InterSatellitesRange.java

  1. /* Copyright 2002-2020 CS Group
  2.  * Licensed to CS Group (CS) under one or more
  3.  * contributor license agreements.  See the NOTICE file distributed with
  4.  * this work for additional information regarding copyright ownership.
  5.  * CS licenses this file to You under the Apache License, Version 2.0
  6.  * (the "License"); you may not use this file except in compliance with
  7.  * the License.  You may obtain a copy of the License at
  8.  *
  9.  *   http://www.apache.org/licenses/LICENSE-2.0
  10.  *
  11.  * Unless required by applicable law or agreed to in writing, software
  12.  * distributed under the License is distributed on an "AS IS" BASIS,
  13.  * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
  14.  * See the License for the specific language governing permissions and
  15.  * limitations under the License.
  16.  */
  17. package org.orekit.estimation.measurements;

  19. import java.util.Arrays;
  20. import java.util.HashMap;
  21. import java.util.Map;

  23. import org.hipparchus.analysis.differentiation.DSFactory;
  24. import org.hipparchus.analysis.differentiation.DerivativeStructure;
  25. import org.orekit.propagation.SpacecraftState;
  26. import org.orekit.time.AbsoluteDate;
  27. import org.orekit.time.FieldAbsoluteDate;
  28. import org.orekit.utils.Constants;
  29. import org.orekit.utils.ParameterDriver;
  30. import org.orekit.utils.TimeStampedFieldPVCoordinates;
  31. import org.orekit.utils.TimeStampedPVCoordinates;

  33. /** One-way or two-way range measurements between two satellites.
  34.  * <p>
  35.  * For one-way measurements, a signal is emitted by a remote satellite and received
  36.  * by local satellite. The measurement value is the elapsed time between emission
  37.  * and reception multiplied by c where c is the speed of light.
  38.  * </p>
  39.  * <p>
  40.  * For two-way measurements, a signal is emitted by local satellite, reflected on
  41.  * remote satellite, and received back by local satellite. The measurement value
  42.  * is the elapsed time between emission and reception multiplied by c/2 where c
  43.  * is the speed of light.
  44.  * </p>
  45.  * <p>
  46.  * Since 9.3, this class also uses the clock offsets of both satellites,
  47.  * which manage the value that must be added to each satellite reading of time to
  48.  * compute the real physical date. In this measurement, these offsets have two effects:
  49.  * </p>
  50.  * <ul>
  51.  *   <li>as measurement date is evaluated at reception time, the real physical date
  52.  *   of the measurement is the observed date to which the local satellite clock
  53.  *   offset is subtracted</li>
  54.  *   <li>as range is evaluated using the total signal time of flight, for one-way
  55.  *   measurements the observed range is the real physical signal time of flight to
  56.  *   which (Δtl - Δtr) ⨉ c is added, where Δtl (resp. Δtr) is the clock offset for the
  57.  *   local satellite (resp. remote satellite). A similar effect exists in
  58.  *   two-way measurements but it is computed as (Δtl - Δtl) ⨉ c / 2 as the local satellite
  59.  *   clock is used for both initial emission and final reception and therefore it evaluates
  60.  *   to zero.</li>
  61.  * </ul>
  62.  * <p>
  63.  * The motion of both satellites during the signal flight time is
  64.  * taken into account. The date of the measurement corresponds to
  65.  * the reception of the signal by satellite 1.
  66.  * </p>
  67.  * @author Luc Maisonobe
  68.  * @since 9.0
  69.  */
  70. public class InterSatellitesRange extends AbstractMeasurement<InterSatellitesRange> {

  72.     /** Flag indicating whether it is a two-way measurement. */
  73.     private final boolean twoway;

  75.     /** Simple constructor.
  76.      * @param local satellite which receives the signal and performs the measurement
  77.      * @param remote satellite which simply emits the signal in the one-way case,
  78.      * or reflects the signal in the two-way case
  79.      * @param twoWay flag indicating whether it is a two-way measurement
  80.      * @param date date of the measurement
  81.      * @param range observed value
  82.      * @param sigma theoretical standard deviation
  83.      * @param baseWeight base weight
  84.      * @since 9.3
  85.      */
  86.     public InterSatellitesRange(final ObservableSatellite local,
  87.                                 final ObservableSatellite remote,
  88.                                 final boolean twoWay,
  89.                                 final AbsoluteDate date, final double range,
  90.                                 final double sigma, final double baseWeight) {
  91.         super(date, range, sigma, baseWeight, Arrays.asList(local, remote));
  92.         this.twoway = twoWay;
  93.     }

  95.     /** Check if the instance represents a two-way measurement.
  96.      * @return true if the instance represents a two-way measurement
  97.      */
  98.     public boolean isTwoWay() {
  99.         return twoway;
  100.     }

  102.     /** {@inheritDoc} */
  103.     @Override
  104.     protected EstimatedMeasurement<InterSatellitesRange> theoreticalEvaluation(final int iteration,
  105.                                                                                final int evaluation,
  106.                                                                                final SpacecraftState[] states) {

