/* Copyright 2002-2016 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;
  
  import java.io.Serializable;
  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.analysis.interpolation.HermiteInterpolator;
  import org.apache.commons.math3.exception.DimensionMismatchException;
  import org.apache.commons.math3.geometry.euclidean.threed.Rotation;
  import org.apache.commons.math3.geometry.euclidean.threed.Vector3D;
  import org.apache.commons.math3.util.FastMath;
  import org.orekit.attitudes.Attitude;
  import org.orekit.attitudes.LofOffset;
  import org.orekit.errors.OrekitIllegalArgumentException;
  import org.orekit.errors.OrekitException;
  import org.orekit.errors.OrekitMessages;
  import org.orekit.frames.Frame;
  import org.orekit.frames.LOFType;
  import org.orekit.frames.Transform;
  import org.orekit.orbits.Orbit;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.time.TimeInterpolable;
  import org.orekit.time.TimeShiftable;
  import org.orekit.time.TimeStamped;
  import org.orekit.utils.TimeStampedAngularCoordinates;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  
  /** This class is the representation of a complete state holding orbit, attitude
   * and mass information at a given date.
   *
   * <p>It contains an {@link Orbit orbital state} at a current
   * {@link AbsoluteDate} both handled by an {@link Orbit}, plus the current
   * mass and attitude. Orbit and state 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 shift is based on
   * a simple keplerian model for orbit, a linear extrapolation for attitude
   * 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>SpacecraftState</code> is guaranteed to be immutable.
   * </p>
   * @see org.orekit.propagation.numerical.NumericalPropagator
   * @author Fabien Maussion
   * @author V&eacute;ronique Pommier-Maurussane
   * @author Luc Maisonobe
   */
  public class SpacecraftState
      implements TimeStamped, TimeShiftable<SpacecraftState>, TimeInterpolable<SpacecraftState>, Serializable {
  
      /** Serializable UID. */
      private static final long serialVersionUID = 20130407L;
  
      /** Default mass. */
      private static final double DEFAULT_MASS = 1000.0;
  
      /**
       * tolerance on date comparison in {@link #checkConsistency(Orbit, Attitude)}. 100 ns
       * corresponds to sub-mm accuracy at LEO orbital velocities.
       */
      private static final double DATE_INCONSISTENCY_THRESHOLD = 100e-9;
  
      /** Orbital state. */
      private final Orbit orbit;
  
      /** Attitude. */
      private final Attitude attitude;
  
      /** Current mass (kg). */
      private final double mass;
  
      /** Additional states. */
      private final Map<String, double[]> additional;
 
     /** Build a spacecraft state from orbit only.
      * <p>Attitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param orbit the orbit
      * @exception OrekitException if default attitude cannot be computed
      */
     public SpacecraftState(final Orbit orbit)
         throws OrekitException {
         this(orbit,
              new LofOffset(orbit.getFrame(), LOFType.VVLH).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              DEFAULT_MASS, null);
     }
 
     /** Build a spacecraft state from orbit and attitude provider.
      * <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 SpacecraftState(final Orbit orbit, final Attitude attitude)
         throws IllegalArgumentException {
         this(orbit, attitude, DEFAULT_MASS, null);
     }
 
     /** Create a new instance from orbit and mass.
      * <p>Attitude law is set to an unspecified default attitude.</p>
      * @param orbit the orbit
      * @param mass the mass (kg)
      * @exception OrekitException if default attitude cannot be computed
      */
     public SpacecraftState(final Orbit orbit, final double mass)
         throws OrekitException {
         this(orbit,
              new LofOffset(orbit.getFrame(), LOFType.VVLH).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              mass, null);
     }
 
     /** Build a spacecraft state from orbit, attitude provider 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 SpacecraftState(final Orbit orbit, final Attitude attitude, final double mass)
         throws IllegalArgumentException {
         this(orbit, attitude, mass, null);
     }
 
