Examples with OneAxisEllipsoid org.orekit.bodies.OneAxisEllipsoid used on opensource projects

Example 61 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class OrbitDeterminationTest method createBody.

/**
 * Create an orbit from input parameters
 * @param parser input file parser
 * @param mu     central attraction coefficient
 * @throws NoSuchElementException if input parameters are missing
 * @throws OrekitException if body frame cannot be created
 */
private OneAxisEllipsoid createBody(final KeyValueFileParser<ParameterKey> parser) throws NoSuchElementException, OrekitException {
    final Frame bodyFrame;
    if (!parser.containsKey(ParameterKey.BODY_FRAME)) {
        bodyFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    } else {
        bodyFrame = parser.getEarthFrame(ParameterKey.BODY_FRAME);
    }
    final double equatorialRadius;
    if (!parser.containsKey(ParameterKey.BODY_EQUATORIAL_RADIUS)) {
        equatorialRadius = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
    } else {
        equatorialRadius = parser.getDouble(ParameterKey.BODY_EQUATORIAL_RADIUS);
    }
    final double flattening;
    if (!parser.containsKey(ParameterKey.BODY_INVERSE_FLATTENING)) {
        flattening = Constants.WGS84_EARTH_FLATTENING;
    } else {
        flattening = 1.0 / parser.getDouble(ParameterKey.BODY_INVERSE_FLATTENING);
    }
    return new OneAxisEllipsoid(equatorialRadius, flattening, bodyFrame);
}

Example 62 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class GroundStationTest method doTestCartesianDerivatives.

private void doTestCartesianDerivatives(double latitude, double longitude, double altitude, double stepFactor, double relativeTolerancePositionValue, double relativeTolerancePositionDerivative, double relativeToleranceVelocityValue, double relativeToleranceVelocityDerivative, String... parameterPattern) throws OrekitException {
    Utils.setDataRoot("regular-data");
    final Frame eme2000 = FramesFactory.getEME2000();
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    final AbsoluteDate date0 = date.shiftedBy(50000);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GroundStation station = new GroundStation(new TopocentricFrame(earth, new GeodeticPoint(latitude, longitude, altitude), "dummy"));
    final DSFactory factory = new DSFactory(parameterPattern.length, 1);
    final FieldAbsoluteDate<DerivativeStructure> dateDS = new FieldAbsoluteDate<>(factory.getDerivativeField(), date);
    ParameterDriver[] selectedDrivers = new ParameterDriver[parameterPattern.length];
    UnivariateDifferentiableVectorFunction[] dFCartesian = new UnivariateDifferentiableVectorFunction[parameterPattern.length];
    final ParameterDriver[] allDrivers = selectAllDrivers(station);
    for (ParameterDriver driver : allDrivers) {
        driver.setReferenceDate(date0);
    }
    Map<String, Integer> indices = new HashMap<>();
    for (int k = 0; k < dFCartesian.length; ++k) {
        for (int i = 0; i < allDrivers.length; ++i) {
            if (allDrivers[i].getName().matches(parameterPattern[k])) {
                selectedDrivers[k] = allDrivers[i];
                dFCartesian[k] = differentiatedStationPV(station, eme2000, date, selectedDrivers[k], stepFactor);
                indices.put(selectedDrivers[k].getName(), k);
            }
        }
    }
    ;
    DSFactory factory11 = new DSFactory(1, 1);
    RandomGenerator generator = new Well19937a(0x084d58a19c498a54l);
    double maxPositionValueRelativeError = 0;
    double maxPositionDerivativeRelativeError = 0;
    double maxVelocityValueRelativeError = 0;
    double maxVelocityDerivativeRelativeError = 0;
    for (int i = 0; i < 1000; ++i) {
        // randomly change one parameter
        ParameterDriver changed = allDrivers[generator.nextInt(allDrivers.length)];
        changed.setNormalizedValue(2 * generator.nextDouble() - 1);
        // transform to check
        FieldTransform<DerivativeStructure> t = station.getOffsetToInertial(eme2000, dateDS, factory, indices);
        FieldPVCoordinates<DerivativeStructure> pv = t.transformPVCoordinates(FieldPVCoordinates.getZero(factory.getDerivativeField()));
        for (int k = 0; k < dFCartesian.length; ++k) {
            // reference values and derivatives computed using finite differences
            DerivativeStructure[] refCartesian = dFCartesian[k].value(factory11.variable(0, selectedDrivers[k].getValue()));
            // position
            final Vector3D refP = new Vector3D(refCartesian[0].getValue(), refCartesian[1].getValue(), refCartesian[2].getValue());
            final Vector3D resP = new Vector3D(pv.getPosition().getX().getValue(), pv.getPosition().getY().getValue(), pv.getPosition().getZ().getValue());
            maxPositionValueRelativeError = FastMath.max(maxPositionValueRelativeError, Vector3D.distance(refP, resP) / refP.getNorm());
            final Vector3D refPD = new Vector3D(refCartesian[0].getPartialDerivative(1), refCartesian[1].getPartialDerivative(1), refCartesian[2].getPartialDerivative(1));
            final Vector3D resPD = new Vector3D(pv.getPosition().getX().getAllDerivatives()[k + 1], pv.getPosition().getY().getAllDerivatives()[k + 1], pv.getPosition().getZ().getAllDerivatives()[k + 1]);
            maxPositionDerivativeRelativeError = FastMath.max(maxPositionDerivativeRelativeError, Vector3D.distance(refPD, resPD) / refPD.getNorm());
            // velocity
            final Vector3D refV = new Vector3D(refCartesian[3].getValue(), refCartesian[4].getValue(), refCartesian[5].getValue());
            final Vector3D resV = new Vector3D(pv.getVelocity().getX().getValue(), pv.getVelocity().getY().getValue(), pv.getVelocity().getZ().getValue());
            maxVelocityValueRelativeError = FastMath.max(maxVelocityValueRelativeError, Vector3D.distance(refV, resV) / refV.getNorm());
            final Vector3D refVD = new Vector3D(refCartesian[3].getPartialDerivative(1), refCartesian[4].getPartialDerivative(1), refCartesian[5].getPartialDerivative(1));
            final Vector3D resVD = new Vector3D(pv.getVelocity().getX().getAllDerivatives()[k + 1], pv.getVelocity().getY().getAllDerivatives()[k + 1], pv.getVelocity().getZ().getAllDerivatives()[k + 1]);
            maxVelocityDerivativeRelativeError = FastMath.max(maxVelocityDerivativeRelativeError, Vector3D.distance(refVD, resVD) / refVD.getNorm());
        }
    }
    Assert.assertEquals(0.0, maxPositionValueRelativeError, relativeTolerancePositionValue);
    Assert.assertEquals(0.0, maxPositionDerivativeRelativeError, relativeTolerancePositionDerivative);
    Assert.assertEquals(0.0, maxVelocityValueRelativeError, relativeToleranceVelocityValue);
    Assert.assertEquals(0.0, maxVelocityDerivativeRelativeError, relativeToleranceVelocityDerivative);
}

