if (absPva.getFrame() != attitude.getReferenceFrame()) {
             throw new OrekitIllegalArgumentException(OrekitMessages.FRAMES_MISMATCH,
                                                      absPva.getFrame().getName(),
                                                      attitude.getReferenceFrame().getName());
         }
     }
 
     /** Get a time-shifted state.
      * <p>
      * The state can be slightly shifted to close dates. This shift is based on
      * a simple Keplerian model for orbit, a linear extrapolation for attitude
      * taking the spin rate into account and neither mass nor additional states
      * changes. It is <em>not</em> intended as a replacement for proper orbit
      * and attitude propagation but should be sufficient for small time shifts
      * or coarse accuracy.
      * </p>
      * <p>
      * As a rough order of magnitude, the following table shows the extrapolation
      * errors obtained between this simple shift method and an {@link
      * org.orekit.propagation.numerical.FieldNumericalPropagator numerical
      * propagator} for a low Earth Sun Synchronous Orbit, with a 20x20 gravity field,
      * Sun and Moon third bodies attractions, drag and solar radiation pressure.
      * Beware that these results will be different for other orbits.
      * </p>
      * <table border="1">
      * <caption>Extrapolation Error</caption>
      * <tr style="background-color: #ccccff;"><th>interpolation time (s)</th>
      * <th>position error without derivatives (m)</th><th>position error with derivatives (m)</th></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px"> 60</td><td>  18</td><td> 1.1</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">120</td><td>  72</td><td> 9.1</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">300</td><td> 447</td><td> 140</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">600</td><td>1601</td><td>1067</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">900</td><td>3141</td><td>3307</td></tr>
      * </table>
      * @param dt time shift in seconds
      * @return a new state, shifted with respect to the instance (which is immutable)
      * except for the mass which stay unchanged
      */
     @Override
     public FieldSpacecraftState<T> shiftedBy(final double dt) {
         if (isOrbitDefined()) {
             return new FieldSpacecraftState<>(orbit.shiftedBy(dt), attitude.shiftedBy(dt),
                                               mass, shiftAdditional(dt), additionalDot);
         } else {
             return new FieldSpacecraftState<>(absPva.shiftedBy(dt), attitude.shiftedBy(dt),
                                               mass, shiftAdditional(dt), additionalDot);
         }
     }
 
     /** Get a time-shifted state.
      * <p>
      * The state can be slightly shifted to close dates. This shift is based on
      * a simple Keplerian model for orbit, a linear extrapolation for attitude
      * taking the spin rate into account and neither mass nor additional states
      * changes. It is <em>not</em> intended as a replacement for proper orbit
      * and attitude propagation but should be sufficient for small time shifts
      * or coarse accuracy.
      * </p>
      * <p>
      * As a rough order of magnitude, the following table shows the extrapolation
      * errors obtained between this simple shift method and an {@link
      * org.orekit.propagation.numerical.FieldNumericalPropagator numerical
      * propagator} for a low Earth Sun Synchronous Orbit, with a 20x20 gravity field,
      * Sun and Moon third bodies attractions, drag and solar radiation pressure.
      * Beware that these results will be different for other orbits.
      * </p>
      * <table border="1">
      * <caption>Extrapolation Error</caption>
      * <tr style="background-color: #ccccff;"><th>interpolation time (s)</th>
      * <th>position error without derivatives (m)</th><th>position error with derivatives (m)</th></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px"> 60</td><td>  18</td><td> 1.1</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">120</td><td>  72</td><td> 9.1</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">300</td><td> 447</td><td> 140</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">600</td><td>1601</td><td>1067</td></tr>
      * <tr><td style="background-color: #eeeeff; padding:5px">900</td><td>3141</td><td>3307</td></tr>
      * </table>
      * @param dt time shift in seconds
      * @return a new state, shifted with respect to the instance (which is immutable)
      * except for the mass which stay unchanged
      */
     @Override
     public FieldSpacecraftState<T> shiftedBy(final T dt) {
         if (isOrbitDefined()) {
             return new FieldSpacecraftState<>(orbit.shiftedBy(dt), attitude.shiftedBy(dt),
                                               mass, shiftAdditional(dt), additionalDot);
         } else {
             return new FieldSpacecraftState<>(absPva.shiftedBy(dt), attitude.shiftedBy(dt),
                                               mass, shiftAdditional(dt), additionalDot);
         }
     }
 
