Examples with Well19937a org.hipparchus.random.Well19937a used on opensource projects

Example 6 with Well19937a

use of org.hipparchus.random.Well19937a in project Orekit by CS-SI.

the class NRLMSISE00Test method testGlob7sSwitchesRandom.

@Test
public void testGlob7sSwitchesRandom() throws OrekitException {
    RandomGenerator random = new Well19937a(0x3671893ce741fc5cl);
    NRLMSISE00 atm = new NRLMSISE00(null, null, null);
    for (int i = 1; i <= 23; ++i) {
        atm = atm.withSwitch(i, random.nextInt(3) - 2);
    }
    doTestDoubleMethod(atm, random, "glob7s", 1.0e-50, 1.0e-50);
}

Example 7 with Well19937a

use of org.hipparchus.random.Well19937a in project Orekit by CS-SI.

the class NRLMSISE00Test method testGlob7sSwitchesOn.

@Test
public void testGlob7sSwitchesOn() throws OrekitException {
    RandomGenerator random = new Well19937a(0xc7c218fabec5e98cl);
    NRLMSISE00 atm = new NRLMSISE00(null, null, null);
    for (int i = 1; i <= 23; ++i) {
        atm = atm.withSwitch(i, 1);
    }
    doTestDoubleMethod(atm, random, "glob7s", 4.0e-15, 9.0e-16);
}

Example 8 with Well19937a

use of org.hipparchus.random.Well19937a in project Orekit by CS-SI.

the class NRLMSISE00Test method testgtd7dSwitchesRandom.

@Test
public void testgtd7dSwitchesRandom() throws OrekitException {
    RandomGenerator random = new Well19937a(0x4a75e29ddf23ccd7l);
    NRLMSISE00 atm = new NRLMSISE00(null, null, null);
    for (int i = 1; i <= 23; ++i) {
        atm = atm.withSwitch(i, random.nextInt(3) - 2);
    }
    doTestVoidMethod(atm, random, "gtd7d", 1.0e-50, 3.0e-14);
}

Example 9 with Well19937a

use of org.hipparchus.random.Well19937a in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method RealFieldTest.

