Keplerian Elements¶

KeplerianElements represents classical orbital elements in osculating or mean form.

Constructors¶

Constructor	Description
`KeplerianElements(a, e, i, raan, aop, m, observer, epoch, frame)`	Create from elements
`KeplerianElements(..., perigeeRadius)`	Create parabolic orbit
`KeplerianElements(..., OrbitalElementsType)`	Create with explicit element type

Method	Description
`FromOMM(meanMotion, e, i, raan, aop, m, observer, epoch, frame)`	Create mean elements from OMM data (units: rev/day, degrees)

Property	Description
`A`	Semi-major axis (m)
`E`	Eccentricity
`I`	Inclination (rad)
`RAAN`	Right ascension of ascending node (rad)
`AOP`	Argument of periapsis (rad)
`M`	Mean anomaly (rad)
`ElementsType`	`Osculating` or `Mean`

Method	Description
`ToStateVector()`	Convert to state vector at epoch
`ToStateVector(Time)`	Convert at specified epoch
`ToEquinoctial()`	Convert to equinoctial elements
`AtEpoch(Time)`	Two-body propagation to new epoch
`Period()`	Orbital period
`PerigeeRadius()` / `ApogeeRadius()`	Apse radii (m)
`IsCircular()` / `IsElliptical()` / `IsParabolic()` / `IsHyperbolic()`	Orbit type checks

EquinoctialElements avoids singularities for circular and equatorial orbits.

Method	Description
`ToStateVector()`	Convert to state vector
`ToKeplerianElements()`	Convert to Keplerian
`EquinoctialEx()` / `EquinoctialEy()`	Eccentricity components
`Hx()` / `Hy()`	Inclination components
`Lv()`	True longitude (rad)