OREKIT (ORbits Extrapolation KIT) is a low level space dynamics Java library. It provides basic elements (such as orbits, dates, attitude, and frames) and various algorithms to handle them (such as conversions, analytical and numerical propagation, and pointing).
|Tags||Scientific/Engineering Astronomy Software Development Libraries Java Libraries Mathematics|
|Operating Systems||OS Independent|
|Translations||English French Galician German Italian Norwegian Spanish|
Release Notes: This release added a solid tides force model, an ocean tides force model, simultaneous support for IERS 1996, 2003, and 2010 for frames, improved accuracy of celestial/terrestrial frames transforms, a classical equinox-based paradigm and non-rotating origin paradigm supported with all IERS conventions, automatic transformation of EOP, support for CCSDS Orbit Data Message, an improved API for events allowing separation of event detection and event handling, a merging of all the elevation related events, and a new attitude mode based on interpolation on a table.
Release Notes: The most noteworthy new features are the addition of thread safety for many parts while still preserving caching for performance even in multi-threaded environments, the inclusion of the DSST semi-analytical propagator together with the new unified propagators architecture, support for IERS 2010 conventions, Jacobians availability for all force models, and greatly improved performance and ability for the gravity fields force model. Users are advised to upgrade to this version, which depends on Apache Commons Math 3.2, despite several incompatibilities with respect to previous 5.x versions.
Release Notes: This is a small bugfix release. It focus on date parsing and performance.
Release Notes: 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.
Release Notes: 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.