Passes time over an area using Geographic zone detector

Hello All, I am new in Orekit, I want to know passes time of a satellite over an area and area I have defined using SphericalPolygonsSet and to know my satellite is passing this area. I have used GeographicZoneDetector, I have attached below my code so actually I want to know is my approach is correct or I need to use any other detector and It is generating output but how can I verify this for visualisation by any tool or something?

public class VisibilityCheck {
public static void main(String args) {
final File home = new File(System.getProperty(“user.home”));
final File orekitData = new File(home, “orekit-data”);
if (!orekitData.exists()) {
System.err.format(Locale.US, “Failed to find %s folder%n”, orekitData.getAbsolutePath());
System.err.format(Locale.US, “You need to download %s from %s, unzip it in %s and rename it ‘orekit-data’ for this tutorial to work%n”,
“”, “”, home.getAbsolutePath());
final DataProvidersManager manager = DataContext.getDefault().getDataProvidersManager();
manager.addProvider(new DirectoryCrawler(orekitData));

    // Load TLE data
    String line1 = "1 25544U 98067A   23235.51284918  .00014007  00000-0  25659-3 0  9995";
    String line2 = "2 25544  51.6426 355.0105 0003727 342.0009 113.8232 15.49590945412235";
    TLE tle = new TLE(line1, line2);

    // Create TLE propagator
    final Frame satelliteFrame = FramesFactory.getTEME();
    final AttitudeProvider attitudeProvider = new LofOffset(satelliteFrame, LOFType.VVLH);
    double mass = 419.725;
    // Propagator setup
    final SGP4 propagator = new SGP4(tle, attitudeProvider, mass, satelliteFrame);
    // Earth and frame
    final Frame earthFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(

    // Define the latitude and longitude arrays

    double[] lat = {33.00098474374916, 29.985123674750596, 29.985123674750596, 33.00098474374916};
    double[] lon = {72.75124738699935, 72.75124738699935, 78.57760920383606, 78.57760920383606};

    // Create S2Point instances for each corner
    S2Point point1 = new S2Point(
            FastMath.toRadians(lon[0]), FastMath.toRadians(90 - lat[0]));
    S2Point point2 = new S2Point(
            FastMath.toRadians(lon[1]), FastMath.toRadians(90 - lat[1]));
    S2Point point3 = new S2Point(
            FastMath.toRadians(lon[2]), FastMath.toRadians(90 - lat[2]));
    S2Point point4 = new S2Point(
            FastMath.toRadians(lon[3]), FastMath.toRadians(90 - lat[3]));

    // Create the SphericalPolygonsSet representing the region of interest (ROI)
    SphericalPolygonsSet myAoi = new SphericalPolygonsSet(1.0e-10, point1, point2, point3, point4);

    // Zone detector parameters
    double margin = 0.1; // Angular margin in radians
    GeographicZoneDetector zoneDetector = new GeographicZoneDetector(
            earth, myAoi, margin)
            .withHandler(new EventHandler<GeographicZoneDetector>() {
                AbsoluteDate start = tle.getDate();
                public Action eventOccurred(SpacecraftState s, GeographicZoneDetector detector, boolean increasing) {
                    if (!increasing) {
                        final GeodeticPoint satelliteAsGeodeticPoint = earth.transform(s.getPVCoordinates().getPosition(), s.getFrame(), s.getDate());

                        start = s.getDate();  // Make sure s.getDate() is not null
                        System.out.format("ENTERED AREA: date: %s Satellite Coordinates: {latitude: %f3.9, longitude: %f3.9, altitude: %f km}\n",
                                (satelliteAsGeodeticPoint.getAltitude() / 1000));

                        return Action.CONTINUE;
                    } else {
                        final double duration = s.getDate().durationFrom(start);  // Make sure start is not null
                        final GeodeticPoint satelliteAsGeodeticPoint = earth.transform(s.getPVCoordinates().getPosition(), s.getFrame(), s.getDate());
                        System.out.format("Exiting Satellite Coordinates: {latitude: %f3.9, longitude: %f3.9, altitude: %f km}\n",
                                (satelliteAsGeodeticPoint.getAltitude() / 1000));
                        System.out.format("EXITING AREA: date: %s Pass duration: %f\n", s.getDate(), duration);
                        return Action.CONTINUE;


    // Propagate from the initial TLE epoch to a specified end time
    AbsoluteDate endDate = tle.getDate().shiftedBy(24 * 36000.0); // Propagate for one day
    propagator.propagate(tle.getDate(), endDate);