Struct sgp4_rs::StateVector

pub struct StateVector {
    pub epoch: DateTime<Utc>,
    pub position: [f64; 3],
    pub velocity: [f64; 3],
    pub coe: ClassicalOrbitalElements,
}

A state vector, in the TEME-ECI coordinate frame, for an orbiting body.

To obtain the state of an object at a specific time, use the propagation functions provided by TwoLineElement.

Fields

epoch: DateTime<Utc>

position: [f64; 3]

The satellite position in km.

velocity: [f64; 3]

The satellite velocity in km/s.

coe: ClassicalOrbitalElements

Implementations

impl StateVector

pub fn new(epoch: DateTime<Utc>, position: [f64; 3], velocity: [f64; 3]) -> Self

pub fn semilatus_rectum(&self) -> Length

pub fn semimajor_axis(&self) -> Length

pub fn inclination(&self) -> Angle

pub fn raan(&self) -> Angle

pub fn mean_anomaly(&self) -> Angle

pub fn true_anomaly(&self) -> Angle

pub fn eccentricity(&self) -> f64

pub fn longitude_of_periapsis(&self) -> Angle

pub fn true_longitude(&self) -> Angle

pub fn argument_of_perigee(&self) -> Angle

pub fn argument_of_latitude(&self) -> Angle

Trait Implementations

impl Clone for StateVector

fn clone(&self) -> StateVector

Returns a copy of the value.

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

Performs copy-assignment from source.

impl Debug for StateVector

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

Formats the value using the given formatter.

impl From<StateVector> for ClassicalOrbitalElements

fn from(sv: StateVector) -> Self

Performs the conversion.

impl Copy for StateVector