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

Packages that use Orbit

Package	Description
fr.cnes.sirius.patrius.attitudes
fr.cnes.sirius.patrius.forces.maneuvers
fr.cnes.sirius.patrius.guidance
fr.cnes.sirius.patrius.orbits
fr.cnes.sirius.patrius.propagation
fr.cnes.sirius.patrius.propagation.analytical
fr.cnes.sirius.patrius.propagation.analytical.covariance
fr.cnes.sirius.patrius.propagation.analytical.tle
fr.cnes.sirius.patrius.propagation.analytical.twod
fr.cnes.sirius.patrius.propagation.events
fr.cnes.sirius.patrius.propagation.numerical
fr.cnes.sirius.patrius.propagation.precomputed
fr.cnes.sirius.patrius.propagation.precomputed.multi
fr.cnes.sirius.patrius.stela.forces.gravity
fr.cnes.sirius.patrius.stela.orbits
fr.cnes.sirius.patrius.stela.propagation.data
fr.cnes.sirius.patrius.time

Uses of Orbit in fr.cnes.sirius.patrius.attitudes

Methods in fr.cnes.sirius.patrius.attitudes with parameters of type Orbit

Modifier and Type	Method and Description
Attitude	AttitudesSequence.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	RelativeTabulatedAttitudeLaw.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedAttitude.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeLegsSequence.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	RelativeTabulatedAttitudeLeg.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeLawLeg.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AbstractSlew.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeLegLaw.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AbstractAttitudeLaw.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeProvider.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.

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

Methods in fr.cnes.sirius.patrius.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 fr.cnes.sirius.patrius.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 fr.cnes.sirius.patrius.guidance

Methods in fr.cnes.sirius.patrius.guidance with parameters of type Orbit

Modifier and Type	Method and Description
Attitude	GuidanceProfile.getAttitude(Orbit orbit) Compute the attitude corresponding to an orbital state.

Uses of Orbit in fr.cnes.sirius.patrius.orbits

Subclasses of Orbit in fr.cnes.sirius.patrius.orbits

Modifier and Type	Class and Description
class	ApsisOrbit This class handles periapsis/apoapsis parameters.
class	CartesianOrbit This class holds cartesian orbital parameters.
class	CircularOrbit This class handles circular orbital parameters.
class	EquatorialOrbit This class handles non circular equatorial 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 fr.cnes.sirius.patrius.orbits that return Orbit

Modifier and Type	Method and Description
abstract Orbit	OrbitType.convertOrbit(Orbit initOrbit, Frame frame) Convert an orbit from a given orbit type to an other in a wished frame.
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.
protected abstract Orbit	Orbit.orbitShiftedBy(double dt) Get a time-shifted orbit.
Orbit	Orbit.shiftedBy(double dt) Call the method orbitShiftedBy(double) implemented in inherited classes of Orbit.

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

Modifier and Type	Method and Description
abstract Orbit	OrbitType.convertOrbit(Orbit initOrbit, Frame frame) Convert an orbit from a given orbit type to an other in a wished frame.
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 fr.cnes.sirius.patrius.orbits with type arguments of type Orbit

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

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

Constructor and Description
ApsisOrbit(Orbit op) Constructor from any kind of orbital parameters.
CartesianOrbit(Orbit op) Constructor from any kind of orbital parameters.
CircularOrbit(Orbit op) Constructor from any kind of orbital parameters.
EquatorialOrbit(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 fr.cnes.sirius.patrius.propagation

Methods in fr.cnes.sirius.patrius.propagation that return Orbit

Modifier and Type	Method and Description
Orbit	SpacecraftState.getOrbit() Gets the current orbit.
Orbit	MeanOsculatingElementsProvider.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	MeanOsculatingElementsProvider.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	MeanOsculatingElementsProvider.propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.
protected Orbit	AnalyticalIntegratedEphemeris.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	PVCoordinatePropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected abstract Orbit	AbstractPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

Modifier and Type	Method and Description
Orbit	MeanOsculatingElementsProvider.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	MeanOsculatingElementsProvider.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
SpacecraftState	SpacecraftState.updateOrbit(Orbit newOrbit) Update the orbit.

