Uses of Class
org.orekit.orbits.Orbit

Packages that use Orbit

Package	Description
org.orekit.estimation.leastsquares	The leastsquares package provides an implementation of a batch least squares estimator engine to perform an orbit determination.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.models.earth.tessellation	This package provides ways to do tessellation and sampling of zones of interest over an ellipsoid surface.
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.gnss	This package provides classes to propagate GNSS orbits.
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).

Uses of Orbit in org.orekit.estimation.leastsquares

Methods in org.orekit.estimation.leastsquares with parameters of type Orbit

Modifier and Type	Method and Description
void	BatchLSObserver.evaluationPerformed(int iterationsCount, int evaluationsCount, Orbit[] orbits, ParameterDriversList estimatedOrbitalParameters, ParameterDriversList estimatedPropagatorParameters, ParameterDriversList estimatedMeasurementsParameters, EstimationsProvider evaluationsProvider, LeastSquaresProblem.Evaluation lspEvaluation) Notification callback for the end of each evaluation.
void	ModelObserver.modelCalled(Orbit[] orbits, Map<ObservedMeasurement<?>,EstimatedMeasurement<?>> estimations) Notification callback for orbit changes.

Uses of Orbit in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers that return Orbit

Modifier and Type	Method and Description
Orbit	SmallManeuverAnalyticalModel.apply(Orbit orbit1) Compute the effect of the maneuver on an orbit.

Methods in org.orekit.forces.maneuvers with parameters of type Orbit

Modifier and Type	Method and Description
Orbit	SmallManeuverAnalyticalModel.apply(Orbit orbit1) Compute the effect of the maneuver on an orbit.
void	SmallManeuverAnalyticalModel.getJacobian(Orbit orbit1, PositionAngle positionAngle, double[][] jacobian) Compute the Jacobian of the orbit with respect to maneuver parameters.

Uses of Orbit in org.orekit.models.earth.tessellation

Constructors in org.orekit.models.earth.tessellation with parameters of type Orbit

Constructor and Description
AlongTrackAiming(OneAxisEllipsoid ellipsoid, Orbit orbit, boolean isAscending) Simple constructor.

Uses of Orbit in org.orekit.orbits

Subclasses of Orbit in org.orekit.orbits

Modifier and Type	Class and Description
class	CartesianOrbit This class holds Cartesian orbital parameters.
class	CircularOrbit This class handles circular orbital parameters.
class	EquinoctialOrbit This class handles equinoctial orbital parameters, which can support both circular and equatorial orbits.
class	KeplerianOrbit This class handles traditional Keplerian orbital parameters.

Methods in org.orekit.orbits that return Orbit

Modifier and Type	Method and Description
abstract Orbit	OrbitType.convertType(Orbit orbit) Convert an orbit to the instance type.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngle type, AbsoluteDate date, double mu, Frame frame) Convert state array to orbital parameters.
abstract Orbit	Orbit.shiftedBy(double dt) Get a time-shifted orbit.
abstract Orbit	FieldOrbit.toOrbit() Transforms the FieldOrbit instance into an Orbit instance.

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

Modifier and Type	Method and Description
abstract Orbit	OrbitType.convertType(Orbit orbit) Convert an orbit to the instance type.
abstract ParameterDriversList	OrbitType.getDrivers(double dP, Orbit orbit, PositionAngle type) Get parameters drivers initialized from a reference orbit.
abstract void	OrbitType.mapOrbitToArray(Orbit orbit, PositionAngle type, double[] stateVector, double[] stateVectorDot) Convert orbit to state array.
protected double[]	OrbitType.scale(double dP, Orbit orbit) Compute scaling factor for parameters drivers.

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

Modifier and Type	Method and Description
KeplerianOrbit	KeplerianOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample) Get an interpolated instance.
CircularOrbit	CircularOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample) Get an interpolated instance.
EquinoctialOrbit	EquinoctialOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample) Get an interpolated instance.
CartesianOrbit	CartesianOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample) Get an interpolated instance.

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

Constructor and Description
CartesianOrbit(Orbit op) Constructor from any kind of orbital parameters.
CircularOrbit(Orbit op) Constructor from any kind of orbital parameters.
EquinoctialOrbit(Orbit op) Constructor from any kind of orbital parameters.
KeplerianOrbit(Orbit op) Constructor from any kind of orbital parameters.

Uses of Orbit in org.orekit.propagation

Methods in org.orekit.propagation that return Orbit

Modifier and Type	Method and Description
Orbit	SpacecraftState.getOrbit() Get the current orbit.

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

Constructor and Description
SpacecraftState(Orbit orbit) Build a spacecraft state from orbit only.
SpacecraftState(Orbit orbit, Attitude attitude) Build a spacecraft state from orbit and attitude provider.
SpacecraftState(Orbit orbit, Attitude attitude, double mass) Build a spacecraft state from orbit, attitude provider and mass.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, Map<String,double[]> additional) Build a spacecraft state from orbit, attitude provider and mass.
SpacecraftState(Orbit orbit, Attitude attitude, Map<String,double[]> additional) Build a spacecraft state from orbit and attitude provider.
SpacecraftState(Orbit orbit, double mass) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, double mass, Map<String,double[]> additional) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, Map<String,double[]> additional) Build a spacecraft state from orbit only.

