Struct sgp4::Orbit

pub struct Orbit {
    pub inclination: f64,
    pub right_ascension: f64,
    pub eccentricity: f64,
    pub argument_of_perigee: f64,
    pub mean_anomaly: f64,
    pub mean_motion: f64,
}

The Brouwer orbital elements

Fields

inclination: f64

Angle between the equator and the orbit plane in rad

right_ascension: f64

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

eccentricity: f64

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 rad

mean_anomaly: f64

Angle of the satellite location measured from perigee in rad

mean_motion: f64

Mean number of orbits per day in rad.min⁻¹

Implementations

impl Orbit

pub fn from_kozai_elements(
    geopotential: &Geopotential,
    inclination: f64,
    right_ascension: f64,
    eccentricity: f64,
    argument_of_perigee: f64,
    mean_anomaly: f64,
    kozai_mean_motion: f64
) -> Result<Self>

Creates a new Brouwer orbit representation from Kozai elements

If the Kozai orbital elements are obtained from a TLE or OMM, the convenience function sgp4::Constants::from_elements can be used instead of manually mapping the Elements fields to the Constants::new parameters.

Arguments

• geopotential - The model of Earth gravity to use in the conversion
• inclination - Angle between the equator and the orbit plane in rad
• right_ascension - Angle between vernal equinox and the point where the orbit crosses the equatorial plane in rad
• eccentricity - The shape of the orbit
• argument_of_perigee - Angle between the ascending node and the orbit’s point of closest approach to the earth in rad
• mean_anomaly - Angle of the satellite location measured from perigee in rad
• kozai_mean_motion - Mean orbital angular velocity in rad.min⁻¹ (Kozai convention)

Example

let elements = sgp4::Elements::from_tle(
    Some("ISS (ZARYA)".to_owned()),
    "1 25544U 98067A   20194.88612269 -.00002218  00000-0 -31515-4 0  9992".as_bytes(),
    "2 25544  51.6461 221.2784 0001413  89.1723 280.4612 15.49507896236008".as_bytes(),
)?;
let orbit_0 = sgp4::Orbit::from_kozai_elements(
    &sgp4::WGS84,
    elements.inclination * (core::f64::consts::PI / 180.0),
    elements.right_ascension * (core::f64::consts::PI / 180.0),
    elements.eccentricity,
    elements.argument_of_perigee * (core::f64::consts::PI / 180.0),
    elements.mean_anomaly * (core::f64::consts::PI / 180.0),
    elements.mean_motion * (core::f64::consts::PI / 720.0),
)?;

Trait Implementations

impl<'de> Deserialize<'de> for Orbit

fn deserialize<__D>(__deserializer: __D) -> Result<Self, __D::Error>where
    __D: Deserializer<'de>,

Deserialize this value from the given Serde deserializer.

impl Serialize for Orbit

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

Serialize this value into the given Serde serializer.