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== LEO propagation == | == LEO propagation == | ||
First, we will have to create a GtmLeoPropagator: | First, we will have to create a [{{PathCurrentJavaDoc}}/fr/cnes/dynvol/gentleman/calc/propagation/GtmLeoPropagator.html GtmLeoPropagator] object: | ||
<syntaxhighlight lang="java"> | <syntaxhighlight lang="java"> | ||
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</syntaxhighlight> | </syntaxhighlight> | ||
Then, we will set all the needed | Then, we will set all the information needed for the propagation ... | ||
=== Initial orbit === | === Initial orbit === | ||
We may use the GtmLeoSimpleOrbit object which allows to enter simplified data as defined [[Orbit#Simple_Orbit|here]] | We may use the [{{PathCurrentJavaDoc}}/fr/cnes/dynvol/gentleman/calc/data/orbit/GtmLeoSimpleOrbit.html GtmLeoSimpleOrbit] object which allows to enter simplified data as defined [[Orbit#Simple_Orbit|here]] | ||
<syntaxhighlight lang="java"> | <syntaxhighlight lang="java"> | ||
Version du 10 septembre 2021 à 09:07
There are two possibilities to initialize an orbital propagation using a GtmLeoPropagator or a GtmLeoPropagator object.
LEO propagation
First, we will have to create a GtmLeoPropagator object:
final GtmLeoPropagator leo = new GtmLeoPropagator();
Then, we will set all the information needed for the propagation ...
Initial orbit
We may use the GtmLeoSimpleOrbit object which allows to enter simplified data as defined here
// Orbit initialization
final AbsoluteDate date = new AbsoluteDate("2020-01-01T00:00:00.000", GtmConstants.UTC);
final double hp = 299.e+3;
final double ha = 300.e+3;
final double inc = FastMath.toRadians(51.6);
final GtmLeoSimpleOrbit simpleOrbit = new GtmLeoSimpleOrbit(date, hp, ha, inc);
leo.setIniOrbit(simpleOrbit.getOrbit());