Module nyx_space::cosmic

source · [−]

Expand description

Provides the solar system planets, and state and ephemeride management.

Modules

The eclipse module allows finding eclipses and (conversely) visibility between a state and another one (e.g. a planet or the Sun).

Known orientation IDs defined for ease of access. All Cosm objects may be accessed via Cosm directly.

Structs

Stores a B-Plane

A spacecraft state

A fixed three-axis Euler rotation

A time varying three-axis Euler rotation

The error type for I/O operations of the Read, Write, Seek, and associated traits.

Orbit defines an orbital state

Orbit defines an orbital state

A type which stores the partial of an element

Enums

Defines the default celestial bodies in the provided de438 XB.

Defines an Euler rotation, angle must be in radians

A list specifying general categories of I/O error.

Enable or not light time correction for the computation of the celestial states

Constants

Astronomical unit, in kilometers, according to the IAU.

Speed of light in meters per second

SPEED_OF_LIGHT_KMS

Speed of light in kilometers per second

Mass of the solar system from https://en.wikipedia.org/w/index.php?title=Special:CiteThisPage&page=Solar_System&id=905437334

From NIST special publication 330, 2008 edition, in meters per second squared

GM of the Sun in km^3/s^2

Traits

Defines a spacecraft extension. This is useful for highly specialized guidance laws that need to store additional data in the spacecraft state. Most guidance laws can be implemented directly with the Spacecraft structure.

A trait for generate propagation and estimation state. The first parameter is the size of the state, the second is the size of the propagated state including STM and extra items.

A trait allowing for something to have an epoch

Functions

assert_orbit_eq_or_abs

assert_orbit_eq_or_rel

try_achieve_b_plane

Returns the Delta V (in km/s) needed to achieve the B Plane specified by B dot R and B dot T. If no LTOF target is set, this method will fix VX, VY and VZ successively and use the minimum of those as a seed for the LTOF variation finding. If the 3x3 search is worse than any of the 2x2s, then a 2x2 will be returned. This uses the hyperdual formulation of the Jacobian and will also vary the linearize time of flight (LTOF).

Type Definitions

A spacecraft state