Comparable<AngularRaDec>
, ComparableMeasurement
, ObservedMeasurement<AngularRaDec>
, TimeStamped
public class AngularRaDec extends AbstractMeasurement<AngularRaDec>
Constructor | Description |
---|---|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight) |
Simple constructor.
|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
int propagatorIndex) |
Simple constructor.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
getReferenceFrame() |
Get the reference frame in which the right ascension - declination angles are given.
|
GroundStation |
getStation() |
Get the ground station from which measurement is performed.
|
protected EstimatedMeasurement<AngularRaDec> |
theoreticalEvaluation(int iteration,
int evaluation,
SpacecraftState[] states) |
Estimate the theoretical value.
|
addModifier, estimate, getBaseWeight, getCoordinates, getDate, getDimension, getModifiers, getObservedValue, getParametersDrivers, getPropagatorsIndices, getTheoreticalStandardDeviation, isEnabled, setEnabled, signalTimeOfFlight, signalTimeOfFlight
compareTo
public AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight) throws OrekitException
This constructor uses 0 as the index of the propagator related to this measurement, thus being well suited for mono-satellite orbit determination.
station
- ground station from which measurement is performedreferenceFrame
- Reference frame in which the right ascension - declination angles are givendate
- date of the measurementangular
- observed valuesigma
- theoretical standard deviationbaseWeight
- base weightOrekitException
- if a ParameterDriver
name conflict occurspublic AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, int propagatorIndex) throws OrekitException
station
- ground station from which measurement is performedreferenceFrame
- Reference frame in which the right ascension - declination angles are givendate
- date of the measurementangular
- observed valuesigma
- theoretical standard deviationbaseWeight
- base weightpropagatorIndex
- index of the propagator related to this measurementOrekitException
- if a ParameterDriver
name conflict occurspublic GroundStation getStation()
public Frame getReferenceFrame()
protected EstimatedMeasurement<AngularRaDec> theoreticalEvaluation(int iteration, int evaluation, SpacecraftState[] states) throws OrekitException
The theoretical value does not have any modifiers applied.
theoreticalEvaluation
in class AbstractMeasurement<AngularRaDec>
iteration
- iteration numberevaluation
- evaluation numberstates
- orbital states at measurement dateOrekitException
- if value cannot be computedAbstractMeasurement.estimate(int, int, SpacecraftState[])
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