Uses of Class
org.orekit.orbits.FieldOrbit

Packages that use FieldOrbit

Package	Description
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.intelsat	This package provides classes to propagate Intelsat's 11 elements.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
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.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
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).
org.orekit.ssa.collision.shorttermencounter.probability.twod	Package specific to calculus assuming a 2D short-term encounter model.

Uses of FieldOrbit in org.orekit.orbits

Subclasses of FieldOrbit in org.orekit.orbits

Modifier and Type	Class	Description
class	FieldCartesianOrbit<T extends CalculusFieldElement<T>>	This class holds Cartesian orbital parameters.
class	FieldCircularOrbit<T extends CalculusFieldElement<T>>	This class handles circular orbital parameters.
class	FieldEquinoctialOrbit<T extends CalculusFieldElement<T>>	This class handles equinoctial orbital parameters, which can support both circular and equatorial orbits.
class	FieldKeplerianOrbit<T extends CalculusFieldElement<T>>	This class handles traditional Keplerian orbital parameters.

Methods in org.orekit.orbits that return FieldOrbit

Modifier and Type	Method	Description
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.convertToFieldOrbit(Field<T> field, Orbit orbit)	Convert an orbit to the "Fielded" instance type.
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.convertType(FieldOrbit<T> orbit)	Convert an orbit to the instance type.
FieldOrbit<KK>	AbstractFieldOrbitInterpolator.interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldOrbit<KK>> sample)	Get an interpolated instance.
FieldOrbit<KK>	FieldOrbitBlender.interpolate(AbstractFieldTimeInterpolator.InterpolationData interpolationData)	Interpolate instance from given interpolation data.
protected FieldOrbit<KK>	FieldOrbitHermiteInterpolator.interpolate(AbstractFieldTimeInterpolator.InterpolationData interpolationData)	Interpolate instance from given interpolation data.
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngleType type, FieldAbsoluteDate<T> date, T mu, Frame frame)	Convert state array to orbital parameters.
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.normalize(FieldOrbit<T> orbit, FieldOrbit<T> reference)	Normalize one orbit with respect to a reference one.
abstract FieldOrbit<T>	FieldOrbit.shiftedBy(T dt)	Get a time-shifted orbit.
abstract FieldOrbit<T>	FieldOrbit.withFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.

Methods in org.orekit.orbits with parameters of type FieldOrbit

Modifier and Type	Method	Description
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.convertType(FieldOrbit<T> orbit)	Convert an orbit to the instance type.
abstract <T extends CalculusFieldElement<T>> void	OrbitType.mapOrbitToArray(FieldOrbit<T> orbit, PositionAngleType type, T[] stateVector, T[] stateVectorDot)	Convert orbit to state array.
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.normalize(FieldOrbit<T> orbit, FieldOrbit<T> reference)	Normalize one orbit with respect to a reference one.

Method parameters in org.orekit.orbits with type arguments of type FieldOrbit

Modifier and Type	Method	Description
FieldOrbit<KK>	AbstractFieldOrbitInterpolator.interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldOrbit<KK>> sample)	Get an interpolated instance.

Constructors in org.orekit.orbits with parameters of type FieldOrbit

Constructor	Description
FieldCartesianOrbit(FieldOrbit<T> op)	Constructor from any kind of orbital parameters.
FieldCircularOrbit(FieldOrbit<T> op)	Constructor from any kind of orbital parameters.
FieldEquinoctialOrbit(FieldOrbit<T> op)	Constructor from any kind of orbital parameters.
FieldKeplerianOrbit(FieldOrbit<T> op)	Constructor from any kind of orbital parameters.

Uses of FieldOrbit in org.orekit.propagation

Methods in org.orekit.propagation that return FieldOrbit

Modifier and Type	Method	Description
FieldOrbit<T>	FieldSpacecraftState.getOrbit()	Get the current orbit.

Methods in org.orekit.propagation that return types with arguments of type FieldOrbit

Modifier and Type	Method	Description
Optional<FieldTimeInterpolator<FieldOrbit<KK>,KK>>	FieldSpacecraftStateInterpolator.getOrbitInterpolator()	Get orbit interpolator.

