Examples with KeplerianOrbit org.orekit.orbits.KeplerianOrbit used on opensource projects

Example 56 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit in project Orekit by CS-SI.

the class SolarRadiationPressureTest method testGlobalStateJacobianBox.

@Test
public void testGlobalStateJacobianBox() throws OrekitException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 03, 01), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN, FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);
    NumericalPropagator propagator = new NumericalPropagator(new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    SolarRadiationPressure forceModel = new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0, Vector3D.PLUS_J, 1.2, 0.7, 0.2));
    propagator.addForceModel(forceModel);
    SpacecraftState state0 = new SpacecraftState(orbit);
    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 1e3, tolerances[0], 5.0e-4);
}

Example 57 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit in project Orekit by CS-SI.

the class SolarRadiationPressureTest method doTestLocalJacobianIsotropicClassicalVsFiniteDifferences.

private void doTestLocalJacobianIsotropicClassicalVsFiniteDifferences(double deltaT, double dP, double checkTolerance, boolean print) throws OrekitException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 03, 01), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN, FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    final SolarRadiationPressure forceModel = new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, new IsotropicRadiationClassicalConvention(2.5, 0.7, 0.2));
    checkStateJacobianVsFiniteDifferences(new SpacecraftState(orbit.shiftedBy(deltaT)), forceModel, Propagator.DEFAULT_LAW, dP, checkTolerance, print);
}

Example 58 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit in project Orekit by CS-SI.

the class IodGibbs method estimate.

/**
 * Give an initial orbit estimation, assuming Keplerian motion.
 * All observations should be from the same location.
 *
 * @param frame measure frame
 * @param r1 position 1 measured in frame
 * @param date1 date of measure 1
 * @param r2 position 2 measured in frame
 * @param date2 date of measure 2
 * @param r3 position 3 measured in frame
 * @param date3 date of measure 3
 * @return an initial orbit estimation
 */
public KeplerianOrbit estimate(final Frame frame, final Vector3D r1, final AbsoluteDate date1, final Vector3D r2, final AbsoluteDate date2, final Vector3D r3, final AbsoluteDate date3) {
    // Checks measures are not at the same date
    if (date1.equals(date2) || date1.equals(date3) || date2.equals(date3)) {
    // throw new OrekitException("The measures are not different!");
    }
    // Checks measures are in the same plane
    final double num = r1.normalize().dotProduct(r2.normalize().crossProduct(r3.normalize()));
    final double alpha = FastMath.PI / 2.0 - FastMath.acos(num);
    if (FastMath.abs(alpha) > COPLANAR_THRESHOLD) {
    // throw something
    // throw new OrekitException("Non coplanar points!");
    }
    final Vector3D D = r1.crossProduct(r2).add(r2.crossProduct(r3).add(r3.crossProduct(r1)));
    final Vector3D N = (r2.crossProduct(r3)).scalarMultiply(r1.getNorm()).add((r3.crossProduct(r1)).scalarMultiply(r2.getNorm())).add((r1.crossProduct(r2)).scalarMultiply(r3.getNorm()));
    final Vector3D B = D.crossProduct(r2);
    final Vector3D S = r1.scalarMultiply(r2.getNorm() - r3.getNorm()).add(r2.scalarMultiply(r3.getNorm() - r1.getNorm()).add(r3.scalarMultiply(r1.getNorm() - r2.getNorm())));
    // middle velocity
    final double vm = FastMath.sqrt(mu / (N.getNorm() * D.getNorm()));
    final Vector3D vlEci = B.scalarMultiply(vm / r2.getNorm()).add(S.scalarMultiply(vm));
    // compile a new middle point with position, velocity
    final PVCoordinates pv = new PVCoordinates(r2, vlEci);
    final AbsoluteDate date = date2;
    // compute the equivalent Keplerian orbit
    return new KeplerianOrbit(pv, frame, date, mu);
}

Example 59 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit in project Orekit by CS-SI.

the class IodGooding method propagatePV.

/**
 * Propagate a solution (Kepler).
 *
 * @param P1  initial position vector
 * @param V1  initial velocity vector
 * @param tau propagation time
 * @return final position vector
 */
private Vector3D propagatePV(final Vector3D P1, final Vector3D V1, final double tau) {
    final PVCoordinates pv1 = new PVCoordinates(P1, V1);
    // create a Keplerian orbit. Assume MU = 1.
    final KeplerianOrbit orbit = new KeplerianOrbit(pv1, frame, date1, 1.);
    return orbit.shiftedBy(tau).getPVCoordinates().getPosition();
}

Example 60 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit in project Orekit by CS-SI.

the class SpacecraftStateTest method setUp.

@Before
public void setUp() {
    try {
        Utils.setDataRoot("regular-data");
        double mu = 3.9860047e14;
        double ae = 6.378137e6;
        double c20 = -1.08263e-3;
        double c30 = 2.54e-6;
        double c40 = 1.62e-6;
        double c50 = 2.3e-7;
        double c60 = -5.5e-7;
        mass = 2500;
        double a = 7187990.1979844316;
        double e = 0.5e-4;
        double i = 1.7105407051081795;
        double omega = 1.9674147913622104;
        double OMEGA = FastMath.toRadians(261);
        double lv = 0;
        AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
        orbit = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
        OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
        attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
        propagator = new EcksteinHechlerPropagator(orbit, attitudeLaw, mass, ae, mu, c20, c30, c40, c50, c60);
    } catch (OrekitException oe) {
        Assert.fail(oe.getLocalizedMessage());
    }
}