Examples with OrekitException org.orekit.errors.OrekitException used on opensource projects

Example 46 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestException.

private <T extends RealFieldElement<T>> void doTestException(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    propagator.setMasterMode(new FieldOrekitStepHandler<T>() {

        private int countDown = 3;

        private FieldAbsoluteDate<T> previousCall = null;

        public void init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) {
        }

        public void handleStep(FieldOrekitStepInterpolator<T> interpolator, boolean isLast) throws OrekitException {
            if (previousCall != null) {
                System.out.println(interpolator.getCurrentState().getDate().compareTo(previousCall) < 0);
            }
            if (--countDown == 0) {
                throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "dummy error");
            }
        }
    });
    propagator.propagate(initDate.shiftedBy(-3600));
}

Example 47 with OrekitException

use of org.orekit.errors.OrekitException 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 48 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class NumericalPropagatorTest method testIssue157.

@Test
public void testIssue157() throws OrekitException {
    try {
        Orbit orbit = new KeplerianOrbit(13378000, 0.05, 0, 0, FastMath.PI, 0, PositionAngle.MEAN, FramesFactory.getTOD(false), new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()), Constants.EIGEN5C_EARTH_MU);
        NumericalPropagator.tolerances(1.0, orbit, OrbitType.KEPLERIAN);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException pe) {
        Assert.assertEquals(OrekitMessages.SINGULAR_JACOBIAN_FOR_ORBIT_TYPE, pe.getSpecifier());
    }
}

Example 49 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class NumericalPropagatorTest method testAdditionalStateEvent.

@Test
public void testAdditionalStateEvent() throws OrekitException {
    propagator.addAdditionalEquations(new AdditionalEquations() {

        public String getName() {
            return "linear";
        }

        public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
            pDot[0] = 1.0;
            return new double[7];
        }
    });
    try {
        propagator.addAdditionalEquations(new AdditionalEquations() {

            public String getName() {
                return "linear";
            }

            public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
                pDot[0] = 1.0;
                return new double[7];
            }
        });
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE);
    }
    try {
        propagator.addAdditionalStateProvider(new AdditionalStateProvider() {

            public String getName() {
                return "linear";
            }

            public double[] getAdditionalState(SpacecraftState state) {
                return null;
            }
        });
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE);
    }
    propagator.addAdditionalStateProvider(new AdditionalStateProvider() {

        public String getName() {
            return "constant";
        }

        public double[] getAdditionalState(SpacecraftState state) {
            return new double[] { 1.0 };
        }
    });
    Assert.assertTrue(propagator.isAdditionalStateManaged("linear"));
    Assert.assertTrue(propagator.isAdditionalStateManaged("constant"));
    Assert.assertFalse(propagator.isAdditionalStateManaged("non-managed"));
    Assert.assertEquals(2, propagator.getManagedAdditionalStates().length);
    propagator.setInitialState(propagator.getInitialState().addAdditionalState("linear", 1.5));
    CheckingHandler<AdditionalStateLinearDetector> checking = new CheckingHandler<AdditionalStateLinearDetector>(Action.STOP);
    propagator.addEventDetector(new AdditionalStateLinearDetector(10.0, 1.0e-8).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    final SpacecraftState finalState = propagator.propagate(initDate.shiftedBy(dt));
    checking.assertEvent(true);
    Assert.assertEquals(3.0, finalState.getAdditionalState("linear")[0], 1.0e-8);
    Assert.assertEquals(1.5, finalState.getDate().durationFrom(initDate), 1.0e-8);
}

Example 50 with OrekitException

use of org.orekit.errors.OrekitException in project Orekit by CS-SI.

the class PartialDerivativesTest method testWrongParametersDimension.

@Test
public void testWrongParametersDimension() throws OrekitException {
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    double dP = 0.001;
    ForceModel sunAttraction = new ThirdBodyAttraction(CelestialBodyFactory.getSun());
    sunAttraction.getParameterDriver("Sun attraction coefficient").setSelected(true);
    ForceModel moonAttraction = new ThirdBodyAttraction(CelestialBodyFactory.getMoon());
    NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE, sunAttraction, moonAttraction);
    PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
    try {
        partials.setInitialJacobians(new SpacecraftState(initialOrbit), new double[6][6], new double[6][3]);
        partials.computeDerivatives(new SpacecraftState(initialOrbit), new double[6]);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH, oe.getSpecifier());
    }
}