Methods in org.orekit.propagation with parameters of type FieldOrbit

Modifier and Type	Method	Description
FieldStateCovariance<T>	FieldStateCovariance.changeCovarianceFrame(FieldOrbit<T> orbit, Frame frameOut)	Get the covariance in the output frame.
FieldStateCovariance<T>	FieldStateCovariance.changeCovarianceFrame(FieldOrbit<T> orbit, LOF lofOut)	Get the covariance in a given local orbital frame.
FieldStateCovariance<T>	FieldStateCovariance.changeCovarianceType(FieldOrbit<T> orbit, OrbitType outOrbitType, PositionAngleType outAngleType)	Get the covariance matrix in another orbit type.
default <T extends CalculusFieldElement<T>> double[][]	ToleranceProvider.getTolerances(FieldOrbit<T> referenceOrbit, OrbitType propagationOrbitType)	Retrieve the integration tolerances given a reference Field orbit.
default <T extends CalculusFieldElement<T>> double[][]	ToleranceProvider.getTolerances(FieldOrbit<T> referenceOrbit, OrbitType propagationOrbitType, PositionAngleType positionAngleType)	Retrieve the integration tolerances given a reference Field orbit.
FieldStateCovariance<T>	FieldStateCovariance.shiftedBy(Field<T> field, FieldOrbit<T> orbit, T dt)	Get a time-shifted covariance matrix.

Constructors in org.orekit.propagation with parameters of type FieldOrbit

Constructor	Description
FieldSpacecraftState(FieldOrbit<T> orbit)	Build a spacecraft state from orbit only.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude)	Build a spacecraft state from orbit and attitude.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional)	Build a spacecraft state from orbit attitude and additional states.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass)	Build a spacecraft state from orbit, attitude and mass.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional)	Build a spacecraft state from orbit, attitude, mass and additional states.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> additionalDot)	Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
FieldSpacecraftState(FieldOrbit<T> orbit, FieldArrayDictionary<T> additional)	Build a spacecraft state from orbit and additional states.
FieldSpacecraftState(FieldOrbit<T> orbit, T mass)	Create a new instance from orbit and mass.
FieldSpacecraftState(FieldOrbit<T> orbit, T mass, FieldArrayDictionary<T> additional)	Create a new instance from orbit, mass and additional states.

Constructor parameters in org.orekit.propagation with type arguments of type FieldOrbit

Constructor

Description

FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator, FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator, FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator)

Constructor.

Uses of FieldOrbit in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that return FieldOrbit

Modifier and Type	Method	Description
protected abstract FieldOrbit<T>	FieldAbstractAnalyticalPropagator.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.
protected FieldOrbit<T>	FieldKeplerianPropagator.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.

Methods in org.orekit.propagation.analytical with parameters of type FieldOrbit

Modifier and Type	Method	Description
static <T extends CalculusFieldElement<T>> FieldKeplerianOrbit<T>	FieldBrouwerLyddanePropagator.computeMeanOrbit(FieldOrbit<T> osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2Value, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldKeplerianOrbit<T>	FieldBrouwerLyddanePropagator.computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2Value)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldKeplerianOrbit<T>	FieldBrouwerLyddanePropagator.computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2Value, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>	FieldEcksteinHechlerPropagator.computeMeanOrbit(FieldOrbit<T> osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>	FieldEcksteinHechlerPropagator.computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)	Conversion from osculating to mean orbit.
static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>	FieldEcksteinHechlerPropagator.computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.

Constructors in org.orekit.propagation.analytical with parameters of type FieldOrbit

Constructor	Description
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double M2)	Build a propagator from orbit and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double M2)	Build a propagator from orbit, attitude provider and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider, double M2)	Build a propagator from orbit, attitude provider and potential provider.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double M2)	Build a propagator from orbit, attitude provider, mass and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, PropagationType initialType, double M2)	Build a propagator from orbit, attitude provider, mass and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, PropagationType initialType, double M2, double epsilon, int maxIterations)	Build a propagator from orbit, attitude provider, mass and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider, double M2)	Build a propagator from orbit, attitude provider, mass and potential provider.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2)	Private helper constructor.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType, double M2)	Private helper constructor.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2)	Build a propagator from orbit, attitude provider, mass and potential provider.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, double M2)	Build a propagator from orbit and potential provider.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2)	Build a propagator from orbit and potential provider.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double M2)	Build a propagator from orbit, mass and potential.
FieldBrouwerLyddanePropagator(FieldOrbit<T> initialOrbit, T mass, UnnormalizedSphericalHarmonicsProvider provider, double M2)	Build a propagator from orbit, mass and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)	Build a propagator from FieldOrbit and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)	Build a propagator from FieldOrbit, attitude provider and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider)	Build a propagator from FieldOrbit, attitude provider and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)	Build a propagator from FieldOrbit, attitude provider, mass and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType)	Build a propagator from FieldOrbit, attitude provider, mass and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, double epsilon, int maxIterations)	Build a propagator from FieldOrbit, attitude provider, mass and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider)	Build a propagator from FieldOrbit, attitude provider, mass and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)	Private helper constructor.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType)	Private helper constructor.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)	Build a propagator from orbit, attitude provider, mass and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider)	Build a propagator from FieldOrbit and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)	Build a propagator from orbit and potential provider.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)	Build a propagator from FieldOrbit, mass and potential.
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, T mass, UnnormalizedSphericalHarmonicsProvider provider)	Build a propagator from FieldOrbit, mass and potential provider.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit)	Build a propagator from orbit only.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv)	Build a propagator from orbit and attitude provider.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, AttitudeProvider attitudeProv, T mu)	Build a propagator from orbit, attitude provider and central attraction coefficient μ.
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mu, T mass)	Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit, T mu)	Build a propagator from orbit and central attraction coefficient μ.

