<p>The tests suite is the first place to look for getting help with Orekit
use. Several tutorials are also provided with the source code in order to
use.
Some tutorials are provided with source code and comments in order to
emphazise particular use cases:</p>
<ulclass="fa-ul">
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<p><spanclass="fa-li fa-lg fa fa-gears"></span><ahref="{{ site.url }}/site-orekit-tutorials-{{ site.data.orekit-tutorials.versions.first }}/tutorials/attitude.html">Attitude</a><br/>
This tutorial emphasizes a specific usage of the attitude package
described in the attitudes section of the library architecture
documentation.</p></li>
documentation.</p>
</li>
<li>
<p><spanclass="fa-li fa-lg fa fa-gears"></span><ahref="{{ site.url }}/site-orekit-tutorials-{{ site.data.orekit-tutorials.versions.first }}/tutorials/frames.html">Frames</a><br/>
This tutorial shows how to solve three problems: (1) computation of the
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</li>
</ul>
<p>Other tutorials are available on the dedicated <ahref="https://gitlab.orekit.org/orekit/orekit-tutorials">Orekit Tutorials</a> project on the forge:</p>
<ulclass="fa-ul">
<li>Attitude / EarthObservation: shows how to easily switch between day and night attitude modes</li>
<p>
<li>Bodies
<ul>
<li>DEFile: reads a DEXXX binary file (JPL or IMCCE inpop ephemeris file) and writes a new one containing only the data asked by the user</li>
<li>Phasing: sets up a Sun-synchronous Earth-phased Low Earth Orbit</li>
</ul>
</li>
<p>
<li>Control / indirect / FixedBoundarySingleShooting: shows how to use the indirect (single) shooting method of Orekit. The study case is inspired by the Global Trajectory Optimization Competition 12</li>
<p>
<li>Conversion
<ul>
<li>PropagatorConversion: helps understand how a propagator can be converted to another with a different model.<br>
Here we convert a numerical propagator into an analytical Keplerian propagator
</li>
<li>TLEConversion: shows how to get a numerical propagator from a TLE and back</li>
</ul>
</li>
<p>
<li>Data / Context: explains how to instantiate several data contexts</li>
<p>
<li>Estimation: orbit determination (OD) example
<ul>
<li>DSSTOrbitDetermination: batch least-square OD with a DSST propagator for a MEO (GNSS) satellite with RINEX measurements</li>
<li>GNSSOrbitDetermination: same but with a numerical propagator instead</li>
<li>ExtendedSemianalyticalKalmanFilter: extended Kalman OD with a DSST propagator for a geodesy (LAGEOS 2) satellite with laser ranging measurements</li>
<li>KalmanNumericalOrbitDetermination: same but with a numerical propagator instead</li>
<li>LaserRangingOrbitDetermination: same but with a batch least-square OD instead</li>
<li>ManeuverEstimation: maneuvers parameters' estimation with simulated measurements</li>
<li>NumericalOrbitDetermination: batch least-square OD with a numerical propagator for a GTO satellite with range and AZEL measurements</li>
<li>SequentialBatchLeastSquares: an example of sequential batch least-square OD with a numerical propagator</li>
<li>TLEBasedOrbitDetermination: batch least-square OD with a SGP4 propagator (TLE) for a MEO (GNSS) satellite with precise ephemeris (PV measurements)</li>
<li>Performance / PerformanceTesting: simulates a large number of measurements on a large time slot to study Orekit OD performances</li>
</ul>
</li>
<p>
<li>Frames / Frames1-2-3: different examples of frame management</li>
<p>
<li>Gnss:
<ul>
<li>DOPComputation: shows a basic usage for computing the DOP over a geographic zone and for a period</li>
<li>RinexObservationFile: reading of Rinex observation files</li>
</ul>
</li>
<p>
<li>Maneuvers:
<ul>
<li>ApogeeManeuver: large apogee maneuver with a long (~1h) constant thrust maneuver</li>
<li>ImpulseAtNode: shows how to perform a given impulse maneuver at node</li>
<li>StationKeeping: East-West GEO Station Keeping with impulse maneuvers using DSST propagator</li>
</ul>
</li>
<p>
<li>Models / TidalDisplacements: shows how to compute stations tidal displacements</li>
<p>
<li>Estimation: orbit determination (OD) example
<ul>
<li>CovariancePropagation: linear covariance propagation example, starting from a CCSDS OPM (Orbit Parameter Message)</li>
<li>DSSTPropagation: propagation with the DSST propagator</li>
<li>EphemerisMode: shows how to produce an ephemeris with Orekit</li>
<li>FieldPropagation: numerical propagation with Taylor-maps and a Monte Carlo sampling at the end</li>
<li>GNSSPropagation: propagation with a GNSS-adapted propagator, starting from a navigation message</li>
<li>GradientComputation: shows how to compute the Jacobian containing the partial derivatives of the acceleration with respect the the spacecraft coordinates</li>
<li>GroundTrack: graphical display of ground tracks</li>
<li>JupiterSwingBy: Swing-by trajectory about Jupiter compared in EME2000, ICRF and Jupiter-centered inertial reference frame</li>
<li>KeplerianPropagation: propagation with a basic Keplerian propagator</li>
<li>NumericalPropagation: propagation with a basic numerical propagator</li>
<li>PropagationInNonInertialFrame: introduction to orbital integration using SingleBodyAttraction and non-inertial frames</li>
<li>PropagationInRotatingFrame: Compared propagation of a LEO satellite in Earth-centered inertial and non-inertial frames: EME2000 and ITRF</li>
<li>PropagationInNonInertialFrame: introduction to orbital integration using SingleBodyAttraction and non-inertial frames</li>
<li>TrackCorridor: tutorial for track corridor display</li>
<li>VisibilityCheck: shows how to easily check for visibility between a satellite and a ground station</li>
<li>VisibilityCircle: computes visibility circles on ground as seen from a satellite</li>
<li>CR3BP: Circular Restricted 3-Body Problem
<ul>
<li>CR3BPSphereCrossingDetector: a detector for checking if a probe crashes on one of the two primary bodies in C3RBP</li>
<li>EarthMoonHaloOrbit: computation of a northern Halo Orbit around Earth-Moon L1</li>
<li>ManifoldTransfer: computation of a transfer from Earth-Moon L2 Halo Orbit to High Lunar Orbit using unstable manifolds</li>
<li>PropagationInCR3BP: example of propagation in the Circular Restricted 3-Body problem with Orekit</li>
<li>SunEarthMultipleShooter: correction of a trajectory using multiple shooting method in the Sun-Earth CR3BP</li>
<li>YZPlaneCrossingDetector: a detector for YZ Planes crossing within C3RBP</li>
</ul>
</li>
</ul>
</li>
<p>
<li>Time / Time1: tutorial for dates support</li>
</ul>
<h3>Maven site for the Java tutorials</h2>
<p>The technical documentation explains how to build, download and contribute to the Orekit tutorials. Please choose the Orekit tutorials release for which you
