Uses of Package
org.orekit.propagation.integration

Packages that use org.orekit.propagation.integration

Package	Description
org.orekit.estimation.measurements.modifiers	This package provides measurement modifier.
org.orekit.forces.maneuvers.jacobians	Generators for columns of Jacobian matrices related to maneuver parameters.
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
org.orekit.propagation.numerical.cr3bp	Top level package for CR3BP Models used with a numerical propagator.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).

Classes in org.orekit.propagation.integration used by org.orekit.estimation.measurements.modifiers

Class	Description
AbstractGradientConverter	Converter for states and parameters arrays.

Classes in org.orekit.propagation.integration used by org.orekit.forces.maneuvers.jacobians

Class	Description
AdditionalDerivativesProvider	Provider for additional derivatives.
CombinedDerivatives	Container for additional derivatives.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.analytical

Class	Description
AbstractGradientConverter	Converter for states and parameters arrays.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.conversion

Class	Description
AdditionalDerivativesProvider	Provider for additional derivatives.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.integration

Class	Description
AbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
AdditionalDerivativesProvider	Provider for additional derivatives.
CombinedDerivatives	Container for additional derivatives.
FieldAbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
FieldAdditionalDerivativesProvider	Provider for additional derivatives.
FieldCombinedDerivatives	Container for additional derivatives.
FieldStateMapper	This class maps between raw double elements and FieldSpacecraftState instances.
StateMapper	This class maps between raw double elements and SpacecraftState instances.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.numerical

Class	Description
AbstractIntegratedPropagator	Common handling of Propagator methods for both numerical and semi-analytical propagators.
AbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
AdditionalDerivativesProvider	Provider for additional derivatives.
CombinedDerivatives	Container for additional derivatives.
FieldAbstractIntegratedPropagator	Common handling of FieldPropagator methods for both numerical and semi-analytical propagators.
FieldAbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
FieldStateMapper	This class maps between raw double elements and FieldSpacecraftState instances.
StateMapper	This class maps between raw double elements and SpacecraftState instances.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.numerical.cr3bp

Class	Description
AdditionalDerivativesProvider	Provider for additional derivatives.
CombinedDerivatives	Container for additional derivatives.

Classes in org.orekit.propagation.integration used by org.orekit.propagation.semianalytical.dsst

Class	Description
AbstractIntegratedPropagator	Common handling of Propagator methods for both numerical and semi-analytical propagators.
AbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
FieldAbstractIntegratedPropagator	Common handling of FieldPropagator methods for both numerical and semi-analytical propagators.
FieldAbstractIntegratedPropagator.MainStateEquations	Differential equations for the main state (orbit, attitude and mass).
FieldStateMapper	This class maps between raw double elements and FieldSpacecraftState instances.
StateMapper	This class maps between raw double elements and SpacecraftState instances.