     /** Shift additional states.
      * @param dt time shift in seconds
      * @return shifted additional states
      * @since 11.1.1
      */
     private FieldArrayDictionary<T> shiftAdditional(final double dt) {
 
         // fast handling when there are no derivatives at all
         if (additionalDot.size() == 0) {
             return additional;
         }
 
         // there are derivatives, we need to take them into account in the additional state
         final FieldArrayDictionary<T> shifted = new FieldArrayDictionary<>(additional);
         for (final FieldArrayDictionary<T>.Entry dotEntry : additionalDot.getData()) {
             final FieldArrayDictionary<T>.Entry entry = shifted.getEntry(dotEntry.getKey());
             if (entry != null) {
                 entry.scaledIncrement(dt, dotEntry);
             }
         }
 
         return shifted;
 
     }
 
     /** Shift additional states.
      * @param dt time shift in seconds
      * @return shifted additional states
      * @since 11.1.1
      */
     private FieldArrayDictionary<T> shiftAdditional(final T dt) {
 
         // fast handling when there are no derivatives at all
         if (additionalDot.size() == 0) {
             return additional;
         }
 
         // there are derivatives, we need to take them into account in the additional state
         final FieldArrayDictionary<T> shifted = new FieldArrayDictionary<>(additional);
         for (final FieldArrayDictionary<T>.Entry dotEntry : additionalDot.getData()) {
             final FieldArrayDictionary<T>.Entry entry = shifted.getEntry(dotEntry.getKey());
             if (entry != null) {
                 entry.scaledIncrement(dt, dotEntry);
             }
         }
 
         return shifted;
 
     }
 
     /** Get the absolute position-velocity-acceleration.
      * <p>
      * A state contains either an {@link FieldAbsolutePVCoordinates absolute
      * position-velocity-acceleration} or an {@link FieldOrbit orbit}. Which
      * one is present can be checked using {@link #isOrbitDefined()}.
      * </p>
      * @return absolute position-velocity-acceleration
      * @exception OrekitIllegalStateException if position-velocity-acceleration is null,
      * which mean the state rather contains an {@link FieldOrbit}
      * @see #isOrbitDefined()
      * @see #getOrbit()
      */
     public FieldAbsolutePVCoordinates<T> getAbsPVA() throws OrekitIllegalStateException {
         if (isOrbitDefined()) {
             throw new OrekitIllegalStateException(OrekitMessages.UNDEFINED_ABSOLUTE_PVCOORDINATES);
         }
         return absPva;
     }
 
     /** Get the current orbit.
      * <p>
      * A state contains either an {@link FieldAbsolutePVCoordinates absolute
      * position-velocity-acceleration} or an {@link FieldOrbit orbit}. Which
      * one is present can be checked using {@link #isOrbitDefined()}.
      * </p>
      * @return the orbit
      * @exception OrekitIllegalStateException if orbit is null,
      * which means the state rather contains an {@link FieldAbsolutePVCoordinates absolute
      * position-velocity-acceleration}
      * @see #isOrbitDefined()
      * @see #getAbsPVA()
      */
     public FieldOrbit<T> getOrbit() throws OrekitIllegalStateException {
         if (orbit == null) {
             throw new OrekitIllegalStateException(OrekitMessages.UNDEFINED_ORBIT);
         }
         return orbit;
     }
 
     /** {@inheritDoc} */
     @Override
     public FieldAbsoluteDate<T> getDate() {
         return isOrbitDefined() ? orbit.getDate() : absPva.getDate();
     }
 
     /** Get the defining frame.
      * @return the frame in which state is defined
      */
     public Frame getFrame() {
         return isOrbitDefined() ? orbit.getFrame() : absPva.getFrame();
     }
 
 
     /** Check if an additional state is available.
      * @param name name of the additional state
      * @return true if the additional state is available
      * @see #addAdditionalState(String, CalculusFieldElement...)
      * @see #getAdditionalState(String)
      * @see #getAdditionalStatesValues()
      */
     public boolean hasAdditionalState(final String name) {
         return additional.getEntry(name) != null;
     }
 
