|
||||||||||
PREV NEXT | FRAMES NO FRAMES |
Packages that use AdditionalStateProvider | |
---|---|
fr.cnes.sirius.patrius.propagation | |
fr.cnes.sirius.patrius.stela.propagation | |
org.orekit.propagation | This package provides tools to propagate orbital states with different methods. |
Uses of AdditionalStateProvider in fr.cnes.sirius.patrius.propagation |
---|
Classes in fr.cnes.sirius.patrius.propagation that implement AdditionalStateProvider | |
---|---|
class |
SimpleAdditionalStateProvider
This class is a simple implementation of additionalStateProvider. |
Constructor parameters in fr.cnes.sirius.patrius.propagation with type arguments of type AdditionalStateProvider | |
---|---|
PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider,
AbsoluteDate initDate,
double mu,
Frame frame,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
List<AdditionalStateProvider> additionalStateProviders)
Creates an instance of PVCoordinatePropagator with PV, attitude for forces, attitude for events, and additional state providers given by the user. |
Uses of AdditionalStateProvider in fr.cnes.sirius.patrius.stela.propagation |
---|
Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type AdditionalStateProvider | |
---|---|
void |
StelaAbstractPropagator.addAdditionalStateProvider(AdditionalStateProvider additionalStateProvider)
Add a set of user-specified state parameters to be computed along with the orbit propagation. |
Method parameters in fr.cnes.sirius.patrius.stela.propagation with type arguments of type AdditionalStateProvider | |
---|---|
void |
StelaBasicInterpolator.setAdditionalStateProviders(List<AdditionalStateProvider> additionalStateProvidersIn)
sets the additionalStateProviders |
Uses of AdditionalStateProvider in org.orekit.propagation |
---|
Methods in org.orekit.propagation with parameters of type AdditionalStateProvider | |
---|---|
void |
AbstractPropagator.addAdditionalStateProvider(AdditionalStateProvider additionalStateProvider)
Add a set of user-specified state parameters to be computed along with the orbit propagation. |
|
||||||||||
PREV NEXT | FRAMES NO FRAMES |