Package org.orekit.propagation.conversion

Interface PropagatorBuilder

All Superinterfaces:

Cloneable

All Known Implementing Classes:

AbstractAnalyticalPropagatorBuilder, AbstractIntegratedPropagatorBuilder, AbstractPropagatorBuilder, BrouwerLyddanePropagatorBuilder, DSSTPropagatorBuilder, EcksteinHechlerPropagatorBuilder, EphemerisPropagatorBuilder, GNSSPropagatorBuilder, KeplerianPropagatorBuilder, NumericalPropagatorBuilder, TLEPropagatorBuilder

public interface PropagatorBuilder
extends Cloneable

This interface is the top-level abstraction to build propagators for conversion.

Since:

6.0

Author:

Pascal Parraud

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.
default Propagator	buildPropagator()	Build a propagator from current value of selected normalized parameters.
Propagator	buildPropagator(double[] normalizedParameters)	Build a propagator.
AttitudeProvider	getAttitudeProvider()	Get the attitude provider.
Frame	getFrame()	Get the frame in which the orbit is propagated.
AbsoluteDate	getInitialOrbitDate()	Get the date of the initial orbit.
double	getMass()	Get the initial mass.
double	getMu()	Get the central attraction coefficient (µ - m³/s²) value.
ParameterDriversList	getOrbitalParametersDrivers()	Get the drivers for the configurable orbital parameters.
OrbitType	getOrbitType()	Get the orbit type expected for the 6 first parameters in buildPropagator(double[]).
PositionAngleType	getPositionAngleType()	Get the position angle type expected for the 6 first parameters in buildPropagator(double[]).
ParameterDriversList	getPropagationParametersDrivers()	Get the drivers for the configurable propagation parameters.
double[]	getSelectedNormalizedParameters()	Get the current value of selected normalized parameters.
void	resetOrbit(Orbit newOrbit)	Reset the orbit in the propagator builder.

Method Details

buildPropagator

Propagator buildPropagator(double[] normalizedParameters)

Build a propagator.

Parameters:

normalizedParameters - normalized values for the selected parameters

Returns:

an initialized propagator

buildPropagator

default Propagator buildPropagator()

Build a propagator from current value of selected normalized parameters.

Returns:

an initialized propagator

buildLeastSquaresModel

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

Since:

12.0

getSelectedNormalizedParameters

double[] getSelectedNormalizedParameters()

Get the current value of selected normalized parameters.

Returns:

current value of selected normalized parameters

getAttitudeProvider

AttitudeProvider getAttitudeProvider()

Get the attitude provider.

Returns:

the attitude provider

Since:

13.0

getOrbitType

OrbitType getOrbitType()

Get the orbit type expected for the 6 first parameters in buildPropagator(double[]).

Returns:

orbit type to use in buildPropagator(double[])

Since:

7.1

See Also:

• buildPropagator(double[])
• getPositionAngleType()

getPositionAngleType

PositionAngleType getPositionAngleType()

Get the position angle type expected for the 6 first parameters in buildPropagator(double[]).

Returns:

position angle type to use in buildPropagator(double[])

Since:

7.1

See Also:

• buildPropagator(double[])
• getOrbitType()

getInitialOrbitDate

AbsoluteDate getInitialOrbitDate()

Get the date of the initial orbit.

Returns:

date of the initial orbit

getFrame

Frame getFrame()

Get the frame in which the orbit is propagated.

Returns:

frame in which the orbit is propagated

getMu

double getMu()

Get the central attraction coefficient (µ - m³/s²) value.

Returns:

the central attraction coefficient (µ - m³/s²) value

Since:

12.0

getMass

double getMass()

Get the initial mass.

Returns:

the mass (kg)

Since:

13.0

getOrbitalParametersDrivers

ParameterDriversList getOrbitalParametersDrivers()

Get the drivers for the configurable orbital parameters. Orbital drivers should have only 1 value estimated (1 span)

Returns:

drivers for the configurable orbital parameters

Since:

8.0

getPropagationParametersDrivers

ParameterDriversList getPropagationParametersDrivers()

Get the drivers for the configurable propagation parameters.

The parameters typically correspond to force models.

Returns:

drivers for the configurable propagation parameters

Since:

8.0

resetOrbit

void resetOrbit(Orbit newOrbit)

Reset the orbit in the propagator builder.

Parameters:

newOrbit - New orbit to set in the propagator builder

Since:

12.0