Uses of Class
agi.foundation.coordinates.KeplerianElements

Packages that use KeplerianElements

Package	Description
agi.foundation.coordinates	Contains types for quantifying and converting between various coordinate representations.
agi.foundation.propagators	Contains types used in producing the state of an object from a known element set.

Uses of KeplerianElements in agi.foundation.coordinates

Methods in agi.foundation.coordinates that return KeplerianElements

Modifier and Type	Method and Description
KeplerianElements	LifetimeElements.toKeplerianMeanElements() Convert these elements to an equivalent KeplerianElements representation at the periapsis.
KeplerianElements	KozaiIzsakMeanElements.toMeanKeplerianElements() Returns a mean Keplerian orbit element representation of these mean orbital elements.
KeplerianElements	KozaiIzsakMeanElements.toOsculatingKeplerianElements() Returns an osculating Keplerian orbit element representation of these mean orbital elements.

Constructors in agi.foundation.coordinates with parameters of type KeplerianElements

Constructor and Description
DelaunayElements(KeplerianElements elements) Initialize a set of Delaunay elements based on a set of classical KeplerianElements.
EquinoctialElements(KeplerianElements elements) Initialize a set of equinoctial elements from a set of classical KeplerianElements.
KozaiIzsakMeanElements(KeplerianElements elements, boolean inputIsMean, double j2UnnormalizedValue, double referenceDistance) Initialize a set of Kozai-Izsak mean elements from a set of osculating or mean KeplerianElements.
ModifiedKeplerianElements(KeplerianElements elements) Initialize a new instance from the given set of classical KeplerianElements.

Uses of KeplerianElements in agi.foundation.propagators

Constructors in agi.foundation.propagators with parameters of type KeplerianElements

Constructor and Description
J2Propagator(JulianDate orbitEpoch, ReferenceFrame referenceFrame, KeplerianElements initialConditions, double j2UnnormalizedValue, double referenceDistance) Initializes a new instance.
J4Propagator(JulianDate orbitEpoch, ReferenceFrame referenceFrame, KeplerianElements initialConditions, double j2UnnormalizedValue, double j4UnnormalizedValue, double referenceDistance) Initializes a new instance.
TwoBodyPropagator(JulianDate orbitEpoch, ReferenceFrame referenceFrame, KeplerianElements elements) Initializes a new instance.