@Test
    public void testForum() {
        Frame ECI = FramesFactory.getEME2000();
        double mu = Constants.WGS84_EARTH_MU;
        double LAT = FastMath.toRadians(43.05722) ;
        double LON = FastMath.toRadians(76.971667) ;
        double ALT = 2735.0;
        AbsoluteDate t1 = new AbsoluteDate(2023, Month.JUNE, 9, 17, 4,59.10, TimeScalesFactory.getUTC());
        AbsoluteDate t2 = new AbsoluteDate(2023, Month.JUNE, 9, 17, 10,50.66, TimeScalesFactory.getUTC());
        AbsoluteDate t3 = new AbsoluteDate(2023, Month.JUNE, 9, 17, 16,21.09, TimeScalesFactory.getUTC());

        Vector3D RA = new Vector3D((15.* (16. + 5./60. + 51.20/3600.)),
                (15.*(16.+ 11./60. + 43.73/3600.)), (15.*(16.+ 17./60. + 15.1/3600. )));

        Vector3D DEC = new Vector3D((-(6.+ 31./60. + 44.22/3600.)),
                (-(6. + 31./60. + 52.36/3600.)),
                (-(6. +32./60. + 0.03/3600.)));

        int nRev = 0;

        Frame ITRF = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        OneAxisEllipsoid earth = new OneAxisEllipsoid( Constants.WGS84_EARTH_EQUATORIAL_RADIUS ,Constants.WGS84_EARTH_FLATTENING, ITRF);
        GeodeticPoint stationCoord = new GeodeticPoint(LAT, LON, ALT);
        TopocentricFrame stationFrame = new TopocentricFrame(earth, stationCoord, "N42");
        GroundStation ground_station = new GroundStation(stationFrame);

        ObservableSatellite sat1 = new ObservableSatellite(1);

        double[] angular1 = {FastMath.toRadians(RA.getX()), FastMath.toRadians(DEC.getX())};
        double[] angular2 = {FastMath.toRadians(RA.getY()), FastMath.toRadians(DEC.getY())};
        double[] angular3 = {FastMath.toRadians(RA.getZ()), FastMath.toRadians(DEC.getZ())};

        double[] sigma  = {1.0, 1.0};
        double[] baseW  = {1.0, 1.0};
        AngularRaDec raDec1 = new AngularRaDec(ground_station, FramesFactory.getEME2000(), t1,
                angular1, sigma, baseW, sat1);
        AngularRaDec raDec2 = new AngularRaDec(ground_station, FramesFactory.getEME2000(), t2,
                angular2, sigma, baseW, sat1);
        AngularRaDec raDec3 = new AngularRaDec(ground_station, FramesFactory.getEME2000(), t3,
                angular3, sigma, baseW, sat1);


        Vector3D pos1 = stationFrame.getPVCoordinates(t1,ECI).getPosition();
        Vector3D pos2 = stationFrame.getPVCoordinates(t2,ECI).getPosition();
        Vector3D pos3 = stationFrame.getPVCoordinates(t3,ECI).getPosition();


        Vector3D posGauss1 = new Vector3D(-2.0921302099117476E7, -3.6670713616811395E7, 34465.7831621021);
        Vector3D posGauss2 = new Vector3D(-1.99735595868321E7, -3.719354402143339E7, 32965.932702185586);
        Vector3D posGauss3 = new Vector3D(-1.90708500448641E7, -3.766276304220245E7, 31536.539604075253);

        double p1 = posGauss1.getNorm();
        double p3 = posGauss3.getNorm();
        Position position1 = new Position(t1,posGauss1, 1., 1.,sat1);
        Position position2 = new Position(t2,posGauss2, 1., 1.,sat1);
        Position position3 = new Position(t3,posGauss3, 1., 1.,sat1);


        IodGauss iodGauss = new IodGauss(mu, eme2000);
        Orbit estimatedGauss = iodGauss.estimate(raDec1,raDec2,raDec3);
        KeplerianOrbit kepOrbitGauss = new KeplerianOrbit(estimatedGauss);
        System.out.print(kepOrbitGauss);

        IodGibbs iodGibbs = new IodGibbs(mu);
        Orbit estimated_orbit_Gibbs = iodGibbs.estimate(ECI,position1, position2, position3);
        KeplerianOrbit kepOrbitGibbs = new KeplerianOrbit(estimated_orbit_Gibbs);
        System.out.print(kepOrbitGibbs);

        IodGooding gooding = new IodGooding(mu,eme2000,p1, p3, 0,true);
        Orbit estimated_orbit_Gooding = gooding.estimate(raDec1,raDec2,raDec3);
        KeplerianOrbit kepOrbitGooding = new KeplerianOrbit(estimated_orbit_Gooding);
        System.out.print(kepOrbitGooding);


        IodLaplace iodLaplace = new IodLaplace(mu, eme2000);
        Orbit estimatedIodLaplace =iodLaplace.estimate(raDec1,raDec2,raDec3);
        KeplerianOrbit kepOrbitLaplace = new KeplerianOrbit(estimatedIodLaplace);
        System.out.print(kepOrbitLaplace);

        IodLambert iodLambert= new IodLambert(mu);
        Orbit estimatedIodLambert =iodLambert.estimate(eme2000, true,0, position1, position2 );
        KeplerianOrbit kepOrbitLambert = new KeplerianOrbit(estimatedIodLambert);
        System.out.print(kepOrbitLambert);


    }