Uses of Class
fr.cnes.sirius.patrius.orbits.PositionAngle

Packages that use PositionAngle

Package	Description
fr.cnes.sirius.patrius.forces.maneuvers
fr.cnes.sirius.patrius.orbits
fr.cnes.sirius.patrius.orbits.orbitalparameters
fr.cnes.sirius.patrius.propagation
fr.cnes.sirius.patrius.propagation.events
fr.cnes.sirius.patrius.propagation.events.multi
fr.cnes.sirius.patrius.propagation.numerical
fr.cnes.sirius.patrius.propagation.numerical.multi
fr.cnes.sirius.patrius.propagation.precomputed
fr.cnes.sirius.patrius.propagation.precomputed.multi
fr.cnes.sirius.patrius.propagation.sampling
fr.cnes.sirius.patrius.propagation.sampling.multi
fr.cnes.sirius.patrius.stela.orbits

Uses of PositionAngle in fr.cnes.sirius.patrius.forces.maneuvers

Methods in fr.cnes.sirius.patrius.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 fr.cnes.sirius.patrius.orbits

Methods in fr.cnes.sirius.patrius.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 fr.cnes.sirius.patrius.orbits with parameters of type PositionAngle

Modifier and Type	Method and Description
void	Orbit.addKeplerContribution(PositionAngle type, double gm, double[] pDot) Call the method Orbit.orbitAddKeplerContribution(PositionAngle, double, double[]) implemented in inherited classes of Orbit.
protected double[][]	Orbit.createInverseJacobian(PositionAngle type) Create an inverse Jacobian.
double	CircularOrbit.getAlpha(PositionAngle type) Get the latitude argument.
double	KeplerianOrbit.getAnomaly(PositionAngle type) Get the anomaly.
double	EquatorialOrbit.getAnomaly(PositionAngle type) Get the anomaly.
double	ApsisOrbit.getAnomaly(PositionAngle type) Get the anomaly.
RealMatrix	Orbit.getJacobian(double dt, Frame initFrame, Frame destFrame, OrbitType initOrbitType, OrbitType destOrbitType, PositionAngle initAngleType, PositionAngle destAngleType) Computes the Jacobian of the transformation between the specified frames, orbit types and position angle types with respect to this orbit and specified time shift.
RealMatrix	Orbit.getJacobian(Frame initFrame, Frame destFrame, OrbitType initOrbitType, OrbitType destOrbitType, PositionAngle initAngleType, PositionAngle destAngleType) Computes the Jacobian of the transformation between the specified frames, orbit types and position angle types with respect to this orbit.
RealMatrix	Orbit.getJacobian(OrbitType numerator, OrbitType denominator, PositionAngle positionAngle) Get coordinate conversion jacobian.
void	Orbit.getJacobianWrtCartesian(PositionAngle type, double[][] 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	EquinoctialOrbit.getJacobianWrtParameters(PositionAngle type, double[][] jacobian) Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
void	AlternateEquinoctialOrbit.getJacobianWrtParameters(PositionAngle type, double[][] jacobian) Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
double	EquinoctialOrbit.getL(PositionAngle type) Get the longitude argument.
double	AlternateEquinoctialOrbit.getL(PositionAngle type) Get the longitude argument.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, PositionAngle type, AbsoluteDate date, double mu, Frame frame) Convert state array to orbital parameters.
abstract void	OrbitType.mapOrbitToArray(Orbit orbit, PositionAngle type, double[] stateVector) Convert orbit to state array.
protected abstract void	Orbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	KeplerianOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	CircularOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	EquatorialOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	EquinoctialOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	ApsisOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	CartesianOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
protected void	AlternateEquinoctialOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.

