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2019-10-03T12:50:51Z

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<syntaxhighlight lang="java">
public class ContinuousManeuverByEvents {

public static void main(String[] args) throws PatriusException, IOException, URISyntaxException {

// Patrius Dataset initialization (needed for example to get the UTC time)
PatriusDataset.addResourcesFromPatriusDataset() ;

// Recovery of the UTC time scale using a "factory" (not to duplicate such unique object)
final TimeScale TUC = TimeScalesFactory.getUTC();

// Creating a mass model with a main part and with a tank
final AssemblyBuilder builder = new AssemblyBuilder();

// Main part (dry mass)
final double dryMass = 1000.;
builder.addMainPart("MAIN");
builder.addProperty(new MassProperty(dryMass), "MAIN");

// Tank part (ergols mass)
final double ergolsMass = 100.;
final TankProperty tank = new TankProperty(ergolsMass);
builder.addPart("TANK", "MAIN", Transform.IDENTITY);
builder.addProperty(tank, "TANK");

// Engine part
final double isp = 300.;
final double thrust = 400.;
final PropulsiveProperty prop = new PropulsiveProperty(thrust, isp); // au lieu de new PropulsiveProperty("PROP", thrust, isp);
builder.addPart("PROP", "MAIN", Transform.IDENTITY);
builder.addProperty(prop, "PROP");

final Assembly assembly = builder.returnAssembly();
final MassProvider mm = new MassModel(assembly);

//SPECIFIC
// Duration of the maneuver to get a 20 m/s boost
final AbsoluteDate startDate = new AbsoluteDate("2010-01-01T12:00:00.000", TUC);
final double G0 = 9.80665;
final double duration = G0*isp*mm.getTotalMass()*(1. - FastMath.exp(-20/(G0*isp)))/thrust;
// Start and end thrust events
final EventDetector eventStart = new DateDetector(startDate);
final EventDetector eventEnd = new DateDetector(startDate.shiftedBy(duration));
// Direction of the thrust in the X vehicle axis
final Vector3D direction = new Vector3D(1., 0., 0.);
// Creation of the continuous thrust maneuver
final ContinuousThrustManeuver man = new ContinuousThrustManeuver(eventStart, eventEnd, prop, direction, mm, tank, LOFType.TNW);
//SPECIFIC

System.out.println("End of the thrust: "+man.getEndDate());
System.out.println("Duration of the thrust: "+duration+" s");
System.out.println("Duration of the thrust: "+man.getEndDate().durationFrom(startDate)+" s");
// The getFrame() method is returning "null" as a LOF frame is not define as a frame.
// Nevertheless, an attitude law will not be mandatory when propagating the orbit.
System.out.println("Maneuver frame: "+man.getFrame());

}

}
</syntaxhighlight>

ContinuousManeuverByEvents 4.4 - Historique des versions

Admin : Page créée avec « public class ContinuousManeuverByEvents { public static void main(String[] args) throws PatriusException, IOException, URISyntaxExceptio... »

Admin : Page créée avec « public class ContinuousManeuverByEvents { public static void main(String[] args) throws PatriusException, IOException, URISyntaxExceptio... »