Uses of Orbit in org.orekit.propagation.analytical

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

Modifier and Type	Method and Description
Orbit	J2DifferentialEffect.apply(Orbit orbit1) Compute the effect of the maneuver on an orbit.
protected Orbit	KeplerianPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AggregateBoundedPropagator.propagateOrbit(AbsoluteDate date)
protected Orbit	AdapterPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected abstract Orbit	AbstractAnalyticalPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	Ephemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

Modifier and Type	Method and Description
Orbit	J2DifferentialEffect.apply(Orbit orbit1) Compute the effect of the maneuver on an orbit.

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

Constructor and Description
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, attitude provider and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) Private helper constructor.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) Build a propagator from orbit, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit and potential provider.
J2DifferentialEffect(Orbit orbit0, Orbit orbit1, boolean applyBefore, double referenceRadius, double mu, double j2) Simple constructor.
J2DifferentialEffect(Orbit orbit0, Orbit orbit1, boolean applyBefore, UnnormalizedSphericalHarmonicsProvider gravityField) Simple constructor.
KeplerianPropagator(Orbit initialOrbit) Build a propagator from orbit only.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv) Build a propagator from orbit and attitude provider.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu) Build a propagator from orbit, attitude provider and central attraction coefficient μ.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, double mass) Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
KeplerianPropagator(Orbit initialOrbit, double mu) Build a propagator from orbit and central attraction coefficient μ.

Uses of Orbit in org.orekit.propagation.analytical.gnss

Methods in org.orekit.propagation.analytical.gnss that return Orbit

Modifier and Type	Method and Description
protected Orbit	GLONASSAnalyticalPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AbstractGNSSPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

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

Modifier and Type	Method and Description
protected Orbit	TLEPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

Uses of Orbit in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion that return Orbit

Modifier and Type	Method and Description
protected Orbit	AbstractPropagatorBuilder.createInitialOrbit() Build an initial orbit using the current selected parameters.

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

Modifier and Type	Method and Description
AbstractIntegrator	ODEIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	EulerIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	ThreeEighthesIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	GraggBulirschStoerIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	DormandPrince54IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	HighamHall54IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	ClassicalRungeKuttaIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	MidpointIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	AdamsMoultonIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	AdamsBashforthIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	LutherIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	GillIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
AbstractIntegrator	DormandPrince853IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
void	IntegratedPropagatorBuilder.resetOrbit(Orbit newOrbit) Reset the orbit in the propagator builder.
void	AbstractPropagatorBuilder.resetOrbit(Orbit newOrbit) Reset the orbit in the propagator builder.

Constructors in org.orekit.propagation.conversion with parameters of type Orbit

Constructor and Description
AbstractPropagatorBuilder(Orbit templateOrbit, PositionAngle positionAngle, double positionScale, boolean addDriverForCentralAttraction) Build a new instance.
DSSTPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, double positionScale, PropagationType propagationType, PropagationType stateType) Build a new instance.
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit, double referenceRadius, double mu, TideSystem tideSystem, double c20, double c30, double c40, double c50, double c60, OrbitType orbitType, PositionAngle positionAngle, double positionScale) Build a new instance.
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit, UnnormalizedSphericalHarmonicsProvider provider, PositionAngle positionAngle, double positionScale) Build a new instance.
KeplerianPropagatorBuilder(Orbit templateOrbit, PositionAngle positionAngle, double positionScale) Build a new instance.
NumericalPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, PositionAngle positionAngle, double positionScale) Build a new instance.

Uses of Orbit in org.orekit.propagation.events

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

Constructor and Description
AlignmentDetector(double threshold, Orbit orbit, PVCoordinatesProvider body, double alignAngle) Build a new alignment detector.
AlignmentDetector(Orbit orbit, PVCoordinatesProvider body, double alignAngle) Build a new alignment detector.
ApsideDetector(double threshold, Orbit orbit) Build a new instance.
ApsideDetector(Orbit orbit) Build a new instance.
NodeDetector(double threshold, Orbit orbit, Frame frame) Build a new instance.
NodeDetector(Orbit orbit, Frame frame) Build a new instance.

Uses of Orbit in org.orekit.propagation.integration

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

Modifier and Type	Method and Description
protected Orbit	IntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

Uses of Orbit in org.orekit.propagation.numerical

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

Modifier and Type	Method and Description
static double[][]	NumericalPropagator.tolerances(double dP, Orbit orbit, OrbitType type) Estimate tolerance vectors for integrators when propagating in orbits.

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

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

Modifier and Type	Method and Description
static double[][]	DSSTPropagator.tolerances(double dP, Orbit orbit) Estimate tolerance vectors for an AdaptativeStepsizeIntegrator.

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

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

Modifier and Type	Method and Description
double[]	ShortPeriodTerms.value(Orbit meanOrbit) Evaluate the contributions of the short period terms.

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

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

Constructor and Description
AuxiliaryElements(Orbit orbit, int retrogradeFactor) Simple constructor.