Example 63 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class GroundStationTest method testNoReferenceDate.

@Test
public void testNoReferenceDate() throws OrekitException {
    Utils.setDataRoot("regular-data");
    final Frame eme2000 = FramesFactory.getEME2000();
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GroundStation station = new GroundStation(new TopocentricFrame(earth, new GeodeticPoint(0.1, 0.2, 100), "dummy"));
    try {
        station.getOffsetToInertial(eme2000, date);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NO_REFERENCE_DATE_FOR_PARAMETER, oe.getSpecifier());
        Assert.assertEquals("prime-meridian-offset", (String) oe.getParts()[0]);
    }
    try {
        DSFactory factory = new DSFactory(9, 1);
        Map<String, Integer> indices = new HashMap<>();
        for (final ParameterDriver driver : Arrays.asList(station.getPrimeMeridianOffsetDriver(), station.getPrimeMeridianDriftDriver(), station.getPolarOffsetXDriver(), station.getPolarDriftXDriver(), station.getPolarOffsetYDriver(), station.getPolarDriftYDriver(), station.getEastOffsetDriver(), station.getNorthOffsetDriver(), station.getZenithOffsetDriver())) {
            indices.put(driver.getName(), indices.size());
        }
        station.getOffsetToInertial(eme2000, new FieldAbsoluteDate<>(factory.getDerivativeField(), date), factory, indices);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NO_REFERENCE_DATE_FOR_PARAMETER, oe.getSpecifier());
        Assert.assertEquals("prime-meridian-offset", (String) oe.getParts()[0]);
    }
}

Example 64 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class GroundStationTest method doTestAngularDerivatives.

