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LUGAN
Orekit
Commits
1922ef54
Commit
1922ef54
authored
Mar 18, 2010
by
Luc Maisonobe
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clarified javadoc
parent
8aea9a63
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src/main/java/org/orekit/propagation/numerical/NumericalPropagator.java
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1922ef54
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@@ -79,11 +79,11 @@ import org.orekit.utils.PVCoordinates;
* keplerian forces. In this case, the simpler {@link
* org.orekit.propagation.analytical.KeplerianPropagator KeplerianPropagator} class would
* perhaps be more effective. The propagator is only in one mode at a time.</p>
* <p>The underlying numerical integrator set up in the constructor
can
also
be configured.
*
Typical tuning
parameters for adaptive stepsize integrators
are the min, max and perhaps
* start step size as well as the absolute and/or relative errors
thresholds. The state
* that is seen by the integrator is a simple seven elements double array.
The six first
* elements are the {@link EquinoctialOrbit equinoxial orbit parameters} (a, e<sub>x</sub>,
* <p>The underlying numerical integrator set up in the constructor
may
also
have its own
*
configuration parameters. Typical configuration
parameters for adaptive stepsize integrators
*
are the min, max and perhaps
start step size as well as the absolute and/or relative errors
*
thresholds. The state
that is seen by the integrator is a simple seven elements double array.
*
The six first
elements are the {@link EquinoctialOrbit equinoxial orbit parameters} (a, e<sub>x</sub>,
* e<sub>y</sub>, h<sub>x</sub>, h<sub>y</sub>, l<sub>v</sub>) in meters and radians, and
* the last element is the mass in kilograms. The following code snippet shows a typical
* setting for Low Earth Orbit propagation:</p>
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