Struct ECIState 

pub struct ECIState {
    pub epoch: DateTime<Utc>,
    pub position: Vector3,
    pub velocity: Vector3,
}

State vector in Earth-Centered Inertial J2000 (ECI) reference frame.

ECI J2000 is an inertial reference frame with:

• Origin at Earth’s center of mass
• X-axis pointing toward the mean vernal equinox at J2000.0
• Z-axis pointing toward the mean celestial pole at J2000.0
• Y-axis completing the right-handed system

Position is in kilometers and velocity is in km/s.

Fields

epoch: DateTime<Utc>

UTC epoch of this state

position: Vector3

Position vector in km

velocity: Vector3

Velocity vector in km/s

Implementations

impl ECIState

pub fn new(epoch: DateTime<Utc>, position: Vector3, velocity: Vector3) -> Self

Create a new ECI state.

pub fn from_tuples( epoch: DateTime<Utc>, position: (f64, f64, f64), velocity: (f64, f64, f64), ) -> Self

Create from position and velocity tuples.

pub fn radius(&self) -> f64

Get the position magnitude (distance from Earth center) in km.

pub fn speed(&self) -> f64

Get the velocity magnitude (speed) in km/s.

pub fn angular_momentum(&self) -> Vector3

Get the specific angular momentum vector (h = r × v) in km²/s.

pub fn specific_energy(&self) -> f64

Get the specific orbital energy in km²/s².

pub fn to_teme(&self) -> TEMEState

Convert to TEME frame.

pub fn to_ecef(&self) -> ECEFState

Convert to ECEF frame.

pub fn to_keplerian(&self) -> KeplerianElements

Convert to Keplerian elements.

Trait Implementations

impl Clone for ECIState

fn clone(&self) -> ECIState

Returns a duplicate of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Debug for ECIState

fn fmt(&self, f: &mut Formatter<'_>) -> Result

Formats the value using the given formatter.