Package org.orekit.estimation.measurements

Class PV

java.lang.Object

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

org.orekit.estimation.measurements.PV

All Implemented Interfaces:

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

public class PV
extends AbstractMeasurement<PV>

Class modeling a position-velocity measurement.

For position-only measurement see Position.

Since:

8.0

Author:

Luc Maisonobe

See Also:

Position

Field Summary

Fields

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

Constructor Summary

Constructors

Constructor	Description
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[][] positionCovarianceMatrix, double[][] velocityCovarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with 2 smaller covariance matrices.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with full covariance matrix and all inputs.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[] sigmaPosition, double[] sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two vectors for the standard deviations.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[] sigmaPV, double baseWeight, ObservableSatellite satellite)	Constructor with one vector for the standard deviations.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two double for the standard deviations.

Method Summary

Modifier and Type	Method	Description
double[][]	getCorrelationCoefficientsMatrix()	Get the correlation coefficients matrix.
double[][]	getCovarianceMatrix()	Get the covariance matrix.
Vector3D	getPosition()	Get the position.
Vector3D	getVelocity()	Get the velocity.
protected EstimatedMeasurement<PV>	theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)	Estimate the theoretical value.
protected EstimatedMeasurementBase<PV>	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

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

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

PV

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          double sigmaPosition,
          double sigmaVelocity,
          double baseWeight,
          ObservableSatellite satellite)

Constructor with two double for the standard deviations.

The first double is the position's standard deviation, common to the 3 position's components. The second 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 measurement

position - position

velocity - velocity

sigmaPosition - theoretical standard deviation on position components

sigmaVelocity - theoretical standard deviation on velocity components

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

PV

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          double[] sigmaPosition,
          double[] sigmaVelocity,
          double baseWeight,
          ObservableSatellite satellite)

Constructor with two vectors for the standard deviations.

One 3-sized vectors for position standard deviations. One 3-sized vectors for velocity standard deviations. The 3-sized vectors are 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 measurement

position - position

velocity - velocity

sigmaPosition - 3-sized vector of the standard deviations of the position

sigmaVelocity - 3-sized vector of the standard deviations of the velocity

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

PV

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          double[] sigmaPV,
          double baseWeight,
          ObservableSatellite satellite)

Constructor with one vector for the standard deviations.

The 6-sized vector is 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 measurement

position - position

velocity - velocity

sigmaPV - 6-sized vector of the standard deviations

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

PV

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          double[][] positionCovarianceMatrix,
          double[][] velocityCovarianceMatrix,
          double baseWeight,
          ObservableSatellite satellite)

Constructor with 2 smaller covariance matrices.

One 3x3 covariance matrix for position and one 3x3 covariance matrix for velocity. The fact that the covariance matrices are symmetric and positive definite is not checked.

The measurement must be in the orbit propagation frame.

Parameters:

date - date of the measurement

position - position

velocity - velocity

positionCovarianceMatrix - 3x3 covariance matrix of the position

velocityCovarianceMatrix - 3x3 covariance matrix of the velocity

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

PV

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          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 measurement

position - position

velocity - velocity

covarianceMatrix - 6x6 covariance matrix of the PV measurement

baseWeight - base weight

satellite - satellite related to this measurement

Since:

9.3

Method Detail

getPosition

public Vector3D getPosition()

Get the position.

Returns:

position

getVelocity

public Vector3D getVelocity()

Get the velocity.

Returns:

velocity

getCovarianceMatrix

public double[][] getCovarianceMatrix()

Get the covariance matrix.

Returns:

the covariance matrix

getCorrelationCoefficientsMatrix

public double[][] getCorrelationCoefficientsMatrix()

Get the correlation coefficients matrix.

This is the 6x6 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 (6x6)

theoreticalEvaluationWithoutDerivatives

protected EstimatedMeasurementBase<PV> 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<PV>

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<PV> 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<PV>

Parameters:

iteration - iteration number

evaluation - evaluation number

states - orbital states at measurement date

Returns:

theoretical value

See Also:

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