/* Copyright 2002-2018 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.estimation.measurements;
  
  import java.util.Arrays;
  
  import org.hipparchus.exception.LocalizedCoreFormats;
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.util.FastMath;
  import org.orekit.errors.OrekitException;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.utils.TimeStampedPVCoordinates;
  
  /** Class modeling a position-velocity state.
   * @author Luc Maisonobe
   * @since 8.0
   */
  public class PV extends AbstractMeasurement<PV> {
  
      /** Identity matrix, for states derivatives. */
      private static final double[][] IDENTITY = new double[][] {
          {
              1, 0, 0, 0, 0, 0
          }, {
              0, 1, 0, 0, 0, 0
          }, {
              0, 0, 1, 0, 0, 0
          }, {
              0, 0, 0, 1, 0, 0
          }, {
              0, 0, 0, 0, 1, 0
          }, {
              0, 0, 0, 0, 0, 1
          }
      };
  
      /** Covariance matrix of the PV measurement (size 6x6). */
      private final double[][] covarianceMatrix;
  
      /** Constructor with two double for the standard deviations.
       * The first double is the position's standard deviation, common to the 3 position's components.
       * The second double is the position's standard deviation, common to the 3 position's components.
       * <p>
       * The measurement must be in the orbit propagation frame.
       * </p>
       * This constructor uses 0 as the index of the propagator related
       * to this measurement, thus being well suited for mono-satellite
       * orbit determination.
       * @param date date of the measurement
       * @param position position
       * @param velocity velocity
       * @param sigmaPosition theoretical standard deviation on position components
       * @param sigmaVelocity theoretical standard deviation on velocity components
       * @param baseWeight base weight
       * @throws OrekitException if the built inside covariance matrix does not have the proper size
       */
      public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
                final double sigmaPosition, final double sigmaVelocity, final double baseWeight) throws OrekitException {
          this(date, position, velocity, sigmaPosition, sigmaVelocity, baseWeight, 0);
      }
  
      /** Constructor with two double for the standard deviations.
       * The first double is the position's standard deviation, common to the 3 position's components.
       * The second double is the position's standard deviation, common to the 3 position's components.
       * <p>
       * The measurement must be in the orbit propagation frame.
       * </p>
       * @param date date of the measurement
       * @param position position
       * @param velocity velocity
       * @param sigmaPosition theoretical standard deviation on position components
       * @param sigmaVelocity theoretical standard deviation on velocity components
       * @param baseWeight base weight
       * @param propagatorIndex index of the propagator related to this measurement
       * @throws OrekitException if the built inside covariance matrix does not have the proper size
       * @since 9.0
       */
      public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
                final double sigmaPosition, final double sigmaVelocity, final double baseWeight,
                final int propagatorIndex) throws OrekitException {
          this(date, position, velocity,
               new double[] {
                   sigmaPosition,
                   sigmaPosition,
                  sigmaPosition,
                  sigmaVelocity,
                  sigmaVelocity,
                  sigmaVelocity
              }, baseWeight, propagatorIndex);
     }
 
     /** Constructor with two vectors for the standard deviations and default value for propagator index..
      * One 3-sized vectors for position standard deviations.
      * One 3-sized vectors for velocity standard deviations.
      * The 3-sized vectors are the square root of the diagonal elements of the covariance matrix.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * This constructor uses 0 as the index of the propagator related
      * to this measurement, thus being well suited for mono-satellite
      * orbit determination.
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param sigmaPosition 3-sized vector of the standard deviations of the position
      * @param sigmaVelocity 3-sized vector of the standard deviations of the velocity
      * @param baseWeight base weight
      * @throws OrekitException if input standard deviations vectors do not have the proper sizes
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[] sigmaPosition, final double[] sigmaVelocity, final double baseWeight) throws OrekitException {
         this(date, position, velocity, sigmaPosition, sigmaVelocity, baseWeight, 0);
     }
 
