Struct Tle 

pub struct Tle { /* private fields */ }

Two-Line Element Set (TLE) data structure.

A TLE is a standardized format for describing the orbit of an Earth-orbiting object. TLEs are used with the SGP4/SDP4 propagators to predict satellite positions at future times.

Implementations

impl Tle

pub fn parse(line1: &str, line2: &str) -> TleResult<Self>

Parse a TLE from two lines.

Arguments

• line1 - First line of the TLE (69 characters)
• line2 - Second line of the TLE (69 characters)

Returns

• Ok(Tle) - Successfully parsed TLE
• Err(TleError) - Parsing failed

pub fn parse_3le(_name: &str, line1: &str, line2: &str) -> TleResult<Self>

Parse a TLE from three lines (name + two TLE lines).

Arguments

• name - Satellite name (ignored)
• line1 - First line of the TLE
• line2 - Second line of the TLE

pub fn line1(&self) -> &str

Get the raw TLE line 1.

pub fn line2(&self) -> &str

Get the raw TLE line 2.

pub fn catalog_number(&self) -> &str

Get the NORAD catalog number.

pub fn classification(&self) -> char

Get the security classification.

pub fn international_designator(&self) -> &str

Get the international designator.

pub fn epoch(&self) -> DateTime<Utc>

Get the TLE epoch.

pub fn mean_motion_dot(&self) -> f64

Get the first derivative of mean motion (rev/day²).

pub fn mean_motion_double_dot(&self) -> f64

Get the second derivative of mean motion (rev/day³).

pub fn bstar(&self) -> f64

Get the BSTAR drag coefficient.

pub fn ephemeris_type(&self) -> u8

Get the ephemeris type.

pub fn element_set_number(&self) -> u32

Get the element set number.

pub fn inclination_deg(&self) -> f64

Get the orbital inclination in degrees.

pub fn raan_deg(&self) -> f64

Get the Right Ascension of Ascending Node in degrees.

pub fn eccentricity(&self) -> f64

Get the orbital eccentricity.

pub fn arg_perigee_deg(&self) -> f64

Get the argument of perigee in degrees.

pub fn mean_anomaly_deg(&self) -> f64

Get the mean anomaly at epoch in degrees.

pub fn mean_motion(&self) -> f64

Get the mean motion in revolutions per day.

pub fn rev_number(&self) -> u32

Get the revolution number at epoch.

pub fn period_minutes(&self) -> f64

Get the orbital period in minutes.

pub fn period_seconds(&self) -> f64

Get the orbital period in seconds.

pub fn propagate(&self, epoch: &DateTime<Utc>) -> TleResult<TEMEState>

Propagate the TLE to a specific epoch using SGP4.

Returns the satellite state in the TEME (True Equator Mean Equinox) frame.

Arguments

• epoch - Target epoch for propagation

Returns

• Ok(TEMEState) - Position and velocity in TEME frame
• Err(TleError) - Propagation failed

pub fn propagate_minutes(&self, minutes: f64) -> TleResult<TEMEState>

Propagate the TLE by a number of minutes from the TLE epoch.

Arguments

• minutes - Minutes since TLE epoch (can be negative)

pub fn get_rv_at_time( &self, epoch: &DateTime<Utc>, ) -> TleResult<((f64, f64, f64), (f64, f64, f64))>

Get position and velocity at a specific epoch.

Returns ((x, y, z), (vx, vy, vz)) in km and km/s.

pub fn minutes_since_epoch(&self, target: &DateTime<Utc>) -> f64

Calculate minutes since TLE epoch.

pub fn accuracy_warning(&self, epoch: &DateTime<Utc>) -> u8

Check if propagation to a given epoch is likely to be accurate.

TLEs are typically valid for a few days before/after their epoch. This function returns a warning level based on the time difference.

Returns

• 0 - Within ±1 day (good accuracy)
• 1 - Within ±3 days (acceptable)
• 2 - Within ±7 days (degraded)
• 3 - Beyond ±7 days (poor accuracy)

Trait Implementations

impl Clone for Tle

fn clone(&self) -> Tle

Returns a duplicate of the value.

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

Performs copy-assignment from source.

impl Debug for Tle

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

Formats the value using the given formatter.