Uses of Class
org.orekit.propagation.FieldSpacecraftState
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Packages that use FieldSpacecraftState Package Description org.orekit.control.indirect.adjoint This package provides routines to model the adjoint dynamics as in the Pontryagin Maximum Principle, as used in indirect control.org.orekit.control.indirect.shooting This package provides routines to solve indirect optimal control within the frame of orbital mechanics, using shooting methods.org.orekit.estimation.measurements.modifiers This package provides measurement modifier.org.orekit.forces This package provides the interface for force models that will be used by theNumericalPropagator
, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).org.orekit.forces.drag This package provides all drag-related forces.org.orekit.forces.empirical This package provides empirical forces.org.orekit.forces.gravity This package provides all gravity-related forces.org.orekit.forces.inertia This package provides inertial force model.org.orekit.forces.maneuvers This package provides models of simple maneuvers.org.orekit.forces.maneuvers.propulsion This package provides propulsion models intended to be used with classManeuver
.org.orekit.forces.maneuvers.trigger This package provides maneuver triggers' models intended to be used with classManeuver
.org.orekit.forces.radiation This package provides all radiation pressure related forces.org.orekit.models.earth.ionosphere This package provides models that simulate the impact of the ionosphere.org.orekit.propagation Propagationorg.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.analytical.tle.generation This package provides classes related to TLE generation.org.orekit.propagation.events This package provides interfaces and classes dealing with events occurring during propagation.org.orekit.propagation.events.handlers This package provides an interface and classes dealing with events occurrence only.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.sampling This package provides interfaces and classes dealing with step handling during propagation.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.utils This package provides useful objects. -
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Uses of FieldSpacecraftState in org.orekit.control.indirect.adjoint
Methods in org.orekit.control.indirect.adjoint with parameters of type FieldSpacecraftState Modifier and Type Method Description FieldCombinedDerivatives<T>
FieldCartesianAdjointDerivativesProvider. combinedDerivatives(FieldSpacecraftState<T> state)
Compute the derivatives related to the additional state (and optionally main state increments).T
FieldCartesianAdjointDerivativesProvider. evaluateHamiltonian(FieldSpacecraftState<T> state)
Evaluate the Hamiltonian from Pontryagin's Maximum Principle.void
FieldCartesianAdjointDerivativesProvider. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the generator at the start of propagation. -
Uses of FieldSpacecraftState in org.orekit.control.indirect.shooting
Methods in org.orekit.control.indirect.shooting that return FieldSpacecraftState Modifier and Type Method Description protected FieldSpacecraftState<Gradient>
AbstractFixedBoundaryCartesianSingleShooting. createFieldStateWithMassAndAdjoint(double initialMass, double[] initialAdjoint)
Create initial state with input mass and adjoint vector.Methods in org.orekit.control.indirect.shooting with parameters of type FieldSpacecraftState Modifier and Type Method Description protected FieldNumericalPropagator<Gradient>
AbstractFixedBoundaryCartesianSingleShooting. buildFieldPropagator(FieldSpacecraftState<Gradient> initialState)
Create Gradient numerical propagator.protected FieldNumericalPropagator<Gradient>
AbstractIndirectShooting. buildFieldPropagator(FieldSpacecraftState<Gradient> initialState)
Create Gradient numerical propagator.protected abstract double[]
AbstractFixedBoundaryCartesianSingleShooting. updateAdjoint(double[] originalInitialAdjoint, FieldSpacecraftState<Gradient> fieldTerminalState)
Update initial adjoint vector.protected double[]
NewtonFixedBoundaryCartesianSingleShooting. updateAdjoint(double[] originalInitialAdjoint, FieldSpacecraftState<Gradient> fieldTerminalState)
Update initial adjoint vector. -
Uses of FieldSpacecraftState in org.orekit.estimation.measurements.modifiers
Methods in org.orekit.estimation.measurements.modifiers with parameters of type FieldSpacecraftState Modifier and Type Method Description Gradient
ParametricModelEffectGradient. evaluate(GroundStation station, FieldSpacecraftState<Gradient> state, Gradient[] parameters)
Evaluate the parametric model effect.protected <T extends CalculusFieldElement<T>>
TBaseRangeIonosphericDelayModifier. rangeErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Ionosphere.<T extends CalculusFieldElement<T>>
TBaseRangeTroposphericDelayModifier. rangeErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Troposphere.protected <T extends CalculusFieldElement<T>>
TBaseRangeRateIonosphericDelayModifier. rangeRateErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Ionosphere.protected <T extends CalculusFieldElement<T>>
TRangeRateIonosphericDelayModifier. rangeRateErrorIonosphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Ionosphere.<T extends CalculusFieldElement<T>>
TBaseRangeRateTroposphericDelayModifier. rangeRateErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Troposphere.<T extends CalculusFieldElement<T>>
TRangeRateTroposphericDelayModifier. rangeRateErrorTroposphericModel(GroundStation station, FieldSpacecraftState<T> state, T[] parameters)
Compute the measurement error due to Troposphere. -
Uses of FieldSpacecraftState in org.orekit.forces
Methods in org.orekit.forces with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>ForceModel. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.default <T extends CalculusFieldElement<T>>
voidForceModel. addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)
