Overview

The Orekit library aims at providing efficient low level components for the development of flight dynamics applications.

Orekit, a pure Java library, depends only on the Java Standard Edition version 8 (or above) and Hipparchus version 1.6 (or above) libraries at runtime.

External dependencies

Runtime component

This component is required to compile and run Orekit:

• Hipparchus
  Copyright © Hipparchus project
  License: Apache License, version 2.0
  Reference: https://www.hipparchus.org/

Test-time component

This component is required for testing purpose only:

• JUnit
  Copyright © Erich Gamma and Kent Beck
  License: Eclipse Public License, version 1.0
  Reference: http://www.junit.org/

Design & Implementation

General concepts

As a a low level library, Orekit aims at being used in very different contexts which cannot be foreseen, from quick studies up to critical operations.

The main driving goals for the development of Orekit are:

• validation
• robustness
• maintainability
• efficiency

These goals lead to design and coding guidelines including:

• comprehensive test suite for high level of coverage
• automated checking tools for robustness
• consistent coding style for readable, clear and well documented code
• wide use of immutable objects for efficiency

Packages

Orekit is made of twelve packages shown in the following diagram.

Features

Time

• high accuracy absolute dates
• time scales (TAI, UTC, UT1, GPS, TT, TCG, TDB, TCB, GMST, GST, GLONASS, QZSS, BDT, IRNSS ...)
• transparent handling of leap seconds

Geometry

• 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 TEME frames, Veis, topocentric, 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 several spacecraft)
• 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

Spacecraft state

• cartesian, elliptical Keplerian, circular and equinoctial parameters, with non-Keplerian derivatives if available
• Two-Line Elements (TLE)
• transparent conversion between all parameters
• automatic binding with frames
• attitude state and derivative
• jacobians
• mass management
• user-defined associated state (for example battery status, or higher order derivatives, or anything else)

Maneuvers

• analytical models for small maneuvers without propagation
• impulse maneuvers for any propagator type
• continuous maneuvers for numerical propagator type

Propagation

• analytical propagation models
  • Kepler
  • Eckstein-Heschler
  • SDP4/SGP4 with 2006 corrections
  • GNSS: GPS, QZSS, Galileo, GLONASS, Beidou, IRNSS and SBAS
• numerical propagators
  • 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
  • general relativity
  • multiple maneuvers
  • state of the art ODE integrators (adaptive stepsize with error control, continuous output, switching functions, G-stop, step normalization ...)
  • computation of Jacobians with respect to orbital parameters and selected force models parameters
  • 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) with customizable force models
• tabulated ephemerides
  • 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 be used in several different modes
  • slave mode: propagator is driven by calling application
  • master mode: propagator drives application callback functions
  • ephemeris generation mode: 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 an analytical model, even if it really is a numerically propagated one, which is ideal for search and iterative algorithms
• 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
  • anomaly, latitude argument or longitude argument crossings, with either true, eccentric or mean angles
  • 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
  • latitude, longitude, altitude crossing
  • latitude, longitude extremum
  • elevation extremum
  • 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

Attitude

• 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)

Orbit determination

• batch least squares fitting
  • optimizers choice (Levenberg-Marquardt or Gauss-Newton)
  • decomposition algorithms choice (QR, LU, SVD, Cholesky)
  • choice between forming normal equations or not
• Kalman filtering
  • customizable process noise matrices providers
  • time dependent process noise provider
• parameters estimation
  • orbital parameters estimation (or only a subset if desired)
  • force model parameters estimation (drag coefficients, radiation pressure coefficients, central attraction, maneuver thrust or flow rate)
  • 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)
• use numerical propagator or DSST propagator
• multi-satellites orbit determination
• 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 ways)
  • turn-around range
  • azimuth/elevation
  • right ascension/declination
  • position-velocity
  • position
  • inter-satellites range (one way and two way)
  • GNSS code
  • GNSS phase with integer ambiguity resolution and wind-up effect
  • multiplexed
• possibility to add custom measurements
• several predefined modifiers
  • tropospheric effects
  • ionospheric effects
  • station offsets
  • biases
  • delays
  • Antenna Phase Center
  • Shapiro relativistic effect
• possibility to add custom measurement modifiers (even for predefined events)
• possibility to parse CCSDS Tracking Data Message files
• measurements generation
  • 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)
• support for Hatanaka compact RINEX format

Orbit file handling

• loading of SP3 orbit files (versions a to d)
• loading of CCSDS Orbit Data Messages (both OPM, OEM, and OMM types are supported)
• loading of SEM and YUMA files for GPS constellation
• exporting of ephemeris in CCSDS OEM file format

Earth models

• 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
• tropospheric delay (modified Saastamoinen, Mendes-Pavlis, Vienna 1, Vienna 3, estimated, fixed)
• tropospheric refraction correction angle (Recommendation ITU-R P.834-7 and Saemundssen's formula quoted by Meeus)
• tropospheric model for laser ranging (Marini-Murray)
• Klobuchar ionospheric model (including parsing α and β coefficients from University of Bern Astronomical Institute files)
• Global Ionospheric Map model
• NeQuick ionospheric model
• 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 from 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

• Danish
• English
• French
• Galician
• German
• Greek
• Italian
• Norwegian
• Romanian
• Spanish