Uses of FieldOrbit in org.orekit.propagation.analytical.intelsat

Methods in org.orekit.propagation.analytical.intelsat that return FieldOrbit

Modifier and Type	Method	Description
protected FieldOrbit<T>	FieldIntelsatElevenElementsPropagator.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.

Uses of FieldOrbit in org.orekit.propagation.analytical.tle

Methods in org.orekit.propagation.analytical.tle that return FieldOrbit

Modifier and Type	Method	Description
FieldOrbit<T>	FieldTLEPropagator.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.

Uses of FieldOrbit in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion with parameters of type FieldOrbit

Modifier and Type	Method	Description
W	FieldAbstractIntegratorBuilder.buildIntegrator(FieldOrbit<T> orbit, OrbitType orbitType)	Build a first order integrator.
FieldExplicitRungeKuttaIntegrator<T>	FieldExplicitRungeKuttaIntegratorBuilder.buildIntegrator(FieldOrbit<T> orbit, OrbitType orbitType)	Build a first order integrator.
FieldODEIntegrator<T>	FieldODEIntegratorBuilder.buildIntegrator(FieldOrbit<T> orbit, OrbitType orbitType)	Build a first order integrator.

Uses of FieldOrbit in org.orekit.propagation.events

Constructors in org.orekit.propagation.events with parameters of type FieldOrbit

Constructor	Description
FieldApsideDetector(FieldOrbit<T> orbit)	Build a new instance.
FieldApsideDetector(T threshold, FieldOrbit<T> orbit)	Build a new instance.
FieldNodeDetector(FieldOrbit<T> orbit, Frame frame)	Build a new instance.
FieldNodeDetector(T threshold, FieldOrbit<T> orbit, Frame frame)	Build a new instance.

Uses of FieldOrbit in org.orekit.propagation.integration

Methods in org.orekit.propagation.integration that return FieldOrbit

Modifier and Type	Method	Description
protected FieldOrbit<T>	FieldIntegratedEphemeris.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.

Uses of FieldOrbit in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical with parameters of type FieldOrbit

Modifier and Type	Method	Description
static <T extends CalculusFieldElement<T>> double[][]	FieldNumericalPropagator.tolerances(T dP, FieldOrbit<T> orbit, OrbitType type)	Deprecated. since 13.0.
static <T extends CalculusFieldElement<T>> double[][]	FieldNumericalPropagator.tolerances(T dP, T dV, FieldOrbit<T> orbit, OrbitType type)	Deprecated. since 13.0.

Uses of FieldOrbit in org.orekit.propagation.semianalytical.dsst

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

Modifier and Type	Method	Description
static <T extends CalculusFieldElement<T>> double[][]	FieldDSSTPropagator.tolerances(T dP, FieldOrbit<T> orbit)	Deprecated. since 13.0.
static <T extends CalculusFieldElement<T>> double[][]	FieldDSSTPropagator.tolerances(T dP, T dV, FieldOrbit<T> orbit)	Deprecated. since 13.0.

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

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

Modifier and Type	Method	Description
T[]	AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients.value(FieldOrbit<T> meanOrbit)	Evaluate the contributions of the short period terms.
T[]	FieldShortPeriodTerms.value(FieldOrbit<T> meanOrbit)	Evaluate the contributions of the short period terms.

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

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

Modifier and Type	Method	Description
FieldOrbit<T>	FieldAuxiliaryElements.getOrbit()	Get the orbit.