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

Constructor and Description
SpacecraftState(Orbit orbitIn) Build a spacecraft state from orbit only.
SpacecraftState(Orbit orbitIn, Attitude attitudeIn) Build a spacecraft state from orbit and a single attitude.
SpacecraftState(Orbit orbitIn, Attitude attForces, Attitude attEvents) Build a spacecraft state from orbit, attitude for forces and events computation.
SpacecraftState(Orbit orbitIn, Attitude attForces, Attitude attEvents, Map<String,double[]> addStates) Build a spacecraft state from orbit, attitude for forces and events computation and additional states map.
SpacecraftState(Orbit orbitIn, Attitude attForces, Attitude attEvents, MassProvider massProvider) Build a spacecraft state from orbit, attitude for forces and events computation and mass provider.
SpacecraftState(Orbit orbitIn, Attitude attForces, Attitude attEvents, MassProvider massProvider, Map<String,double[]> additionalStatesIn) Build a spacecraft state from orbit, attitude for forces and events computation, mass provider and additional states map.
SpacecraftState(Orbit orbitIn, Attitude attitudeIn, MassProvider massProvider) Build a spacecraft state from orbit, attitude and mass provider.
SpacecraftState(Orbit orbitIn, MassProvider massProvider) Create a new instance from orbit and mass provider.

Uses of Orbit in fr.cnes.sirius.patrius.propagation.analytical

Fields in fr.cnes.sirius.patrius.propagation.analytical declared as Orbit

Modifier and Type	Field and Description
protected Orbit	AbstractLyddanePropagator.secularOrbitIn Secular orbit.

Methods in fr.cnes.sirius.patrius.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	AbstractLyddanePropagator.computeSecular(Orbit orbit, AbstractLyddanePropagator.LyddaneParametersType fromType) Compute secular orbit in body frame from provided orbit.
protected Orbit	AbstractLyddanePropagator.convertFrame(Orbit orbit, Frame outputFrame) Convert provided orbit in output frame.
Orbit	EcksteinHechlerPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	LyddaneSecularPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	LyddaneLongPeriodPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	EcksteinHechlerPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	LyddaneSecularPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	LyddaneLongPeriodPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	EcksteinHechlerPropagator.propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.
Orbit	LyddaneSecularPropagator.propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.
Orbit	AbstractLyddanePropagator.propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.
Orbit	EcksteinHechlerPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	AdapterPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
Orbit	J2SecularPropagator.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 Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date, Orbit secularOrbit, Frame outputFrame, AbstractLyddanePropagator.LyddaneParametersType returnType) Propagate orbit to provided date.

Methods in fr.cnes.sirius.patrius.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.
protected Orbit	AbstractLyddanePropagator.computeSecular(Orbit orbit, AbstractLyddanePropagator.LyddaneParametersType fromType) Compute secular orbit in body frame from provided orbit.
protected Orbit	AbstractLyddanePropagator.convertFrame(Orbit orbit, Frame outputFrame) Convert provided orbit in output frame.
Orbit	EcksteinHechlerPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	LyddaneSecularPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	LyddaneLongPeriodPropagator.mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	EcksteinHechlerPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	LyddaneSecularPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	LyddaneLongPeriodPropagator.osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
protected Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date, Orbit secularOrbit, Frame outputFrame, AbstractLyddanePropagator.LyddaneParametersType returnType) Propagate orbit to provided date.
protected void	AbstractLyddanePropagator.updateSecularOrbit(Orbit secularOrbit) Update for secular Orbit.

