Struct EllipticalOrbit

Source

pub struct EllipticalOrbit {
    pub mu: f64,
    pub periapsis_radius: f64,
    pub apoapsis_radius: f64,
}

Expand description

Elliptical orbit state described by a gravitational parameter and apsides.

Fields§

§mu: f64

Central-body gravitational parameter in cubic meters per second squared.

§periapsis_radius: f64

Periapsis radius in meters.

§apoapsis_radius: f64

Apoapsis radius in meters.

Implementations§

Source §

impl EllipticalOrbit

Source

pub fn new(mu: f64, periapsis_radius: f64, apoapsis_radius: f64) -> Option<Self>

Creates an elliptical orbit from a gravitational parameter and apsides.

Returns None when mu is less than or equal to zero or not finite, or when the apsides are invalid.

Examples found in repository ?

examples/basic_usage.rs (line 15)

3fn main() {
4    let earth = CentralBody::with_radius(5.972e24, 6.371e6);
5    let low_orbit_radius = earth.and_then(|body| body.orbital_radius_from_altitude(400_000.0));
6    let low_orbit_speed = earth.and_then(|body| {
7        low_orbit_radius.and_then(|radius| body.circular_orbital_speed_at_radius(radius))
8    });
9    let transfer = hohmann_total_delta_v(398_600_441_800_000.0, 6_771_000.0, 42_164_000.0);
10
11    assert_eq!(low_orbit_radius, Some(6_771_000.0));
12    assert!(low_orbit_speed.is_some_and(|speed| speed > 7_600.0));
13    assert!(transfer.is_some_and(|delta_v| delta_v > 0.0));
14    assert!(
15        EllipticalOrbit::new(100.0, 10.0, 20.0)
16            .and_then(|orbit| orbit.period())
17            .is_some_and(|period| period > 0.0)
18    );
19}

Source

pub fn semi_major_axis(&self) -> Option<f64>

Computes the semi-major axis.

Source

pub fn eccentricity(&self) -> Option<f64>

Computes eccentricity.

Source

pub fn period(&self) -> Option<f64>

Computes the orbital period.

§Examples

use use_orbit::EllipticalOrbit;

let orbit = EllipticalOrbit::new(100.0, 10.0, 20.0);

assert!(orbit.and_then(|value| value.period()).is_some_and(|period| period > 0.0));

Examples found in repository ?

examples/basic_usage.rs (line 16)

3fn main() {
4    let earth = CentralBody::with_radius(5.972e24, 6.371e6);
5    let low_orbit_radius = earth.and_then(|body| body.orbital_radius_from_altitude(400_000.0));
6    let low_orbit_speed = earth.and_then(|body| {
7        low_orbit_radius.and_then(|radius| body.circular_orbital_speed_at_radius(radius))
8    });
9    let transfer = hohmann_total_delta_v(398_600_441_800_000.0, 6_771_000.0, 42_164_000.0);
10
11    assert_eq!(low_orbit_radius, Some(6_771_000.0));
12    assert!(low_orbit_speed.is_some_and(|speed| speed > 7_600.0));
13    assert!(transfer.is_some_and(|delta_v| delta_v > 0.0));
14    assert!(
15        EllipticalOrbit::new(100.0, 10.0, 20.0)
16            .and_then(|orbit| orbit.period())
17            .is_some_and(|period| period > 0.0)
18    );
19}