Compute the contribution of the force model to the perturbing acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>BoxAndSolarArraySpacecraft. dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
Compute the acceleration due to drag.<T extends CalculusFieldElement<T>>
FieldVector3D<T>FixedPanel. getNormal(FieldSpacecraftState<T> state)
Get panel normal in spacecraft frame.abstract <T extends CalculusFieldElement<T>>
FieldVector3D<T>Panel. getNormal(FieldSpacecraftState<T> state)
Get panel normal in spacecraft frame.<T extends CalculusFieldElement<T>>
FieldVector3D<T>PointingPanel. getNormal(FieldSpacecraftState<T> state)
Get panel normal in spacecraft frame.<T extends CalculusFieldElement<T>>
FieldVector3D<T>SlewingPanel. getNormal(FieldSpacecraftState<T> state)
Get panel normal in spacecraft frame.default <T extends CalculusFieldElement<T>>
voidForceModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.<T extends CalculusFieldElement<T>>
FieldVector3D<T>BoxAndSolarArraySpacecraft. radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
Compute the acceleration due to radiation pressure. -
Uses of FieldSpacecraftState in org.orekit.forces.drag
Methods in org.orekit.forces.drag with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>DragForce. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>TimeSpanDragForce. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Deprecated.Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>DragSensitive. dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
Compute the acceleration due to drag.<T extends CalculusFieldElement<T>>
FieldVector3D<T>IsotropicDrag. dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
Compute the acceleration due to drag.protected <T extends CalculusFieldElement<T>>
TAbstractDragForceModel. getFieldDensity(FieldSpacecraftState<T> s)
Evaluate the Field density.protected <T extends CalculusFieldElement<T>>
booleanAbstractDragForceModel. isDSStateDerivative(FieldSpacecraftState<T> state)
Check if a field state corresponds to derivatives with respect to state.protected <T extends CalculusFieldElement<T>>
booleanAbstractDragForceModel. isGradientStateDerivative(FieldSpacecraftState<T> state)
Check if a field state corresponds to derivatives with respect to state. -
Uses of FieldSpacecraftState in org.orekit.forces.empirical
Methods in org.orekit.forces.empirical with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>ParametricAcceleration. acceleration(FieldSpacecraftState<T> state, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>TimeSpanParametricAcceleration. acceleration(FieldSpacecraftState<T> state, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
TAccelerationModel. signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)
Compute the signed amplitude of the acceleration.<T extends CalculusFieldElement<T>>
THarmonicAccelerationModel. signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)
Compute the signed amplitude of the acceleration.<T extends CalculusFieldElement<T>>
TPolynomialAccelerationModel. signedAmplitude(FieldSpacecraftState<T> state, T[] parameters)
Compute the signed amplitude of the acceleration. -
Uses of FieldSpacecraftState in org.orekit.forces.gravity
Methods in org.orekit.forces.gravity with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>DeSitterRelativity. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>HolmesFeatherstoneAttractionModel. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>J2OnlyPerturbation. acceleration(FieldSpacecraftState<T> state, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>LenseThirringRelativity. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>NewtonianAttraction. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>OceanTides. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>Relativity. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>SingleBodyAbsoluteAttraction. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>SingleBodyRelativeAttraction. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>SolidTides. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>ThirdBodyAttraction. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
voidNewtonianAttraction. addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)
Compute the contribution of the force model to the perturbing acceleration. -
Uses of FieldSpacecraftState in org.orekit.forces.inertia
Methods in org.orekit.forces.inertia with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>InertialForces. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration. -
Uses of FieldSpacecraftState in org.orekit.forces.maneuvers
Methods in org.orekit.forces.maneuvers with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>Maneuver. acceleration(FieldSpacecraftState<T> s, T[] parameters)
<T extends CalculusFieldElement<T>>
voidManeuver. addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)
Compute the contribution of the force model to the perturbing acceleration.T
FieldImpulseManeuver. g(FieldSpacecraftState<T> fieldSpacecraftState)
Compute the value of the switching function.void
FieldImpulseManeuver. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.<T extends CalculusFieldElement<T>>
voidManeuver. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.<T extends CalculusFieldElement<T>>
booleanConstantThrustManeuver. isFiring(FieldSpacecraftState<T> s)
Check if maneuvering is on. -
Uses of FieldSpacecraftState in org.orekit.forces.maneuvers.propulsion
Methods in org.orekit.forces.maneuvers.propulsion with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>PropulsionModel. getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.default <T extends CalculusFieldElement<T>>
FieldVector3D<T>ThrustPropulsionModel. getAcceleration(FieldSpacecraftState<T> s, FieldAttitude<T> maneuverAttitude, T[] parameters)
Get the acceleration of the spacecraft during maneuver and in maneuver frame.<T extends CalculusFieldElement<T>>
TAbstractConstantThrustPropulsionModel. getFlowRate(FieldSpacecraftState<T> s, T[] parameters)
Get the flow rate (kg/s).<T extends CalculusFieldElement<T>>
TProfileThrustPropulsionModel. getFlowRate(FieldSpacecraftState<T> s, T[] parameters)