     /** Constructor with two vectors for the standard deviations.
      * One 3-sized vectors for position standard deviations.
      * One 3-sized vectors for velocity standard deviations.
      * The 3-sized vectors are the square root of the diagonal elements of the covariance matrix.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param sigmaPosition 3-sized vector of the standard deviations of the position
      * @param sigmaVelocity 3-sized vector of the standard deviations of the velocity
      * @param baseWeight base weight
      * @param propagatorIndex index of the propagator related to this measurement
      * @throws OrekitException if input standard deviations vectors do not have the proper sizes
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[] sigmaPosition, final double[] sigmaVelocity,
               final double baseWeight, final int propagatorIndex) throws OrekitException {
         this(date, position, velocity,
              buildPvCovarianceMatrix(sigmaPosition, sigmaVelocity),
              baseWeight, propagatorIndex);
     }
 
     /** Constructor with one vector for the standard deviations and default value for propagator index.
      * The 6-sized vector is the square root of the diagonal elements of the covariance matrix.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * This constructor uses 0 as the index of the propagator related
      * to this measurement, thus being well suited for mono-satellite
      * orbit determination.
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param sigmaPV 6-sized vector of the standard deviations
      * @param baseWeight base weight
      * @throws OrekitException if input standard deviations vector does not have the proper size
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[] sigmaPV, final double baseWeight) throws OrekitException {
         this(date, position, velocity, sigmaPV, baseWeight, 0);
     }
 
     /** Constructor with one vector for the standard deviations.
      * The 6-sized vector is the square root of the diagonal elements of the covariance matrix.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param sigmaPV 6-sized vector of the standard deviations
      * @param baseWeight base weight
      * @param propagatorIndex index of the propagator related to this measurement
      * @throws OrekitException if input standard deviations vector does not have the proper size
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[] sigmaPV, final double baseWeight, final int propagatorIndex) throws OrekitException {
         this(date, position, velocity,
              buildPvCovarianceMatrix(sigmaPV),
              baseWeight, propagatorIndex);
     }
 
     /**
      * Constructor with 2 smaller covariance matrices and default value for propagator index.
      * One 3x3 covariance matrix for position and one 3x3 covariance matrix for velocity.
      * The fact that the covariance matrices are symmetric and positive definite is not checked.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * This constructor uses 0 as the index of the propagator related
      * to this measurement, thus being well suited for mono-satellite
      * orbit determination.
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param positionCovarianceMatrix 3x3 covariance matrix of the position
      * @param velocityCovarianceMatrix 3x3 covariance matrix of the velocity
      * @param baseWeight base weight
      * @throws OrekitException if input covariance matrices do not have the proper sizes
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[][] positionCovarianceMatrix, final double[][] velocityCovarianceMatrix,
               final double baseWeight) throws OrekitException {
         this(date, position, velocity, positionCovarianceMatrix, velocityCovarianceMatrix, baseWeight, 0);
     }
 
     /**
      * Constructor with 2 smaller covariance matrices.
      * One 3x3 covariance matrix for position and one 3x3 covariance matrix for velocity.
      * The fact that the covariance matrices are symmetric and positive definite is not checked.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param positionCovarianceMatrix 3x3 covariance matrix of the position
      * @param velocityCovarianceMatrix 3x3 covariance matrix of the velocity
      * @param baseWeight base weight
      * @param propagatorIndex index of the propagator related to this measurement
      * @throws OrekitException if input covariance matrices do not have the proper sizes
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[][] positionCovarianceMatrix, final double[][] velocityCovarianceMatrix,
               final double baseWeight, final int propagatorIndex) throws OrekitException {
         this(date, position, velocity,
              buildPvCovarianceMatrix(positionCovarianceMatrix, velocityCovarianceMatrix),
              baseWeight, propagatorIndex);
     }
 
     /**
      * Constructor with full covariance matrix but default index for propagator.
      * The fact that the covariance matrix is symmetric and positive definite is not checked.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * This constructor uses 0 as the index of the propagator related
      * to this measurement, thus being well suited for mono-satellite
      * orbit determination.
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param covarianceMatrix 6x6 covariance matrix of the PV measurement
      * @param baseWeight base weight
      * @throws OrekitException if input covariance matrix does not have the proper size
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[][] covarianceMatrix, final double baseWeight) throws OrekitException {
         this(date, position, velocity, covarianceMatrix, baseWeight, 0);
     }
 
