/* Copyright 2002-2021 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.estimation.measurements.generation;
  
  import org.hipparchus.geometry.euclidean.threed.Vector3D;
  import org.hipparchus.random.CorrelatedRandomVectorGenerator;
  import org.orekit.estimation.measurements.EstimationModifier;
  import org.orekit.estimation.measurements.ObservableSatellite;
  import org.orekit.estimation.measurements.PV;
  import org.orekit.propagation.SpacecraftState;
  import org.orekit.time.AbsoluteDate;
  import org.orekit.utils.ParameterDriver;
  
  
  /** Builder for {@link PV} measurements.
   * @author Luc Maisonobe
   * @since 9.3
   */
  public class PVBuilder extends AbstractMeasurementBuilder<PV> {
  
      /** Simple constructor.
       * @param noiseSource noise source, may be null for generating perfect measurements
       * @param sigmaPosition theoretical standard deviation on position components
       * @param sigmaVelocity theoretical standard deviation on velocity components
       * @param baseWeight base weight
       * @param satellite satellite related to this builder
       */
      public PVBuilder(final CorrelatedRandomVectorGenerator noiseSource,
                       final double sigmaPosition, final double sigmaVelocity,
                       final double baseWeight, final ObservableSatellite satellite) {
          super(noiseSource,
                new double[] {
                    sigmaPosition, sigmaVelocity
                }, new double[] {
                    baseWeight
                }, satellite);
      }
  
      /** {@inheritDoc} */
      @Override
      public PV build(final SpacecraftState[] states) {
  
          final ObservableSatellite satellite = getSatellites()[0];
          final double[] sigma                = getTheoreticalStandardDeviation();
          final double baseWeight             = getBaseWeight()[0];
          final SpacecraftState[] relevant    = new SpacecraftState[] { states[satellite.getPropagatorIndex()] };
  
          // create a dummy measurement
          final PV dummy = new PV(relevant[0].getDate(), Vector3D.NaN, Vector3D.NaN,
                                  sigma[0], sigma[1], baseWeight, satellite);
          for (final EstimationModifier<PV> modifier : getModifiers()) {
              dummy.addModifier(modifier);
          }
  
          // set a reference date for parameters missing one
          for (final ParameterDriver driver : dummy.getParametersDrivers()) {
              if (driver.getReferenceDate() == null) {
                  final AbsoluteDate start = getStart();
                  final AbsoluteDate end   = getEnd();
                  driver.setReferenceDate(start.durationFrom(end) <= 0 ? start : end);
              }
          }
  
          // estimate the perfect value of the measurement
          final double[] pv = dummy.estimate(0, 0, relevant).getEstimatedValue();
  
          // add the noise
          final double[] noise = getNoise();
          if (noise != null) {
              pv[0] += noise[0];
              pv[1] += noise[1];
              pv[2] += noise[2];
              pv[3] += noise[3];
              pv[4] += noise[4];
              pv[5] += noise[5];
          }
  
          // generate measurement
          final PV measurement = new PV(relevant[0].getDate(),
                                        new Vector3D(pv[0], pv[1], pv[2]), new Vector3D(pv[3], pv[4], pv[5]),
                                        sigma[0], sigma[1], baseWeight, satellite);
          for (final EstimationModifier<PV> modifier : getModifiers()) {
              measurement.addModifier(modifier);
          }
          return measurement;
 
     }
 
 }