     /** Check if an additional state derivative is available.
      * @param name name of the additional state derivative
      * @return true if the additional state derivative is available
      * @see #addAdditionalStateDerivative(String, CalculusFieldElement...)
      * @see #getAdditionalStateDerivative(String)
      * @see #getAdditionalStatesDerivatives()
      */
     public boolean hasAdditionalStateDerivative(final String name) {
         return additionalDot.getEntry(name) != null;
     }
 
     /** Check if two instances have the same set of additional states available.
      * <p>
      * Only the names and dimensions of the additional states are compared,
      * not their values.
      * </p>
      * @param state state to compare to instance
      * @exception MathIllegalArgumentException if an additional state does not have
      * the same dimension in both states
      */
     public void ensureCompatibleAdditionalStates(final FieldSpacecraftState<T> state)
         throws MathIllegalArgumentException {
 
         // check instance additional states is a subset of the other one
         for (final FieldArrayDictionary<T>.Entry entry : additional.getData()) {
             final T[] other = state.additional.get(entry.getKey());
             if (other == null) {
                 throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
                                           entry.getKey());
             }
             if (other.length != entry.getValue().length) {
                 throw new MathIllegalStateException(LocalizedCoreFormats.DIMENSIONS_MISMATCH,
                                                     other.length, entry.getValue().length);
             }
         }
 
         // check instance additional states derivatives is a subset of the other one
         for (final FieldArrayDictionary<T>.Entry entry : additionalDot.getData()) {
             final T[] other = state.additionalDot.get(entry.getKey());
             if (other == null) {
                 throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
                                           entry.getKey());
             }
             if (other.length != entry.getValue().length) {
                 throw new MathIllegalStateException(LocalizedCoreFormats.DIMENSIONS_MISMATCH,
                                                     other.length, entry.getValue().length);
             }
         }
 
         if (state.additional.size() > additional.size()) {
             // the other state has more additional states
             for (final FieldArrayDictionary<T>.Entry entry : state.additional.getData()) {
                 if (additional.getEntry(entry.getKey()) == null) {
                     throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
                                               entry.getKey());
                 }
             }
         }
 
         if (state.additionalDot.size() > additionalDot.size()) {
             // the other state has more additional states
             for (final FieldArrayDictionary<T>.Entry entry : state.additionalDot.getData()) {
                 if (additionalDot.getEntry(entry.getKey()) == null) {
                     throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
                                               entry.getKey());
                 }
             }
         }
 
     }
 
     /** Get an additional state.
      * @param name name of the additional state
      * @return value of the additional state
           * @see #addAdditionalState(String, CalculusFieldElement...)
      * @see #hasAdditionalState(String)
      * @see #getAdditionalStatesValues()
      */
     public T[] getAdditionalState(final String name) {
         final FieldArrayDictionary<T>.Entry entry = additional.getEntry(name);
         if (entry == null) {
             throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE, name);
         }
         return entry.getValue();
     }
 
     /** Get an additional state derivative.
      * @param name name of the additional state derivative
      * @return value of the additional state derivative
      * @see #addAdditionalStateDerivative(String, CalculusFieldElement...)
      * @see #hasAdditionalStateDerivative(String)
      * @see #getAdditionalStatesDerivatives()
      * @since 11.1
      */
     public T[] getAdditionalStateDerivative(final String name) {
         final FieldArrayDictionary<T>.Entry entry = additionalDot.getEntry(name);
         if (entry == null) {
             throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE, name);
         }
         return entry.getValue();
     }
 
     /** Get an unmodifiable map of additional states.
      * @return unmodifiable map of additional states
      * @see #addAdditionalState(String, CalculusFieldElement...)
      * @see #hasAdditionalState(String)
      * @see #getAdditionalState(String)
      * @since 11.1
      */
     public FieldArrayDictionary<T> getAdditionalStatesValues() {
         return additional.unmodifiableView();
     }
 
     /** Get an unmodifiable map of additional states derivatives.
      * @return unmodifiable map of additional states derivatives
      * @see #addAdditionalStateDerivative(String, CalculusFieldElement...)
      * @see #hasAdditionalStateDerivative(String)
      * @see #getAdditionalStateDerivative(String)
     * @since 11.1
       */
     public FieldArrayDictionary<T> getAdditionalStatesDerivatives() {
         return additionalDot.unmodifiableView();
     }
 