Constructors in fr.cnes.sirius.patrius.orbits with parameters of type PositionAngle

Constructor and Description
AlternateEquinoctialOrbit(double n, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
ApsisOrbit(double peri, double apo, double i, double pa, double raan, double anomaly, 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.
EquatorialOrbit(double a, double e, double pomega, double ix, double iy, double anomaly, 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.
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 fr.cnes.sirius.patrius.orbits.orbitalparameters

Methods in fr.cnes.sirius.patrius.orbits.orbitalparameters with parameters of type PositionAngle

Modifier and Type	Method and Description
double	CircularParameters.getAlpha(PositionAngle type) Get the latitude argument.
double	EquatorialParameters.getAnomaly(PositionAngle type) Get the anomaly.
double	ApsisAltitudeParameters.getAnomaly(PositionAngle type) Get the anomaly.
double	KeplerianParameters.getAnomaly(PositionAngle type) Get the anomaly.
double	ApsisRadiusParameters.getAnomaly(PositionAngle type) Get the anomaly.
double	EquinoctialParameters.getL(PositionAngle type) Get the longitude argument.
double	AlternateEquinoctialParameters.getL(PositionAngle type) Get the longitude argument.

Constructors in fr.cnes.sirius.patrius.orbits.orbitalparameters with parameters of type PositionAngle

Constructor and Description
AlternateEquinoctialParameters(double nIn, double exIn, double eyIn, double hxIn, double hyIn, double l, PositionAngle type, double mu) Creates a new instance.
ApsisAltitudeParameters(double periapsisAltitudeIn, double apoapsisAltitudeIn, double i, double pa, double raan, double anomaly, PositionAngle type, double mu, double aeIn) Creates a new instance.
ApsisRadiusParameters(double periapsisIn, double apoapsisIn, double i, double pa, double raan, double anomaly, PositionAngle type, double mu) Creates a new instance.
CircularParameters(double aIn, double exIn, double eyIn, double iIn, double raanIn, double alpha, PositionAngle type, double mu) Creates a new instance.
EquatorialParameters(double aIn, double eIn, double pomegaIn, double ixIn, double iyIn, double anomaly, PositionAngle type, double mu) Creates a new instance.
EquinoctialParameters(double aIn, double exIn, double eyIn, double hxIn, double hyIn, double l, PositionAngle type, double mu) Creates a new instance.
KeplerianParameters(double aIn, double eIn, double iIn, double paIn, double raanIn, double anomaly, PositionAngle type, double mu) Creates a new instance.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation

Methods in fr.cnes.sirius.patrius.propagation with parameters of type PositionAngle

Modifier and Type	Method and Description
void	SpacecraftState.mapStateToArray(OrbitType orbitType, PositionAngle angleType, double[] stateVector) Convert SpacecraftState to state vector.

Constructors in fr.cnes.sirius.patrius.propagation with parameters of type PositionAngle

Constructor and Description
SpacecraftState(double[] y, OrbitType orbitType, PositionAngle angleType, AbsoluteDate date, double mu, Frame frame, Map<String,AdditionalStateInfo> addStatesInfo, Attitude attForces, Attitude attEvents) Build a spacecraft from an array (a state vector) and an additional states informations map.
SpacecraftState(double[] y, OrbitType orbitType, PositionAngle angleType, AbsoluteDate date, double mu, Frame frame, Map<String,AdditionalStateInfo> addStatesInfo, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents) Build a spacecraft from an array (a state vector) and an additional states informations map.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.events

Methods in fr.cnes.sirius.patrius.propagation.events that return PositionAngle

Modifier and Type	Method and Description
PositionAngle	AnomalyDetector.getAnomalyType() Get the type of anomaly to detect.
PositionAngle	AOLDetector.getAOLType() Get the type of AOL to detect.

Methods in fr.cnes.sirius.patrius.propagation.events with parameters of type PositionAngle

Modifier and Type	Method and Description
void	AdaptedEventDetector.reinitialize(Map<String,AdditionalStateInfo> info, OrbitType orbitTypeIn, PositionAngle angleTypeIn, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, AbsoluteDate referenceDateIn, double muIn, Frame integrationFrameIn) Reinitialize reference data.

