Class AngularRaDec
- java.lang.Object
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- org.orekit.estimation.measurements.AbstractMeasurement<T>
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- org.orekit.estimation.measurements.GroundReceiverMeasurement<AngularRaDec>
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- org.orekit.estimation.measurements.AngularRaDec
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- 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
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Field Summary
Fields Modifier and Type Field Description static String
MEASUREMENT_TYPE
Type of the measurement.
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Constructor Summary
Constructors Constructor Description AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description 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
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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, signalTimeOfFlight, signalTimeOfFlight, signalTimeOfFlight, signalTimeOfFlight
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.estimation.measurements.ComparableMeasurement
compareTo
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Methods inherited from interface org.orekit.estimation.measurements.ObservedMeasurement
estimateWithoutDerivatives, getMeasurementType
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Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Methods inherited from interface org.orekit.time.TimeStamped
durationFrom
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Field Detail
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MEASUREMENT_TYPE
public static final String MEASUREMENT_TYPE
Type of the measurement.- See Also:
- Constant Field Values
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Constructor Detail
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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 performedreferenceFrame
- Reference frame in which the right ascension - declination angles are givendate
- date of the measurementangular
- observed valuesigma
- theoretical standard deviationbaseWeight
- base weightsatellite
- satellite related to this measurement- Since:
- 9.3
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Method Detail
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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
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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 classAbstractMeasurement<AngularRaDec>
- Parameters:
iteration
- iteration numberevaluation
- evaluation numberstates
- orbital states at measurement date- Returns:
- theoretical value
- See Also:
AbstractMeasurement.estimate(int, int, SpacecraftState[])
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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 classAbstractMeasurement<AngularRaDec>
- Parameters:
iteration
- iteration numberevaluation
- evaluation numberstates
- orbital states at measurement date- Returns:
- theoretical value
- See Also:
AbstractMeasurement.estimate(int, int, SpacecraftState[])
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