Uses of Class
org.orekit.orbits.Orbit

Packages that use Orbit

Package	Description
org.orekit.estimation.iod	This package provides initial orbit determination methods.
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).
org.orekit.ssa.collision.shorttermencounter.probability.twod	Package specific to calculus assuming a 2D short-term encounter model.
org.orekit.utils	This package provides useful objects.

Uses of Orbit in org.orekit.estimation.iod

Methods in org.orekit.estimation.iod that return Orbit

Modifier and Type	Method and Description
Orbit	IodGauss.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3) Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodLaplace.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3) Estimate the orbit from three angular observations at the same location.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init) Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init, int nRev, boolean direction) Estimate orbit from three angular observations.
Orbit	IodGauss.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3) Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodLaplace.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3) Estimate the orbit from three angular observations at the same location.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init) Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init, int nRev, boolean direction) Estimate orbit from three angular observations.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2) Estimate an initial orbit from two position measurements.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, PV pv1, PV pv2) Estimate an initial orbit from two PV measurements.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, org.hipparchus.geometry.euclidean.threed.Vector3D p1, AbsoluteDate t1, org.hipparchus.geometry.euclidean.threed.Vector3D p2, AbsoluteDate t2) Estimate a Keplerian orbit given two position vectors and a duration.
Orbit	IodGibbs.estimate(Frame frame, Position p1, Position p2, Position p3) Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodLaplace.estimate(Frame outputFrame, PVCoordinates obsPva, AbsoluteDate obsDate1, org.hipparchus.geometry.euclidean.threed.Vector3D los1, AbsoluteDate obsDate2, org.hipparchus.geometry.euclidean.threed.Vector3D los2, AbsoluteDate obsDate3, org.hipparchus.geometry.euclidean.threed.Vector3D los3) Estimate orbit from three line of sight angles at the same location.
Orbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3) Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGibbs.estimate(Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D r1, AbsoluteDate date1, org.hipparchus.geometry.euclidean.threed.Vector3D r2, AbsoluteDate date2, org.hipparchus.geometry.euclidean.threed.Vector3D r3, AbsoluteDate date3) Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGauss.estimate(Frame outputFrame, org.hipparchus.geometry.euclidean.threed.Vector3D obsP1, AbsoluteDate obsDate1, org.hipparchus.geometry.euclidean.threed.Vector3D los1, org.hipparchus.geometry.euclidean.threed.Vector3D obsP2, AbsoluteDate obsDate2, org.hipparchus.geometry.euclidean.threed.Vector3D los2, org.hipparchus.geometry.euclidean.threed.Vector3D obsP3, AbsoluteDate obsDate3, org.hipparchus.geometry.euclidean.threed.Vector3D los3) Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodGooding.estimate(Frame outputFrame, org.hipparchus.geometry.euclidean.threed.Vector3D O1, org.hipparchus.geometry.euclidean.threed.Vector3D O2, org.hipparchus.geometry.euclidean.threed.Vector3D O3, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight1, AbsoluteDate dateObs1, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight2, AbsoluteDate dateObs2, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init) Estimate orbit from three line of sight.
Orbit	IodGooding.estimate(Frame outputFrame, org.hipparchus.geometry.euclidean.threed.Vector3D O1, org.hipparchus.geometry.euclidean.threed.Vector3D O2, org.hipparchus.geometry.euclidean.threed.Vector3D O3, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight1, AbsoluteDate dateObs1, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight2, AbsoluteDate dateObs2, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init, int nRev, boolean direction) Estimate orbit from three line of sight.

Uses of Orbit in org.orekit.estimation.leastsquares

Methods in org.orekit.estimation.leastsquares that return Orbit

Modifier and Type	Method and Description
protected abstract Orbit	AbstractBatchLSModel.configureOrbits(MatricesHarvester harvester, Propagator propagator) Configure the current estimated orbits.
protected Orbit	BatchLSModel.configureOrbits(MatricesHarvester harvester, Propagator propagator) Configure the current estimated orbits.
protected Orbit	DSSTBatchLSModel.configureOrbits(MatricesHarvester harvester, Propagator propagator) Configure the current estimated orbits.

