StateVector¶

StateVector stores Cartesian position and velocity in a frame around an observer body.

Constructor¶

var sv = new StateVector(
    new Vector3(6800000.0, 0.0, 0.0),
    new Vector3(0.0, 8000.0, 0.0),
    earth, epoch, Frames.Frame.ICRF);

An optional 6x6 covariance matrix can be attached:

var sv = new StateVector(position, velocity, earth, epoch, Frame.ICRF, covarianceMatrix);

Method	Description
`SemiMajorAxis()`	Semi-major axis (m)
`Eccentricity()`	Eccentricity
`Inclination()`	Inclination (rad)
`AscendingNode()`	RAAN (rad)
`ArgumentOfPeriapsis()`	Argument of periapsis (rad)
`TrueAnomaly()`	True anomaly (rad)
`MeanAnomaly()`	Mean anomaly (rad)
`EccentricAnomaly()`	Eccentric anomaly (rad)
`Period()`	Orbital period
`MeanMotion()`	Mean motion (rad/s)
`SpecificOrbitalEnergy()`	Vis-viva energy (m²/s²)
`SpecificAngularMomentum()`	Angular momentum vector
`EccentricityVector()`	Eccentricity vector
`PerigeeVector()` / `ApogeeVector()`	Apse position vectors
`PerigeeVelocity()` / `ApogeeVelocity()`	Apse velocities (m/s)

Method	Description
`ToKeplerianElements()`	Convert to Keplerian elements
`ToEquinoctial()`	Convert to equinoctial elements
`ToEquatorial()`	Convert to equatorial coordinates
`ToFrame(Frame)`	Transform to different reference frame
`RelativeTo(ILocalizable, Aberration)`	Transform to different center
`Inverse()`	Invert position and velocity
`ToTLE(TLE.Configuration)`	Convert to TLE format