element_conversion

Functions for converting between sets of orbital elements.

This module provide a variety of functions and classes to convert between different representations of translational and rotational states (e.g. Cartesian ↔ Keplerian).

Note

Rotations between different reference frames are provided in the frame_conversion module.

Notes

Unless specified otherwise, the Keplerian elements are ordered as:

Index	Keplerian Element
0	Semi-major axis (except if eccentricity = 1.0, then represents semilatus rectum)
1	Eccentricity
2	Inclination
3	Argument of periapsis
4	Longitude of ascending node
5	True anomaly

Unless specified otherwise, the sphreical elements are ordered as:

Index	Spherical State Element
0	Radial distance
1	Latitude
2	Longitude
3	Speed
4	Flight-path angle
5	Heading angle

Unless specified otherwise, the Modified equinoctial elements (MEE; see here, element set k) are ordered as follows. The element \(I\), which defines the location of the MEE singularity is not treated as a state element, but is provided/determined separately:

Index	Modified equinoctial Element
0	Semi-parameter
1	f-element
2	g-element
3	h-element
4	k-element
5	True longitude

Functions