Struct Elements

pub struct Elements {

    pub object_name: Option<String>,
    pub international_designator: Option<String>,
    pub norad_id: u64,
    pub classification: Classification,
    pub datetime: NaiveDateTime,
    pub mean_motion_dot: f64,
    pub mean_motion_ddot: f64,
    pub drag_term: f64,
    pub element_set_number: u64,
    pub inclination: f64,
    pub right_ascension: f64,
    pub eccentricity: f64,
    pub argument_of_perigee: f64,
    pub mean_anomaly: f64,
    pub mean_motion: f64,
    pub revolution_number: u64,
    pub ephemeris_type: u8,
}

General perturbations orbital data parsed from a TLE or OMM

Elements can be retrieved from either a Two-Line Element Set (TLE) or an Orbit Mean-Elements Message (OMM). See https://celestrak.com/NORAD/documentation/gp-data-formats.php for more information on the difference between the two formats.

The fields’ documentation is adapted from https://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/SSOP_Help/tle_def.html.

See sgp4::Elements::from_tle to parse a TLE.

serde_json can be used to parse a JSON OMM object (into a sgp4::Elements) or a JSON list of OMM objects (into a Vec<sgp4::Elements>).

Example

let elements: sgp4::Elements = serde_json::from_str(
    r#"{
        "OBJECT_NAME": "ISS (ZARYA)",
        "OBJECT_ID": "1998-067A",
        "EPOCH": "2020-07-12T01:19:07.402656",
        "MEAN_MOTION": 15.49560532,
        "ECCENTRICITY": 0.0001771,
        "INCLINATION": 51.6435,
        "RA_OF_ASC_NODE": 225.4004,
        "ARG_OF_PERICENTER": 44.9625,
        "MEAN_ANOMALY": 5.1087,
        "EPHEMERIS_TYPE": 0,
        "CLASSIFICATION_TYPE": "U",
        "NORAD_CAT_ID": 25544,
        "ELEMENT_SET_NO": 999,
        "REV_AT_EPOCH": 23587,
        "BSTAR": 0.0049645,
        "MEAN_MOTION_DOT": 0.00289036,
        "MEAN_MOTION_DDOT": 0
    }"#,
)?;

Fields

object_name: Option<String>

Available on crate feature alloc only.

The name associated with the satellite

international_designator: Option<String>

Available on crate feature alloc only.

The satellite’s international designator

It consists of the launch year, the launch number of that year and a letter code representing the sequential identifier of a piece in a launch.

norad_id: u64

The catalog number USSPACECOM has designated for this object

classification: Classification

The elements’ classification

datetime: NaiveDateTime

The UTC timestamp of the elements

mean_motion_dot: f64

Time derivative of the mean motion

mean_motion_ddot: f64

Second time derivative of the mean motion

drag_term: f64

Radiation pressure coefficient in earth radii⁻¹

element_set_number: u64

A running count of all 2 line element sets generated by USSPACECOM for this object

inclination: f64

Angle between the equator and the orbit plane in deg

right_ascension: f64

Angle between vernal equinox and the point where the orbit crosses the equatorial plane in deg

eccentricity: f64

The shape of the orbit

argument_of_perigee: f64

Angle between the ascending node and the orbit’s point of closest approach to the earth in deg

mean_anomaly: f64

Angle of the satellite location measured from perigee in deg

mean_motion: f64

Mean number of orbits per day in day⁻¹ (Kozai convention)

revolution_number: u64

The orbit number at epoch

ephemeris_type: u8

NORAD internal use, always 0 in distributed data

Implementations

impl Elements

pub fn from_tle( object_name: Option<String>, line1: &[u8], line2: &[u8], ) -> Result<Elements, Error>

Parses a Two-Line Element Set (TLE) with an optionnal title

Arguments

• object_name - The name of the satellite, usually given by a third line placed before the TLE
• line1 - The first line of the TLE composed of 69 ASCII characters
• line2 - The second line of the TLE composed of 69 ASCII characters

Example

let elements = sgp4::Elements::from_tle(
    Some("ISS (ZARYA)".to_owned()),
    "1 25544U 98067A   08264.51782528 -.00002182  00000-0 -11606-4 0  2927".as_bytes(),
    "2 25544  51.6416 247.4627 0006703 130.5360 325.0288 15.72125391563537".as_bytes(),
)?;

pub fn epoch(&self) -> f64

Returns the number of years since UTC 1 January 2000 12h00 (J2000)

This is the recommended method to calculate the epoch

pub fn epoch_afspc_compatibility_mode(&self) -> f64

Returns the number of years since UTC 1 January 2000 12h00 (J2000) using the AFSPC expression

This function should be used if compatibility with the AFSPC implementation is needed

pub fn datetime_to_minutes_since_epoch( &self, datetime: &NaiveDateTime, ) -> Result<MinutesSinceEpoch, DatetimeToMinutesSinceEpochError>

Returns the time difference in minutes between the given datetime and the elements’ epoch

This method does not take leap seconds into account

pub fn minutes_since_epoch_to_datetime( &self, minutes_since_epoch: &MinutesSinceEpoch, ) -> Result<NaiveDateTime, MinutesSinceEpochToDatetimeError>

Builds a datetime from a number of minutes since epoch

This method does not take leap seconds into account

Trait Implementations

impl Clone for Elements

fn clone(&self) -> Elements

Returns a copy of the value.

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

Performs copy-assignment from source.

impl Debug for Elements

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

Formats the value using the given formatter.

impl<'de> Deserialize<'de> for Elements

fn deserialize<__D>(__deserializer: __D) -> Result<Self, __D::Error>

where __D: Deserializer<'de>,

Deserialize this value from the given Serde deserializer.

impl Serialize for Elements

fn serialize<__S>(&self, __serializer: __S) -> Result<__S::Ok, __S::Error>

where __S: Serializer,

Serialize this value into the given Serde serializer.