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, org.hipparchus.optim.nonlinear.vector.leastsquares.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, PositionAngleType positionAngleType, 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.
Orbit	AbstractOrbitInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<Orbit> sample) Get an interpolated instance.
protected Orbit	OrbitBlender.interpolate(AbstractTimeInterpolator.InterpolationData interpolationData) Interpolate instance from given interpolation data.
protected Orbit	OrbitHermiteInterpolator.interpolate(AbstractTimeInterpolator.InterpolationData interpolationData) Interpolate instance from given interpolation data.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngleType type, AbsoluteDate date, double mu, Frame frame) Convert state array to orbital parameters.
abstract Orbit	OrbitType.normalize(Orbit orbit, Orbit reference) Normalize one orbit with respect to a reference one.
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 <T extends org.hipparchus.CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.convertToFieldOrbit(org.hipparchus.Field<T> field, Orbit orbit) Convert an orbit to the "Fielded" instance type.
abstract Orbit	OrbitType.convertType(Orbit orbit) Convert an orbit to the instance type.
abstract ParameterDriversList	OrbitType.getDrivers(double dP, Orbit orbit, PositionAngleType type) Get parameters drivers initialized from a reference orbit.
abstract void	OrbitType.mapOrbitToArray(Orbit orbit, PositionAngleType type, double[] stateVector, double[] stateVectorDot) Convert orbit to state array.
abstract Orbit	OrbitType.normalize(Orbit orbit, Orbit reference) Normalize one orbit with respect to a reference one.
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
static void	AbstractOrbitInterpolator.checkOrbitsConsistency(Collection<Orbit> sample) Check orbits consistency by comparing their gravitational parameters µ.
Orbit	AbstractOrbitInterpolator.interpolate(AbsoluteDate interpolationDate, 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.
FieldCartesianOrbit(org.hipparchus.Field<T> field, Orbit op) Constructor from Field and Orbit.
FieldCircularOrbit(org.hipparchus.Field<T> field, Orbit op) Constructor from Field and Orbit.
FieldEquinoctialOrbit(org.hipparchus.Field<T> field, Orbit op) Constructor from Field and Orbit.
FieldKeplerianOrbit(org.hipparchus.Field<T> field, Orbit op) Constructor from Field and Orbit.
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.
protected Orbit	AbstractStateCovarianceInterpolator.interpolateOrbit(AbsoluteDate interpolationDate, List<TimeStampedPair<Orbit,StateCovariance>> neighborList) Interpolate orbit at given interpolation date.

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

Modifier and Type	Method and Description
protected TimeStampedPair<Orbit,StateCovariance>	AbstractStateCovarianceInterpolator.expressCovarianceInDesiredOutput(Orbit interpolatedOrbit, StateCovariance covarianceInOrbitFrame) Express covariance in output configuration defined at this instance construction.
Optional<TimeInterpolator<Orbit>>	SpacecraftStateInterpolator.getOrbitInterpolator() Get orbit interpolator.
TimeInterpolator<Orbit>	AbstractStateCovarianceInterpolator.getOrbitInterpolator() Get orbit interpolator.
TimeStampedPair<Orbit,StateCovariance>	AbstractStateCovarianceInterpolator.interpolate(AbstractTimeInterpolator.InterpolationData interpolationData) Interpolate orbit and associated covariance.

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

Modifier and Type	Method and Description
StateCovariance	StateCovariance.changeCovarianceFrame(Orbit orbit, Frame frameOut) Get the covariance in the output frame.
StateCovariance	StateCovariance.changeCovarianceFrame(Orbit orbit, LOF lofOut) Get the covariance in a given local orbital frame.
StateCovariance	StateCovariance.changeCovarianceType(Orbit orbit, OrbitType outOrbitType, PositionAngleType outAngleType) Get the covariance matrix in another orbit type.
protected StateCovariance	StateCovarianceBlender.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected StateCovariance	StateCovarianceKeplerianHermiteInterpolator.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected abstract StateCovariance	AbstractStateCovarianceInterpolator.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected TimeStampedPair<Orbit,StateCovariance>	AbstractStateCovarianceInterpolator.expressCovarianceInDesiredOutput(Orbit interpolatedOrbit, StateCovariance covarianceInOrbitFrame) Express covariance in output configuration defined at this instance construction.
static org.hipparchus.linear.RealMatrix	StateCovariance.getStm(Orbit initialOrbit, double dt) Get the state transition matrix considering Keplerian contribution only.
StateCovariance	StateCovariance.shiftedBy(Orbit orbit, double dt) Get a time-shifted covariance matrix.

