Uses of Class
org.orekit.orbits.Orbit

Packages that use Orbit

Package	Description
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	This package provides tools to propagate orbital states with different methods.
org.orekit.propagation.analytical
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
org.orekit.propagation.numerical
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.utilities

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.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, 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.

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 void	OrbitType.mapOrbitToArray(Orbit orbit, PositionAngle type, double[] stateVector) Convert orbit to state array.

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

Modifier and Type	Method and Description
CircularOrbit	CircularOrbit.interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.
CartesianOrbit	CartesianOrbit.interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.
EquinoctialOrbit	EquinoctialOrbit.interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.
KeplerianOrbit	KeplerianOrbit.interpolate(AbsoluteDate date, Collection<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() Gets 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	AdapterPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	KeplerianPropagator.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.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 with parameters of type Orbit

Modifier and Type	Method and Description
AbstractIntegrator	ThreeEighthesIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	MidpointIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	AdamsMoultonIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	DormandPrince853IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	DormandPrince54IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	EulerIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	AdamsBashforthIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	ClassicalRungeKuttaIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	GraggBulirschStoerIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	GillIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	HighamHall54IntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.
AbstractIntegrator	FirstOrderIntegratorBuilder.buildIntegrator(Orbit orbit) Build a first order integrator.

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.

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.utilities

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

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