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OREKIT (ORbits Extrapolation KIT) is a free low-level space dynamics library
written in Java.
It provides basic elements (orbits, dates, attitude, frames ...) and
various algorithms to handle them (conversions, analytical and numerical
propagation, pointing ...).
* time scales (TAI, UTC, UT1, GPS, TT, TCG, TDB, TCB, GMST, GST, GLONASS, QZSS, BDT, IRNSS ...)
* support for CCSDS time code standards
* frames hierarchy supporting fixed and time-dependent
(or telemetry-dependent) frames
* predefined frames (EME2000/J2000, ICRF, GCRF, all ITRF from 1988 to 2014
and intermediate frames, TOD, MOD, GTOD and TOD frames, Veis, topocentric, TEME and PZ-90.11 frames,
tnw and qsw local orbital frames, Moon, Sun, planets, solar system barycenter,
Earth-Moon barycenter, ecliptic)
* user extensible (used operationally in real time with a set of about 60 frames on
* transparent handling of IERS Earth Orientation Parameters (for both new CIO-based frames
following IERS 2010 conventions and old equinox-based frames)
* transparent handling of JPL DE 4xx (405, 406 and more recent) and INPOP ephemerides
* transforms including kinematic combination effects
* composite transforms reduction and caching for efficiency
* extensible central body shapes models (with predefined spherical and ellipsoidic shapes)
* Cartesian and geodesic coordinates, kinematics
* computation of Dilution Of Precision (DOP) with respect to GNSS constellations
* projection of sensor Field Of View footprint on ground for any FoV shape
* Cartesian, elliptical Keplerian, circular and equinoctial parameters, with non-Keplerian
derivatives if available
* transparent conversion between all parameters
* automatic binding with frames
* attitude state and derivative
(for example battery status, or higher order derivatives, or anything else)
* analytical models for small maneuvers without propagation
* impulse maneuvers for any propagator type
* continuous maneuvers for numerical propagator type
* configurable low thrust maneuver model based on event detectors
* propulsion models intended to be used with maneuver class
* user-friendly interface for the maneuver triggers
* Kepler
* Eckstein-Heschler
* Brouwer-Lyddane with Warren Phipps' correction for the critical inclination of 63.4°
and the perturbative acceleration due to atmospheric drag
* SDP4/SGP4 with 2006 corrections
* GNSS: GPS, QZSS, Galileo, GLONASS, Beidou, IRNSS and SBAS
* central attraction
* gravity models including time-dependent like trends and pulsations
(automatic reading of ICGEM (new Eigen models), SHM (old Eigen models),
EGM and GRGS gravity field files formats, even compressed)
* atmospheric drag
* third body attraction (with data for Sun, Moon and all solar systems planets)
* radiation pressure with eclipses
* solid tides, with or without solid pole tide
* ocean tides, with or without ocean pole tide
* Earth's albedo and infrared
* empirical accelerations to account for the unmodeled forces
* general relativity (including Lense-Thirring and De Sitter corrections)
* multiple maneuvers
* state of the art ODE integrators (adaptive stepsize with error control,
continuous output, switching functions, G-stop, step normalization ...)
* serialization mechanism to store complete results on persistent storage for
later use
* propagation in non-inertial frames (e.g. for Lagrange point halo orbits)
* semi-analytical propagation model (DSST)
* central attraction
* gravity models
* atmospheric drag
* third body attraction
* radiation pressure with eclipses
* computation of Jacobians with respect to orbital parameters and selected
model parameters for numerical, semi-analytical, and analytical propagation
models
* trajectories around Lagragian points using CR3BP model
* file based
* memory based
* integration based
* Taylor-algebra (or any other real field) version of most of the above propagators,
with all force models, events detection, orbits types, coordinates types and frames
allowing high order uncertainties and derivatives computation or very fast Monte-Carlo
analyzes
* unified interface above analytical/numerical/tabulated propagators for easy
switch from coarse analysis to fine simulation with one line change
* all propagators can manage the time loop by themselves and handle callback
functions (called step handlers) from the calling application at each time step.
* step handlers can be called at discrete time at regular time steps, which are
independent of propagator time steps
* step handlers can be called with interpolators valid throughout one propagator
time step, which can have varying sizes
* step handlers can be switched off completely, when only final state is desired
* special step handlers are provided for a posteriori ephemeris generation: all
intermediate results are stored during propagation and provided back to the application
which can navigate at will through them, effectively using the propagated orbit as if
it was analytical model, even if it really is a numerically propagated one, which
is ideal for search and iterative algorithms
* several step handlers can be used simultaneously, so it is possible to have a fine
grained fixed time step to log state in a huge file, and have at the same time a
coarse grained time step to display progress for user at a more human-friendly rate,
this feature can also be used for debugging purpose, by setting up a temporary
step handler alongside the operational ones
* handling of discrete events during integration
(models changes, G-stop, simple notifications ...)
