public class Position extends AbstractMeasurement<Position>
For position-velocity measurement see PV
.
PV
Modifier and Type | Field and Description |
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static String |
MEASUREMENT_TYPE
Type of the measurement.
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Constructor and Description |
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Position(AbsoluteDate date,
Vector3D position,
double[][] covarianceMatrix,
double baseWeight,
ObservableSatellite satellite)
Constructor with full covariance matrix and all inputs.
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Position(AbsoluteDate date,
Vector3D position,
double[] sigmaPosition,
double baseWeight,
ObservableSatellite satellite)
Constructor with one vector for the standard deviation.
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Position(AbsoluteDate date,
Vector3D position,
double sigmaPosition,
double baseWeight,
ObservableSatellite satellite)
Constructor with one double for the standard deviation.
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Modifier and Type | Method and Description |
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double[][] |
getCorrelationCoefficientsMatrix()
Get the correlation coefficients matrix.
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double[][] |
getCovarianceMatrix()
Get the covariance matrix.
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Vector3D |
getPosition()
Get the position.
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protected EstimatedMeasurement<Position> |
theoreticalEvaluation(int iteration,
int evaluation,
SpacecraftState[] states)
Estimate the theoretical value.
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addModifier, addParameterDriver, estimate, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getSatellites, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
getMeasurementType
compareTo
public static final String MEASUREMENT_TYPE
public Position(AbsoluteDate date, 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 measurementpublic Position(AbsoluteDate date, 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 measurementpublic Position(AbsoluteDate date, 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
- 3x3 covariance matrix of the position only measurementbaseWeight
- base weightsatellite
- satellite related to this measurementpublic Vector3D getPosition()
public double[][] getCovarianceMatrix()
public double[][] getCorrelationCoefficientsMatrix()
This is the 3x3 matrix M such that:
Mij = Pij/(σi.σj)
Where:
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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