  108.         // Range derivatives are computed with respect to spacecrafts states in inertial frame
  109.         // ----------------------
  110.         //
  111.         // Parameters:
  112.         //  - 0..2  - Position of the receiver satellite in inertial frame
  113.         //  - 3..5  - Velocity of the receiver satellite in inertial frame
  114.         //  - 6..8  - Position of the remote satellite in inertial frame
  115.         //  - 9..11 - Velocity of the remote satellite in inertial frame
  116.         //  - 12..  - Measurement parameters: local clock offset, remote clock offset...
  117.         int nbParams = 12;
  118.         final Map<String, Integer> indices = new HashMap<>();
  119.         for (ParameterDriver driver : getParametersDrivers()) {
  120.             if (driver.isSelected()) {
  121.                 indices.put(driver.getName(), nbParams++);
  122.             }
  123.         }
  124.         final DSFactory factory = new DSFactory(nbParams, 1);

  126.         // coordinates of both satellites
  127.         final SpacecraftState local = states[0];
  128.         final TimeStampedFieldPVCoordinates<DerivativeStructure> pvaL = getCoordinates(local, 0, factory);
  129.         final SpacecraftState remote = states[1];
  130.         final TimeStampedFieldPVCoordinates<DerivativeStructure> pvaR = getCoordinates(remote, 6, factory);

  132.         // compute propagation times
  133.         // (if state has already been set up to pre-compensate propagation delay,
  134.         //  we will have delta == tauD and transitState will be the same as state)

  136.         // downlink delay
  137.         final DerivativeStructure dtl = getSatellites().get(0).getClockOffsetDriver().getValue(factory, indices);
  138.         final FieldAbsoluteDate<DerivativeStructure> arrivalDate =
  139.                         new FieldAbsoluteDate<DerivativeStructure>(getDate(), dtl.negate());

  141.         final TimeStampedFieldPVCoordinates<DerivativeStructure> s1Downlink =
  142.                         pvaL.shiftedBy(arrivalDate.durationFrom(pvaL.getDate()));
  143.         final DerivativeStructure tauD = signalTimeOfFlight(pvaR, s1Downlink.getPosition(), arrivalDate);

  145.         // Transit state
  146.         final double              delta      = getDate().durationFrom(remote.getDate());
  147.         final DerivativeStructure deltaMTauD = tauD.negate().add(delta);

  149.         // prepare the evaluation
  150.         final EstimatedMeasurement<InterSatellitesRange> estimated;

  152.         final DerivativeStructure range;
  153.         if (twoway) {
  154.             // Transit state (re)computed with derivative structures
  155.             final TimeStampedFieldPVCoordinates<DerivativeStructure> transitStateDS = pvaR.shiftedBy(deltaMTauD);

  157.             // uplink delay
  158.             final DerivativeStructure tauU = signalTimeOfFlight(pvaL,
  159.                                                                 transitStateDS.getPosition(),
  160.                                                                 transitStateDS.getDate());
  161.             estimated = new EstimatedMeasurement<>(this, iteration, evaluation,
  162.                                                    new SpacecraftState[] {
  163.                                                        local.shiftedBy(deltaMTauD.getValue()),
  164.                                                        remote.shiftedBy(deltaMTauD.getValue())
  165.                                                    }, new TimeStampedPVCoordinates[] {
  166.                                                        local.shiftedBy(delta - tauD.getValue() - tauU.getValue()).getPVCoordinates(),
  167.                                                        remote.shiftedBy(delta - tauD.getValue()).getPVCoordinates(),
  168.                                                        local.shiftedBy(delta).getPVCoordinates()
  169.                                                    });

  171.             // Range value
  172.             range  = tauD.add(tauU).multiply(0.5 * Constants.SPEED_OF_LIGHT);

  174.         } else {

  176.             estimated = new EstimatedMeasurement<>(this, iteration, evaluation,
  177.                                                    new SpacecraftState[] {
  178.                                                        local.shiftedBy(deltaMTauD.getValue()),
  179.                                                        remote.shiftedBy(deltaMTauD.getValue())
  180.                                                    }, new TimeStampedPVCoordinates[] {
  181.                                                        remote.shiftedBy(delta - tauD.getValue()).getPVCoordinates(),
  182.                                                        local.shiftedBy(delta).getPVCoordinates()
  183.                                                    });

  185.             // Clock offsets
  186.             final DerivativeStructure dtr = getSatellites().get(1).getClockOffsetDriver().getValue(factory, indices);

  188.             // Range value
  189.             range  = tauD.add(dtl).subtract(dtr).multiply(Constants.SPEED_OF_LIGHT);

  191.         }
  192.         estimated.setEstimatedValue(range.getValue());

  194.         // Range partial derivatives with respect to states
  195.         final double[] derivatives = range.getAllDerivatives();
  196.         estimated.setStateDerivatives(0, Arrays.copyOfRange(derivatives, 1,  7));
  197.         estimated.setStateDerivatives(1, Arrays.copyOfRange(derivatives, 7, 13));

  199.         return estimated;

  201.     }

  203. }
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