Constructors in fr.cnes.sirius.patrius.propagation.events with parameters of type PositionAngle

Constructor and Description
AdaptedEventDetector(EventDetector detectorIn, Map<String,AdditionalStateInfo> info, OrbitType orbitTypeIn, PositionAngle angleTypeIn, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, AbsoluteDate referenceDateIn, double muIn, Frame integrationFrameIn) Build a wrapped event detector.
AnomalyDetector(PositionAngle angleType, double angle) Constructor for an AnomalyDetector instance.
AnomalyDetector(PositionAngle angleType, double angle, double maxCheck, double threshold) Constructor for an AnomalyDetector instance with complementary parameters.
AnomalyDetector(PositionAngle angleType, double angle, double maxCheck, double threshold, EventDetector.Action action) Constructor for an AnomalyDetector instance with complementary parameters.
AnomalyDetector(PositionAngle angleType, double angle, double maxCheck, double threshold, EventDetector.Action action, boolean remove) Constructor for an AnomalyDetector instance with complementary parameters.
AOLDetector(double angle, PositionAngle type, Frame equator) Constructor for an AOLDetector instance.
AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold) Constructor for an AOLDetector instance with complementary parameters.
AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold, EventDetector.Action action) Constructor for an AOLDetector instance with complementary parameters.
AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold, EventDetector.Action action, boolean remove) Constructor for an AOLDetector instance with complementary parameters.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.events.multi

Methods in fr.cnes.sirius.patrius.propagation.events.multi with parameters of type PositionAngle

Modifier and Type	Method and Description
void	AdaptedMultiEventDetector.reinitialize(OrbitType orbitType, PositionAngle angleType, Map<String,MultiAttitudeProvider> attProvidersForces, Map<String,MultiAttitudeProvider> attProvidersEvents, AbsoluteDate referenceDate, Map<String,Double> muMap, Map<String,Frame> framesMap, MultiStateVectorInfo stateVectorInfo) Reinitialize data.
void	AdaptedMonoEventDetector.reinitialize(OrbitType orbitType, PositionAngle angleType, MultiAttitudeProvider attProviderForces, MultiAttitudeProvider attProviderEvents, AbsoluteDate referenceDate, MultiStateVectorInfo stateVectorInfo, String satId) Reinitialize data.

Constructors in fr.cnes.sirius.patrius.propagation.events.multi with parameters of type PositionAngle

Constructor and Description
AdaptedMonoEventDetector(EventDetector detector, OrbitType orbitType, PositionAngle angleType, MultiAttitudeProvider attProviderForces, MultiAttitudeProvider attProviderEvents, AbsoluteDate referenceDate, MultiStateVectorInfo stateVectorInfo, String satId) Build a wrapped event detector.
AdaptedMultiEventDetector(MultiEventDetector detector, OrbitType orbitType, PositionAngle angleType, Map<String,MultiAttitudeProvider> attProvidersForces, Map<String,MultiAttitudeProvider> attProvidersEvents, AbsoluteDate referenceDate, Map<String,Double> muMap, Map<String,Frame> framesMap, MultiStateVectorInfo stateVectorInfo) Build a wrapped multi-sat event detector.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.numerical

Methods in fr.cnes.sirius.patrius.propagation.numerical that return PositionAngle

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

Methods in fr.cnes.sirius.patrius.propagation.numerical with parameters of type PositionAngle

Modifier and Type	Method and Description
void	ModeHandler.initialize(OrbitType orbit, PositionAngle angle, AttitudeProvider attitudeProviderForces, AttitudeProvider attitudeProviderEvents, Map<String,AdditionalStateInfo> additionalStateInfos, boolean activateHandlers, AbsoluteDate reference, Frame frame, double mu) Initialize the mode handler.
void	NumericalPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.

