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@@ -10,7 +10,9 @@ layout: default_orekit
<h2>Java tutorials, by the Orekit team</h2>
<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>
<ul class="fa-ul">
@@ -18,7 +20,8 @@ layout: default_orekit
<p><span class="fa-li fa-lg fa fa-gears"></span><a href="{{ 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><span class="fa-li fa-lg fa fa-gears"></span><a href="{{ 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
@@ -59,6 +62,106 @@ layout: default_orekit
</li>
</ul>
+<p>Other tutorials are available on the dedicated <a href="https://gitlab.orekit.org/orekit/orekit-tutorials">Orekit Tutorials</a> project on the forge:</p>
+<ul class="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