Get the flow rate (kg/s).<T extends CalculusFieldElement<T>>
TThrustPropulsionModel. getFlowRate(FieldSpacecraftState<T> s, T[] parameters)
Get the flow rate (kg/s).<T extends CalculusFieldElement<T>>
TPropulsionModel. getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)
Get the mass derivative (i.e.default <T extends CalculusFieldElement<T>>
TThrustPropulsionModel. getMassDerivatives(FieldSpacecraftState<T> s, T[] parameters)
Get the mass derivative (i.e.<T extends CalculusFieldElement<T>>
FieldVector3D<T>AbstractConstantThrustPropulsionModel. getThrustVector(FieldSpacecraftState<T> s, T[] parameters)
Get the thrust vector in spacecraft frame (N).<T extends CalculusFieldElement<T>>
FieldVector3D<T>ProfileThrustPropulsionModel. getThrustVector(FieldSpacecraftState<T> s, T[] parameters)
Get the thrust vector in spacecraft frame (N).<T extends CalculusFieldElement<T>>
FieldVector3D<T>ThrustPropulsionModel. getThrustVector(FieldSpacecraftState<T> s, T[] parameters)
Get the thrust vector in spacecraft frame (N).default <T extends CalculusFieldElement<T>>
voidPropulsionModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialization method. -
Uses of FieldSpacecraftState in org.orekit.forces.maneuvers.trigger
Methods in org.orekit.forces.maneuvers.trigger that return FieldSpacecraftState Modifier and Type Method Description protected <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>AbstractManeuverTriggers. applyResetters(FieldSpacecraftState<T> state)
Apply resetters.FieldSpacecraftState<T>
FieldManeuverTriggersResetter. resetState(FieldSpacecraftState<T> state)
Reset state as a maneuver triggers.Methods in org.orekit.forces.maneuvers.trigger with parameters of type FieldSpacecraftState Modifier and Type Method Description protected <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>AbstractManeuverTriggers. applyResetters(FieldSpacecraftState<T> state)
Apply resetters.<T extends CalculusFieldElement<T>>
voidAbstractManeuverTriggers. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialization method called at propagation start.default void
FieldManeuverTriggersResetter. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialization method called at propagation start.<D extends CalculusFieldElement<D>>
voidIntervalEventTrigger. init(FieldSpacecraftState<D> initialState, FieldAbsoluteDate<D> target)
Initialization method called at propagation start.default <T extends CalculusFieldElement<T>>
voidManeuverTriggers. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialization method called at propagation start.protected <T extends CalculusFieldElement<T>>
voidAbstractManeuverTriggers. initializeResetters(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize resetters.void
FieldManeuverTriggersResetter. maneuverTriggered(FieldSpacecraftState<T> state, boolean start)
Observe a maneuver trigger.protected <T extends CalculusFieldElement<T>>
voidAbstractManeuverTriggers. notifyResetters(FieldSpacecraftState<T> state, boolean start)
Notify resetters.FieldSpacecraftState<T>
FieldManeuverTriggersResetter. resetState(FieldSpacecraftState<T> state)
Reset state as a maneuver triggers. -
Uses of FieldSpacecraftState in org.orekit.forces.radiation
Methods in org.orekit.forces.radiation with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>ECOM2. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>KnockeRediffusedForceModel. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>RadiationPressureModel. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>SolarRadiationPressure. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldVector3D<T>KnockeRediffusedForceModel. computeElementaryFlux(FieldSpacecraftState<T> state, FieldVector3D<T> elementCenter, FieldVector3D<T> sunPosition, OneAxisEllipsoid earth, T elementArea)
Compute elementary rediffused flux on satellite.<T extends CalculusFieldElement<T>>
FieldVector3D<T>AbstractLightFluxModel. getLightFluxVector(FieldSpacecraftState<T> state)
Get the light flux vector in the state's frame.<T extends CalculusFieldElement<T>>
FieldVector3D<T>LightFluxModel. getLightFluxVector(FieldSpacecraftState<T> state)
Get the light flux vector in the state's frame.<T extends CalculusFieldElement<T>>
TAbstractLightFluxModel. getLightingRatio(FieldSpacecraftState<T> state)
Get the lighting ratio ([0-1]).<T extends CalculusFieldElement<T>>
TSolarRadiationPressure. getLightingRatio(FieldSpacecraftState<T> state)
Get the lighting ratio ([0-1]).<T extends CalculusFieldElement<T>>
voidConicallyShadowedLightFluxModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> targetDate)
Perform initialization steps before starting propagation.default <T extends CalculusFieldElement<T>>
voidLightFluxModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> targetDate)
Perform initialization steps before starting propagation.<T extends CalculusFieldElement<T>>
voidRadiationPressureModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.<T extends CalculusFieldElement<T>>
FieldVector3D<T>IsotropicRadiationClassicalConvention. radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
Compute the acceleration due to radiation pressure.<T extends CalculusFieldElement<T>>
FieldVector3D<T>IsotropicRadiationCNES95Convention. radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
Compute the acceleration due to radiation pressure.<T extends CalculusFieldElement<T>>
FieldVector3D<T>IsotropicRadiationSingleCoefficient. radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
Compute the acceleration due to radiation pressure.<T extends CalculusFieldElement<T>>
FieldVector3D<T>RadiationSensitive. radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
Compute the acceleration due to radiation pressure. -
Uses of FieldSpacecraftState in org.orekit.models.earth.ionosphere
Methods in org.orekit.models.earth.ionosphere with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
TEstimatedIonosphericModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
Calculates the ionospheric path delay for the signal path from a ground station to a satellite.<T extends CalculusFieldElement<T>>
TGlobalIonosphereMapModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
<T extends CalculusFieldElement<T>>
TIonosphericModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
Calculates the ionospheric path delay for the signal path from a ground station to a satellite.<T extends CalculusFieldElement<T>>
TKlobucharIonoModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
Calculates the ionospheric path delay for the signal path from a ground station to a satellite.<T extends CalculusFieldElement<T>>
TNeQuickModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
<T extends CalculusFieldElement<T>>
TSsrVtecIonosphericModel. pathDelay(FieldSpacecraftState<T> state, TopocentricFrame baseFrame, double frequency, T[] parameters)
Calculates the ionospheric path delay for the signal path from a ground station to a satellite. -
Uses of FieldSpacecraftState in org.orekit.propagation
Methods in org.orekit.propagation that return FieldSpacecraftState Modifier and Type Method Description FieldSpacecraftState<T>
FieldSpacecraftState. addAdditionalState(String name, T... value)
Add an additional state.FieldSpacecraftState<T>
FieldSpacecraftState. addAdditionalStateDerivative(String name, T... value)
Add an additional state derivative.abstract FieldSpacecraftState<T>
FieldAbstractStateModifier. change(FieldSpacecraftState<T> state)
Change main state.FieldSpacecraftState<T>
FieldAbstractPropagator. getInitialState()
Get the propagator initial state.FieldSpacecraftState<T>
FieldPropagator. getInitialState()
Get the propagator initial state.protected FieldSpacecraftState<KK>
FieldSpacecraftStateInterpolator. interpolate(AbstractFieldTimeInterpolator.InterpolationData interpolationData)
Interpolate instance from given interpolation data.FieldSpacecraftState<KK>
FieldSpacecraftStateInterpolator. interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldSpacecraftState<KK>> sample)
Get an interpolated instance.FieldSpacecraftState<T>
FieldAbstractPropagator. propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.FieldSpacecraftState<T>
FieldPropagator. propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.FieldSpacecraftState<T>
FieldPropagator. propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.FieldSpacecraftState<T>
FieldSpacecraftState. shiftedBy(double dt)
Get a time-shifted state.FieldSpacecraftState<T>
FieldSpacecraftState. shiftedBy(T dt)
Get a time-shifted state.FieldSpacecraftState<T>
FieldAbstractStateModifier. update(FieldSpacecraftState<T> state)
Update a state.default FieldSpacecraftState<T>
FieldAdditionalStateProvider. update(FieldSpacecraftState<T> state)
Update a state.protected FieldSpacecraftState<T>
FieldAbstractPropagator. updateAdditionalStates(FieldSpacecraftState<T> original)
Update state by adding all additional states.protected FieldSpacecraftState<T>
FieldAbstractPropagator. updateUnmanagedStates(FieldSpacecraftState<T> original)
Update state by adding unmanaged states.Methods in org.orekit.propagation with parameters of type FieldSpacecraftState Modifier and Type Method Description abstract FieldSpacecraftState<T>
FieldAbstractStateModifier. change(FieldSpacecraftState<T> state)
Change main state.void
FieldSpacecraftState. ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state)
Check if two instances have the same set of additional states available.T[]
FieldAbstractStateModifier. getAdditionalState(FieldSpacecraftState<T> state)
Get the additional state.T[]
FieldAdditionalStateProvider. getAdditionalState(FieldSpacecraftState<T> state)
Get the additional state.default void
FieldAdditionalStateProvider. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the additional state provider at the start of propagation.void
FieldAbstractPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.void
FieldPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected void
FieldAbstractPropagator. stateChanged(FieldSpacecraftState<T> state)
Notify about a state change.FieldSpacecraftState<T>
FieldAbstractStateModifier. update(FieldSpacecraftState<T> state)
Update a state.default FieldSpacecraftState<T>
FieldAdditionalStateProvider. update(FieldSpacecraftState<T> state)
Update a state.protected FieldSpacecraftState<T>
FieldAbstractPropagator. updateAdditionalStates(FieldSpacecraftState<T> original)
Update state by adding all additional states.protected FieldSpacecraftState<T>
FieldAbstractPropagator. updateUnmanagedStates(FieldSpacecraftState<T> original)
Update state by adding unmanaged states.default boolean
FieldAdditionalStateProvider. yields(FieldSpacecraftState<T> state)
Check if this provider should yield so another provider has an opportunity to add missing parts.Method parameters in org.orekit.propagation with type arguments of type FieldSpacecraftState Modifier and Type Method Description FieldSpacecraftState<KK>
FieldSpacecraftStateInterpolator. interpolate(FieldAbsoluteDate<KK> interpolationDate, Collection<FieldSpacecraftState<KK>> sample)
Get an interpolated instance. -
Uses of FieldSpacecraftState in org.orekit.propagation.analytical
Methods in org.orekit.propagation.analytical that return FieldSpacecraftState Modifier and Type Method Description protected FieldSpacecraftState<T>
FieldAbstractAnalyticalPropagator. acceptStep(org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator.FieldBasicStepInterpolator interpolator, FieldAbsoluteDate<T> target)
Accept a step, triggering events and step handlers.protected FieldSpacecraftState<T>
FieldAbstractAnalyticalPropagator. basicPropagate(FieldAbsoluteDate<T> date)
Propagate an orbit without any fancy features.FieldSpacecraftState<Gradient>
AbstractAnalyticalGradientConverter. getState()
Get the state with the number of parameters consistent with the propagation model.FieldSpacecraftState<T>
FieldAbstractAnalyticalPropagator. propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.Methods in org.orekit.propagation.analytical with parameters of type FieldSpacecraftState Modifier and Type Method Description abstract FieldAbstractAnalyticalPropagator<Gradient>
