Class Position
- java.lang.Object
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- org.orekit.estimation.measurements.AbstractMeasurement<Position>
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- org.orekit.estimation.measurements.Position
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- All Implemented Interfaces:
Comparable<ComparableMeasurement>
,ComparableMeasurement
,ObservedMeasurement<Position>
,TimeStamped
,ParameterDriversProvider
public class Position extends AbstractMeasurement<Position>
Class modeling a position only measurement.For position-velocity measurement see
PV
.- Since:
- 9.3
- Author:
- Luc Maisonobe
- See Also:
PV
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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 Position(AbsoluteDate date, Vector3D position, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)
Constructor with full covariance matrix and all inputs.Position(AbsoluteDate date, Vector3D position, double[] sigmaPosition, double baseWeight, ObservableSatellite satellite)
Constructor with one vector for the standard deviation.Position(AbsoluteDate date, Vector3D position, double sigmaPosition, double baseWeight, ObservableSatellite satellite)
Constructor with one double for the standard deviation.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description double[][]
getCorrelationCoefficientsMatrix()
Get the correlation coefficients matrix.double[][]
getCovarianceMatrix()
Get the covariance matrix.Vector3D
getPosition()
Get the position.protected EstimatedMeasurement<Position>
theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)
Estimate the theoretical value.protected EstimatedMeasurementBase<Position>
theoreticalEvaluationWithoutDerivatives(int iteration, int evaluation, SpacecraftState[] states)
Estimate the theoretical value without derivatives.-
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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Position
public Position(AbsoluteDate date, Vector3D position, double sigmaPosition, double baseWeight, ObservableSatellite satellite)
Constructor with one double for the standard deviation.The double is the position's standard deviation, common to the 3 position's components.
The measurement must be in the orbit propagation frame.
- Parameters:
date
- date of the measurementposition
- positionsigmaPosition
- theoretical standard deviation on position componentsbaseWeight
- base weightsatellite
- satellite related to this measurement- Since:
- 9.3
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Position
public Position(AbsoluteDate date, Vector3D position, double[] sigmaPosition, double baseWeight, ObservableSatellite satellite)
Constructor with one vector for the standard deviation.The 3-sized vector represents the square root of the diagonal elements of the covariance matrix.
The measurement must be in the orbit propagation frame.
- Parameters:
date
- date of the measurementposition
- positionsigmaPosition
- 3-sized vector of the standard deviations of the positionbaseWeight
- base weightsatellite
- satellite related to this measurement- Since:
- 9.3
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Position
public Position(AbsoluteDate date, Vector3D position, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)
Constructor with full covariance matrix and all inputs.The fact that the covariance matrix is symmetric and positive definite is not checked.
The measurement must be in the orbit propagation frame.
- Parameters:
date
- date of the measurementposition
- positioncovarianceMatrix
- 3x3 covariance matrix of the position only measurementbaseWeight
- base weightsatellite
- satellite related to this measurement- Since:
- 9.3
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Method Detail
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getPosition
public Vector3D getPosition()
Get the position.- Returns:
- position
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getCovarianceMatrix
public double[][] getCovarianceMatrix()
Get the covariance matrix.- Returns:
- the covariance matrix
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getCorrelationCoefficientsMatrix
public double[][] getCorrelationCoefficientsMatrix()
Get the correlation coefficients matrix.This is the 3x3 matrix M such that:
Mij = Pij/(σi.σj)
Where:
- P is the covariance matrix
- σi is the i-th standard deviation (σi² = Pii)
- Returns:
- the correlation coefficient matrix (3x3)
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theoreticalEvaluationWithoutDerivatives
protected EstimatedMeasurementBase<Position> 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<Position>
- 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<Position> 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<Position>
- 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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