     /** Build a spacecraft state from orbit only.
      * <p>Attitude and mass are set to unspecified non-null arbitrary values.</p>
      * @param orbit the orbit
      * @param additional additional states
      * @exception OrekitException if default attitude cannot be computed
      */
     public SpacecraftState(final Orbit orbit, final Map<String, double[]> additional)
         throws OrekitException {
         this(orbit,
              new LofOffset(orbit.getFrame(), LOFType.VVLH).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              DEFAULT_MASS, additional);
     }
 
     /** Build a spacecraft state from orbit and attitude provider.
      * <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
      */
     public SpacecraftState(final Orbit orbit, final Attitude attitude, final Map<String, double[]> additional)
         throws IllegalArgumentException {
         this(orbit, attitude, DEFAULT_MASS, additional);
     }
 
     /** Create a new instance from orbit and mass.
      * <p>Attitude law is set to an unspecified default attitude.</p>
      * @param orbit the orbit
      * @param mass the mass (kg)
      * @param additional additional states
      * @exception OrekitException if default attitude cannot be computed
      */
     public SpacecraftState(final Orbit orbit, final double mass, final Map<String, double[]> additional)
         throws OrekitException {
         this(orbit,
              new LofOffset(orbit.getFrame(), LOFType.VVLH).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
              mass, additional);
     }
 
     /** Build a spacecraft state from orbit, attitude provider and mass.
      * @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)
      * @exception IllegalArgumentException if orbit and attitude dates
      * or frames are not equal
      */
     public SpacecraftState(final Orbit orbit, final Attitude attitude,
                            final double mass, final Map<String, double[]> additional)
         throws IllegalArgumentException {
         checkConsistency(orbit, attitude);
         this.orbit      = orbit;
         this.attitude   = attitude;
         this.mass       = mass;
         if (additional == null) {
             this.additional = Collections.emptyMap();
         } else {
             this.additional = new HashMap<String, double[]>(additional.size());
             for (final Map.Entry<String, double[]> entry : additional.entrySet()) {
                 this.additional.put(entry.getKey(), entry.getValue().clone());
             }
         }
     }
 
     /** Add an additional state.
      * <p>
      * {@link SpacecraftState 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 #getAdditionalStates()
      */
     public SpacecraftState addAdditionalState(final String name, final double ... value) {
         final Map<String, double[]> newMap = new HashMap<String, double[]>(additional.size() + 1);
         newMap.putAll(additional);
         newMap.put(name, value.clone());
         return new SpacecraftState(orbit, attitude, mass, newMap);
     }
 
     /** Check orbit and attitude dates are equal.
      * @param orbit the orbit
      * @param attitude attitude
      * @exception IllegalArgumentException if orbit and attitude dates
      * are not equal
      */
     private static void checkConsistency(final Orbit orbit, final Attitude attitude)
         throws IllegalArgumentException {
         if (FastMath.abs(orbit.getDate().durationFrom(attitude.getDate())) >
             DATE_INCONSISTENCY_THRESHOLD) {
             throw new OrekitIllegalArgumentException(OrekitMessages.ORBIT_AND_ATTITUDE_DATES_MISMATCH,
                                                      orbit.getDate(), attitude.getDate());
         }
         if (orbit.getFrame() != attitude.getReferenceFrame()) {
             throw new OrekitIllegalArgumentException(OrekitMessages.FRAMES_MISMATCH,
                                                      orbit.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 interpolation
      * errors obtained between this simple shift method and an {@link
      * org.orekit.propagation.analytical.EcksteinHechlerPropagator Eckstein-Heschler
      * propagator} for an 800km altitude nearly circular polar Earth orbit with
      * {@link org.orekit.attitudes.BodyCenterPointing body center pointing}. Beware
      * that these results may be different for other orbits.
      * </p>
      * <table border="1" cellpadding="5">
      * <tr bgcolor="#ccccff"><th>interpolation time (s)</th>
      * <th>position error (m)</th><th>velocity error (m/s)</th>
      * <th>attitude error (&deg;)</th></tr>
      * <tr><td bgcolor="#eeeeff"> 60</td><td>  20</td><td>1</td><td>0.001</td></tr>
      * <tr><td bgcolor="#eeeeff">120</td><td> 100</td><td>2</td><td>0.002</td></tr>
      * <tr><td bgcolor="#eeeeff">300</td><td> 600</td><td>4</td><td>0.005</td></tr>
      * <tr><td bgcolor="#eeeeff">600</td><td>2000</td><td>6</td><td>0.008</td></tr>
      * <tr><td bgcolor="#eeeeff">900</td><td>4000</td><td>6</td><td>0.010</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
      */
     public SpacecraftState shiftedBy(final double dt) {
         return new SpacecraftState(orbit.shiftedBy(dt), attitude.shiftedBy(dt),
                                    mass, additional);
     }
 
