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

Example 11 with CartesianOrbit

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

the class NumericalPropagatorTest method testParallelismIssue258.

@Test
public void testParallelismIssue258() throws OrekitException, InterruptedException, ExecutionException, FileNotFoundException {
    Utils.setDataRoot("regular-data:atmosphere:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));
    final double mu = GravityFieldFactory.getNormalizedProvider(2, 2).getMu();
    // Geostationary transfer orbit
    // semi major axis in meters
    final double a = 24396159;
    // eccentricity
    final double e = 0.72831215;
    // inclination
    final double i = FastMath.toRadians(7);
    // perigee argument
    final double omega = FastMath.toRadians(180);
    // right ascension of ascending node
    final double raan = FastMath.toRadians(261);
    // mean anomaly
    final double lM = 0;
    final Frame inertialFrame = FramesFactory.getEME2000();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final AbsoluteDate initialDate = new AbsoluteDate(2003, 1, 1, 00, 00, 00.000, utc);
    final Orbit initialOrbit = new CartesianOrbit(new KeplerianOrbit(a, e, i, omega, raan, lM, PositionAngle.MEAN, inertialFrame, initialDate, mu));
    final SpacecraftState initialState = new SpacecraftState(initialOrbit, 1000);
    // initialize the testing points
    final List<SpacecraftState> states = new ArrayList<SpacecraftState>();
    final NumericalPropagator propagator = createPropagator(initialState, OrbitType.CARTESIAN, PositionAngle.TRUE);
    final double samplingStep = 10000.0;
    propagator.setMasterMode(samplingStep, (state, isLast) -> states.add(state));
    propagator.propagate(initialDate.shiftedBy(5 * samplingStep));
    // compute reference errors, using serial computation in a for loop
    final double[][] referenceErrors = new double[states.size() - 1][];
    for (int startIndex = 0; startIndex < states.size() - 1; ++startIndex) {
        referenceErrors[startIndex] = recomputeFollowing(startIndex, states);
    }
    final Consumer<SpacecraftState> checker = point -> {
        try {
            final int startIndex = states.indexOf(point);
            double[] errors = recomputeFollowing(startIndex, states);
            for (int k = 0; k < errors.length; ++k) {
                Assert.assertEquals(startIndex + " to " + (startIndex + k + 1), referenceErrors[startIndex][k], errors[k], 1.0e-9);
            }
        } catch (OrekitException oe) {
            Assert.fail(oe.getLocalizedMessage());
        }
    };
    // serial propagation using Stream
    states.stream().forEach(checker);
    // parallel propagation using parallelStream
    states.parallelStream().forEach(checker);
}

Example 12 with CartesianOrbit

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

the class NumericalPropagatorTest method createEllipticOrbit.

private CartesianOrbit createEllipticOrbit() throws OrekitException {
    final AbsoluteDate date = new AbsoluteDate("2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final Vector3D position = new Vector3D(6896874.444705, 1956581.072644, -147476.245054);
    final Vector3D velocity = new Vector3D(166.816407662, -1106.783301861, -7372.745712770);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    return new CartesianOrbit(pv, frame, mu);
}

Example 13 with CartesianOrbit

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

the class DSSTPropagatorTest method testEphemerisDates.

@Test
public void testEphemerisDates() throws OrekitException {
    // setup
    TimeScale tai = TimeScalesFactory.getTAI();
    AbsoluteDate initialDate = new AbsoluteDate("2015-07-01", tai);
    AbsoluteDate startDate = new AbsoluteDate("2015-07-03", tai).shiftedBy(-0.1);
    AbsoluteDate endDate = new AbsoluteDate("2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    KeplerianOrbit orbit = new KeplerianOrbit(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS, 0, 0, 0, 0, 0, PositionAngle.TRUE, eci, initialDate, Constants.EIGEN5C_EARTH_MU);
    double[][] tol = DSSTPropagator.tolerances(1, orbit);
    Propagator prop = new DSSTPropagator(new DormandPrince853Integrator(0.1, 500, tol[0], tol[1]));
    prop.resetInitialState(new SpacecraftState(new CartesianOrbit(orbit)));
    // action
    prop.setEphemerisMode();
    prop.propagate(startDate, endDate);
    BoundedPropagator ephemeris = prop.getGeneratedEphemeris();
    // verify
    TimeStampedPVCoordinates actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedPVCoordinates expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition(), OrekitMatchers.vectorCloseTo(expectedPV.getPosition(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity(), OrekitMatchers.vectorCloseTo(expectedPV.getVelocity(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate), OrekitMatchers.closeTo(0, 0));
    // test date
    AbsoluteDate date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date), 0, 0);
}

Example 14 with CartesianOrbit

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

the class ThirdBodyAttractionTest method testParameterDerivative.

@Test
public void testParameterDerivative() throws OrekitException {
    final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
    final Vector3D vel = new Vector3D(2.14718074509906819e+03, 7.38239351251748485e+03, -1.14097953925384523e+01);
    final SpacecraftState state = new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel), FramesFactory.getGCRF(), new AbsoluteDate(2003, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()), Constants.EIGEN5C_EARTH_MU));
    final CelestialBody moon = CelestialBodyFactory.getMoon();
    final ThirdBodyAttraction forceModel = new ThirdBodyAttraction(moon);
    Assert.assertTrue(forceModel.dependsOnPositionOnly());
    final String name = moon.getName() + ThirdBodyAttraction.ATTRACTION_COEFFICIENT_SUFFIX;
    checkParameterDerivative(state, forceModel, name, 1.0, 7.0e-15);
}

Example 15 with CartesianOrbit

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

the class SolarRadiationPressureTest method testParameterDerivativeIsotropicSingle.

@Test
public void testParameterDerivativeIsotropicSingle() throws OrekitException {
    final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
    final Vector3D vel = new Vector3D(2.14718074509906819e+03, 7.38239351251748485e+03, -1.14097953925384523e+01);
    final SpacecraftState state = new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel), FramesFactory.getGCRF(), new AbsoluteDate(2003, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()), Constants.EIGEN5C_EARTH_MU));
    RadiationSensitive rs = new IsotropicRadiationSingleCoefficient(2.5, 0.7);
    SolarRadiationPressure forceModel = new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, rs);
    checkParameterDerivative(state, forceModel, RadiationSensitive.REFLECTION_COEFFICIENT, 1.0, 2.0e-15);
    try {
        rs.radiationPressureAcceleration(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation(), state.getMass(), Vector3D.ZERO, new double[2], RadiationSensitive.ABSORPTION_COEFFICIENT);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, oe.getSpecifier());
    }
    for (ParameterDriver driver : rs.getRadiationParametersDrivers()) {
        Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, driver.getName());
    }
}