Module nyx_space::cosmic

Expand description

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

Modules

eclipse
The eclipse module allows finding eclipses and (conversely) visibility between a state and another one (e.g. a planet or the Sun).
orientations
Known orientation IDs defined for ease of access. All Cosm objects may be accessed via Cosm directly.

BPlane
Stores a B-Plane
BPlaneTarget
BaseSpacecraft
A spacecraft state
Cosm
Euler3Axis
A fixed three-axis Euler rotation
Euler3AxisDt
A time varying three-axis Euler rotation
FrameTree
IoError
The error type for I/O operations of the Read, Write, Seek, and associated traits.
NoRotation
Orbit
Orbit defines an orbital state
OrbitDual
Orbit defines an orbital state
OrbitPartial
A type which stores the partial of an element
Xb

AngleUnit
Bodies
Defines the default celestial bodies in the provided de438 XB.
EulerRotation
Defines an Euler rotation, angle must be in radians
Frame
GuidanceMode
IoErrorKind
A list specifying general categories of I/O error.
LightTimeCalc
Enable or not light time correction for the computation of the celestial states
NyxError

AU
Astronomical unit, in kilometers, according to the IAU.
SPEED_OF_LIGHT
Speed of light in meters per second
SPEED_OF_LIGHT_KMS
Speed of light in kilometers per second
SS_MASS
Mass of the solar system from https://en.wikipedia.org/w/index.php?title=Special:CiteThisPage&page=Solar_System&id=905437334
STD_GRAVITY
From NIST special publication 330, 2008 edition, in meters per second squared
SUN_GM
GM of the Sun in km^3/s^2

ParentRotation
SpacecraftExt
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.
State
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.
TimeTagged
A trait allowing for something to have an epoch

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).