AbstractAnalyticalGradientConverter. getPropagator(FieldSpacecraftState<Gradient> state, Gradient[] parameters)
Get the converted analytical orbit propagator.void
FieldBrouwerLyddanePropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.void
FieldBrouwerLyddanePropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)
Reset the propagator initial state.void
FieldBrouwerLyddanePropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, double epsilon, int maxIterations)
Reset the propagator initial state.void
FieldEcksteinHechlerPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.void
FieldEcksteinHechlerPropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)
Reset the propagator initial state.void
FieldEcksteinHechlerPropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, double epsilon, int maxIterations)
Reset the propagator initial state.void
FieldKeplerianPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected abstract void
FieldAbstractAnalyticalPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.protected void
FieldBrouwerLyddanePropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.protected void
FieldBrouwerLyddanePropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, double epsilon, int maxIterations)
Reset an intermediate state.protected void
FieldEcksteinHechlerPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.protected void
FieldEcksteinHechlerPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, double epsilon, int maxIterations)
Reset an intermediate state.protected void
FieldKeplerianPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state. -
Uses of FieldSpacecraftState in org.orekit.propagation.analytical.intelsat
Methods in org.orekit.propagation.analytical.intelsat with parameters of type FieldSpacecraftState Modifier and Type Method Description void
FieldIntelsatElevenElementsPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected void
FieldIntelsatElevenElementsPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state. -
Uses of FieldSpacecraftState in org.orekit.propagation.analytical.tle
Methods in org.orekit.propagation.analytical.tle with parameters of type FieldSpacecraftState Modifier and Type Method Description void
FieldTLEPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected void
FieldTLEPropagator. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.static <T extends CalculusFieldElement<T>>
FieldTLE<T>FieldTLE. stateToTLE(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE, TleGenerationAlgorithm generationAlgorithm)
Convert Spacecraft State into TLE. -
Uses of FieldSpacecraftState in org.orekit.propagation.analytical.tle.generation
Methods in org.orekit.propagation.analytical.tle.generation with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldTLE<T>FixedPointTleGenerationAlgorithm. generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)
Generate a TLE from a given spacecraft state and a template TLE.<T extends CalculusFieldElement<T>>
FieldTLE<T>LeastSquaresTleGenerationAlgorithm. generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)
Generate a TLE from a given spacecraft state and a template TLE.<T extends CalculusFieldElement<T>>
FieldTLE<T>TleGenerationAlgorithm. generate(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE)
Generate a TLE from a given spacecraft state and a template TLE. -
Uses of FieldSpacecraftState in org.orekit.propagation.events
Methods in org.orekit.propagation.events that return FieldSpacecraftState Modifier and Type Method Description FieldSpacecraftState<T>
FieldEventState.EventOccurrence. getNewState()
Get the new state for a reset action.FieldSpacecraftState<T>
FieldEventsLogger.FieldLoggedEvent. getState()
Get the triggering state.Methods in org.orekit.propagation.events that return types with arguments of type FieldSpacecraftState Modifier and Type Method Description Function<FieldSpacecraftState<T>,T>
FieldFunctionalDetector. getFunction()
Get the switching function.Methods in org.orekit.propagation.events with parameters of type FieldSpacecraftState Modifier and Type Method Description static <T extends CalculusFieldElement<T>>
TFieldBetaAngleDetector. calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider)
Calculate the beta angle between the orbit plane and the celestial body.static <T extends CalculusFieldElement<T>>
TFieldBetaAngleDetector. calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame frame)
Calculate the beta angle between the orbit plane and the celestial body.FieldPVCoordinates<T>
FieldExtremumApproachDetector. computeDeltaPV(FieldSpacecraftState<T> s)
Deprecated.The output type of this method shall be modified in the future to improve code efficiency (though it will still give access to the relative position and velocity)double
FieldAdaptableInterval. currentInterval(FieldSpacecraftState<T> state)
Get the current value of maximal time interval between events handler checks.FieldEventState.EventOccurrence<T>
FieldEventState. doEvent(FieldSpacecraftState<T> state)
Notify the user's listener of the event.boolean
FieldEnablingPredicate. eventIsEnabled(FieldSpacecraftState<T> state, FieldEventDetector<T> detector, T g)
Compute an event enabling function of state.void
FieldAdapterDetector. finish(FieldSpacecraftState<T> state)
This method finalizes the event detector's job.default void
FieldEventDetector. finish(FieldSpacecraftState<T> state)
This method finalizes the event detector's job.void
FieldEventState. finish(FieldSpacecraftState<T> state)
This method finalizes the event detector's job.T
FieldAdapterDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldAltitudeDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldApsideDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldBetaAngleDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldBooleanDetector. g(FieldSpacecraftState<T> s)
T
FieldCylindricalShadowEclipseDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldDateDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldEclipseDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldElevationDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldElevationExtremumDetector. g(FieldSpacecraftState<T> s)
