0.8

v0.8

Added
-----

- Python 3.11, 3.12 and 3.13 support
- Differentiation between osculating and mean orbit objects
- Eckstein-Hechler analytical propagator
- LVLH local orbital reference frame
- Yamanaka-Ankersen Rendez-vous and Proximity Operations propagator
- MoonEclipse Listener to detect, well..., eclipses of the sun by the moon, as seen from a satellite
- A bunch of tests were created or given more robustness

Modified
--------

- Change in propagator subpackage structure, now grouped by categories
- Build process handled by pyproject.toml

Fixed
-----

- Rotation rate
- Impulsive maneuvers are integrated at their exact date

Deprecated
----------

- Beyond is no longer tested with python 3.6, but should still work

v0.7.5

Added
-----

- B-plane computation for planetary capture of flyby
- Generic Lagrange and linear interpolators

Modified
--------

- CCSDS : OEM and OMM optional fields are now optionals
- Consistency of API between impulsive and continuous thrusts
- Simplification of frame transition matrices
- Printing a TLE object display its name, if available
- CCSDS : TDM de-duplication of code

Fixed
-----

- CCSDS : OEM interpolation degree
- Improve error messages

v0.7.4

Added
-----

- Altitude of periapsis/apoapsis in Info object
- Python 3.10 support
- Lagrange Points frames
- Propagators can be attached to Body objects in a clean fashion

Modified
--------

- Ephem interpolation is made in TAI
- W component of local orbital frames were miscomputed. The effect was very small for circular
  orbit, hence the difficulty to spot it.
- Setting an attribute of StateVector/Orbit objects is handled more robustly.
- Analytical propagators of the Sun and the Moon are now differentiated to provide velocity
- Osculating keplerian elements in CCSDS OPM can be disabled

v0.7.3

Added
-----

- python 3.9 support and tests
- Sphere of Influence propagators (both analytical and numerical) have their own module
- ``StateVector.copy()`` now accepts "same" argument, to express two StateVector objects
  in the same form and frame.
- Maneuvers in terms of keplerian elements

Modified
--------

- ``beyond.orbits.man.dkep2dv()`` function has clearer arguments, is better documented
- Better exception messages when failing to parse a TLE
- Clarification of matrix building when handling rotating frames
- ``DateRange`` object simplification
- f-string everywhere
- LTAN now computed in seconds

Fixed
-----

- A dangling modulo messed with hyperbolic keplerian representation
- Barycentric frames correctly handled in CCSDS files