     /** {@inheritDoc}
      * <p>
      * The additional states that are interpolated are the ones already present
      * in the instance. The sample instances must therefore have at least the same
      * additional states has the instance. They may have more additional states,
      * but the extra ones will be ignored.
      * </p>
      * <p>
      * As this implementation of interpolation is polynomial, it should be used only
      * with small samples (about 10-20 points) in order to avoid <a
      * href="http://en.wikipedia.org/wiki/Runge%27s_phenomenon">Runge's phenomenon</a>
      * and numerical problems (including NaN appearing).
      * </p>
      */
     public SpacecraftState interpolate(final AbsoluteDate date,
                                        final Collection<SpacecraftState> sample)
         throws OrekitException {
 
         // prepare interpolators
         final List<Orbit> orbits = new ArrayList<Orbit>(sample.size());
         final List<Attitude> attitudes = new ArrayList<Attitude>(sample.size());
         final HermiteInterpolator massInterpolator = new HermiteInterpolator();
         final Map<String, HermiteInterpolator> additionalInterpolators =
                 new HashMap<String, HermiteInterpolator>(additional.size());
         for (final String name : additional.keySet()) {
             additionalInterpolators.put(name, new HermiteInterpolator());
         }
 
         // extract sample data
         for (final SpacecraftState state : sample) {
             final double deltaT = state.getDate().durationFrom(date);
             orbits.add(state.getOrbit());
             attitudes.add(state.getAttitude());
             massInterpolator.addSamplePoint(deltaT,
                                             new double[] {
                                                 state.getMass()
                                             });
             for (final Map.Entry<String, HermiteInterpolator> entry : additionalInterpolators.entrySet()) {
                 entry.getValue().addSamplePoint(deltaT, state.getAdditionalState(entry.getKey()));
             }
         }
 
         // perform interpolations
         final Orbit interpolatedOrbit       = orbit.interpolate(date, orbits);
         final Attitude interpolatedAttitude = attitude.interpolate(date, attitudes);
         final double interpolatedMass       = massInterpolator.value(0)[0];
         final Map<String, double[]> interpolatedAdditional;
         if (additional.isEmpty()) {
             interpolatedAdditional = null;
         } else {
             interpolatedAdditional = new HashMap<String, double[]>(additional.size());
             for (final Map.Entry<String, HermiteInterpolator> entry : additionalInterpolators.entrySet()) {
                 interpolatedAdditional.put(entry.getKey(), entry.getValue().value(0));
             }
         }
 
         // create the complete interpolated state
         return new SpacecraftState(interpolatedOrbit, interpolatedAttitude,
                                    interpolatedMass, interpolatedAdditional);
 
     }
 
     /** Gets the current orbit.
      * @return the orbit
      */
     public Orbit getOrbit() {
         return orbit;
     }
 
     /** Get the date.
      * @return date
      */
     public AbsoluteDate getDate() {
         return orbit.getDate();
     }
 
     /** Get the inertial frame.
      * @return the frame
      */
     public Frame getFrame() {
         return orbit.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, double[])
      * @see #getAdditionalState(String)
      * @see #getAdditionalStates()
      */
     public boolean hasAdditionalState(final String name) {
         return additional.containsKey(name);
     }
 
