Range.java
/* 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.estimation.measurements;
import java.util.Arrays;
import org.hipparchus.analysis.differentiation.Gradient;
import org.orekit.propagation.SpacecraftState;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.Constants;
import org.orekit.utils.ParameterDriver;
import org.orekit.utils.TimeSpanMap.Span;
import org.orekit.utils.TimeStampedFieldPVCoordinates;
import org.orekit.utils.TimeStampedPVCoordinates;
/** Class modeling a range measurement from a ground station.
* <p>
* For one-way measurements, a signal is emitted by the satellite
* and received by the ground station. The measurement value is the
* elapsed time between emission and reception multiplied by c where
* c is the speed of light.
* </p>
* <p>
* For two-way measurements, the measurement is considered to be a signal
* emitted from a ground station, reflected on spacecraft, and received
* on the same ground station. Its value is the elapsed time between
* emission and reception multiplied by c/2 where c is the speed of light.
* </p>
* <p>
* The motion of both the station and the spacecraft during the signal
* flight time are taken into account. The date of the measurement
* corresponds to the reception on ground of the emitted or reflected signal.
* </p>
* <p>
* The clock offsets of both the ground station and the satellite are taken
* into account. These offsets correspond to the values that must be subtracted
* from station (resp. satellite) reading of time to compute the real physical
* date. These offsets have two effects:
* </p>
* <ul>
* <li>as measurement date is evaluated at reception time, the real physical date
* of the measurement is the observed date to which the receiving ground station
* clock offset is subtracted</li>
* <li>as range is evaluated using the total signal time of flight, for one-way
* measurements the observed range is the real physical signal time of flight to
* which (Δtg - Δts) ⨯ c is added, where Δtg (resp. Δts) is the clock offset for the
* receiving ground station (resp. emitting satellite). A similar effect exists in
* two-way measurements but it is computed as (Δtg - Δtg) ⨯ c / 2 as the same ground
* station clock is used for initial emission and final reception and therefore it evaluates
* to zero.</li>
* </ul>
* @author Thierry Ceolin
* @author Luc Maisonobe
* @author Maxime Journot
* @since 8.0
*/
public class Range extends GroundReceiverMeasurement<Range> {
/** Type of the measurement. */
public static final String MEASUREMENT_TYPE = "Range";
/** Simple constructor.
* @param station ground station from which measurement is performed
* @param twoWay flag indicating whether it is a two-way measurement
* @param date date of the measurement
* @param range observed value
* @param sigma theoretical standard deviation
* @param baseWeight base weight
* @param satellite satellite related to this measurement
* @since 9.3
*/
public Range(final GroundStation station, final boolean twoWay, final AbsoluteDate date,
final double range, final double sigma, final double baseWeight,
final ObservableSatellite satellite) {
super(station, twoWay, date, range, sigma, baseWeight, satellite);
}
/** {@inheritDoc} */
@Override
protected EstimatedMeasurementBase<Range> theoreticalEvaluationWithoutDerivatives(final int iteration,
final int evaluation,
final SpacecraftState[] states) {
final GroundReceiverCommonParametersWithoutDerivatives common = computeCommonParametersWithout(states[0]);
final TimeStampedPVCoordinates transitPV = common.getTransitState().getPVCoordinates();
// prepare the evaluation
final EstimatedMeasurementBase<Range> estimated;
final double range;
if (isTwoWay()) {
// Station at transit state date (derivatives of tauD taken into account)
final TimeStampedPVCoordinates stationAtTransitDate = common.getStationDownlink().shiftedBy(-common.getTauD());
// Uplink delay
final double tauU = signalTimeOfFlightAdjustableEmitter(stationAtTransitDate, transitPV.getPosition(),
transitPV.getDate(), common.getState().getFrame());
final TimeStampedPVCoordinates stationUplink = common.getStationDownlink().shiftedBy(-common.getTauD() - tauU);
// Prepare the evaluation
