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Page créée avec « There are two possibilities to initialize an orbital propagation using a GtmLeoPropagator or a GtmLeoPropagator object. == LEO propagation == First, we will have to crea... » |
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<syntaxhighlight lang="java"> | <syntaxhighlight lang="java"> | ||
// 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()); | |||
</syntaxhighlight> | </syntaxhighlight> | ||
== GEO progation == | == GEO progation == | ||
Version du 10 septembre 2021 à 08:31
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:
final GtmLeoPropagator leo = new GtmLeoPropagator();
Then, we will set all the needed information ...
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());