     /** 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 OrekitException if either instance or state supports an additional
      * state not supported by the other one
      * @exception DimensionMismatchException if an additional state does not have
      * the same dimension in both states
      */
     public void ensureCompatibleAdditionalStates(final SpacecraftState state)
         throws OrekitException, DimensionMismatchException {
 
         // check instance additional states is a subset of the other one
         for (final Map.Entry<String, double[]> entry : additional.entrySet()) {
             final double[] 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 DimensionMismatchException(other.length, entry.getValue().length);
             }
         }
 
         if (state.additional.size() > additional.size()) {
             // the other state has more additional states
             for (final String name : state.additional.keySet()) {
                 if (!additional.containsKey(name)) {
                     throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
                                               name);
                 }
             }
         }
 
     }
 
     /** Get an additional state.
      * @param name name of the additional state
      * @return value of the additional state
      * @exception OrekitException if no additional state with that name exists
      * @see #addAdditionalState(String, double[])
      * @see #hasAdditionalState(String)
      * @see #getAdditionalStates()
      */
     public double[] getAdditionalState(final String name) throws OrekitException {
         if (!additional.containsKey(name)) {
             throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE, name);
         }
         return additional.get(name).clone();
     }
 
     /** Get an unmodifiable map of additional states.
      * @return unmodifiable map of additional states
      * @see #addAdditionalState(String, double[])
      * @see #hasAdditionalState(String)
      * @see #getAdditionalState(String)
      */
     public Map<String, double[]> getAdditionalStates() {
         return Collections.unmodifiableMap(additional);
     }
 
     /** Compute the transform from orbite/attitude reference 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 Transform toTransform() {
         final AbsoluteDate date = orbit.getDate();
         return new Transform(date,
                              new Transform(date, orbit.getPVCoordinates().negate()),
                              new Transform(date, attitude.getOrientation()));
     }
 
     /** Get the central attraction coefficient.
      * @return mu central attraction coefficient (m^3/s^2)
      */
     public double getMu() {
         return orbit.getMu();
     }
 
     /** 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
      */
     public double getKeplerianPeriod() {
         return orbit.getKeplerianPeriod();
     }
 
     /** 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
      */
     public double getKeplerianMeanMotion() {
         return orbit.getKeplerianMeanMotion();
     }
 
     /** Get the semi-major axis.
      * @return semi-major axis (m)
      */
     public double getA() {
         return orbit.getA();
     }
 
     /** Get the first component of the eccentricity vector (as per equinoctial parameters).
      * @return e cos(ω + Ω), first component of eccentricity vector
      * @see #getE()
      */
     public double getEquinoctialEx() {
         return orbit.getEquinoctialEx();
     }
 
     /** Get the second component of the eccentricity vector (as per equinoctial parameters).
      * @return e sin(ω + Ω), second component of the eccentricity vector
      * @see #getE()
      */
     public double getEquinoctialEy() {
         return orbit.getEquinoctialEy();
     }
 
     /** Get the first component of the inclination vector (as per equinoctial parameters).
      * @return tan(i/2) cos(Ω), first component of the inclination vector
      * @see #getI()
      */
     public double getHx() {
         return orbit.getHx();
     }
 
     /** Get the second component of the inclination vector (as per equinoctial parameters).
      * @return tan(i/2) sin(Ω), second component of the inclination vector
      * @see #getI()
      */
     public double getHy() {
         return orbit.getHy();
     }
 
     /** Get the true latitude argument (as per equinoctial parameters).
      * @return v + ω + Ω true latitude argument (rad)
      * @see #getLE()
      * @see #getLM()
      */
     public double getLv() {
         return orbit.getLv();
     }
 
     /** Get the eccentric latitude argument (as per equinoctial parameters).
      * @return E + ω + Ω eccentric latitude argument (rad)
      * @see #getLv()
      * @see #getLM()
      */
     public double getLE() {
         return orbit.getLE();
     }
 
