Package org.orekit.propagation.conversion

Class EphemerisPropagatorBuilder

java.lang.Object

org.orekit.propagation.conversion.AbstractPropagatorBuilder<Ephemeris>

org.orekit.propagation.conversion.EphemerisPropagatorBuilder

All Implemented Interfaces:

Cloneable, PropagatorBuilder

public class EphemerisPropagatorBuilder
extends AbstractPropagatorBuilder<Ephemeris>

Builder for Ephemeris propagator.

Since:

11.3

Author:

Bryan Cazabonne, Vincent Cucchietti

Constructor Summary

Constructors

Constructor	Description
EphemerisPropagatorBuilder(List<SpacecraftState> states, int interpolationPoints, double extrapolationThreshold, AttitudeProvider attitudeProvider)	Constructor.
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator)	Constructor using the default attitude provider.
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)	Constructor with covariances and default attitude provider.
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider)	Constructor.
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, AttitudeProvider attitudeProvider)	Constructor.

Method Summary

Modifier and Type	Method	Description
AbstractBatchLSModel	buildLeastSquaresModel(PropagatorBuilder[] builders, List<ObservedMeasurement<?>> measurements, ParameterDriversList estimatedMeasurementsParameters, ModelObserver observer)	Build a new batch least squares model.
Ephemeris	buildPropagator(double[] normalizedParameters)	Build a propagator.
EphemerisPropagatorBuilder	clone()	.

Methods inherited from class org.orekit.propagation.conversion.AbstractPropagatorBuilder

addAdditionalDerivativesProvider, addSupportedParameters, buildPropagator, createInitialOrbit, deselectDynamicParameters, getAdditionalDerivativesProviders, getAttitudeProvider, getFrame, getInitialOrbitDate, getMass, getMu, getOrbitalParametersDrivers, getOrbitType, getPositionAngleType, getPositionScale, getPropagationParametersDrivers, getSelectedNormalizedParameters, resetOrbit, setAttitudeProvider, setMass, setParameters

Methods inherited from class java.lang.Object

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

Constructor Details

EphemerisPropagatorBuilder

public EphemerisPropagatorBuilder(List<SpacecraftState> states,
 TimeInterpolator<SpacecraftState> stateInterpolator)

Constructor using the default attitude provider.

The default attitude provider is an inertial provider built from the frame of the first spacecraft state instance in given list

Parameters:

states - list of spacecraft states

stateInterpolator - spacecraft state interpolator

EphemerisPropagatorBuilder

public EphemerisPropagatorBuilder(List<SpacecraftState> states,
 TimeInterpolator<SpacecraftState> stateInterpolator,
 AttitudeProvider attitudeProvider)

Constructor.

Parameters:

states - list of spacecraft states

stateInterpolator - spacecraft state interpolator

attitudeProvider - attitude law to use

EphemerisPropagatorBuilder

public EphemerisPropagatorBuilder(List<SpacecraftState> states,
 int interpolationPoints,
 double extrapolationThreshold,
 AttitudeProvider attitudeProvider)

Constructor.

Parameters:

states - list of spacecraft states

interpolationPoints - number of interpolation points

extrapolationThreshold - extrapolation threshold beyond which the propagation will fail

attitudeProvider - attitude law to use

EphemerisPropagatorBuilder

public EphemerisPropagatorBuilder(List<SpacecraftState> states,
 TimeInterpolator<SpacecraftState> stateInterpolator,
 List<StateCovariance> covariances,
 TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator)

Constructor with covariances and default attitude provider.

The default attitude provider is an inertial provider built from the frame of the first spacecraft state instance in given list

Parameters:

states - list of spacecraft states

stateInterpolator - spacecraft state interpolator

covariances - tabulated covariances associated to tabulated states

covarianceInterpolator - covariance interpolator

See Also:

• StateCovariance
• FrameAlignedProvider

EphemerisPropagatorBuilder

public EphemerisPropagatorBuilder(List<SpacecraftState> states,
 TimeInterpolator<SpacecraftState> stateInterpolator,
 List<StateCovariance> covariances,
 TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator,
 AttitudeProvider attitudeProvider)

Constructor.

Parameters:

states - list of spacecraft states

stateInterpolator - spacecraft state interpolator

covariances - tabulated covariances associated to tabulated states

covarianceInterpolator - covariance interpolator

attitudeProvider - attitude law to use

Method Details

clone

public EphemerisPropagatorBuilder clone()

..

Overrides:

clone in class AbstractPropagatorBuilder<Ephemeris>

buildPropagator

public Ephemeris buildPropagator(double[] normalizedParameters)

Build a propagator..

Specified by:

buildPropagator in interface PropagatorBuilder

Specified by:

buildPropagator in class AbstractPropagatorBuilder<Ephemeris>

Parameters:

normalizedParameters - normalized values for the selected parameters

Returns:

an initialized propagator

buildLeastSquaresModel

public AbstractBatchLSModel buildLeastSquaresModel(PropagatorBuilder[] builders,
 List<ObservedMeasurement<?>> measurements,
 ParameterDriversList estimatedMeasurementsParameters,
 ModelObserver observer)

Build a new batch least squares model.

Parameters:

builders - builders to use for propagation

measurements - measurements

estimatedMeasurementsParameters - estimated measurements parameters

observer - observer to be notified at model calls

Returns:

a new model for the Batch Least Squares orbit determination