Package org.orekit.estimation.measurements.gnss

Class OneWayGNSSRangeRate

java.lang.Object

org.orekit.estimation.measurements.AbstractMeasurement<OneWayGNSSRangeRate>

org.orekit.estimation.measurements.SignalBasedMeasurement<OneWayGNSSRangeRate>

org.orekit.estimation.measurements.gnss.AbstractOneWayGNSS<OneWayGNSSRangeRate>

org.orekit.estimation.measurements.gnss.OneWayGNSSRangeRate

All Implemented Interfaces:

Comparable<ComparableMeasurement>, ComparableMeasurement, ObservedMeasurement<OneWayGNSSRangeRate>, TimeStamped, ParameterDriversProvider

public class OneWayGNSSRangeRate
extends AbstractOneWayGNSS<OneWayGNSSRangeRate>

One-way GNSS range rate measurement.

This class can be used in precise orbit determination applications for modeling a range rate measurement between a GNSS emitter and a LEO satellite (receiver).

The one-way GNSS range rate measurement assumes knowledge of the orbit and the clock offset of the emitting GNSS satellite. For instance, it is possible to use a SP3 file or a GNSS navigation message to recover the satellite's orbit and clock.

This class is very similar to InterSatellitesOneWayRangeRate measurement class. However, using the one-way GNSS range measurement, the orbit and clock of the emitting GNSS satellite are NOT estimated simultaneously with LEO satellite coordinates.

Since:

12.1

Author:

Luc Maisonobe

Field Summary

Fields

Modifier and Type	Field	Description
static final String	MEASUREMENT_TYPE	Type of the measurement.

Constructor Summary

Constructors

Constructor	Description
OneWayGNSSRangeRate(Observer observer, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
OneWayGNSSRangeRate(Observer observer, AbsoluteDate date, double rangeRate, MeasurementQuality measurementQuality, SignalTravelTimeModel signalTravelTimeModel, ObservableSatellite local)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
protected EstimatedMeasurement<OneWayGNSSRangeRate>	theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)	Estimate the theoretical value.
protected EstimatedMeasurementBase<OneWayGNSSRangeRate>	theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)	Estimate the theoretical value without derivatives.

Methods inherited from class org.orekit.estimation.measurements.gnss.AbstractOneWayGNSS

fillDerivatives, getObserver

Methods inherited from class org.orekit.estimation.measurements.SignalBasedMeasurement

getSignalTravelTimeModel, isTwoWay

Methods inherited from class org.orekit.estimation.measurements.AbstractMeasurement

addModifier, addParameterDriver, addParametersDrivers, estimate, estimateWithoutDerivatives, getCoordinates, getDate, getMeasurementQuality, getModifiers, getObservedValue, getParameterIndices, getParametersDrivers, getSatellites, isEnabled, setEnabled, setObservedValue

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.estimation.measurements.ComparableMeasurement

compareTo

Methods inherited from interface org.orekit.estimation.measurements.ObservedMeasurement

estimateWithoutDerivatives, getBaseWeight, getDimension, getMeasurementType, getTheoreticalStandardDeviation

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom

Field Details

MEASUREMENT_TYPE

public static final String MEASUREMENT_TYPE

Type of the measurement.

See Also:

• Constant Field Values

Constructor Details

OneWayGNSSRangeRate

public OneWayGNSSRangeRate(Observer observer,
 AbsoluteDate date,
 double rangeRate,
 double sigma,
 double baseWeight,
 ObservableSatellite local)

Simple constructor.

Parameters:

observer - object that sends GNSS signal

date - date of the measurement

rangeRate - observed value

sigma - theoretical standard deviation

baseWeight - base weight

local - satellite which receives the signal and perform the measurement

Since:

12.1

OneWayGNSSRangeRate

public OneWayGNSSRangeRate(Observer observer,
 AbsoluteDate date,
 double rangeRate,
 MeasurementQuality measurementQuality,
 SignalTravelTimeModel signalTravelTimeModel,
 ObservableSatellite local)

Simple constructor.

Parameters:

observer - object that sends GNSS signal

date - date of the measurement

rangeRate - observed value

measurementQuality - measurement quality data as used in orbit determination

signalTravelTimeModel - signal model

local - satellite which receives the signal and perform the measurement

Since:

14.0

Method Details

theoreticalEvaluationWithoutDerivatives

protected EstimatedMeasurementBase<OneWayGNSSRangeRate> theoreticalEvaluationWithoutDerivatives(int iteration,
 int evaluation,
 SpacecraftState[] states)

Estimate the theoretical value without derivatives. The default implementation uses the computation with derivatives and ought to be overwritten for performance.

The theoretical value does not have any modifiers applied.

Overrides:

theoreticalEvaluationWithoutDerivatives in class AbstractMeasurement<OneWayGNSSRangeRate>

Parameters:

iteration - iteration number

evaluation - evaluation number

states - orbital states at measurement date

Returns:

theoretical value

See Also:

• AbstractMeasurement.estimate(int, int, SpacecraftState[])

theoreticalEvaluation

protected EstimatedMeasurement<OneWayGNSSRangeRate> theoreticalEvaluation(int iteration,
 int evaluation,
 SpacecraftState[] states)

Estimate the theoretical value.

The theoretical value does not have any modifiers applied.

Specified by:

theoreticalEvaluation in class AbstractMeasurement<OneWayGNSSRangeRate>

Parameters:

iteration - iteration number

evaluation - evaluation number

states - orbital states at measurement date

Returns:

theoretical value

See Also:

• AbstractMeasurement.estimate(int, int, SpacecraftState[])