Uses of Class
org.orekit.propagation.semianalytical.dsst.utilities.AuxiliaryElements

Packages that use AuxiliaryElements

Package	Description
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.utilities	This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).

Uses of AuxiliaryElements in org.orekit.propagation.semianalytical.dsst.forces

Methods in org.orekit.propagation.semianalytical.dsst.forces that return AuxiliaryElements

Modifier and Type	Method	Description
AuxiliaryElements	ForceModelContext.getAuxiliaryElements()	Method to get the auxiliary elements related to the ForceModelContext.

Methods in org.orekit.propagation.semianalytical.dsst.forces with parameters of type AuxiliaryElements

Modifier and Type	Method	Description
protected abstract double[]	AbstractGaussianContribution.getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTAtmosphericDrag.getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTSolarRadiationPressure.getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
double[]	AbstractGaussianContribution.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTForceModel.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTJ2SquaredClosedForm.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTNewtonianAttraction.getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTTesseral.getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTThirdBody.getMeanElementRate(SpacecraftState currentState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTZonal.getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters)	Computes the mean equinoctial elements rates dai / dt.
List<ShortPeriodTerms>	AbstractGaussianContribution.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTJ2SquaredClosedForm.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTNewtonianAttraction.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTTesseral.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTThirdBody.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Computes the highest power of the eccentricity and the highest power of a/R3 to appear in the truncated analytical power series expansion.
List<ShortPeriodTerms>	DSSTZonal.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)	Performs initialization prior to propagation for the current force model.

Constructors in org.orekit.propagation.semianalytical.dsst.forces with parameters of type AuxiliaryElements

Constructor	Description
DSSTJ2SquaredClosedFormContext(AuxiliaryElements auxiliaryElements, UnnormalizedSphericalHarmonicsProvider provider)	Simple constructor.
DSSTNewtonianAttractionContext(AuxiliaryElements auxiliaryElements, double[] parameters)	Simple constructor.
DSSTThirdBodyDynamicContext(AuxiliaryElements aux, CelestialBody body, double[] parameters)	Constructor.
DSSTThirdBodyStaticContext(AuxiliaryElements aux, double x, double r3, double[] parameters)	Constructor.
ForceModelContext(AuxiliaryElements auxiliaryElements)	Simple constructor.

Uses of AuxiliaryElements in org.orekit.propagation.semianalytical.dsst.utilities

Methods in org.orekit.propagation.semianalytical.dsst.utilities that return AuxiliaryElements

Modifier and Type	Method	Description
AuxiliaryElements	FieldAuxiliaryElements.toAuxiliaryElements()	Transforms the FieldAuxiliaryElements instance into an AuxiliaryElements instance.