Data initialization : Différence entre versions

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);

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

final Assembly assembly = vehicle.createAssembly(GCRF);
final MassProvider mm = new MassModel(assembly);

// Dry mass
final double dryMass = 1000.;
final MassProperty dryMassProperty = new MassProperty(dryMass);
 
// Shape
final double sref = 5.0;
Sphere sphere = new Sphere(sref);
final RightParallelepiped solarPanels = new RightParallelepiped(10., 0., 0.);
VehicleSurfaceModel vehicleRefSurface = new VehicleSurfaceModel(sphere, solarPanels);
 
// Aerodynamic properties
final double cd = 2.0;
final double cl = 0.;
final AerodynamicProperties aerodynamicProperties = new AerodynamicProperties(vehicleRefSurface, cd, cl);
 
final Vehicle vehicle = new Vehicle(vehicleRefSurface, null, dryMassProperty, aerodynamicProperties, null, null, null);
 
final Assembly assembly = vehicle.createAssembly(GCRF);
final MassProvider mm = new MassModel(assembly);

// Potential
final ForceModel potential = EarthGravitationalModelFactory.getDroziner(GravityFieldNames.GRGS, "grim4s4_gr", 8, 8, true);
 
final ForceModelsData forces = new ForceModelsData(potential, null, null, null, null, null, null, null, null, null, null, null, null,  null, null);

final double REQ  = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
final double FLAT = Constants.WGS84_EARTH_FLATTENING;
final Frame ITRF = FramesFactory.getITRF();
final ExtendedOneAxisEllipsoid EARTH =
   new ExtendedOneAxisEllipsoid(REQ, FLAT, ITRF, "EARTH");
 
final Atmosphere atmosphere = new US76(EARTH);
final DragForce dragForce = new DragForce(1., atmosphere, assembly);
 
forces.setDragForce(dragForce);

final CelestialBody sunBody = new MeeusSun();
final double dRef = 1.4959787E11;
final double pRef = 4.5605E-6;
final ExtendedOneAxisEllipsoid EARTH =
   new ExtendedOneAxisEllipsoid(REQ, FLAT, ITRF, "EARTH");
 
SolarRadiationPressureEllipsoid radPres = new SolarRadiationPressureEllipsoid(dRef, pRef, sunBody, EARTH, assembly, 1.);
 
forces.setSolarRadiationPressure(radPres);
 
// By default values used when GUI mode ...
final int inCorona = 1;
final int inMeridian = 10;
final IEmissivityModel inEmissivityModel = new KnockeRiesModel();
// Value accessible via GUI mode
final boolean inAlbedo = false;
final boolean inIr = false;
final double coefAlbedo = 1.;
final double coefIr = 1.;
 
RediffusedRadiativeModel rdm = new RediffusedRadiativeModel(inAlbedo, inIr, coefAlbedo, coefIr, assembly);
RediffusedRadiationPressure reDiff =  new RediffusedRadiationPressure(sunBody, GCRF, inCorona, inMeridian, inEmissivityModel, rdm);
 
forces.setRediffusedRadiationPressure(reDiff);

final Psimu test = new Psimu(...);
test.addForceModel(myForce);

// Propulsive properties
final PropulsiveProperty engine = new PropulsiveProperty(400, 320.);
engine.setPartName("ENGINE");
final ArrayList<PropulsiveProperty> listOfEngines = new ArrayList<PropulsiveProperty>();
listOfEngines.add(engine);
final TankProperty tank = new TankProperty(200.);
tank.setPartName("TANK");
final ArrayList<TankProperty> listOfTanks = new ArrayList<TankProperty>();
listOfTanks.add(tank);
listOfTanks.add(tank);
 
final Vehicle vehicle = new Vehicle(vehicleRefSurface, null, dryMassProperty, null, null, listOfEngines, listOfTanks);

final double aol = FastMath.toRadians(180.);
final CustomAOLDetector aolDetector = new CustomAOLDetector(aol, PositionAngle.TRUE, GCRF, MAXCHECK, THRESHOLD, Action.STOP);
final IntervalOccurrenceDetectorWrapper impEvent = new IntervalOccurrenceDetectorWrapper(aolDetector, 1, 1, 1, Action.STOP);
final Vector3D deltaV = new Vector3D(10., 0., 0.);
final CustomImpulseManeuver imp = new CustomImpulseManeuver("Impulse maneuver", listOfEngines.get(0), listOfTanks.get(0), LOFType.TNW, impEvent, deltaV, mm);

final CustomManeuverSequence manSeq = new CustomManeuverSequence(0., 0.);
manSeq.addManeuver(imp);

final double start = iniOrbit.getKeplerianPeriod();
final AbsoluteDate startDate = date.shiftedBy(start);
final CustomDateDetector startEvent = new CustomDateDetector(startDate, MAXCHECK, THRESHOLD, Action.STOP);
final double dur = 1000.;
final AbsoluteDate endDate = startDate.shiftedBy(dur);
final CustomDateDetector stopEvent = new CustomDateDetector(endDate, MAXCHECK, THRESHOLD, Action.STOP);
final Vector3D direction = new Vector3D(-1., 0., 0.);
CustomConstantManeuver cont =
    new CustomConstantManeuver("Continuous maneuver", listOfEngines.get(0), listOfTanks.get(0), LOFType.TNW, startEvent, stopEvent, direction, mm);

final AttitudeLaw attitudeLaw = new LofOffset(LOFType.TNW);

final AttitudeLaw law = new LofOffset(LOFType.TNW, RotationOrder.ZYX, 0., 0., 0.);
final double maxCheck = AbstractDetector.DEFAULT_MAXCHECK;
final double threshold = AbstractDetector.DEFAULT_THRESHOLD;
final EventDetector event =
   new DateDetector(date, maxCheck, threshold, Action.RESET_STATE);
final AttitudesSequence seqAtt = new AttitudesSequence();
seqAtt.addSwitchingCondition(law, event, true, false, law);

final double duration = 86400.;
final double hStop = 120.e+3;
final PsimuPropagationData propagationData = new PsimuPropagationData(duration, GCRF, hStop);
final double step = 5.;
final RK4data integrationData = new RK4data(propagationData, step);

final double minStep = 0.1;
final double maxStep = 30.;
final double[] vecAbsoluteTolerance =
   { 1.0E-5, 1.0E-5, 1.0E-5, 1.0E-8, 1.0E-8, 1.0E-8 };
final double[] vecRelativeTolerance =
   { 1.0E-8, 1.0E-8, 1.0E-8, 1.0E-8, 1.0E-8, 1.0E-8 };
final double absMassTolerance = 1.0E-3;
final double relMassTolerance = 1.0E-2;
final double positionError = 0.;
final DopData intData = new DopData(propagationData, minStep, maxStep, vecAbsoluteTolerance, vecRelativeTolerance, absMassTolerance, relMassTolerance);

final Psimu test = new Psimu(iniOrbit, EARTH, UserFramesConfsEnum.IGNORE, integrationData, vehicle, mm, forces, manSeq, attitudeLaw);