org.orekit.estimation.measurements

Class AngularRaDec

java.lang.Object

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

org.orekit.estimation.measurements.AngularRaDec

All Implemented Interfaces:

ObservedMeasurement<AngularRaDec>, TimeStamped

public class AngularRaDec
extends AbstractMeasurement<AngularRaDec>

Class modeling an 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

Constructor Summary

Constructors

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

Method Summary

Modifier and Type	Method and Description
Frame	getReferenceFrame() Get the reference frame in which the right ascension - declination angles are given.
GroundStation	getStation() Get the ground station from which measurement is performed.
protected EstimatedMeasurement<AngularRaDec>	theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states) Estimate the theoretical value.

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

addModifier, estimate, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getPropagatorsIndices, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight

Methods inherited from class java.lang.Object

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

Constructor Detail

AngularRaDec

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

Simple constructor.

This constructor uses 0 as the index of the propagator related to this measurement, thus being well suited for mono-satellite orbit determination.

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

Throws:

OrekitException - if a ParameterDriver name conflict occurs

AngularRaDec

public AngularRaDec(GroundStation station,
                    Frame referenceFrame,
                    AbsoluteDate date,
                    double[] angular,
                    double[] sigma,
                    double[] baseWeight,
                    int propagatorIndex)
             throws OrekitException

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

propagatorIndex - index of the propagator related to this measurement

Throws:

OrekitException - if a ParameterDriver name conflict occurs

Method Detail

getStation

public GroundStation getStation()

Get the ground station from which measurement is performed.

Returns:

ground station from which measurement is performed

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

theoreticalEvaluation

protected EstimatedMeasurement<AngularRaDec> theoreticalEvaluation(int iteration,
                                                                   int evaluation,
                                                                   SpacecraftState[] states)
                                                            throws OrekitException

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

Throws:

OrekitException - if value cannot be computed

See Also:

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