Uses of Class
org.orekit.orbits.PositionAngle

Packages that use PositionAngle

Package	Description
org.orekit.estimation.sequential
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.orbits	This package provides classes to represent orbits.
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.utils	This package provides useful objects.

Uses of PositionAngle in org.orekit.estimation.sequential

Methods in org.orekit.estimation.sequential that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	UnivariateProcessNoise.getPositionAngle() Getter for the positionAngle.

Constructors in org.orekit.estimation.sequential with parameters of type PositionAngle

Constructor and Description
UnivariateProcessNoise(RealMatrix initialCovarianceMatrix, LOFType lofType, PositionAngle positionAngle, UnivariateFunction[] lofCartesianOrbitalParametersEvolution, UnivariateFunction[] propagationParametersEvolution) Simple constructor.

Uses of PositionAngle in org.orekit.files.ccsds

Methods in org.orekit.files.ccsds that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	OGMFile.getAnomalyType() Get the type of anomaly (true or mean).

Uses of PositionAngle in org.orekit.forces.maneuvers

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

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

Uses of PositionAngle in org.orekit.orbits

Methods in org.orekit.orbits that return PositionAngle

Modifier and Type	Method and Description
static PositionAngle	PositionAngle.valueOf(String name) Returns the enum constant of this type with the specified name.
static PositionAngle[]	PositionAngle.values() Returns an array containing the constants of this enum type, in the order they are declared.

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

Modifier and Type	Method and Description
void	KeplerianOrbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	CircularOrbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	EquinoctialOrbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	CartesianOrbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
abstract void	Orbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	FieldCircularOrbit.addKeplerContribution(PositionAngle type, T gm, T[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	FieldCartesianOrbit.addKeplerContribution(PositionAngle type, T gm, T[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
abstract void	FieldOrbit.addKeplerContribution(PositionAngle type, T gm, T[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	FieldEquinoctialOrbit.addKeplerContribution(PositionAngle type, T gm, T[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
void	FieldKeplerianOrbit.addKeplerContribution(PositionAngle type, T gm, T[] pDot) Add the contribution of the Keplerian motion to parameters derivatives
T	FieldCircularOrbit.getAlpha(PositionAngle type) Get the latitude argument.
double	CircularOrbit.getAlpha(PositionAngle type) Get the latitude argument.
T	FieldCircularOrbit.getAlphaDot(PositionAngle type) Get the latitude argument derivative.
double	CircularOrbit.getAlphaDot(PositionAngle type) Get the latitude argument derivative.
double	KeplerianOrbit.getAnomaly(PositionAngle type) Get the anomaly.
T	FieldKeplerianOrbit.getAnomaly(PositionAngle type) Get the anomaly.
double	KeplerianOrbit.getAnomalyDot(PositionAngle type) Get the anomaly derivative.
T	FieldKeplerianOrbit.getAnomalyDot(PositionAngle type) Get the anomaly derivative.
abstract ParameterDriversList	OrbitType.getDrivers(double dP, Orbit orbit, PositionAngle type) Get parameters drivers initialized from a reference orbit.
void	Orbit.getJacobianWrtCartesian(PositionAngle type, double[][] jacobian) Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
void	FieldOrbit.getJacobianWrtCartesian(PositionAngle type, T[][] jacobian) Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
void	Orbit.getJacobianWrtParameters(PositionAngle type, double[][] jacobian) Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
void	FieldOrbit.getJacobianWrtParameters(PositionAngle type, T[][] jacobian) Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
T	FieldEquinoctialOrbit.getL(PositionAngle type) Get the longitude argument.
double	EquinoctialOrbit.getL(PositionAngle type) Get the longitude argument.
T	FieldEquinoctialOrbit.getLDot(PositionAngle type) Get the longitude argument derivative.
double	EquinoctialOrbit.getLDot(PositionAngle type) Get the longitude argument derivative.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngle type, AbsoluteDate date, double mu, Frame frame) Convert state array to orbital parameters.
abstract <T extends RealFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngle type, FieldAbsoluteDate<T> date, T mu, Frame frame) Convert state array to orbital parameters.
abstract <T extends RealFieldElement<T>> void	OrbitType.mapOrbitToArray(FieldOrbit<T> orbit, PositionAngle type, T[] stateVector, T[] stateVectorDot) Convert orbit to state array.
abstract void	OrbitType.mapOrbitToArray(Orbit orbit, PositionAngle type, double[] stateVector, double[] stateVectorDot) Convert orbit to state array.