Compute the value of the detection function.T
FieldEventDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldEventEnablingPredicateFilter. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldEventSlopeFilter. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldExtremumApproachDetector. g(FieldSpacecraftState<T> s)
Theg
is positive when the primary object is getting further away from the secondary object and is negative when it is getting closer to it.T
FieldFunctionalDetector. g(FieldSpacecraftState<T> s)
T
FieldLatitudeCrossingDetector. g(FieldSpacecraftState<T> s)
Compute the value of the detection function.T
FieldLatitudeRangeCrossingDetector. g(FieldSpacecraftState<T> s)
Compute the value of the detection function.T
FieldLongitudeCrossingDetector. g(FieldSpacecraftState<T> s)
Compute the value of the detection function.T
FieldLongitudeRangeCrossingDetector. g(FieldSpacecraftState<T> s)
Compute the value of the detection function.T
FieldNegateDetector. g(FieldSpacecraftState<T> s)
T
FieldNodeDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldParameterDrivenDateIntervalDetector. g(FieldSpacecraftState<T> s)
Compute the value of the switching function.T
FieldRelativeDistanceDetector. g(FieldSpacecraftState<T> s)
Theg
is positive when the relative distance is larger or equal than the threshold, non-positive otherwise.T
FieldElevationExtremumDetector. getElevation(FieldSpacecraftState<T> s)
Get the elevation value.void
FieldAbstractDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldAdapterDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldBooleanDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
default void
FieldEventDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldEventEnablingPredicateFilter. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldEventSlopeFilter. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldEventState. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldLongitudeCrossingDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.void
FieldNegateDetector. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
boolean
FieldEventState. tryAdvance(FieldSpacecraftState<T> state, FieldOrekitStepInterpolator<T> interpolator)
Try to accept the current history up to the given time.Method parameters in org.orekit.propagation.events with type arguments of type FieldSpacecraftState Modifier and Type Method Description FieldFunctionalDetector<T>
FieldFunctionalDetector. withFunction(Function<FieldSpacecraftState<T>,T> newGFunction)
Create a new event detector with a new g function, keeping all other attributes the same.Constructor parameters in org.orekit.propagation.events with type arguments of type FieldSpacecraftState Constructor Description FieldFunctionalDetector(FieldAdaptableInterval<T> maxCheck, T threshold, int maxIter, FieldEventHandler<T> handler, Function<FieldSpacecraftState<T>,T> function)
Private constructor. -
Uses of FieldSpacecraftState in org.orekit.propagation.events.handlers
Methods in org.orekit.propagation.events.handlers that return FieldSpacecraftState Modifier and Type Method Description FieldSpacecraftState<T>
FieldRecordAndContinue.Event. getState()
Get the spacecraft's state at the event.default FieldSpacecraftState<T>
FieldEventHandler. resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)
Reset the state prior to continue propagation.FieldSpacecraftState<T>
FieldRecallLastOccurrence. resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)
Reset the state prior to continue propagation.Methods in org.orekit.propagation.events.handlers with parameters of type FieldSpacecraftState Modifier and Type Method Description Action
FieldContinueOnEvent. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Specific implementation of the eventOccurred interface.Action
FieldEventHandler. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Handle an event.Action
FieldRecallLastOccurrence. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Handle an event.Action
FieldRecordAndContinue. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Action
FieldResetDerivativesOnEvent. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Specific implementation of the eventOccurred interface.Action
FieldStopOnDecreasing. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Handle a detection event and choose what to do next.Action
FieldStopOnEvent. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Specific implementation of the eventOccurred interface.Action
FieldStopOnIncreasing. eventOccurred(FieldSpacecraftState<T> s, FieldEventDetector<T> detector, boolean increasing)
Handle a detection event and choose what to do next.default void
FieldEventHandler. finish(FieldSpacecraftState<T> finalState, FieldEventDetector<T> detector)
This method finalize event handler at the end of a propagation.void
FieldRecallLastOccurrence. finish(FieldSpacecraftState<T> finalState, FieldEventDetector<T> detector)
This method finalize event handler at the end of a propagation.default void
FieldEventHandler. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target, FieldEventDetector<T> detector)
Initialize event handler at the start of a propagation.void
FieldRecallLastOccurrence. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target, FieldEventDetector<T> detector)
Initialize event handler at the start of a propagation.default FieldSpacecraftState<T>
FieldEventHandler. resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)
Reset the state prior to continue propagation.FieldSpacecraftState<T>
FieldRecallLastOccurrence. resetState(FieldEventDetector<T> detector, FieldSpacecraftState<T> oldState)
Reset the state prior to continue propagation. -
Uses of FieldSpacecraftState in org.orekit.propagation.integration
Methods in org.orekit.propagation.integration that return FieldSpacecraftState Modifier and Type Method Description protected FieldSpacecraftState<T>
FieldIntegratedEphemeris. basicPropagate(FieldAbsoluteDate<T> date)