* predefined discrete events
* eclipse (both umbra and penumbra)
* ascending and descending node crossing
* apogee and perigee crossing
* alignment with some body in the orbital plane
(with customizable threshold angle)
* angular separation thresholds crossing between spacecraft and a beacon (typically the Sun)
as seen from an observer (typically a ground station)
* raising/setting with respect to a ground location
(with customizable triggering elevation and ground mask, optionally considering refraction)
* date and on-the-fly resetting countdown
* date interval with parameter-driven boundaries
* latitude, longitude, altitude crossing
* latitude, longitude extremum
* elevation extremum
* anomaly, latitude argument, or longitude argument crossings, either true, mean or eccentric
* moving target detection (with optional radius) in spacecraft sensor Field Of View (any shape, with special case for circular)
* spacecraft detection in ground based Field Of View (any shape)
* sensor Field Of View (any shape) overlapping complex geographic zone
* complex geographic zones traversal
* inter-satellites direct view
* ground at night
* impulse maneuvers occurrence
* geomagnetic intensity
* possibility of slightly shifting events in time (for example to switch from
solar pointing mode to something else a few minutes before eclipse entry and
reverting to solar pointing mode a few minutes after eclipse exit)
* events filtering based on their direction (for example to detect
only eclipse entries and not eclipse exits)
* events filtering based on an external enabling function (for
example to detect events only during selected orbits and not others)
* events combination with boolean operators
* ability to run several propagators in parallel and manage their states
simultaneously throughout propagation
* extensible attitude evolution models
* predefined laws
* central body related attitude (nadir pointing, center pointing, target pointing, yaw compensation, yaw-steering),
* orbit referenced attitudes (LOF aligned, offset on all axes),
* space referenced attitudes (inertial, celestial body-pointed, spin-stabilized)
* tabulated attitudes, either respective to inertial frame or respective to Local Orbital Frames
* specific law for GNSS satellites: GPS (block IIA, block IIF, block IIF), GLONASS, GALILEO, BEIDOU (GEO, IGSO, MEO)
* loading and writing of CCSDS Attitude Data Messages (both AEM, and APM types are supported, in both KVN and XML formats, standalone or in combined NDM)
* exporting of attitude ephemeris in CCSDS AEM file format
* optimizers choice (Levenberg-Marquardt or Gauss-Newton)
* decomposition algorithms choice (QR, LU, SVD, Cholesky)
* choice between forming normal equations or not
* sequential batch least squares fitting
* sequential Gauss-Newton optimizer
* decomposition algorithms choice (QR, LU, SVD, Cholesky)
* possibility to use an initial covariance matrix
* customizable process noise matrices providers
* time dependent process noise provider
* implementation of the Extended Semi-analytical Kalman Filter
* parameters estimation
* orbital parameters estimation (or only a subset if desired)
* force model parameters estimation (drag coefficients, radiation pressure coefficients,
central attraction, maneuver thrust, flow rate or start/stop epoch)
* measurements parameters estimation (biases, satellite clock offset, station clock offset,
station position, pole motion and rate, prime meridian correction and rate, total zenith
delay in tropospheric correction)
* orbit determination can be performed with numerical, DSST, SDP4/SGP4, Eckstein-Hechler, Brouwer-Lyddane, or Keplerian propagators
* multi-satellites orbit determination
* initial orbit determination methods (Gibbs, Gooding, Lambert and Laplace)
* ground stations displacements due to solid tides
* ground stations displacements due to ocean loading (based on Onsala Space Observatory files in BLQ format)
* several predefined measurements
* range
* range rate (one way and two way)
* turn-around range
* azimuth/elevation
* right ascension/declination
* position-velocity
* position
* inter-satellites range (one way and two way)
* inter-satellites GNSS phase
* GNSS phase with integer ambiguity resolution and wind-up effect
* multiplexed
* possibility to add custom measurements
* loading of ILRS CRD laser ranging measurements file
* loading and writing of CCSDS Tracking Data Messages (in both KVN and XML formats, standalone or in combined NDM)
* several predefined modifiers
* tropospheric effects
* ionospheric effects
* clock relativistic effects
* station offsets
* biases
* delays
* Antenna Phase Center
* Shapiro relativistic effect
* possibility to add custom measurement modifiers (even for predefined events)
* combination of GNSS measurements
* dual frequency combination of measurements
(Geometry-free, Ionosphere-free, Narrow-lane, Wide-lane and Melbourne-Wübbena)
* single frequency combination of measurements
(Phase minus code and GRAPHIC)
* possibility to parse CCSDS Tracking Data Message files
* with measurements feasibility triggered by regular event detectors
(ground visibility, ground at night, sunlit satellite, inter satellites
direct view, boolean combination...)