     /** Constructor with full covariance matrix and all inputs.
      * The fact that the covariance matrix is symmetric and positive definite is not checked.
      * <p>The measurement must be in the orbit propagation frame.</p>
      * @param date date of the measurement
      * @param position position
      * @param velocity velocity
      * @param covarianceMatrix 6x6 covariance matrix of the PV measurement
      * @param baseWeight base weight
      * @param propagatorIndex index of the propagator related to this measurement
      * @throws OrekitException if input covariance matrix does not have the proper size
      * @since 9.2
      */
     public PV(final AbsoluteDate date, final Vector3D position, final Vector3D velocity,
               final double[][] covarianceMatrix, final double baseWeight, final int propagatorIndex)
         throws OrekitException {
         super(date,
               new double[] {
                   position.getX(), position.getY(), position.getZ(),
                   velocity.getX(), velocity.getY(), velocity.getZ()
               }, extractSigmas(covarianceMatrix),
               new double[] {
                   baseWeight, baseWeight, baseWeight,
                   baseWeight, baseWeight, baseWeight
               }, Arrays.asList(propagatorIndex));
         this.covarianceMatrix = covarianceMatrix;
     }
 
     /** Get the position.
      * @return position
      */
     public Vector3D getPosition() {
         final double[] pv = getObservedValue();
         return new Vector3D(pv[0], pv[1], pv[2]);
     }
 
     /** Get the velocity.
      * @return velocity
      */
     public Vector3D getVelocity() {
         final double[] pv = getObservedValue();
         return new Vector3D(pv[3], pv[4], pv[5]);
     }
 
     /** Get the covariance matrix.
      * @return the covariance matrix
      */
     public double[][] getCovarianceMatrix() {
         return covarianceMatrix;
     }
 
     /** Get the correlation coefficients matrix.
      * <br>This is the 6x6 matrix M such that:</br>
      * <br>Mij = Pij/(σi.σj)</br>
      * <br>Where: <ul>
      * <li> P is the covariance matrix
      * <li> σi is the i-th standard deviation (σi² = Pii)
      * </ul>
      * @return the correlation coefficient matrix (6x6)
      */
     public double[][] getCorrelationCoefficientsMatrix() {
 
         // Get the standard deviations
         final double[] sigmas = getTheoreticalStandardDeviation();
 
         // Initialize the correlation coefficients matric to the covariance matrix
         final double[][] corrCoefMatrix = new double[sigmas.length][sigmas.length];
 
         // Divide by the standard deviations
         for (int i = 0; i < sigmas.length; i++) {
             for (int j = 0; j < sigmas.length; j++) {
                 corrCoefMatrix[i][j] = covarianceMatrix[i][j] / (sigmas[i] * sigmas[j]);
             }
         }
         return corrCoefMatrix;
     }
 
     /** {@inheritDoc} */
     @Override
     protected EstimatedMeasurement<PV> theoreticalEvaluation(final int iteration, final int evaluation,
                                                              final SpacecraftState[] states)
         throws OrekitException {
 
         // PV value
         final TimeStampedPVCoordinates pv = states[getPropagatorsIndices().get(0)].getPVCoordinates();
 
         // prepare the evaluation
         final EstimatedMeasurement<PV> estimated =
                         new EstimatedMeasurement<>(this, iteration, evaluation, states,
                                                    new TimeStampedPVCoordinates[] {
                                                        pv
                                                    });
 
         estimated.setEstimatedValue(new double[] {
             pv.getPosition().getX(), pv.getPosition().getY(), pv.getPosition().getZ(),
             pv.getVelocity().getX(), pv.getVelocity().getY(), pv.getVelocity().getZ()
         });
 
         // partial derivatives with respect to state
         estimated.setStateDerivatives(0, IDENTITY);
 
         return estimated;
     }
 
     /** Extract standard deviations from a 6x6 PV covariance matrix.
      * Check the size of the PV covariance matrix first.
      * @param pvCovarianceMatrix the 6x6 PV covariance matrix
      * @return the standard deviations (6-sized vector), they are
      * the square roots of the diagonal elements of the covariance matrix in input.
      * @throws OrekitException if the PV covariance matrix is not a 6x6 matrix
      */
     private static double[] extractSigmas(final double[][] pvCovarianceMatrix) throws OrekitException {
 
         // Check the size of the covariance matrix, should be 6x6
         if (pvCovarianceMatrix[0].length != 6 || pvCovarianceMatrix[1].length != 6) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH_2x2,
                                       pvCovarianceMatrix[0].length, pvCovarianceMatrix[1],
                                       6, 6);
         }
 