estimated = new EstimatedMeasurementBase<>(this, iteration, evaluation,
new SpacecraftState[] {
common.getTransitState()
}, new TimeStampedPVCoordinates[] {
stationUplink,
transitPV,
common.getStationDownlink()
});
// Range value
final double cOver2 = 0.5 * Constants.SPEED_OF_LIGHT;
final double tau = common.getTauD() + tauU;
range = tau * cOver2;
} else {
estimated = new EstimatedMeasurementBase<>(this, iteration, evaluation,
new SpacecraftState[] {
common.getTransitState()
}, new TimeStampedPVCoordinates[] {
transitPV,
common.getStationDownlink()
});
// Clock offsets
final ObservableSatellite satellite = getSatellites().get(0);
final double dts = satellite.getClockOffsetDriver().getValue(common.getState().getDate());
final double dtg = getStation().getClockOffsetDriver().getValue(common.getState().getDate());
// Range value
range = (common.getTauD() + dtg - dts) * Constants.SPEED_OF_LIGHT;
}
estimated.setEstimatedValue(range);
return estimated;
}
/** {@inheritDoc} */
@Override
protected EstimatedMeasurement<Range> theoreticalEvaluation(final int iteration,
final int evaluation,
final SpacecraftState[] states) {
final SpacecraftState state = states[0];
// Range derivatives are computed with respect to spacecraft state in inertial frame
// and station parameters
// ----------------------
//
// Parameters:
// - 0..2 - Position of the spacecraft in inertial frame
// - 3..5 - Velocity of the spacecraft in inertial frame
// - 6..n - measurements parameters (clock offset, station offsets, pole, prime meridian, sat clock offset...)
final GroundReceiverCommonParametersWithDerivatives common = computeCommonParametersWithDerivatives(state);
final int nbParams = common.getTauD().getFreeParameters();
final TimeStampedFieldPVCoordinates<Gradient> transitPV = common.getTransitPV();
// prepare the evaluation
final EstimatedMeasurement<Range> estimated;
final Gradient range;
if (isTwoWay()) {
// Station at transit state date (derivatives of tauD taken into account)
final TimeStampedFieldPVCoordinates<Gradient> stationAtTransitDate =
common.getStationDownlink().shiftedBy(common.getTauD().negate());
// Uplink delay
final Gradient tauU =
signalTimeOfFlightAdjustableEmitter(stationAtTransitDate, transitPV.getPosition(), transitPV.getDate(),
state.getFrame());
final TimeStampedFieldPVCoordinates<Gradient> stationUplink =
common.getStationDownlink().shiftedBy(-common.getTauD().getValue() - tauU.getValue());
// Prepare the evaluation
estimated = new EstimatedMeasurement<Range>(this, iteration, evaluation,
new SpacecraftState[] {
common.getTransitState()
}, new TimeStampedPVCoordinates[] {
stationUplink.toTimeStampedPVCoordinates(),
transitPV.toTimeStampedPVCoordinates(),
common.getStationDownlink().toTimeStampedPVCoordinates()
});
// Range value
final double cOver2 = 0.5 * Constants.SPEED_OF_LIGHT;
final Gradient tau = common.getTauD().add(tauU);
range = tau.multiply(cOver2);
} else {
estimated = new EstimatedMeasurement<Range>(this, iteration, evaluation,
new SpacecraftState[] {
common.getTransitState()
}, new TimeStampedPVCoordinates[] {
transitPV.toTimeStampedPVCoordinates(),
common.getStationDownlink().toTimeStampedPVCoordinates()
});
// Clock offsets
final ObservableSatellite satellite = getSatellites().get(0);
final Gradient dts = satellite.getClockOffsetDriver().getValue(nbParams, common.getIndices(), state.getDate());
final Gradient dtg = getStation().getClockOffsetDriver().getValue(nbParams, common.getIndices(), state.getDate());
// Range value
range = common.getTauD().add(dtg).subtract(dts).multiply(Constants.SPEED_OF_LIGHT);
}
estimated.setEstimatedValue(range.getValue());
// Range first order derivatives with respect to state
final double[] derivatives = range.getGradient();
estimated.setStateDerivatives(0, Arrays.copyOfRange(derivatives, 0, 6));
// Set first order derivatives with respect to parameters
for (final ParameterDriver driver : getParametersDrivers()) {
for (Span<String> span = driver.getNamesSpanMap().getFirstSpan(); span != null; span = span.next()) {
final Integer index = common.getIndices().get(span.getData());
if (index != null) {
estimated.setParameterDerivatives(driver, span.getStart(), derivatives[index]);
}
}
}
return estimated;
}
}