org.orekit.estimation.measurements

Class AngularRaDec

java.lang.Object

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

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

org.orekit.estimation.measurements.AngularRaDec

All Implemented Interfaces:

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

public class AngularRaDec
extends GroundReceiverMeasurement<AngularRaDec>

Class modeling a Right Ascension - Declination measurement from a ground point (station, telescope). The angles are given in an inertial reference frame. The motion of the spacecraft during the signal flight time is taken into account. The date of the measurement corresponds to the reception on ground of the reflected signal.

Since:

9.0

Author:

Thierry Ceolin, Maxime Journot

Field Summary

Fields

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

Constructor Summary

Constructors

Constructor and Description
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite) Simple constructor.

Method Summary

Modifier and Type	Method and Description
org.hipparchus.geometry.euclidean.threed.Vector3D	getObservedLineOfSight(Frame outputFrame) Calculate the Line Of Sight of the given measurement.
Frame	getReferenceFrame() Get the reference frame in which the right ascension - declination angles are given.
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.GroundReceiverMeasurement

computeCommonParametersWithDerivatives, computeCommonParametersWithout, getGroundStationCoordinates, getGroundStationPosition, getStation, isTwoWay

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

addModifier, addParameterDriver, estimate, estimateWithoutDerivatives, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getSatellites, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight

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.ObservedMeasurement

getMeasurementType

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

compareTo

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

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

Field Detail

MEASUREMENT_TYPE

public static final String MEASUREMENT_TYPE

Type of the measurement.

See Also:

Constant Field Values

Constructor Detail

AngularRaDec

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

Simple constructor.

Parameters:

station - ground station 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

Method Detail

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 theoretical value does not have any modifiers applied.

Specified by:

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 org.hipparchus.geometry.euclidean.threed.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