Comparable<Position>
, ComparableMeasurement
, ObservedMeasurement<Position>
, TimeStamped
public class Position extends AbstractMeasurement<Position>
For position-velocity measurement see PV
.
PV
Constructor | Description |
---|---|
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[][] positionCovarianceMatrix,
double baseWeight) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double[][], double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[][] covarianceMatrix,
double baseWeight,
int propagatorIndex) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double[][], double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[][] covarianceMatrix,
double baseWeight,
ObservableSatellite satellite) |
Constructor with full covariance matrix and all inputs.
|
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[] sigmaPosition,
double baseWeight) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double[], double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[] sigmaPosition,
double baseWeight,
int propagatorIndex) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double[], double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double[] sigmaPosition,
double baseWeight,
ObservableSatellite satellite) |
Constructor with one vector for the standard deviation.
|
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double sigmaPosition,
double baseWeight) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double, double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double sigmaPosition,
double baseWeight,
int propagatorIndex) |
Deprecated.
as of 9.3, replaced by
Position(AbsoluteDate, Vector3D,
double, double, ObservableSatellite) |
Position(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
double sigmaPosition,
double baseWeight,
ObservableSatellite satellite) |
Constructor with one double for the standard deviation.
|
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.
|
protected EstimatedMeasurement<Position> |
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 Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight)
Position(AbsoluteDate, Vector3D,
double, double, ObservableSatellite)
The 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
- positionsigmaPosition
- theoretical standard deviation on position componentsbaseWeight
- base weight@Deprecated public Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight, int propagatorIndex)
Position(AbsoluteDate, Vector3D,
double, double, ObservableSatellite)
The 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
- positionsigmaPosition
- theoretical standard deviation on position componentsbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight, ObservableSatellite satellite)
The 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
- positionsigmaPosition
- theoretical standard deviation on position componentsbaseWeight
- base weightsatellite
- satellite related to this measurement@Deprecated public Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight)
Position(AbsoluteDate, Vector3D,
double[], double, ObservableSatellite)
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.
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
- positionsigmaPosition
- 3-sized vector of the standard deviations of the positionbaseWeight
- base weight@Deprecated public Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight, int propagatorIndex)
Position(AbsoluteDate, Vector3D,
double[], double, ObservableSatellite)
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.
date
- date of the measurementposition
- positionsigmaPosition
- 3-sized vector of the standard deviations of the positionbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight, ObservableSatellite satellite)
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.
date
- date of the measurementposition
- positionsigmaPosition
- 3-sized vector of the standard deviations of the positionbaseWeight
- base weightsatellite
- satellite related to this measurement@Deprecated public Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[][] positionCovarianceMatrix, double baseWeight)
Position(AbsoluteDate, Vector3D,
double[][], double, ObservableSatellite)
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
- positionpositionCovarianceMatrix
- 3x3 covariance matrix of the positionbaseWeight
- base weight@Deprecated public Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[][] covarianceMatrix, double baseWeight, int propagatorIndex)
Position(AbsoluteDate, 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
- positioncovarianceMatrix
- 6x6 covariance matrix of the PV measurementbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementpublic Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, 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
- positioncovarianceMatrix
- 6x6 covariance matrix of the PV measurementbaseWeight
- base weightsatellite
- satellite related to this measurementpublic org.hipparchus.geometry.euclidean.threed.Vector3D getPosition()
public double[][] getCovarianceMatrix()
public double[][] getCorrelationCoefficientsMatrix()
protected EstimatedMeasurement<Position> theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states)
The theoretical value does not have any modifiers applied.
theoreticalEvaluation
in class AbstractMeasurement<Position>
iteration
- iteration numberevaluation
- evaluation numberstates
- orbital states at measurement dateAbstractMeasurement.estimate(int, int, SpacecraftState[])
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