Skip to content
GitLab
Menu
Projects
Groups
Snippets
Loading...
Help
Help
Support
Community forum
Keyboard shortcuts
?
Submit feedback
Contribute to GitLab
Sign in
Toggle navigation
Menu
Open sidebar
Orekit
Orekit
Commits
7b59e644
Commit
7b59e644
authored
Dec 10, 2020
by
Bryan Cazabonne
Browse files
Improved package-info of propagation package.
parent
be8112bf
Changes
1
Show whitespace changes
Inline
Side-by-side
src/main/java/org/orekit/propagation/package-info.java
View file @
7b59e644
...
...
@@ -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
...
...
Write
Preview
Markdown
is supported
0%
Try again
or
attach a new file
.
Attach a file
Cancel
You are about to add
0
people
to the discussion. Proceed with caution.
Finish editing this message first!
Cancel
Please
register
or
sign in
to comment