Commit 7b59e644 authored by Bryan Cazabonne's avatar Bryan Cazabonne
Browse files

Improved package-info of propagation package.

parent be8112bf
......@@ -51,6 +51,21 @@
* position. As the Keplerian propagator, it implements the
* {@link org.orekit.propagation.Propagator} interface.
* <h3> TLE propagation </h3>
* <p> This analytical model allows propagating {org.orekit.propagation.analytical.tle.TLE}
* data using SGP4 or SDP4 models. It is very easy to initialize, only the initial
* TLE is needed. As the other analytical propagators, it implements the
* {@link org.orekit.propagation.Propagator} interface.
* <h3> GNSS propagation </h3>
* <p> These analytical models allow propagating navigation messages such as
* in GNSS almanacs available thanks to {@link org.orekit.gnss.SEMParser SEM}
* or {@link org.orekit.gnss.YUMAParser YUMA} files. Each GNSS constellation
* has its own propagation model availables in {@link org.orekit.propagation.analytical.gnss}
* package.
* <h3> Numerical propagation </h3>
* <p> It is the most important part of the OREKIT project. Based on Hipparchus
......@@ -60,10 +75,10 @@
* fact quite clear and intuitive.
* <p>
* The mathematical problem to integrate is a seven dimension time derivative
* The mathematical problem to integrate is a 6 dimension time derivative
* equations system. The six first equations are given by the Gauss equations
* (expressed in {@link org.orekit.orbits.EquinoctialOrbit}) and the seventh
* is simply the flow rate and mass equation. This first order system is computed
* (expressed in {@link org.orekit.orbits.EquinoctialOrbit}).
* This first order system is computed
* by the {@link org.orekit.propagation.numerical.TimeDerivativesEquations}
* class. It will be instanced by the propagator and then be modified at each
* step (a fixed t value) by all the needed {@link
......@@ -77,6 +92,16 @@
* for the next first time derivative, etc. until it reaches the final asked date.
* </p>
* <h3> Semi-analytical propagation </h3>
* <p> Semi-analytical propagation in Orekit is based on Draper Semi-analytical
* Satellite Theory (DSST), which is applicable to all orbit types. DSST divides
* the computation of the osculating orbital elements into two contributions: the
* mean orbital elements and the short-periodic terms. Both models are developed
* in the equinoctial orbital elements via the Method of Averaging. Mean orbital
* elements are computed numerically while short period motion is computed using
* a combination of analytical and numerical techniques.
* @author Luc Maisonobe
* @author Fabien Maussion
* @author Pascal Parraud
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