Propagate an orbit without any fancy features.protected static FieldSpacecraftState<Gradient>
AbstractGradientConverter. buildBasicGradientSpacecraftState(SpacecraftState state, int freeStateParameters, AttitudeProvider provider)
Process a state into a Gradient version without force model parameter.protected FieldSpacecraftState<T>
FieldAbstractIntegratedPropagator. getInitialIntegrationState()
Get the initial state for integration.FieldSpacecraftState<T>
FieldIntegratedEphemeris. getInitialState()
Get the propagator initial state.FieldSpacecraftState<Gradient>
AbstractGradientConverter. getState(ParameterDriversProvider parametricModel)
Get the state with the number of parameters consistent with parametric model.abstract FieldSpacecraftState<T>
FieldStateMapper. mapArrayToState(FieldAbsoluteDate<T> date, T[] y, T[] yDot, PropagationType type)
Map the raw double components to a spacecraft state.FieldSpacecraftState<T>
FieldStateMapper. mapArrayToState(T t, T[] y, T[] yDot, PropagationType type)
Map the raw double components to a spacecraft state.FieldSpacecraftState<T>
FieldAbstractIntegratedPropagator. propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.FieldSpacecraftState<T>
FieldAbstractIntegratedPropagator. propagate(FieldAbsoluteDate<T> tStart, FieldAbsoluteDate<T> tEnd)
Propagate from a start date towards a target date.protected FieldSpacecraftState<T>
FieldIntegratedEphemeris. updateAdditionalStates(FieldSpacecraftState<T> original)
Update state by adding all additional states.Methods in org.orekit.propagation.integration with parameters of type FieldSpacecraftState Modifier and Type Method Description protected void
FieldAbstractIntegratedPropagator. beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd)
Method called just before integration.FieldCombinedDerivatives<T>
FieldAdditionalDerivativesProvider. combinedDerivatives(FieldSpacecraftState<T> s)
Compute the derivatives related to the additional state (and optionally main state increments).T[]
FieldAbstractIntegratedPropagator.MainStateEquations. computeDerivatives(FieldSpacecraftState<T> state)
Compute differential equations for main state.Gradient[]
AbstractGradientConverter. getParameters(FieldSpacecraftState<Gradient> state, ParameterDriversProvider parametricModel)
Get the parametric model parameters, return gradient values for each span of each driver (several gradient values for each parameter).Gradient[]
AbstractGradientConverter. getParametersAtStateDate(FieldSpacecraftState<Gradient> state, ParameterDriversProvider parametricModel)
Get the parametric model parameters, return gradient values at state date for each driver (only 1 gradient value for each parameter).void
FieldAbstractIntegratedPropagator.MainStateEquations. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the equations at the start of propagation.default void
FieldAdditionalDerivativesProvider. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the generator at the start of propagation.protected void
AbstractGradientConverter. initStates(FieldSpacecraftState<Gradient> zeroParametersState)
Initialize first state with 0 parameters.abstract void
FieldStateMapper. mapStateToArray(FieldSpacecraftState<T> state, T[] y, T[] yDot)
Map a spacecraft state to raw double components.void
FieldAbstractIntegratedPropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)
Reset initial state with a given propagation type.void
FieldIntegratedEphemeris. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.protected void
FieldIntegratedEphemeris. resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)
Reset an intermediate state.protected FieldSpacecraftState<T>
FieldIntegratedEphemeris. updateAdditionalStates(FieldSpacecraftState<T> original)
Update state by adding all additional states.default boolean
FieldAdditionalDerivativesProvider. yields(FieldSpacecraftState<T> state)
Check if this provider should yield so another provider has an opportunity to add missing parts. -
Uses of FieldSpacecraftState in org.orekit.propagation.numerical
Methods in org.orekit.propagation.numerical with parameters of type FieldSpacecraftState Modifier and Type Method Description void
FieldNumericalPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the propagator initial state.void
FieldNumericalPropagator. setInitialState(FieldSpacecraftState<T> initialState)
Set the initial state. -
Uses of FieldSpacecraftState in org.orekit.propagation.numerical.cr3bp
Methods in org.orekit.propagation.numerical.cr3bp with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>CR3BPForceModel. acceleration(FieldSpacecraftState<T> s, T[] parameters)
Compute acceleration.<T extends CalculusFieldElement<T>>
FieldDerivativeStructure<T>CR3BPForceModel. getPotential(FieldSpacecraftState<T> s)
Calculate spacecraft potential. -
Uses of FieldSpacecraftState in org.orekit.propagation.sampling
Methods in org.orekit.propagation.sampling that return FieldSpacecraftState Modifier and Type Method Description FieldSpacecraftState<T>
FieldOrekitStepInterpolator. getCurrentState()
Get the state at previous grid point date.FieldSpacecraftState<T>
FieldOrekitStepInterpolator. getInterpolatedState(FieldAbsoluteDate<T> date)
Get the state at interpolated date.FieldSpacecraftState<T>
FieldOrekitStepInterpolator. getPreviousState()
Get the state at previous grid point date.Methods in org.orekit.propagation.sampling with parameters of type FieldSpacecraftState Modifier and Type Method Description default void
FieldOrekitFixedStepHandler. finish(FieldSpacecraftState<T> finalState)
Finalize propagation.default void
FieldOrekitStepHandler. finish(FieldSpacecraftState<T> finalState)
Finalize propagation.void
FieldOrekitStepNormalizer. finish(FieldSpacecraftState<T> finalState)
Finalize propagation.void
FieldStepHandlerMultiplexer. finish(FieldSpacecraftState<T> finalState)
Finalize propagation.void
FieldOrekitFixedStepHandler. handleStep(FieldSpacecraftState<T> currentState)
Handle the current step.default void
FieldOrekitFixedStepHandler. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t, T step)
Initialize step handler at the start of a propagation.default void
