Package org.orekit.estimation.measurements

Class AngularRaDec

java.lang.Object

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

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

org.orekit.estimation.measurements.AngularMeasurement<AngularRaDec>

org.orekit.estimation.measurements.AngularRaDec

All Implemented Interfaces:

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

public class AngularRaDec
extends AngularMeasurement<AngularRaDec>

Class modeling a Right Ascension - Declination measurement from an optical sensor, typically via astrometry. The angles are given using the axes of an inertial reference frame. The date of the measurement corresponds to the reception of the reflected signal.

Since:

9.0

Author:

Thierry Ceolin, Maxime Journot

Field Summary

Fields

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

Constructor Summary

Constructors

Constructor	Description
AngularRaDec(Observer observer, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor using default light time delay.
AngularRaDec(Observer observer, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, SignalTravelTimeModel signalTravelTimeModel, ObservableSatellite satellite)	Constructor.

Method Summary

Modifier and Type	Method	Description
Vector3D	getObservedLineOfSight(Frame outputFrame)	Calculate the Line Of Sight of the given measurement.
Observer	getObserver()	Getter for the observer.
Frame	getReferenceFrame()	Get the reference frame in which the right ascension - declination angles are given.
GroundStation	getStation()	Deprecated. as of 14.0
protected EstimatedMeasurement<AngularRaDec>	theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)	Estimate the theoretical value.
protected EstimatedMeasurementBase<AngularRaDec>	theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)	Estimate the theoretical value without derivatives.

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

computeEmissionDate, computeEmissionDateField, fillDerivatives, fillEstimatedMeasurement, wrapFirstAngle, wrapFirstAngle

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, getBaseWeight, getCoordinates, getDate, getDimension, getMeasurementQuality, getModifiers, getObservedValue, getParameterIndices, getParametersDrivers, getSatellites, getTheoreticalStandardDeviation, 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, getMeasurementType

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 Detail

MEASUREMENT_TYPE

public static final String MEASUREMENT_TYPE

Type of the measurement.

See Also:

Constant Field Values

Constructor Detail

AngularRaDec

public AngularRaDec(Observer observer,
                    Frame referenceFrame,
                    AbsoluteDate date,
                    double[] angular,
                    double[] sigma,
                    double[] baseWeight,
                    ObservableSatellite satellite)

Simple constructor using default light time delay.

Parameters:

observer - sensor from which measurement is performed

referenceFrame - Reference frame in which the right ascension - declination angles are given

date - date of the measurement

angular - observed value

sigma - theoretical standard deviation

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

AngularRaDec

public AngularRaDec(Observer observer,
                    Frame referenceFrame,
                    AbsoluteDate date,
                    double[] angular,
                    double[] sigma,
                    double[] baseWeight,
                    SignalTravelTimeModel signalTravelTimeModel,
                    ObservableSatellite satellite)

Constructor.

Parameters:

observer - sensor from which measurement is performed

referenceFrame - Reference frame in which the right ascension - declination angles are given

date - date of the measurement

angular - observed value

sigma - theoretical standard deviation

baseWeight - base weight

signalTravelTimeModel - signal travel time model

satellite - satellite related to this measurement

Since:

14.0

Method Detail

getObserver

public Observer getObserver()

Getter for the observer.

Returns:

observer

Since:

14.0

getStation

@Deprecated
public GroundStation getStation()

Deprecated.

as of 14.0

Getter for the ground station.

Returns:

station

getReferenceFrame

public Frame getReferenceFrame()

Get the reference frame in which the right ascension - declination angles are given.

Returns:

reference frame in which the right ascension - declination angles are given

theoreticalEvaluationWithoutDerivatives

protected EstimatedMeasurementBase<AngularRaDec> 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<AngularRaDec>

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<AngularRaDec> 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<AngularRaDec>

Parameters:

iteration - iteration number

evaluation - evaluation number

states - orbital states at measurement date

Returns:

theoretical value

See Also:

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

getObservedLineOfSight

public Vector3D getObservedLineOfSight(Frame outputFrame)

Calculate the Line Of Sight of the given measurement.

Parameters:

outputFrame - output frame of the line of sight vector

Returns:

Vector3D the line of Sight of the measurement

Since:

12.0