* with measurement scheduling as fixed step streams (optionally aligned with round UTC time)
* with measurement scheduling as high rate bursts rest periods (optionally aligned with round UTC time)
* possibility to customize measurement scheduling
* GNSS
* computation of Dilution Of Precision
* loading of ANTEX antenna models file
* loading of RINEX observation files (version 2 and version 3)
* loading of RINEX navigation files (version 3)
* support for Hatanaka compact RINEX format
* loading of SINEX station file
* loading of RINEX clock files (version 2 and version 3)
* parsing of IGS SSR messages for all constellations (version 1)
* implementation of Ntrip protocol
* loading of SP3 orbit files (from version a to d)
* loading and writing of CCSDS Orbit Data Messages (OPM, OEM, OMM and OCM types are supported, in both KVN and XML formats, standalone or in combined NDM)
* loading of SEM and YUMA files for GPS constellation
* exporting of ephemeris in CCSDS OEM file format
* loading of ILRS CPF orbit files
* atmospheric models (DTM2000, Jacchia-Bowman 2008, NRL MSISE 2000, Harris-Priester and simple exponential models), and Marshall solar Activity Future Estimation, optionally with lift component
* support for CSSI space weather data
* tropospheric delay (modified Saastamoinen, estimated, fixed)
* tropospheric mapping functions (Vienna 1, Vienna 3, Global, Niell)
* tropospheric refraction correction angle (Recommendation ITU-R P.834-7 and Saemundssen's formula quoted by Meeus)
* tropospheric model for laser ranging (Marini-Murray, Mendes-Pavlis)
* Klobuchar ionospheric model (including parsing α and β coefficients from University of Bern Astronomical Institute files)
* Global Ionospheric Map (GIM) model
* VTEC estimated ionospheric model with Single Layer Model (SLM) ionospheric mapping function
* Global Pression and Temperature models (GPT and GPT2)
* geomagnetic field (WMM, IGRF)
* geoid model from any gravity field
* displacement of ground points due to tides
* tessellation of zones of interest as tiles
* sampling of zones of interest as grids of points
* Customizable data loading
* loading by exploring folders hierarchy on local disk
* loading from explicit lists of files on local disk
* loading from classpath
* loading from network (even through internet proxies)
* support for zip archives
* automatic decompression of gzip compressed (.gz) files upon loading
* automatic decompression of Unix compressed (.Z) files upon loading
* automatic decompression of Hatanaka compressed files upon loading
* plugin mechanism to add filtering like custom decompression algorithms, deciphering or monitoring
* plugin mechanism to delegate loading to user defined database or data access library
* possibility to have different data context (a way to separate sets of EOP, leap seconds, etc)
* Localized in several languages
* English
* French
* Galician
* German
* The top level packages provided by Orekit are the following one:
Orekit is freely available both in source and binary formats, with all related
documentation and tests.
It is distributed under the [Apache License Version 2.0](./licenses.html). This
is a well known business-friendly license. This means anybody can use it to build
any application, free or not. There are no strings attached to your own code.
Everybody is encouraged to use Orekit as a common low level layer to improve
interoperability in space systems.
## Maintained library
Orekit has been in development since 2002 inside [CS GROUP](https://www.csgroup.eu/)
and is still used and maintained by its
experts and an open community. It is ruled by a meritocratic governance
model and the Project Management Committee involves actors from
industry (CS, Thales Alenia Space, Applied Defense Solutions), research
(Naval Research Laboratory), agencies (European Space Operations Centre,
European Space Research and Technology Centre) and academics (University
at Buffalo, Institut National Supérieur de l'Aéronautique et de l'Espace - Sup'Aéro).
Orekit has already been successfully used during the real time monitoring of the rendez-vous
phase between the Automated Transfer Vehicle (ATV) and the International Space Station (ISS)
by the Centre National d'Études Spatiales (CNES, the French space agency) and European Space
Agency (ESA).
Orekit has been selected in early 2011 by CNES to be the basis of its next generation space
flight dynamics systems, including operational systems, study systems and mission analysis
systems.
It has been used in numerous studies and for operational systems among the world.