     /** Get the mean latitude argument (as per equinoctial parameters).
      * @return M + ω + Ω mean latitude argument (rad)
      * @see #getLv()
      * @see #getLE()
      */
     public double getLM() {
         return orbit.getLM();
     }
 
     // Additional orbital elements
 
     /** Get the eccentricity.
      * @return eccentricity
      * @see #getEquinoctialEx()
      * @see #getEquinoctialEy()
      */
     public double getE() {
         return orbit.getE();
     }
 
     /** Get the inclination.
      * @return inclination (rad)
      * @see #getHx()
      * @see #getHy()
      */
     public double getI() {
         return orbit.getI();
     }
 
     /** Get the {@link TimeStampedPVCoordinates} in orbit definition frame.
      * 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 TimeStampedPVCoordinates}, so the caller is responsible to copy it in a separate
      * {@link TimeStampedPVCoordinates} if it needs to keep the value for a while.
      * @return pvCoordinates in orbit definition frame
      */
     public TimeStampedPVCoordinates getPVCoordinates() {
         return orbit.getPVCoordinates();
     }
 
     /** Get the {@link TimeStampedPVCoordinates} in given output frame.
      * 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 TimeStampedPVCoordinates}, so the caller is responsible to copy it in a separate
      * {@link TimeStampedPVCoordinates} if it needs to keep the value for a while.
      * @param outputFrame frame in which coordinates should be defined
      * @return pvCoordinates in orbit definition frame
      * @exception OrekitException if the transformation between frames cannot be computed
      */
     public TimeStampedPVCoordinates getPVCoordinates(final Frame outputFrame)
         throws OrekitException {
         return orbit.getPVCoordinates(outputFrame);
     }
 
     /** Get the attitude.
      * @return the attitude.
      */
     public Attitude getAttitude() {
         return attitude;
     }
 
     /** Gets the current mass.
      * @return the mass (kg)
      */
     public double getMass() {
         return mass;
     }
 
     /** Replace the instance with a data transfer object for serialization.
      * @return data transfer object that will be serialized
      */
     private Object writeReplace() {
         return new DTO(this);
     }
 
     /** Internal class used only for serialization. */
     private static class DTO implements Serializable {
 
         /** Serializable UID. */
         private static final long serialVersionUID = 20140617L;
 
         /** Orbit. */
         private final Orbit orbit;
 
         /** Attitude and mass double values. */
         private double[] d;
 
         /** Additional states. */
         private final Map<String, double[]> additional;
 
         /** Simple constructor.
          * @param state instance to serialize
          */
         private DTO(final SpacecraftState state) {
 
             this.orbit      = state.orbit;
             this.additional = state.additional.isEmpty() ? null : state.additional;
 
             final Rotation rotation             = state.attitude.getRotation();
             final Vector3D spin                 = state.attitude.getSpin();
             final Vector3D rotationAcceleration = state.attitude.getRotationAcceleration();
             this.d = new double[] {
                 rotation.getQ0(), rotation.getQ1(), rotation.getQ2(), rotation.getQ3(),
                 spin.getX(), spin.getY(), spin.getZ(),
                 rotationAcceleration.getX(), rotationAcceleration.getY(), rotationAcceleration.getZ(),
                 state.mass
             };
 
         }
 
         /** Replace the deserialized data transfer object with a {@link SpacecraftState}.
          * @return replacement {@link SpacecraftState}
          */
         private Object readResolve() {
             return new SpacecraftState(orbit,
                                        new Attitude(orbit.getFrame(),
                                                     new TimeStampedAngularCoordinates(orbit.getDate(),
                                                                                       new Rotation(d[0], d[1], d[2], d[3], false),
                                                                                       new Vector3D(d[4], d[5], d[6]),
                                                                                       new Vector3D(d[7], d[8], d[9]))),
                                        d[10], additional);
         }
 
     }
 
 }