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

Packages that use FieldAuxiliaryElements

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

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

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

Modifier and Type	Method and Description
protected abstract <T extends RealFieldElement<T>> T[]	AbstractGaussianContribution.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected <T extends RealFieldElement<T>> T[]	DSSTSolarRadiationPressure.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected <T extends RealFieldElement<T>> T[]	DSSTAtmosphericDrag.getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
<T extends RealFieldElement<T>> T[]	AbstractGaussianContribution.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTThirdBody.getMeanElementRate(FieldSpacecraftState<T> currentState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTTesseral.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTNewtonianAttraction.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTZonal.getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> T[]	DSSTForceModel.getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	AbstractGaussianContribution.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	DSSTThirdBody.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	DSSTTesseral.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	DSSTNewtonianAttraction.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	DSSTZonal.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.
<T extends RealFieldElement<T>> List<FieldShortPeriodTerms<T>>	DSSTForceModel.initialize(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters) Performs initialization prior to propagation for the current force model.