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

Constructor and Description
AbstractLyddanePropagator(Orbit secularOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, ParametersType paramsType) Build a propagator from orbit, attitude provider for forces and events computation and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, attitude provider, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, ParametersType paramsType) Build a propagator from orbit, attitude provider and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, MassProvider massProvider, ParametersType paramsType) Build a propagator from orbit, mass and potential.
EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, Frame frame, double c20In, double c30In, double c40In, double c50In, double c60In, ParametersType paramsType) Build a propagator from orbit and potential.
J2DifferentialEffect(Orbit orbit0, Orbit orbit1, boolean applyBeforeIn, double referenceRadius, double mu, double j2) Simple constructor.
J2DifferentialEffect(Orbit orbit0, Orbit orbit1, boolean applyBeforeIn, PotentialCoefficientsProvider gravityField) Simple constructor.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn) Constructor without attitude provider and mass provider.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider) Constructor without mass provider.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents) Constructor without mass provider.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider, MassProvider massProvider) Generic constructor.
J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, MassProvider massProvider) Constructor without attitude provider.
KeplerianPropagator(Orbit initialOrbit) Build a propagator from orbit only.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv) Build a propagator from orbit and a single attitude provider.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents) Build a propagator from orbit and attitude provider for forces and event computation.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double mu) Build a propagator from orbit, attitude provider for forces and events computation and central attraction coefficient μ.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double mu, MassProvider massProvider) Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu) Build a propagator from orbit, a single attitude provider and central attraction coefficient μ.
KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, MassProvider massProvider) 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.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn) Constructor without attitude provider and mass provider.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider) Constructor without mass provider.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents) Constructor without mass provider.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider, MassProvider massProvider) Generic constructor.
LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, MassProvider massProvider) Constructor without attitude provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn) Constructor without attitude provider and mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider) Constructor without mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents) Constructor without mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider, MassProvider massProvider) Generic constructor.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, MassProvider massProvider) Constructor without attitude provider.

Uses of Orbit in fr.cnes.sirius.patrius.propagation.analytical.covariance

Methods in fr.cnes.sirius.patrius.propagation.analytical.covariance that return Orbit

Modifier and Type	Method and Description
Orbit	CovarianceInterpolation.getOrbit()

Methods in fr.cnes.sirius.patrius.propagation.analytical.covariance with parameters of type Orbit

Modifier and Type	Method and Description
SymmetricMatrix	OrbitCovariance.getCovarianceMatrix(Orbit refOrbit, OrbitType outCovType, Frame outFrame) Covariance matrix getter.
OrbitCovariance	OrbitCovariance.propagate(Orbit refOrbit, AbsoluteDate target) Propagate covariance.
void	CovarianceInterpolation.setOrbit(Orbit newOrbit) Allows to change the orbit.

Constructors in fr.cnes.sirius.patrius.propagation.analytical.covariance with parameters of type Orbit

Constructor and Description
CovarianceInterpolation(AbsoluteDate t1In, double[][] matrix1, AbsoluteDate t2In, double[][] matrix2, int order, Orbit orbitSatellite, double muValue) Constructor of the class CovarianceInterpolation
CovarianceInterpolation(AbsoluteDate t1In, RealMatrix matrix1, AbsoluteDate t2In, RealMatrix matrix2, int order, Orbit orbitSatellite, double muValue) Constructor of the class CovarianceInterpolation
OrbitCovariance(Orbit orbit, OrbitType coordType, RealMatrix covMat) Simple constructor.
OrbitCovariance(Orbit orbit, RealMatrix covMat) Simple constructor.

Uses of Orbit in fr.cnes.sirius.patrius.propagation.analytical.tle

Methods in fr.cnes.sirius.patrius.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 fr.cnes.sirius.patrius.propagation.analytical.twod

Methods in fr.cnes.sirius.patrius.propagation.analytical.twod that return Orbit

Modifier and Type	Method and Description
protected Orbit	Analytical2DPropagator.propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.