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

Modifier and Type	Method and Description
protected StateCovariance	StateCovarianceBlender.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected StateCovariance	StateCovarianceKeplerianHermiteInterpolator.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected abstract StateCovariance	AbstractStateCovarianceInterpolator.computeInterpolatedCovarianceInOrbitFrame(List<TimeStampedPair<Orbit,StateCovariance>> uncertainStates, Orbit interpolatedOrbit) Compute the interpolated covariance expressed in the interpolated orbit frame.
protected Orbit	AbstractStateCovarianceInterpolator.interpolateOrbit(AbsoluteDate interpolationDate, List<TimeStampedPair<Orbit,StateCovariance>> neighborList) Interpolate orbit at given interpolation date.

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.
SpacecraftState(Orbit orbit, Attitude attitude, double mass) Build a spacecraft state from orbit, attitude and mass.
SpacecraftState(Orbit orbit, Attitude attitude, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude, mass and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
SpacecraftState(Orbit orbit, double mass) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, DoubleArrayDictionary additional) Build a spacecraft state from orbit and additional states.
SpacecraftState(Orbit orbit, double mass, DoubleArrayDictionary additional) Create a new instance from orbit, mass and additional states.

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

Constructor and Description
AbstractStateCovarianceInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor.
AbstractStateCovarianceInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, LOFType outLOF) Constructor.
SpacecraftStateInterpolator(Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator) Constructor with: Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold of DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator) Constructor.
StateCovarianceBlender(org.hipparchus.analysis.polynomials.SmoothStepFactory.SmoothStepFunction blendingFunction, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor.
StateCovarianceBlender(org.hipparchus.analysis.polynomials.SmoothStepFactory.SmoothStepFunction blendingFunction, TimeInterpolator<Orbit> orbitInterpolator, LOFType outLOF) Constructor.
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor using an output frame.
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, LOFType outLOF) Constructor using an output local orbital frame.
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor using an output frame and : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, LOFType outLOF) Constructor using an output local orbital frame and : Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor using an output frame and : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, LOFType outLOF) Constructor using an output local orbital frame and : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType) Constructor using an output frame and : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(TimeInterpolator<Orbit> orbitInterpolator, LOFType outLOF) Constructor using an output local orbital frame and : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).

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	AggregateBoundedPropagator.propagateOrbit(AbsoluteDate 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.
protected Orbit	KeplerianPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

Modifier and Type	Method and Description
Optional<TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>>>	Ephemeris.getCovarianceInterpolator() Get covariance interpolator.

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.
static CircularOrbit	EcksteinHechlerPropagator.computeMeanOrbit(Orbit 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 KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit 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 CircularOrbit	EcksteinHechlerPropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2Value) Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2Value, double epsilon, int maxIterations) Conversion from osculating to mean orbit.
static CircularOrbit	EcksteinHechlerPropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double epsilon, int maxIterations) Conversion from osculating to mean orbit.

Method parameters in org.orekit.propagation.analytical with type arguments of type Orbit

Modifier and Type	Method and Description
static void	Ephemeris.checkInputConsistency(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator) Check input consistency between states, covariances and their associated interpolators.

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

Constructor and Description
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2) Build a propagator from orbit, attitude provider and potential.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2) Build a propagator from orbit, attitude provider, mass and potential.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, PropagationType initialType, double M2) Build a propagator from orbit, attitude provider, mass and potential.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double 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.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, double M2) Build a propagator from orbit, attitude provider, mass and potential provider.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2) Build a propagator from orbit, attitude provider, mass and potential provider.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2) Private helper constructor.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType, double M2) Private helper constructor.
BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider, double M2) Build a propagator from orbit, attitude provider and potential provider.
BrouwerLyddanePropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2) Build a propagator from orbit and potential.
BrouwerLyddanePropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2) Build a propagator from orbit, mass and potential.
BrouwerLyddanePropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider, double M2) Build a propagator from orbit, mass and potential provider.
BrouwerLyddanePropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, double M2) Build a propagator from orbit and potential provider.
BrouwerLyddanePropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2) Build a propagator from orbit and potential provider.
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, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, double epsilon, int maxIterations) 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 attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType) 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 attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType) 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.
EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType) 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.

Constructor parameters in org.orekit.propagation.analytical with type arguments of type Orbit

Constructor and Description
Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator) Constructor with tabulated states and associated covariances.
Ephemeris(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider) Constructor with tabulated states and associated covariances.

