org.orekit.estimation.measurements

Class PV

java.lang.Object

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

org.orekit.estimation.measurements.PV

All Implemented Interfaces:

ObservedMeasurement<PV>, TimeStamped

public class PV
extends AbstractMeasurement<PV>

Class modeling a position-velocity state.

Since:

8.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor and Description
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight) Simple constructor.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight, int propagatorIndex) Simple constructor.

Method Summary

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

Methods inherited from class org.orekit.estimation.measurements.AbstractMeasurement

addModifier, estimate, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getPropagatorsIndices, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

PV

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

Simple constructor.

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

public PV(AbsoluteDate date,
          Vector3D position,
          Vector3D velocity,
          double sigmaPosition,
          double sigmaVelocity,
          double baseWeight,
          int propagatorIndex)

Simple constructor.

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

Method Detail

getPosition

public Vector3D getPosition()

Get the position.

Returns:

position

getVelocity

public Vector3D getVelocity()

Get the velocity.

Returns:

velocity

theoreticalEvaluation

protected EstimatedMeasurement<PV> theoreticalEvaluation(int iteration,
                                                         int evaluation,
                                                         SpacecraftState[] states)
                                                  throws OrekitException

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

Throws:

OrekitException - if value cannot be computed

See Also:

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