Examples with Vector3D org.hipparchus.geometry.euclidean.threed.Vector3D used on opensource projects

Example 21 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testEcksteinHechlerReference.

// test the difference with the analytical extrapolator Eckstein Hechler
@Test
public void testEcksteinHechlerReference() throws OrekitException {
    // Definition of initial conditions with position and velocity
    AbsoluteDate date = AbsoluteDate.J2000_EPOCH.shiftedBy(584.);
    Vector3D position = new Vector3D(3220103., 69623., 6449822.);
    Vector3D velocity = new Vector3D(6414.7, -2006., -3180.);
    Transform itrfToEME2000 = itrf.getTransformTo(FramesFactory.getEME2000(), date);
    Vector3D pole = itrfToEME2000.transformVector(Vector3D.PLUS_K);
    Frame poleAligned = new Frame(FramesFactory.getEME2000(), new Transform(date, new Rotation(pole, Vector3D.PLUS_K)), "pole aligned", true);
    Orbit initialOrbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), poleAligned, date, mu);
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(itrf, GravityFieldFactory.getNormalizedProvider(ae, mu, TideSystem.UNKNOWN, new double[][] { { 0.0 }, { 0.0 }, { normalizedC20 }, { normalizedC30 }, { normalizedC40 }, { normalizedC50 }, { normalizedC60 } }, new double[][] { { 0.0 }, { 0.0 }, { 0.0 }, { 0.0 }, { 0.0 }, { 0.0 }, { 0.0 } })));
    // let the step handler perform the test
    propagator.setInitialState(new SpacecraftState(initialOrbit));
    propagator.setMasterMode(20, new EckStepHandler(initialOrbit, ae, unnormalizedC20, unnormalizedC30, unnormalizedC40, unnormalizedC50, unnormalizedC60));
    propagator.propagate(date.shiftedBy(50000));
    Assert.assertTrue(propagator.getCalls() < 1100);
}

Example 22 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testHelioSynchronous.

// rough test to determine if J2 alone creates heliosynchronism
@Test
public void testHelioSynchronous() throws OrekitException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 07, 01), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    Transform itrfToEME2000 = itrf.getTransformTo(FramesFactory.getEME2000(), date);
    Vector3D pole = itrfToEME2000.transformVector(Vector3D.PLUS_K);
    Frame poleAligned = new Frame(FramesFactory.getEME2000(), new Transform(date, new Rotation(pole, Vector3D.PLUS_K)), "pole aligned", true);
    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, poleAligned, date, mu);
    double[][] c = new double[3][1];
    c[0][0] = 0.0;
    c[2][0] = normalizedC20;
    double[][] s = new double[3][1];
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(itrf, GravityFieldFactory.getNormalizedProvider(6378136.460, mu, TideSystem.UNKNOWN, c, s)));
    // let the step handler perform the test
    propagator.setMasterMode(Constants.JULIAN_DAY, new SpotStepHandler(date, mu));
    propagator.setInitialState(new SpacecraftState(orbit));
    propagator.propagate(date.shiftedBy(7 * Constants.JULIAN_DAY));
    Assert.assertTrue(propagator.getCalls() < 9200);
}

Example 23 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testGradient.

@Test
public void testGradient() throws OrekitException {
    int max = 50;
    NormalizedSphericalHarmonicsProvider provider = new GleasonProvider(max, max);
    HolmesFeatherstoneAttractionModel model = new HolmesFeatherstoneAttractionModel(itrf, provider);
    double r = 1.25;
    for (double lambda = 0; lambda < 2 * FastMath.PI; lambda += 0.5) {
        for (double theta = 0.05; theta < 3.11; theta += 0.03) {
            Vector3D position = new Vector3D(r * FastMath.sin(theta) * FastMath.cos(lambda), r * FastMath.sin(theta) * FastMath.sin(lambda), r * FastMath.cos(theta));
            double[] refGradient = gradient(model, null, position, 1.0e-3);
            double norm = FastMath.sqrt(refGradient[0] * refGradient[0] + refGradient[1] * refGradient[1] + refGradient[2] * refGradient[2]);
            double[] gradient = model.gradient(null, position, model.getMu());
            double errorX = refGradient[0] - gradient[0];
            double errorY = refGradient[1] - gradient[1];
            double errorZ = refGradient[2] - gradient[2];
            double relativeError = FastMath.sqrt(errorX * errorX + errorY * errorY + errorZ * errorZ) / norm;
            Assert.assertEquals(0, relativeError, 3.0e-12);
        }
    }
}

Example 24 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testIssue97.

@Test
@Deprecated
public void testIssue97() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));
    // pos-vel (from a ZOOM ephemeris reference)
    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(2005, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()), GravityFieldFactory.getUnnormalizedProvider(1, 1).getMu()));
    for (int i = 2; i <= 69; i++) {
        final ForceModel holmesFeatherstoneModel = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(i, i));
        final ForceModel cunninghamModel = new CunninghamAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getUnnormalizedProvider(i, i));
        double relativeError = accelerationRelativeError(holmesFeatherstoneModel, cunninghamModel, state);
        Assert.assertEquals(0.0, relativeError, 8.0e-15);
    }
}

Example 25 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HolmesFeatherstoneAttractionModelTest method testTimeDependentField.

@Test
public void testTimeDependentField() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("eigen-6s-truncated", true));
    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 spacecraftState = new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel), FramesFactory.getGCRF(), new AbsoluteDate(2005, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()), GravityFieldFactory.getUnnormalizedProvider(1, 1).getMu()));
    double dP = 0.1;
    double duration = 3 * Constants.JULIAN_DAY;
    BoundedPropagator fixedFieldEphemeris = createEphemeris(dP, spacecraftState, duration, GravityFieldFactory.getConstantNormalizedProvider(8, 8));
    BoundedPropagator varyingFieldEphemeris = createEphemeris(dP, spacecraftState, duration, GravityFieldFactory.getNormalizedProvider(8, 8));
    double step = 60.0;
    double maxDeltaT = 0;
    double maxDeltaN = 0;
    double maxDeltaW = 0;
    for (AbsoluteDate date = fixedFieldEphemeris.getMinDate(); date.compareTo(fixedFieldEphemeris.getMaxDate()) < 0; date = date.shiftedBy(step)) {
        PVCoordinates pvFixedField = fixedFieldEphemeris.getPVCoordinates(date, FramesFactory.getGCRF());
        PVCoordinates pvVaryingField = varyingFieldEphemeris.getPVCoordinates(date, FramesFactory.getGCRF());
        Vector3D t = pvFixedField.getVelocity().normalize();
        Vector3D w = pvFixedField.getMomentum().normalize();
        Vector3D n = Vector3D.crossProduct(w, t);
        Vector3D delta = pvVaryingField.getPosition().subtract(pvFixedField.getPosition());
        maxDeltaT = FastMath.max(maxDeltaT, FastMath.abs(Vector3D.dotProduct(delta, t)));
        maxDeltaN = FastMath.max(maxDeltaN, FastMath.abs(Vector3D.dotProduct(delta, n)));
        maxDeltaW = FastMath.max(maxDeltaW, FastMath.abs(Vector3D.dotProduct(delta, w)));
    }
    Assert.assertTrue(maxDeltaT > 0.15);
    Assert.assertTrue(maxDeltaT < 0.25);
    Assert.assertTrue(maxDeltaN > 0.01);
    Assert.assertTrue(maxDeltaN < 0.02);
    Assert.assertTrue(maxDeltaW > 0.05);
    Assert.assertTrue(maxDeltaW < 0.10);
}