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	GNSSPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	GLONASSAnalyticalPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	SBASPropagator.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
org.hipparchus.ode.AbstractFieldIntegrator<T>	MidpointFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	GillFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	LutherFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
abstract org.hipparchus.ode.AbstractFieldIntegrator<T>	AbstractVariableStepFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	DormandPrince54FieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
abstract org.hipparchus.ode.AbstractFieldIntegrator<T>	AbstractFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	AdamsBashforthFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	EulerFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	FieldODEIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	ThreeEighthesFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	ClassicalRungeKuttaFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	HighamHall54FieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	DormandPrince853FieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractFieldIntegrator<T>	AdamsMoultonFieldIntegratorBuilder.buildIntegrator(org.hipparchus.Field<T> field, Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	MidpointIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	ClassicalRungeKuttaIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	DormandPrince853IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	HighamHall54IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	AdamsMoultonIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	EulerIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	AdamsBashforthIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	LutherIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	ThreeEighthesIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	ODEIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	DormandPrince54IntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	GraggBulirschStoerIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
org.hipparchus.ode.AbstractIntegrator	GillIntegratorBuilder.buildIntegrator(Orbit orbit, OrbitType orbitType) Build a first order integrator.
void	AbstractPropagatorBuilder.resetOrbit(Orbit newOrbit) Reset the orbit in the propagator builder.
void	PropagatorBuilder.resetOrbit(Orbit newOrbit) Reset the orbit in the propagator builder.
void	DSSTPropagatorBuilder.resetOrbit(Orbit newOrbit, PropagationType orbitType) Reset the orbit in the propagator builder.

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

Constructor and Description
AbstractPropagatorBuilder(Orbit templateOrbit, PositionAngleType positionAngleType, double positionScale, boolean addDriverForCentralAttraction) Build a new instance.
AbstractPropagatorBuilder(Orbit templateOrbit, PositionAngleType positionAngleType, double positionScale, boolean addDriverForCentralAttraction, AttitudeProvider attitudeProvider) Build a new instance.
BrouwerLyddanePropagatorBuilder(Orbit templateOrbit, double referenceRadius, double mu, TideSystem tideSystem, double c20, double c30, double c40, double c50, OrbitType orbitType, PositionAngleType positionAngleType, double positionScale, double M2) Build a new instance.
BrouwerLyddanePropagatorBuilder(Orbit templateOrbit, UnnormalizedSphericalHarmonicsProvider provider, PositionAngleType positionAngleType, double positionScale, AttitudeProvider attitudeProvider, double M2) Build a new instance.
BrouwerLyddanePropagatorBuilder(Orbit templateOrbit, UnnormalizedSphericalHarmonicsProvider provider, PositionAngleType positionAngleType, double positionScale, double M2) Build a new instance.
DSSTPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, double positionScale, PropagationType propagationType, PropagationType stateType) Build a new instance.
DSSTPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, double positionScale, PropagationType propagationType, PropagationType stateType, AttitudeProvider attitudeProvider) 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, PositionAngleType positionAngleType, double positionScale) Build a new instance.
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit, UnnormalizedSphericalHarmonicsProvider provider, PositionAngleType positionAngleType, double positionScale) Build a new instance.
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit, UnnormalizedSphericalHarmonicsProvider provider, PositionAngleType positionAngleType, double positionScale, AttitudeProvider attitudeProvider) Build a new instance.
KeplerianPropagatorBuilder(Orbit templateOrbit, PositionAngleType positionAngleType, double positionScale) Build a new instance.
KeplerianPropagatorBuilder(Orbit templateOrbit, PositionAngleType positionAngleType, double positionScale, AttitudeProvider attitudeProvider) Build a new instance.
NumericalPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, PositionAngleType positionAngleType, double positionScale) Build a new instance.
NumericalPropagatorBuilder(Orbit referenceOrbit, ODEIntegratorBuilder builder, PositionAngleType positionAngleType, double positionScale, AttitudeProvider attitudeProvider) Build a new instance.

Constructor parameters in org.orekit.propagation.conversion with type arguments of type Orbit

Constructor and Description
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator) Constructor with covariances and default attitude provider.
EphemerisPropagatorBuilder(List<SpacecraftState> states, TimeInterpolator<SpacecraftState> stateInterpolator, List<StateCovariance> covariances, TimeInterpolator<TimeStampedPair<Orbit,StateCovariance>> covarianceInterpolator, AttitudeProvider attitudeProvider) Constructor.