Constructors in fr.cnes.sirius.patrius.propagation.numerical with parameters of type PositionAngle

Constructor and Description
JacobiansMapper(String nameIn, List<Parameter> list, OrbitType orbitTypeIn, PositionAngle angleTypeIn, Frame frame) Simple constructor.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.numerical.multi

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return PositionAngle

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

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type PositionAngle

Modifier and Type	Method and Description
void	MultiModeHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,MultiAttitudeProvider> attitudeProvidersForces, Map<String,MultiAttitudeProvider> attitudeProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frame, Map<String,Double> mu) Initialize the mode handler.
void	MultiEphemerisModeHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,MultiAttitudeProvider> attitudeProvidersForces, Map<String,MultiAttitudeProvider> attitudeProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frame, Map<String,Double> mu) Initialize the mode handler.
SpacecraftState	MultiStateVectorInfo.mapArrayToState(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, MultiAttitudeProvider attProviderForces, MultiAttitudeProvider attProviderEvents, String id) Extract a given SpacecraftState from the state vector.
Map<String,SpacecraftState>	MultiStateVectorInfo.mapArrayToStates(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, Map<String,MultiAttitudeProvider> attProvidersForces, Map<String,MultiAttitudeProvider> attProvidersEvents, Map<String,Double> mu, Map<String,Frame> integrationFrame) Convert state vector into a Map of SpacecraftState
void	MultiStateVectorInfo.mapStatesToArray(Map<String,SpacecraftState> s, OrbitType orbitType, PositionAngle angleType, double[] y) Convert a map of SpacecraftState into a state vector.
void	MultiNumericalPropagator.setPositionAngleType(PositionAngle positionAngleType) Set position angle type.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.precomputed

Constructors in fr.cnes.sirius.patrius.propagation.precomputed with parameters of type PositionAngle

Constructor and Description

IntegratedEphemeris(List<AbsoluteDate> startDatesIn, List<AbsoluteDate> minDatesIn, List<AbsoluteDate> maxDatesIn, OrbitType orbitTypeIn, PositionAngle angleTypeIn, AttitudeProvider attitudeForcesProvider, AttitudeProvider attitudeEventsProvider, Map<String,AdditionalStateInfo> additionalStateInfos, List<ContinuousOutputModel> modelsIn, Frame referenceFrameIn, double muIn) Creates a new instance of IntegratedEphemeris.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.precomputed.multi

Constructors in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type PositionAngle

Constructor and Description

MultiIntegratedEphemeris(List<AbsoluteDate> startDatesIn, List<AbsoluteDate> minDatesIn, List<AbsoluteDate> maxDatesIn, OrbitType orbitTypeIn, PositionAngle angleTypeIn, MultiAttitudeProvider multiAttitudeProviderForcesIn, MultiAttitudeProvider multiAttitudeProviderEventsIn, MultiStateVectorInfo stateInfos, List<ContinuousOutputModel> modelsIn, Frame referenceFrameIn, String satIdIn) Creates a new instance of IntegratedEphemeris.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.sampling

Methods in fr.cnes.sirius.patrius.propagation.sampling with parameters of type PositionAngle

Modifier and Type	Method and Description
void	AdaptedStepHandler.initialize(OrbitType orbit, PositionAngle angle, AttitudeProvider attitudeProviderForces, AttitudeProvider attitudeProviderEvents, Map<String,AdditionalStateInfo> additionalStateInfos, boolean activateHandlers, AbsoluteDate reference, Frame frame, double mu) Initialize the mode handler.

Uses of PositionAngle in fr.cnes.sirius.patrius.propagation.sampling.multi

Methods in fr.cnes.sirius.patrius.propagation.sampling.multi with parameters of type PositionAngle

Modifier and Type	Method and Description
void	MultiAdaptedStepHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,MultiAttitudeProvider> attProvidersForces, Map<String,MultiAttitudeProvider> attProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frameMap, Map<String,Double> muMap) Initialize the mode handler.

Uses of PositionAngle in fr.cnes.sirius.patrius.stela.orbits

Methods in fr.cnes.sirius.patrius.stela.orbits with parameters of type PositionAngle

Modifier and Type	Method and Description
protected void	StelaEquinoctialOrbit.orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot) Add the contribution of the Keplerian motion to parameters derivatives This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.