     /** Compute the transform from state defining frame to spacecraft frame.
      * <p>The spacecraft frame origin is at the point defined by the orbit,
      * and its orientation is defined by the attitude.</p>
      * @return transform from specified frame to current spacecraft frame
      */
     public FieldTransform<T> toTransform() {
         final TimeStampedFieldPVCoordinates<T> pv = getPVCoordinates();
         return new FieldTransform<>(pv.getDate(),
                                     new FieldTransform<>(pv.getDate(), pv.negate()),
                                     new FieldTransform<>(pv.getDate(), attitude.getOrientation()));
     }
 
     /** Compute the static transform from state defining frame to spacecraft frame.
      * @return static transform from specified frame to current spacecraft frame
      * @see #toTransform()
      * @since 12.0
      */
     public FieldStaticTransform<T> toStaticTransform() {
         return FieldStaticTransform.of(getDate(), getPosition().negate(), attitude.getRotation());
     }
 
     /** Get the central attraction coefficient.
      * @return mu central attraction coefficient (m^3/s^2), or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather than an orbit
      */
     public T getMu() {
         return isOrbitDefined() ? orbit.getMu() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the Keplerian period.
      * <p>The Keplerian period is computed directly from semi major axis
      * and central acceleration constant.</p>
      * @return Keplerian period in seconds, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      */
     public T getKeplerianPeriod() {
         return isOrbitDefined() ? orbit.getKeplerianPeriod() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the Keplerian mean motion.
      * <p>The Keplerian mean motion is computed directly from semi major axis
      * and central acceleration constant.</p>
      * @return Keplerian mean motion in radians per second, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      */
     public T getKeplerianMeanMotion() {
         return isOrbitDefined() ? orbit.getKeplerianMeanMotion() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the semi-major axis.
      * @return semi-major axis (m), or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      */
     public T getA() {
         return isOrbitDefined() ? orbit.getA() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the first component of the eccentricity vector (as per equinoctial parameters).
      * @return e cos(ω + Ω), first component of eccentricity vector, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getE()
      */
     public T getEquinoctialEx() {
         return isOrbitDefined() ? orbit.getEquinoctialEx() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the second component of the eccentricity vector (as per equinoctial parameters).
      * @return e sin(ω + Ω), second component of the eccentricity vector, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getE()
      */
     public T getEquinoctialEy() {
         return isOrbitDefined() ? orbit.getEquinoctialEy() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the first component of the inclination vector (as per equinoctial parameters).
      * @return tan(i/2) cos(Ω), first component of the inclination vector, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getI()
      */
     public T getHx() {
         return isOrbitDefined() ? orbit.getHx() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the second component of the inclination vector (as per equinoctial parameters).
      * @return tan(i/2) sin(Ω), second component of the inclination vector, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getI()
      */
     public T getHy() {
         return isOrbitDefined() ? orbit.getHy() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the true latitude argument (as per equinoctial parameters).
      * @return v + ω + Ω true longitude argument (rad), or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getLE()
      * @see #getLM()
      */
     public T getLv() {
         return isOrbitDefined() ? orbit.getLv() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the eccentric latitude argument (as per equinoctial parameters).
      * @return E + ω + Ω eccentric longitude argument (rad), or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getLv()
      * @see #getLM()
      */
     public T getLE() {
         return isOrbitDefined() ? orbit.getLE() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the mean longitude argument (as per equinoctial parameters).
      * @return M + ω + Ω mean latitude argument (rad), or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getLv()
      * @see #getLE()
      */
     public T getLM() {
         return isOrbitDefined() ? orbit.getLM() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     // Additional orbital elements
 
     /** Get the eccentricity.
      * @return eccentricity, or {code Double.NaN} if the
      * state contains an absolute position-velocity-acceleration rather
      * than an orbit
      * @see #getEquinoctialEx()
      * @see #getEquinoctialEy()
      */
     public T getE() {
         return isOrbitDefined() ? orbit.getE() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the inclination.
      * @return inclination (rad)
      * @see #getHx()
      * @see #getHy()
      */
     public T getI() {
         return isOrbitDefined() ? orbit.getI() : absPva.getDate().getField().getZero().add(Double.NaN);
     }
 
     /** Get the position in orbit definition frame.
      * @return position in orbit definition frame
      * @since 12.0
      */
     public FieldVector3D<T> getPosition() {
         return isOrbitDefined() ? orbit.getPosition() : absPva.getPosition();
     }
 