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, double dV, Orbit orbit, OrbitType type) Estimate tolerance vectors for integrators when propagating in orbits.
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, double dV, Orbit orbit) Estimate tolerance vectors for an AdaptativeStepsizeIntegrator.
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.
double[]	AbstractGaussianContribution.GaussianShortPeriodicCoefficients.value(Orbit meanOrbit) Evaluate the contributions of the short period terms.

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

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

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

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

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

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

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

Modifier and Type	Method and Description
protected Orbit	AbstractShortTermEncounter2DPOCMethod.getObjectOrbitFromCdm(CdmRelativeMetadata cdmRelativeMetadata, CdmData cdmData, CdmMetadata cdmMetadata, DataContext cdmDataContext) Extract collision object spacecraft state from given Conjunction Data Message data.
Orbit	ShortTermEncounter2DDefinition.getOtherAtTCA() Get other's orbit at time of closest approach.
Orbit	ShortTermEncounter2DDefinition.getReferenceAtTCA() Get reference's orbit at time of closest approach.

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

Modifier and Type	Method and Description
default ProbabilityOfCollision	ShortTermEncounter2DPOCMethod.compute(Orbit primaryAtTCA, StateCovariance primaryCovariance, double primaryRadius, Orbit secondaryAtTCA, StateCovariance secondaryCovariance, double secondaryRadius) Compute the probability of collision using parameters necessary for creating a collision definition instance.
ProbabilityOfCollision	AbstractShortTermEncounter1DNumerical2DPOCMethod.compute(Orbit primaryAtTCA, StateCovariance primaryCovariance, double primaryRadius, Orbit secondaryAtTCA, StateCovariance secondaryCovariance, double secondaryRadius, org.hipparchus.analysis.integration.UnivariateIntegrator customIntegrator, int customMaxNbOfEval, double zeroThreshold) Compute the probability of collision using parameters necessary for creating a collision definition instance.
default ProbabilityOfCollision	ShortTermEncounter2DPOCMethod.compute(Orbit primaryAtTCA, StateCovariance primaryCovariance, Orbit secondaryAtTCA, StateCovariance secondaryCovariance, double combinedRadius) Compute the probability of collision using parameters necessary for creating a collision definition instance.
ProbabilityOfCollision	AbstractShortTermEncounter2DPOCMethod.compute(Orbit primaryAtTCA, StateCovariance primaryCovariance, Orbit secondaryAtTCA, StateCovariance secondaryCovariance, double combinedRadius, double zeroThreshold) Compute the probability of collision using parameters necessary for creating a collision definition instance.
ProbabilityOfCollision	ShortTermEncounter2DPOCMethod.compute(Orbit primaryAtTCA, StateCovariance primaryCovariance, Orbit secondaryAtTCA, StateCovariance secondaryCovariance, double combinedRadius, double zeroThreshold) 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 Orbit

Constructor and Description
ShortTermEncounter2DDefinition(Orbit referenceAtTCA, StateCovariance referenceCovariance, double referenceRadius, Orbit otherAtTCA, StateCovariance otherCovariance, double otherRadius) Constructor.
ShortTermEncounter2DDefinition(Orbit referenceAtTCA, StateCovariance referenceCovariance, double referenceRadius, Orbit otherAtTCA, StateCovariance otherCovariance, double otherRadius, EncounterLOFType encounterFrameType, double tcaTolerance) Constructor.
ShortTermEncounter2DDefinition(Orbit referenceAtTCA, StateCovariance referenceCovariance, Orbit otherAtTCA, StateCovariance otherCovariance, double combinedRadius) Constructor.
ShortTermEncounter2DDefinition(Orbit referenceAtTCA, StateCovariance referenceCovariance, Orbit otherAtTCA, StateCovariance otherCovariance, double combinedRadius, EncounterLOFType encounterFrameType, double tcaTolerance) Constructor.

Uses of Orbit in org.orekit.utils

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

Modifier and Type	Method and Description
static <T extends org.hipparchus.CalculusFieldElement<T>> FieldOrbit<T>	Fieldifier.fieldify(org.hipparchus.Field<T> field, Orbit orbit) Fieldify given orbit with given field.