Beyond

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

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

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

Added

- equinoctial, cylindrical and mean circular forms
- OMM in SGP and TLE formats are compatibles
- A lot of small additions to the documentation of existing functions/methods

Modified

- Following horizon format changes

Removed

- RSW and LVLV are not synonym to QSW any more
- Disable keplerian representation of non inertial CCSDS OPM

Added

- Clohessy-Wiltshire propagator for relative motion

Modified

- Listeners are now part of the `beyond.propagators` subpackage
- Diminished precision on covariance ccsds output, for increased tests reliability

Added

- Optional dynamic interplanetary frame via the `env.jpl.dynamic_frames` configuration variable
- Single function to retrieve local orbital reference frame rotation matrix
- Creation of the `StateVector` class as parent of the `Orbit` class. It has
the same behavior as `Orbit` but can't be extrapolated.
- Covariance matrix can now be expressed in a reference frame independent of its orbit.

Modified

- The list of `bsp` and `tpc` files to read for the `beyond.env.jpl` module to work
should be provided to the `env.jpl.files` configuration variable, instead of the previous
`env.jpl`.
- The `beyond.utils.matrix.expand()` function now takes a single argument.
- Refactoring of `beyond.propagator.keplernum` and `beyond.orbits.man` to remove unused method argument
- Refactoring of `beyond.frames.frames` to avoid using metaclasses. This has huge code repercussions
and affected a large number of files.
- The `skip_if_no_mpl` test decorator is replaced by `mpl`

Fixed

- Wrong assumption on the config dict structure now leads to a ``ConfigError``
- The BSTAR drag term of the TLE format can be above 1e-1