/**
 *Testing if the propagation between the FieldPropagation and the propagation
 * is equivalent.
 * Also testing if propagating X+dX with the propagation is equivalent to
 * propagation X with the FieldPropagation and then applying the taylor
 * expansion of dX to the result.
 */
@Test
public void RealFieldTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 4);
    DerivativeStructure a_0 = factory.variable(0, 7201009.7124401);
    DerivativeStructure e_0 = factory.variable(1, 1e-3);
    DerivativeStructure i_0 = factory.variable(2, 98.7 * FastMath.PI / 180);
    DerivativeStructure R_0 = factory.variable(3, 15.0 * 22.5 * FastMath.PI / 180);
    DerivativeStructure O_0 = factory.variable(4, 93.0 * FastMath.PI / 180);
    DerivativeStructure n_0 = factory.variable(5, 0.1);
    Field<DerivativeStructure> field = a_0.getField();
    DerivativeStructure zero = field.getZero();
    FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<>(field);
    Frame EME = FramesFactory.getEME2000();
    FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<>(a_0, e_0, i_0, R_0, O_0, n_0, PositionAngle.MEAN, EME, J2000, Constants.EIGEN5C_EARTH_MU);
    FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<>(FKO);
    SpacecraftState iSR = initialState.toSpacecraftState();
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(10.0, FKO.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<DerivativeStructure> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    AdaptiveStepsizeIntegrator RIntegrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    RIntegrator.setInitialStepSize(60);
    FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
    FNP.setOrbitType(type);
    FNP.setInitialState(initialState);
    NumericalPropagator NP = new NumericalPropagator(RIntegrator);
    NP.setOrbitType(type);
    NP.setInitialState(iSR);
    double[][] c = new double[3][1];
    c[0][0] = 0.0;
    c[2][0] = normalizedC20;
    double[][] s = new double[3][1];
    NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(6378136.460, mu, TideSystem.UNKNOWN, c, s);
    HolmesFeatherstoneAttractionModel forceModel = new HolmesFeatherstoneAttractionModel(itrf, provider);
    FNP.addForceModel(forceModel);
    NP.addForceModel(forceModel);
    FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1005.);
    FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
    SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
    FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
    PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getX(), finPVC_R.getPosition().getX(), FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getY(), finPVC_R.getPosition().getY(), FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getZ(), finPVC_R.getPosition().getZ(), FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
    long number = 23091991;
    RandomGenerator RG = new Well19937a(number);
    GaussianRandomGenerator NGG = new GaussianRandomGenerator(RG);
    UncorrelatedRandomVectorGenerator URVG = new UncorrelatedRandomVectorGenerator(new double[] { 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 }, new double[] { 1e1, 0.001, 0.001, 0.001, 0.001, 0.001 }, NGG);
    double a_R = a_0.getReal();
    double e_R = e_0.getReal();
    double i_R = i_0.getReal();
    double R_R = R_0.getReal();
    double O_R = O_0.getReal();
    double n_R = n_0.getReal();
    for (int ii = 0; ii < 1; ii++) {
        double[] rand_next = URVG.nextVector();
        double a_shift = a_R + rand_next[0];
        double e_shift = e_R + rand_next[1];
        double i_shift = i_R + rand_next[2];
        double R_shift = R_R + rand_next[3];
        double O_shift = O_R + rand_next[4];
        double n_shift = n_R + rand_next[5];
        KeplerianOrbit shiftedOrb = new KeplerianOrbit(a_shift, e_shift, i_shift, R_shift, O_shift, n_shift, PositionAngle.MEAN, EME, J2000.toAbsoluteDate(), Constants.EIGEN5C_EARTH_MU);
        SpacecraftState shift_iSR = new SpacecraftState(shiftedOrb);
        NumericalPropagator shift_NP = new NumericalPropagator(RIntegrator);
        shift_NP.setOrbitType(type);
        shift_NP.setInitialState(shift_iSR);
        shift_NP.addForceModel(forceModel);
        SpacecraftState finalState_shift = shift_NP.propagate(target.toAbsoluteDate());
        PVCoordinates finPVC_shift = finalState_shift.getPVCoordinates();
        // position check
        FieldVector3D<DerivativeStructure> pos_DS = finPVC_DS.getPosition();
        double x_DS = pos_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double y_DS = pos_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double z_DS = pos_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double x = finPVC_shift.getPosition().getX();
        double y = finPVC_shift.getPosition().getY();
        double z = finPVC_shift.getPosition().getZ();
        Assert.assertEquals(x_DS, x, FastMath.abs(x - pos_DS.getX().getReal()) * 1e-8);
        Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 1e-8);
        Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 1e-8);
        // velocity check
        FieldVector3D<DerivativeStructure> vel_DS = finPVC_DS.getVelocity();
        double vx_DS = vel_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vy_DS = vel_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vz_DS = vel_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vx = finPVC_shift.getVelocity().getX();
        double vy = finPVC_shift.getVelocity().getY();
        double vz = finPVC_shift.getVelocity().getZ();
        Assert.assertEquals(vx_DS, vx, FastMath.abs(vx) * 1e-9);
        Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 1e-9);
        Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 1e-9);
        // acceleration check
        FieldVector3D<DerivativeStructure> acc_DS = finPVC_DS.getAcceleration();
        double ax_DS = acc_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ay_DS = acc_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double az_DS = acc_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ax = finPVC_shift.getAcceleration().getX();
        double ay = finPVC_shift.getAcceleration().getY();
        double az = finPVC_shift.getAcceleration().getZ();
        Assert.assertEquals(ax_DS, ax, FastMath.abs(ax) * 1e-9);
        Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 1e-9);
        Assert.assertEquals(az_DS, az, FastMath.abs(az) * 1e-9);
    }
}

Example 10 with Well19937a

use of org.hipparchus.random.Well19937a in project Orekit by CS-SI.

the class GroundStationTest method testEstimateStationPosition.