     /** Get the {@link TimeStampedFieldPVCoordinates} in orbit definition frame.
      * <p>
      * Compute the position and velocity of the satellite. This method caches its
      * results, and recompute them only when the method is called with a new value
      * for mu. The result is provided as a reference to the internally cached
      * {@link TimeStampedFieldPVCoordinates}, so the caller is responsible to copy it in a separate
      * {@link TimeStampedFieldPVCoordinates} if it needs to keep the value for a while.
      * </p>
      * @return pvCoordinates in orbit definition frame
      */
     public TimeStampedFieldPVCoordinates<T> getPVCoordinates() {
         return isOrbitDefined() ? orbit.getPVCoordinates() : absPva.getPVCoordinates();
     }
 
     /** Get the position in given output frame.
      * @param outputFrame frame in which position should be defined
      * @return position in given output frame
      * @since 12.0
      * @see #getPVCoordinates(Frame)
      */
     public FieldVector3D<T> getPosition(final Frame outputFrame) {
         return isOrbitDefined() ? orbit.getPosition(outputFrame) : absPva.getPosition(outputFrame);
     }
 
     /** Get the {@link TimeStampedFieldPVCoordinates} in given output frame.
      * <p>
      * Compute the position and velocity of the satellite. This method caches its
      * results, and recompute them only when the method is called with a new value
      * for mu. The result is provided as a reference to the internally cached
      * {@link TimeStampedFieldPVCoordinates}, so the caller is responsible to copy it in a separate
      * {@link TimeStampedFieldPVCoordinates} if it needs to keep the value for a while.
      * </p>
      * @param outputFrame frame in which coordinates should be defined
      * @return pvCoordinates in orbit definition frame
      */
     public TimeStampedFieldPVCoordinates<T> getPVCoordinates(final Frame outputFrame) {
         return isOrbitDefined() ? orbit.getPVCoordinates(outputFrame) : absPva.getPVCoordinates(outputFrame);
     }
 
     /** Get the attitude.
      * @return the attitude.
      */
     public FieldAttitude<T> getAttitude() {
         return attitude;
     }
 
     /** Gets the current mass.
      * @return the mass (kg)
      */
     public T getMass() {
         return mass;
     }
 
     /**To convert a FieldSpacecraftState instance into a SpacecraftState instance.
      *
      * @return SpacecraftState instance with the same properties
      */
     public SpacecraftState toSpacecraftState() {
         final DoubleArrayDictionary dictionary;
         if (additional.size() == 0) {
             dictionary = new DoubleArrayDictionary();
         } else {
             dictionary = new DoubleArrayDictionary(additional.size());
             for (final FieldArrayDictionary<T>.Entry entry : additional.getData()) {
                 final double[] array = new double[entry.getValue().length];
                 for (int k = 0; k < array.length; ++k) {
                     array[k] = entry.getValue()[k].getReal();
                 }
                 dictionary.put(entry.getKey(), array);
             }
         }
         final DoubleArrayDictionary dictionaryDot;
         if (additionalDot.size() == 0) {
             dictionaryDot = new DoubleArrayDictionary();
         } else {
             dictionaryDot = new DoubleArrayDictionary(additionalDot.size());
             for (final FieldArrayDictionary<T>.Entry entry : additionalDot.getData()) {
                 final double[] array = new double[entry.getValue().length];
                 for (int k = 0; k < array.length; ++k) {
                     array[k] = entry.getValue()[k].getReal();
                 }
                 dictionaryDot.put(entry.getKey(), array);
             }
         }
         if (isOrbitDefined()) {
             return new SpacecraftState(orbit.toOrbit(), attitude.toAttitude(),
                                        mass.getReal(), dictionary, dictionaryDot);
         } else {
             return new SpacecraftState(absPva.toAbsolutePVCoordinates(),
                                        attitude.toAttitude(), mass.getReal(),
                                        dictionary, dictionaryDot);
         }
     }
 
     @Override
     public String toString() {
         return "FieldSpacecraftState{" +
                 "orbit=" + orbit +
                 ", attitude=" + attitude +
                 ", mass=" + mass +
                 ", additional=" + additional +
                 ", additionalDot=" + additionalDot +
                 '}';
     }
 
 }