Project Release Information
This release introduces several new features and bugfixes. Many time-dependent instances (Orbit, Attitude, etc.) can be slightly shifted in time using simple evolution models. The attitude interfaces have been redesigned. An experimental numerical propagator able to compute Jacobians of the state with respect to both initial state and force models parameters has been added. New discrete events have been addedm and a wrapper can time-shift any event occurrence. A new spacecraft model is available, allowing surface force models to take the body shape and rotating solar arrays into account.
The equinox-based frames family with IAU1980 precession-nutation models that are still used by many legacy systems are now supported. The data loading mechanism used to retrieve IERS data (Earth Orientation Parameters, UTC-TAI history) and JPL ephemerides is now also used to retrieve gravity field files. This mechanism has also been vastly improved to support new use cases (loading from disk, from classpath, from network delegating loading to an external library, etc.). Support for the TDB time scale has been added.
This release includes GCRF and ITRF2005 frames, support for JPL DE 405 and DE 406 Ephemerides, improved and greatly simplified date/time support, vastly improved data configuration with zip files support, new tutorials, improved performance, more tests, and new translation files for Italian, Spanish, and Norse. All identified bugs have been fixed.
This is the first public release of Orekit. The
library has been in development since 2002 and has
been successfully used in currently flying space
OREKIT (ORbits Extrapolation KIT) is a low level