Constructors in org.orekit.propagation.semianalytical.dsst.utilities with parameters of type FieldOrbit

Constructor	Description
FieldAuxiliaryElements(FieldOrbit<T> orbit, int retrogradeFactor)	Simple constructor.

Uses of FieldOrbit in org.orekit.ssa.collision.shorttermencounter.probability.twod

Methods in org.orekit.ssa.collision.shorttermencounter.probability.twod that return FieldOrbit

Modifier and Type	Method	Description
FieldOrbit<T>	FieldShortTermEncounter2DDefinition.getOtherAtTCA()	Get other's orbit at time of closest approach.
FieldOrbit<T>	FieldShortTermEncounter2DDefinition.getReferenceAtTCA()	Get reference's orbit at time of closest approach.

Methods in org.orekit.ssa.collision.shorttermencounter.probability.twod with parameters of type FieldOrbit

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldProbabilityOfCollision<T>	AbstractShortTermEncounter1DNumerical2DPOCMethod.compute(FieldOrbit<T> primaryAtTCA, FieldStateCovariance<T> primaryCovariance, T primaryRadius, FieldOrbit<T> secondaryAtTCA, FieldStateCovariance<T> secondaryCovariance, T secondaryRadius, FieldUnivariateIntegrator<T> customIntegrator, int customMaxNbOfEval, double zeroThreshold)	Compute the probability of collision using parameters necessary for creating a collision definition instance.
<T extends CalculusFieldElement<T>> FieldProbabilityOfCollision<T>	AbstractShortTermEncounter2DPOCMethod.compute(FieldOrbit<T> primaryAtTCA, FieldStateCovariance<T> primaryCovariance, FieldOrbit<T> secondaryAtTCA, FieldStateCovariance<T> secondaryCovariance, T combinedRadius, double zeroThreshold)	Compute the probability of collision using parameters necessary for creating a collision definition instance.
default <T extends CalculusFieldElement<T>> FieldProbabilityOfCollision<T>	ShortTermEncounter2DPOCMethod.compute(FieldOrbit<T> primaryAtTCA, FieldStateCovariance<T> primaryCovariance, FieldOrbit<T> secondaryAtTCA, FieldStateCovariance<T> secondaryCovariance, T combinedRadius)	Compute the probability of collision using parameters necessary for creating a collision definition instance.
<T extends CalculusFieldElement<T>> FieldProbabilityOfCollision<T>	ShortTermEncounter2DPOCMethod.compute(FieldOrbit<T> primaryAtTCA, FieldStateCovariance<T> primaryCovariance, FieldOrbit<T> secondaryAtTCA, FieldStateCovariance<T> secondaryCovariance, T combinedRadius, double zeroThreshold)	Compute the probability of collision using parameters necessary for creating a collision definition instance.
default <T extends CalculusFieldElement<T>> FieldProbabilityOfCollision<T>	ShortTermEncounter2DPOCMethod.compute(FieldOrbit<T> primaryAtTCA, FieldStateCovariance<T> primaryCovariance, T primaryRadius, FieldOrbit<T> secondaryAtTCA, FieldStateCovariance<T> secondaryCovariance, T secondaryRadius)	Compute the probability of collision using parameters necessary for creating a collision definition instance.

Constructors in org.orekit.ssa.collision.shorttermencounter.probability.twod with parameters of type FieldOrbit

Constructor	Description
FieldShortTermEncounter2DDefinition(FieldOrbit<T> referenceAtTCA, FieldStateCovariance<T> referenceCovariance, FieldOrbit<T> otherAtTCA, FieldStateCovariance<T> otherCovariance, T combinedRadius)	Constructor.
FieldShortTermEncounter2DDefinition(FieldOrbit<T> referenceAtTCA, FieldStateCovariance<T> referenceCovariance, FieldOrbit<T> otherAtTCA, FieldStateCovariance<T> otherCovariance, T combinedRadius, EncounterLOFType encounterFrameType, double tcaTolerance)	Constructor.
FieldShortTermEncounter2DDefinition(FieldOrbit<T> referenceAtTCA, FieldStateCovariance<T> referenceCovariance, T referenceRadius, FieldOrbit<T> otherAtTCA, FieldStateCovariance<T> otherCovariance, T otherRadius)	Constructor.
FieldShortTermEncounter2DDefinition(FieldOrbit<T> referenceAtTCA, FieldStateCovariance<T> referenceCovariance, T referenceRadius, FieldOrbit<T> otherAtTCA, FieldStateCovariance<T> otherCovariance, T otherRadius, EncounterLOFType encounterFrameType, double tcaTolerance)	Constructor.