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).

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

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

Modifier and Type	Method and 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[]	DSSTZonal.getMeanElementRate(SpacecraftState spacecraftState, AuxiliaryElements auxiliaryElements, double[] parameters) Computes the mean equinoctial elements rates dai / dt.
double[]	AbstractGaussianContribution.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[]	DSSTForceModel.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.
List<ShortPeriodTerms>	DSSTZonal.initialize(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	AbstractGaussianContribution.initialize(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTNewtonianAttraction.initialize(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTForceModel.initialize(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTTesseral.initialize(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
List<ShortPeriodTerms>	DSSTThirdBody.initialize(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.