         // Extract the standard deviations (square roots of the diagonal elements)
         final double[] sigmas = new double[6];
         for (int i = 0; i < sigmas.length; i++) {
             sigmas[i] = FastMath.sqrt(pvCovarianceMatrix[i][i]);
         }
         return sigmas;
     }
 
     /** Build a 6x6 PV covariance matrix from two 3x3 matrices (covariances in position and velocity).
      * Check the size of the matrices first.
      * @param positionCovarianceMatrix the 3x3 covariance matrix in position
      * @param velocityCovarianceMatrix the 3x3 covariance matrix in velocity
      * @return the 6x6 PV covariance matrix
      * @throws OrekitException if the matrices do not have the proper size
      */
     private static double[][] buildPvCovarianceMatrix(final double[][] positionCovarianceMatrix,
                                                       final double[][] velocityCovarianceMatrix)
         throws OrekitException {
         // Check the sizes of the matrices first
         if (positionCovarianceMatrix[0].length != 3 || positionCovarianceMatrix[1].length != 3) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH_2x2,
                                       positionCovarianceMatrix[0].length, positionCovarianceMatrix[1],
                                       3, 3);
         }
         if (velocityCovarianceMatrix[0].length != 3 || velocityCovarianceMatrix[1].length != 3) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH_2x2,
                                       velocityCovarianceMatrix[0].length, velocityCovarianceMatrix[1],
                                       3, 3);
         }
 
         // Build the PV 6x6 covariance matrix
         final double[][] pvCovarianceMatrix = new double[6][6];
         for (int i = 0; i < 3; i++) {
             for (int j = 0; j < 3; j++) {
                 pvCovarianceMatrix[i][j]         = positionCovarianceMatrix[i][j];
                 pvCovarianceMatrix[i + 3][j + 3] = velocityCovarianceMatrix[i][j];
             }
         }
         return pvCovarianceMatrix;
     }
 
     /** Build a 6x6 PV covariance matrix from a 6-sized vector (position and velocity standard deviations).
      * Check the size of the vector first.
      * @param sigmaPV 6-sized vector with position standard deviations on the first 3 elements
      * and velocity standard deviations on the last 3 elements
      * @return the 6x6 PV covariance matrix
      * @throws OrekitException if the size of the vector is different from 6
      */
     private static double[][] buildPvCovarianceMatrix(final double[] sigmaPV) throws OrekitException {
         // Check the size of the vector first
         if (sigmaPV.length != 6) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH, sigmaPV.length, 6);
 
         }
 
         // Build the PV 6x6 covariance matrix
         final double[][] pvCovarianceMatrix = new double[6][6];
         for (int i = 0; i < sigmaPV.length; i++) {
             pvCovarianceMatrix[i][i] =  sigmaPV[i] * sigmaPV[i];
         }
         return pvCovarianceMatrix;
     }
 
     /** Build a 6x6 PV covariance matrix from two 3-sized vectors (position and velocity standard deviations).
      * Check the sizes of the vectors first.
      * @param sigmaPosition standard deviations of the position (3-size vector)
      * @param sigmaVelocity standard deviations of the velocity (3-size vector)
      * @return the 6x6 PV covariance matrix
      * @throws OrekitException if the vectors do not have the proper sizes
      */
     private static double[][] buildPvCovarianceMatrix(final double[] sigmaPosition,
                                                       final double[] sigmaVelocity)
         throws OrekitException {
 
         // Check the sizes of the vectors first
         if (sigmaPosition.length != 3) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH, sigmaPosition.length, 3);
 
         }
         if (sigmaVelocity.length != 3) {
             throw new OrekitException(LocalizedCoreFormats.DIMENSIONS_MISMATCH, sigmaVelocity.length, 3);
 
         }
 
         // Build the PV 6x6 covariance matrix
         final double[][] pvCovarianceMatrix = new double[6][6];
         for (int i = 0; i < sigmaPosition.length; i++) {
             pvCovarianceMatrix[i][i]         =  sigmaPosition[i] * sigmaPosition[i];
             pvCovarianceMatrix[i + 3][i + 3] =  sigmaVelocity[i] * sigmaVelocity[i];
         }
         return pvCovarianceMatrix;
     }
 }