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

Constructor and Description
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, T aDot, T exDot, T eyDot, T iDot, T raanDot, T alphaDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.

Uses of PositionAngle in org.orekit.propagation.conversion

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

Modifier and Type	Method and Description
PositionAngle	PropagatorBuilder.getPositionAngle() Get the position angle type expected for the 6 first parameters in PropagatorBuilder.buildPropagator(double[]).
PositionAngle	AbstractPropagatorBuilder.getPositionAngle() Get the position angle type expected for the 6 first parameters in PropagatorBuilder.buildPropagator(double[]).

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

Constructor and Description
AbstractPropagatorBuilder(Orbit templateOrbit, PositionAngle positionAngle, double positionScale, boolean addDriverForCentralAttraction) 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.
TLEPropagatorBuilder(TLE templateTLE, PositionAngle positionAngle, double positionScale) Build a new instance.

Uses of PositionAngle in org.orekit.propagation.events

Methods in org.orekit.propagation.events that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	PositionAngleDetector.getPositionAngle() Get the type of position angle.

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

Constructor and Description
PositionAngleDetector(double maxCheck, double threshold, OrbitType orbitType, PositionAngle positionAngle, double angle) Build a detector.
PositionAngleDetector(OrbitType orbitType, PositionAngle positionAngle, double angle) Build a new detector.

Uses of PositionAngle in org.orekit.propagation.integration

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

Modifier and Type	Method and Description
protected PositionAngle	AbstractIntegratedPropagator.getPositionAngleType() Get propagation parameter type.
PositionAngle	StateMapper.getPositionAngleType() Get propagation parameter type.
PositionAngle	FieldStateMapper.getPositionAngleType() Get propagation parameter type.
protected PositionAngle	FieldAbstractIntegratedPropagator.getPositionAngleType() Get propagation parameter type.

Methods in org.orekit.propagation.integration with parameters of type PositionAngle

Modifier and Type	Method and Description
protected abstract StateMapper	AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected abstract FieldStateMapper<T>	FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected void	AbstractIntegratedPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.
protected void	FieldAbstractIntegratedPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.

Constructors in org.orekit.propagation.integration with parameters of type PositionAngle

Constructor and Description
FieldStateMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Simple constructor.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Simple constructor.

Uses of PositionAngle in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	FieldNumericalPropagator.getPositionAngleType() Get propagation parameter type.
PositionAngle	NumericalPropagator.getPositionAngleType() Get propagation parameter type.

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

Modifier and Type	Method and Description
protected StateMapper	GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected FieldStateMapper<T>	FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
void	FieldNumericalPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.
void	NumericalPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.

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

Methods in org.orekit.propagation.semianalytical.dsst that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	FieldDSSTPropagator.getPositionAngleType() Get propagation parameter type.
PositionAngle	DSSTPropagator.getPositionAngleType() Get propagation parameter type.

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

Modifier and Type	Method and Description
protected StateMapper	DSSTPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected FieldStateMapper<T>	FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.

Uses of PositionAngle in org.orekit.utils

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

Modifier and Type	Method and Description
static StateJacobian	Differentiation.differentiate(StateFunction function, int dimension, AttitudeProvider provider, OrbitType orbitType, PositionAngle positionAngle, double dP, int nbPoints) Differentiate a vector function using finite differences.