Package org.orekit.estimation.measurements

Class PV

    • Constructor Detail

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double sigmaPosition,
          double sigmaVelocity,
          double baseWeight)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double, double, double, ObservableSatellite)
        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.

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

        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

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double sigmaPosition,
          double sigmaVelocity,
          double baseWeight,
          int propagatorIndex)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double, double, double, ObservableSatellite)
        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
        propagatorIndex - index of the propagator related to this measurement
        Since:
        9.0

      • PV

        public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.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

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[] sigmaPosition,
          double[] sigmaVelocity,
          double baseWeight)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double[], double, ObservableSatellite)
        Constructor with two vectors for the standard deviations and default value for propagator index.

        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.

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

        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
        Since:
        9.2

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[] sigmaPosition,
          double[] sigmaVelocity,
          double baseWeight,
          int propagatorIndex)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double[], double, ObservableSatellite)
        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
        propagatorIndex - index of the propagator related to this measurement
        Since:
        9.2

      • PV

        public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.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

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[] sigmaPV,
          double baseWeight)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double, ObservableSatellite)
        Constructor with one vector for the standard deviations and default value for propagator index.

        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.

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

        Parameters:
        date - date of the measurement
        position - position
        velocity - velocity
        sigmaPV - 6-sized vector of the standard deviations
        baseWeight - base weight
        Since:
        9.2

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[] sigmaPV,
          double baseWeight,
          int propagatorIndex)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double, ObservableSatellite)
        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
        propagatorIndex - index of the propagator related to this measurement
        Since:
        9.2

      • PV

        public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.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

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[][] positionCovarianceMatrix,
          double[][] velocityCovarianceMatrix,
          double baseWeight)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double[][], double, ObservableSatellite)
        Constructor with 2 smaller covariance matrices and default value for propagator index.

        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.

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

        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
        Since:
        9.2

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[][] positionCovarianceMatrix,
          double[][] velocityCovarianceMatrix,
          double baseWeight,
          int propagatorIndex)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double[][], double, ObservableSatellite)
        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
        propagatorIndex - index of the propagator related to this measurement
        Since:
        9.2

      • PV

        public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.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

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[][] covarianceMatrix,
          double baseWeight)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double, ObservableSatellite)
        Constructor with full covariance matrix but default index for propagator.

        The fact that the covariance matrix is symmetric and positive definite is not checked.

        The measurement must be in the orbit propagation frame.

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

        Parameters:
        date - date of the measurement
        position - position
        velocity - velocity
        covarianceMatrix - 6x6 covariance matrix of the PV measurement
        baseWeight - base weight
        Since:
        9.2

      • PV

        @Deprecated
public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
          double[][] covarianceMatrix,
          double baseWeight,
          int propagatorIndex)
        Deprecated.
        as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double, ObservableSatellite)
        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
        propagatorIndex - index of the propagator related to this measurement
        Since:
        9.2

      • PV

        public PV​(AbsoluteDate date,
          org.hipparchus.geometry.euclidean.threed.Vector3D position,
          org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.geometry.euclidean.threed.Vector3D getPosition()
        Get the position.
        Returns:
        position

      • getVelocity

        public org.hipparchus.geometry.euclidean.threed.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)