@Test
public void testEstimateStationPosition() throws OrekitException, IOException, ClassNotFoundException {
    Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
    final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
    // create perfect range measurements
    final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
    final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeMeasurementCreator(context), 1.0, 3.0, 300.0);
    // move one station
    final RandomGenerator random = new Well19937a(0x4adbecfc743bda60l);
    final TopocentricFrame base = context.stations.get(0).getBaseFrame();
    final BodyShape parent = base.getParentShape();
    final Vector3D baseOrigin = parent.transform(base.getPoint());
    final Vector3D deltaTopo = new Vector3D(2 * random.nextDouble() - 1, 2 * random.nextDouble() - 1, 2 * random.nextDouble() - 1);
    final Transform topoToParent = base.getTransformTo(parent.getBodyFrame(), (AbsoluteDate) null);
    final Vector3D deltaParent = topoToParent.transformVector(deltaTopo);
    final String movedSuffix = "-moved";
    final GroundStation moved = new GroundStation(new TopocentricFrame(parent, parent.transform(baseOrigin.subtract(deltaParent), parent.getBodyFrame(), null), base.getName() + movedSuffix), context.ut1.getEOPHistory(), context.stations.get(0).getDisplacements());
    // create orbit estimator
    final BatchLSEstimator estimator = new BatchLSEstimator(new LevenbergMarquardtOptimizer(), propagatorBuilder);
    for (final ObservedMeasurement<?> measurement : measurements) {
        final Range range = (Range) measurement;
        final String name = range.getStation().getBaseFrame().getName() + movedSuffix;
        if (moved.getBaseFrame().getName().equals(name)) {
            estimator.addMeasurement(new Range(moved, range.getDate(), range.getObservedValue()[0], range.getTheoreticalStandardDeviation()[0], range.getBaseWeight()[0]));
        } else {
            estimator.addMeasurement(range);
        }
    }
    estimator.setParametersConvergenceThreshold(1.0e-3);
    estimator.setMaxIterations(100);
    estimator.setMaxEvaluations(200);
    // we want to estimate station offsets
    moved.getEastOffsetDriver().setSelected(true);
    moved.getNorthOffsetDriver().setSelected(true);
    moved.getZenithOffsetDriver().setSelected(true);
    EstimationTestUtils.checkFit(context, estimator, 2, 3, 0.0, 5.6e-7, 0.0, 1.4e-6, 0.0, 4.8e-7, 0.0, 2.6e-10);
    Assert.assertEquals(deltaTopo.getX(), moved.getEastOffsetDriver().getValue(), 4.5e-7);
    Assert.assertEquals(deltaTopo.getY(), moved.getNorthOffsetDriver().getValue(), 6.2e-7);
    Assert.assertEquals(deltaTopo.getZ(), moved.getZenithOffsetDriver().getValue(), 2.6e-7);
    GeodeticPoint result = moved.getOffsetGeodeticPoint(null);
    GeodeticPoint reference = context.stations.get(0).getBaseFrame().getPoint();
    Assert.assertEquals(reference.getLatitude(), result.getLatitude(), 1.4e-14);
    Assert.assertEquals(reference.getLongitude(), result.getLongitude(), 2.9e-14);
    Assert.assertEquals(reference.getAltitude(), result.getAltitude(), 2.6e-7);
    RealMatrix normalizedCovariances = estimator.getOptimum().getCovariances(1.0e-10);
    RealMatrix physicalCovariances = estimator.getPhysicalCovariances(1.0e-10);
    Assert.assertEquals(9, normalizedCovariances.getRowDimension());
    Assert.assertEquals(9, normalizedCovariances.getColumnDimension());
    Assert.assertEquals(9, physicalCovariances.getRowDimension());
    Assert.assertEquals(9, physicalCovariances.getColumnDimension());
    Assert.assertEquals(0.55431, physicalCovariances.getEntry(6, 6), 1.0e-5);
    Assert.assertEquals(0.22694, physicalCovariances.getEntry(7, 7), 1.0e-5);
    Assert.assertEquals(0.13106, physicalCovariances.getEntry(8, 8), 1.0e-5);
    ByteArrayOutputStream bos = new ByteArrayOutputStream();
    ObjectOutputStream oos = new ObjectOutputStream(bos);
    oos.writeObject(moved.getEstimatedEarthFrame().getTransformProvider());
    Assert.assertTrue(bos.size() > 155000);
    Assert.assertTrue(bos.size() < 160000);
    ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
    ObjectInputStream ois = new ObjectInputStream(bis);
    EstimatedEarthFrameProvider deserialized = (EstimatedEarthFrameProvider) ois.readObject();
    Assert.assertEquals(moved.getPrimeMeridianOffsetDriver().getValue(), deserialized.getPrimeMeridianOffsetDriver().getValue(), 1.0e-15);
    Assert.assertEquals(moved.getPrimeMeridianDriftDriver().getValue(), deserialized.getPrimeMeridianDriftDriver().getValue(), 1.0e-15);
    Assert.assertEquals(moved.getPolarOffsetXDriver().getValue(), deserialized.getPolarOffsetXDriver().getValue(), 1.0e-15);
    Assert.assertEquals(moved.getPolarDriftXDriver().getValue(), deserialized.getPolarDriftXDriver().getValue(), 1.0e-15);
    Assert.assertEquals(moved.getPolarOffsetYDriver().getValue(), deserialized.getPolarOffsetYDriver().getValue(), 1.0e-15);
    Assert.assertEquals(moved.getPolarDriftYDriver().getValue(), deserialized.getPolarDriftYDriver().getValue(), 1.0e-15);
}