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

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

Constructor and Description
AlignmentDetector(Orbit orbit, PVCoordinatesProvider bodyIn, double alignAngleIn) Build a new alignment detector.
AlignmentDetector(Orbit orbit, PVCoordinatesProvider bodyIn, double alignAngleIn, double thresholdIn) Build a new alignment detector.
AlignmentDetector(Orbit orbit, PVCoordinatesProvider bodyIn, double alignAngleIn, double threshold, EventDetector.Action actionStart, EventDetector.Action actionEnd) Build a new alignment detector.
AlignmentDetector(Orbit orbit, PVCoordinatesProvider bodyIn, double alignAngleIn, double threshold, EventDetector.Action actionStart, EventDetector.Action actionEnd, boolean removeStart, boolean removeEnd) Build a new alignment detector.
ApsideDetector(Orbit orbit, int slopeSelection) Build a new instance.
ApsideDetector(Orbit orbit, int slopeSelection, double threshold) Build a new instance.
NodeDetector(Orbit orbit, Frame frameIn, int slopeSelection) Build a new instance.
NodeDetector(Orbit orbit, Frame frameIn, int slopeSelection, double threshold) Build a new instance.

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

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

Modifier and Type	Method and Description
void	TimeDerivativesEquations.initDerivatives(double[] yDot, Orbit currentOrbit) Initialize all derivatives to zero.
static double[][]	NumericalPropagator.tolerances(double dP, Orbit orbit, OrbitType type) Estimate tolerance vectors for integrators.

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

Methods in fr.cnes.sirius.patrius.propagation.precomputed that return Orbit

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

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

Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi that return Orbit

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

Uses of Orbit in fr.cnes.sirius.patrius.stela.forces.gravity

Methods in fr.cnes.sirius.patrius.stela.forces.gravity with parameters of type Orbit

Modifier and Type	Method and Description
void	TesseralQuad.updateEccentricityInterval(Orbit orbit) Update eccentricity interval [ec - Δe; ec + Δe].
void	StelaTesseralAttraction.updateQuads(Orbit orbit) Compute quads (n, m, p, q).

Constructors in fr.cnes.sirius.patrius.stela.forces.gravity with parameters of type Orbit

Constructor and Description
TesseralQuad(PotentialCoefficientsProvider provider, int coefN, int coefM, int coefP, int coefQ, Orbit orbit) Constructor.

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

Subclasses of Orbit in fr.cnes.sirius.patrius.stela.orbits

Modifier and Type	Class and Description
class	StelaEquinoctialOrbit This class handles Stela equinoctial orbital parameters, which can support both circular and equatorial orbits.

Methods in fr.cnes.sirius.patrius.stela.orbits that return Orbit

Modifier and Type	Method and Description
Orbit	StelaEquinoctialOrbit.interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.
protected Orbit	StelaEquinoctialOrbit.orbitShiftedBy(double dt)

Method parameters in fr.cnes.sirius.patrius.stela.orbits with type arguments of type Orbit

Modifier and Type	Method and Description
Orbit	StelaEquinoctialOrbit.interpolate(AbsoluteDate date, Collection<Orbit> sample) Get an interpolated instance.

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

Constructor and Description
StelaEquinoctialOrbit(Orbit op) Constructor from any kind of orbital parameters with correction when inclination is close to 180°
StelaEquinoctialOrbit(Orbit op, boolean isCorrectedIn) Constructor from any kind of orbital parameters.

Uses of Orbit in fr.cnes.sirius.patrius.stela.propagation.data

Methods in fr.cnes.sirius.patrius.stela.propagation.data that return Orbit

Modifier and Type	Method and Description
Orbit	TimeDerivativeData.getOrbit() Returns the orbit.

Constructors in fr.cnes.sirius.patrius.stela.propagation.data with parameters of type Orbit

Constructor and Description
TimeDerivativeData(Orbit aOrbit, double[] aMeanMotion, double[][] aMeanMotionSTM, Map<StelaForceModel,double[]> aDerivatives, Map<StelaForceModel,double[][]> aDerivativesSTM) Constructor.

Uses of Orbit in fr.cnes.sirius.patrius.time

Methods in fr.cnes.sirius.patrius.time with parameters of type Orbit

Modifier and Type	Method and Description
double	LocalTimeAngle.computeMeanLocalTimeAngle(Orbit orbit) Compute mean local time angle in TIRF frame in the range [-Π, Π[.
double	LocalTimeAngle.computeTrueLocalTimeAngle(Orbit orbit) Compute true local time angle in TIRF frame in the range [-Π, Π[.