org.orekit.estimation.measurements

Class Range

java.lang.Object

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

org.orekit.estimation.measurements.Range

All Implemented Interfaces:

ObservedMeasurement<Range>, TimeStamped

public class Range
extends AbstractMeasurement<Range>

Class modeling a range measurement from a ground station.

The measurement is considered to be a signal emitted from a ground station, reflected on spacecraft, and received on the same ground station. Its value is the elapsed time between emission and reception divided by 2c were c is the speed of light. The motion of both the station and the spacecraft during the signal flight time are taken into account. The date of the measurement corresponds to the reception on ground of the reflected signal.

Since:

8.0

Author:

Thierry Ceolin, Luc Maisonobe, Maxime Journot

Constructor Summary

Constructors

Constructor and Description
Range(GroundStation station, AbsoluteDate date, double range, double sigma, double baseWeight) Simple constructor.
Range(GroundStation station, AbsoluteDate date, double range, double sigma, double baseWeight, int propagatorIndex) Simple constructor.

Method Summary

Modifier and Type	Method and Description
GroundStation	getStation() Get the ground station from which measurement is performed.
protected EstimatedMeasurement<Range>	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

Range

public Range(GroundStation station,
             AbsoluteDate date,
             double range,
             double sigma,
             double baseWeight)
      throws OrekitException

Simple constructor.

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

Parameters:

station - ground station from which measurement is performed

date - date of the measurement

range - observed value

sigma - theoretical standard deviation

baseWeight - base weight

Throws:

OrekitException - if a ParameterDriver name conflict occurs

Range

public Range(GroundStation station,
             AbsoluteDate date,
             double range,
             double sigma,
             double baseWeight,
             int propagatorIndex)
      throws OrekitException

Simple constructor.

Parameters:

station - ground station from which measurement is performed

date - date of the measurement

range - observed value

sigma - theoretical standard deviation

baseWeight - base weight

propagatorIndex - index of the propagator related to this measurement

Throws:

OrekitException - if a ParameterDriver name conflict occurs

Since:

9.0

Method Detail

getStation

public GroundStation getStation()

Get the ground station from which measurement is performed.

Returns:

ground station from which measurement is performed

theoreticalEvaluation

protected EstimatedMeasurement<Range> 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<Range>

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[])