FieldOrekitStepHandler. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.void
FieldOrekitStepNormalizer. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.void
FieldStepHandlerMultiplexer. init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.FieldOrekitStepInterpolator<T>
FieldOrekitStepInterpolator. restrictStep(FieldSpacecraftState<T> newPreviousState, FieldSpacecraftState<T> newCurrentState)
Create a new restricted version of the instance. -
Uses of FieldSpacecraftState in org.orekit.propagation.semianalytical.dsst
Methods in org.orekit.propagation.semianalytical.dsst that return FieldSpacecraftState Modifier and Type Method Description static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel)
Conversion from osculating to mean orbit.static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations)
Conversion from osculating to mean orbit.static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeOsculatingState(FieldSpacecraftState<T> mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces)
Conversion from mean to osculating orbit.protected FieldSpacecraftState<T>
FieldDSSTPropagator. getInitialIntegrationState()
Get the initial state for integration.Methods in org.orekit.propagation.semianalytical.dsst with parameters of type FieldSpacecraftState Modifier and Type Method Description protected void
FieldDSSTPropagator. beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd)
Method called just before integration.static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel)
Conversion from osculating to mean orbit.static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeMeanState(FieldSpacecraftState<T> osculating, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forceModel, double epsilon, int maxIterations)
Conversion from osculating to mean orbit.static <T extends CalculusFieldElement<T>>
FieldSpacecraftState<T>FieldDSSTPropagator. computeOsculatingState(FieldSpacecraftState<T> mean, AttitudeProvider attitudeProvider, Collection<DSSTForceModel> forces)
Conversion from mean to osculating orbit.void
FieldDSSTPropagator. resetInitialState(FieldSpacecraftState<T> state)
Reset the initial state.void
FieldDSSTPropagator. resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)
Reset initial state with a given propagation type.void
FieldDSSTPropagator. setInitialState(FieldSpacecraftState<T> initialState)
Set the initial state with osculating orbital elements.void
FieldDSSTPropagator. setInitialState(FieldSpacecraftState<T> initialState, PropagationType stateType)
Set the initial state. -
Uses of FieldSpacecraftState in org.orekit.propagation.semianalytical.dsst.forces
Methods in org.orekit.propagation.semianalytical.dsst.forces with parameters of type FieldSpacecraftState Modifier and Type Method Description AbstractGaussianContribution.FieldSlot<T>
AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients. createSlot(FieldSpacecraftState<T>... meanStates)
Get the slot valid for some date.protected abstract <T extends CalculusFieldElement<T>>
T[]AbstractGaussianContribution. getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)
Compute the limits in L, the true longitude, for integration.protected <T extends CalculusFieldElement<T>>
T[]DSSTAtmosphericDrag. getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)
Compute the limits in L, the true longitude, for integration.protected <T extends CalculusFieldElement<T>>
T[]DSSTSolarRadiationPressure. getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)
Compute the limits in L, the true longitude, for integration.protected <T extends CalculusFieldElement<T>>
T[]AbstractGaussianContribution. getMeanElementRate(FieldSpacecraftState<T> state, AbstractGaussianContribution.GaussQuadrature gauss, T low, T high, FieldAbstractGaussianContributionContext<T> context, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]AbstractGaussianContribution. getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTForceModel. getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTJ2SquaredClosedForm. getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTNewtonianAttraction. getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTTesseral. getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTThirdBody. getMeanElementRate(FieldSpacecraftState<T> currentState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
T[]DSSTZonal. getMeanElementRate(FieldSpacecraftState<T> spacecraftState, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.<T extends CalculusFieldElement<T>>
voidAbstractGaussianContribution. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.default <T extends CalculusFieldElement<T>>
voidDSSTForceModel. init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.<T extends CalculusFieldElement<T>>
voidAbstractGaussianContribution. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTForceModel. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTJ2SquaredClosedForm. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTNewtonianAttraction. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTTesseral. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTThirdBody. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidDSSTZonal. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.default <T extends CalculusFieldElement<T>>
voidJ2SquaredModel. updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the J2-squared short period terms.Constructors in org.orekit.propagation.semianalytical.dsst.forces with parameters of type FieldSpacecraftState Constructor Description FieldIntegrableFunction(FieldSpacecraftState<T> state, boolean meanMode, int j, T[] parameters, Field<T> field)
Build a new instance with a new field. -
Uses of FieldSpacecraftState in org.orekit.utils
Methods in org.orekit.utils with parameters of type FieldSpacecraftState Modifier and Type Method Description <T extends CalculusFieldElement<T>>
OccultationEngine.FieldOccultationAngles<T>OccultationEngine. angles(FieldSpacecraftState<T> state)
Compute the occultation angles as seen from a spacecraft.
-