Data initialization

Data initialization

Orbit

To initialize an orbit, we simply have to build it using [PATRIUS] object. For example:

final TimeScale TUC = TimeScalesFactory.getUTC();
final AbsoluteDate date = new AbsoluteDate("2010-01-01T12:00:00.000", TUC);       
final double sma = Constants.WGS84_EARTH_EQUATORIAL_RADIUS + 250.e3;
final double ecc = 0.;
final double inc = FastMath.toRadians(51.6);
final double raan = FastMath.toRadians(0.);
final double pa  = FastMath.toRadians(0.);
final double ano = FastMath.toRadians(0.);
final Frame GCRF = FramesFactory.getGCRF();
final KeplerianOrbit iniOrbit =
  new KeplerianOrbit(sma, ecc, inc, raan, pa, ano, PositionAngle.MEAN, GCRF, date, MU);

Earth features

Data equivalent to the “Earth features” tab are distributed via two arguments:

1. A ExtendedOneAxisEllipsoid object which will define the shape of the planet

final ExtendedOneAxisEllipsoid EARTH =
   new ExtendedOneAxisEllipsoid(REQ, FLAT, ITRF, "EARTH");

2. A type of enumerates that will propose some pre-defined configurations as:

• NOTHING (all options set to null)
• ONLY_PREC_NUT (only precession and nutation)
• FACTORY (equivalent to the most complete definition as in the GUI)
• IGNORE (nothing is define internally by PSIMU which will take into account the user parametrization previously done)

Vehicle

In fact, we need to pass both an Assembly</font and a MassProvider. It could seem curious but it is due to the fact that, if we have maneuvers, it will be mandatory to initialize them with the same MassProvider (see example with maneuvers). To get them, we could use the AssemblyBuilder given by [PATRIUS] or the CustomVehicle class coming from [GENOPUS] waiting for the next Vehicle class that will appear from [PATRIUS] V3.4. In the example below, we will use the CustomVehicle class initializing mass and aerodynamic properties (here no engines and no tanks):

// Dry mass
final double dryMass = 1000.;
final MassProperty dryMassProperty = new MassProperty(dryMass);
// Shape
final CustomSphere sphere = new CustomSphere(5.0);
final CustomVehicleSurfaceModel vehicleRefSurface =
   new CustomVehicleSurfaceModel(sphere);
// Aerodynamic properties
final double cd = 2.0;
final double cl = 0.;
final CustomAerodynamicProperties aerodynamicProperties =
   new CustomAerodynamicProperties(vehicleRefSurface, cd, cl);
 
final CustomVehicle vehicle =
   new CustomVehicle(dryMassProperty, aerodynamicProperties, null, null, null);
final Assembly assembly = vehicle.getAssembly(GCRF);
final MassProvider mm = new MassModel(assembly);

Note : be careful that the frame (GCRF in the previous example), mandatory in the construction of the vehicle must be exactly the same that the one used for the propagation (limitation due to PATRIUS).>