Struct vsop87::KeplerianElements [] [src]

pub struct KeplerianElements { /* fields omitted */ }

Structure representing the keplerian elements of an orbit.

Methods

impl KeplerianElements
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Gets the eccentricity of the orbit (e).

A number smaller to one would be a closed ellipse, while 0 would be a circle orbit. Values higher than one would be hyperbolic orbits, that are not closed, while a 1 would be a parabolical orbit. Negative values cannot exist.

Gets the semimajor axis of an orbit (a), in AU (Astronomical units).

This value represents the average distance from the orbiting body to the center of mass.

Gets the inclination of the orbit (i), in radians.

This value represents the inclination of the plane where the object is orbiting with respect to the reference plane.

Gets the longitude of the ascending node of the orbit (Ω), in radians.

This value represents the angle in the orbit ellipse of the point where the reference plane and the orbit plane cross when the orbiting body crosses the plane ascending in the orbit.

Gets the longitude of the periapsis of the orbit (ϖ), in radians.

This value represents the angle in the orbit ellipse of the nearest point of the orbit to the center of mass of the system.

Gets the mean anomaly of the orbiting object at the given epoch.

This value represents the angle in the orbit ellipse of the orbiting body at the given moment.

Trait Implementations

impl Debug for KeplerianElements
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Formats the value using the given formatter.

impl Clone for KeplerianElements
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Returns a copy of the value. Read more

Performs copy-assignment from source. Read more

impl Copy for KeplerianElements
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impl PartialEq for KeplerianElements
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This method tests for self and other values to be equal, and is used by ==. Read more

This method tests for !=.

impl From<VSOP87Elements> for KeplerianElements
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Performs the conversion.