Comparable<PV>
, ComparableMeasurement
, ObservedMeasurement<PV>
, TimeStamped
public class PV extends AbstractMeasurement<PV>
For position-only measurement see Position
.
Position
Constructor | Description |
---|---|
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) |
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) |
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) |
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.
|
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) |
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.
|
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) |
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) |
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) |
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.
|
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) |
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.
|
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) |
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) |
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.
|
Modifier and Type | Method | Description |
---|---|---|
double[][] |
getCorrelationCoefficientsMatrix() |
Get the correlation coefficients matrix.
|
double[][] |
getCovarianceMatrix() |
Get the covariance matrix.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
getPosition() |
Get the position.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
getVelocity() |
Get the velocity.
|
protected EstimatedMeasurement<PV> |
theoreticalEvaluation(int iteration,
int evaluation,
SpacecraftState[] states) |
Estimate the theoretical value.
|
addModifier, addParameterDriver, estimate, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getPropagatorsIndices, getSatellites, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight
compareTo
@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double, double, double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- theoretical standard deviation on position componentssigmaVelocity
- theoretical standard deviation on velocity componentsbaseWeight
- base weight@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double, double, double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- theoretical standard deviation on position componentssigmaVelocity
- theoretical standard deviation on velocity componentsbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic 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)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- theoretical standard deviation on position componentssigmaVelocity
- theoretical standard deviation on velocity componentsbaseWeight
- base weightsatellite
- satellite related to this measurement@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[], double[], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- 3-sized vector of the standard deviations of the positionsigmaVelocity
- 3-sized vector of the standard deviations of the velocitybaseWeight
- base weight@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[], double[], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- 3-sized vector of the standard deviations of the positionsigmaVelocity
- 3-sized vector of the standard deviations of the velocitybaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic 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)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPosition
- 3-sized vector of the standard deviations of the positionsigmaVelocity
- 3-sized vector of the standard deviations of the velocitybaseWeight
- base weightsatellite
- satellite related to this measurement@Deprecated public PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPV, double baseWeight)
PV(AbsoluteDate, Vector3D, Vector3D,
double[], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPV
- 6-sized vector of the standard deviationsbaseWeight
- base weight@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPV
- 6-sized vector of the standard deviationsbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPV, double baseWeight, ObservableSatellite satellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitysigmaPV
- 6-sized vector of the standard deviationsbaseWeight
- base weightsatellite
- satellite related to this measurement@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[][], double[][], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitypositionCovarianceMatrix
- 3x3 covariance matrix of the positionvelocityCovarianceMatrix
- 3x3 covariance matrix of the velocitybaseWeight
- base weight@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[][], double[][], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitypositionCovarianceMatrix
- 3x3 covariance matrix of the positionvelocityCovarianceMatrix
- 3x3 covariance matrix of the velocitybaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic 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)
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.
date
- date of the measurementposition
- positionvelocity
- velocitypositionCovarianceMatrix
- 3x3 covariance matrix of the positionvelocityCovarianceMatrix
- 3x3 covariance matrix of the velocitybaseWeight
- base weightsatellite
- satellite related to this measurement@Deprecated public PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] covarianceMatrix, double baseWeight)
PV(AbsoluteDate, Vector3D, Vector3D,
double[][], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionvelocity
- velocitycovarianceMatrix
- 6x6 covariance matrix of the PV measurementbaseWeight
- base weight@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)
PV(AbsoluteDate, Vector3D, Vector3D,
double[][], double, ObservableSatellite)
The fact that the covariance matrix is symmetric and positive definite is not checked.
The measurement must be in the orbit propagation frame.
date
- date of the measurementposition
- positionvelocity
- velocitycovarianceMatrix
- 6x6 covariance matrix of the PV measurementbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)
The fact that the covariance matrix is symmetric and positive definite is not checked.
The measurement must be in the orbit propagation frame.
date
- date of the measurementposition
- positionvelocity
- velocitycovarianceMatrix
- 6x6 covariance matrix of the PV measurementbaseWeight
- base weightsatellite
- satellite related to this measurementpublic org.hipparchus.geometry.euclidean.threed.Vector3D getPosition()
public org.hipparchus.geometry.euclidean.threed.Vector3D getVelocity()
public double[][] getCovarianceMatrix()
public double[][] getCorrelationCoefficientsMatrix()
protected EstimatedMeasurement<PV> theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)
The theoretical value does not have any modifiers applied.
theoreticalEvaluation
in class AbstractMeasurement<PV>
iteration
- iteration numberevaluation
- evaluation numberstates
- orbital states at measurement dateAbstractMeasurement.estimate(int, int, SpacecraftState[])
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