private void doTestAngularDerivatives(double latitude, double longitude, double altitude, double stepFactor, double toleranceRotationValue, double toleranceRotationDerivative, double toleranceRotationRateValue, double toleranceRotationRateDerivative, String... parameterPattern) throws OrekitException {
    Utils.setDataRoot("regular-data");
    final Frame eme2000 = FramesFactory.getEME2000();
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    final AbsoluteDate date0 = date.shiftedBy(50000);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final GroundStation station = new GroundStation(new TopocentricFrame(earth, new GeodeticPoint(latitude, longitude, altitude), "dummy"));
    final DSFactory factory = new DSFactory(parameterPattern.length, 1);
    final FieldAbsoluteDate<DerivativeStructure> dateDS = new FieldAbsoluteDate<>(factory.getDerivativeField(), date);
    ParameterDriver[] selectedDrivers = new ParameterDriver[parameterPattern.length];
    UnivariateDifferentiableVectorFunction[] dFAngular = new UnivariateDifferentiableVectorFunction[parameterPattern.length];
    final ParameterDriver[] allDrivers = selectAllDrivers(station);
    for (ParameterDriver driver : allDrivers) {
        driver.setReferenceDate(date0);
    }
    Map<String, Integer> indices = new HashMap<>();
    for (int k = 0; k < dFAngular.length; ++k) {
        for (int i = 0; i < allDrivers.length; ++i) {
            if (allDrivers[i].getName().matches(parameterPattern[k])) {
                selectedDrivers[k] = allDrivers[i];
                dFAngular[k] = differentiatedTransformAngular(station, eme2000, date, selectedDrivers[k], stepFactor);
                indices.put(selectedDrivers[k].getName(), k);
            }
        }
    }
    ;
    DSFactory factory11 = new DSFactory(1, 1);
    RandomGenerator generator = new Well19937a(0xa01a1d8fe5d80af7l);
    double maxRotationValueError = 0;
    double maxRotationDerivativeError = 0;
    double maxRotationRateValueError = 0;
    double maxRotationRateDerivativeError = 0;
    for (int i = 0; i < 1000; ++i) {
        // randomly change one parameter
        ParameterDriver changed = allDrivers[generator.nextInt(allDrivers.length)];
        changed.setNormalizedValue(2 * generator.nextDouble() - 1);
        // transform to check
        FieldTransform<DerivativeStructure> t = station.getOffsetToInertial(eme2000, dateDS, factory, indices);
        for (int k = 0; k < dFAngular.length; ++k) {
            // reference values and derivatives computed using finite differences
            DerivativeStructure[] refAngular = dFAngular[k].value(factory11.variable(0, selectedDrivers[k].getValue()));
            // rotation
            final Rotation refQ = new Rotation(refAngular[0].getValue(), refAngular[1].getValue(), refAngular[2].getValue(), refAngular[3].getValue(), true);
            final Rotation resQ = t.getRotation().toRotation();
            maxRotationValueError = FastMath.max(maxRotationValueError, Rotation.distance(refQ, resQ));
            double sign = FastMath.copySign(1.0, refAngular[0].getValue() * t.getRotation().getQ0().getValue() + refAngular[1].getValue() * t.getRotation().getQ1().getValue() + refAngular[2].getValue() * t.getRotation().getQ2().getValue() + refAngular[3].getValue() * t.getRotation().getQ3().getValue());
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[0].getPartialDerivative(1) - t.getRotation().getQ0().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[1].getPartialDerivative(1) - t.getRotation().getQ1().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[2].getPartialDerivative(1) - t.getRotation().getQ2().getAllDerivatives()[k + 1]));
            maxRotationDerivativeError = FastMath.max(maxRotationDerivativeError, FastMath.abs(sign * refAngular[3].getPartialDerivative(1) - t.getRotation().getQ3().getAllDerivatives()[k + 1]));
            // rotation rate
            final Vector3D refRate = new Vector3D(refAngular[4].getValue(), refAngular[5].getValue(), refAngular[6].getValue());
            final Vector3D resRate = t.getRotationRate().toVector3D();
            final Vector3D refRateD = new Vector3D(refAngular[4].getPartialDerivative(1), refAngular[5].getPartialDerivative(1), refAngular[6].getPartialDerivative(1));
            final Vector3D resRateD = new Vector3D(t.getRotationRate().getX().getAllDerivatives()[k + 1], t.getRotationRate().getY().getAllDerivatives()[k + 1], t.getRotationRate().getZ().getAllDerivatives()[k + 1]);
            maxRotationRateValueError = FastMath.max(maxRotationRateValueError, Vector3D.distance(refRate, resRate));
            maxRotationRateDerivativeError = FastMath.max(maxRotationRateDerivativeError, Vector3D.distance(refRateD, resRateD));
        }
    }
    Assert.assertEquals(0.0, maxRotationValueError, toleranceRotationValue);
    Assert.assertEquals(0.0, maxRotationDerivativeError, toleranceRotationDerivative);
    Assert.assertEquals(0.0, maxRotationRateValueError, toleranceRotationRateValue);
    Assert.assertEquals(0.0, maxRotationRateDerivativeError, toleranceRotationRateDerivative);
}

Example 65 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class SolarRadiationPressureTest method RealFieldIsotropicTest.

/**
 *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 RealFieldIsotropicTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 5);
    DerivativeStructure a_0 = factory.variable(0, 7e7);
    DerivativeStructure e_0 = factory.variable(1, 0.4);
    DerivativeStructure i_0 = factory.variable(2, 85 * FastMath.PI / 180);
    DerivativeStructure R_0 = factory.variable(3, 0.7);
    DerivativeStructure O_0 = factory.variable(4, 0.5);
    DerivativeStructure n_0 = factory.variable(5, 0.1);
    Field<DerivativeStructure> field = a_0.getField();
    DerivativeStructure zero = field.getZero();
    FieldAbsoluteDate<DerivativeStructure> J2000 = FieldAbsoluteDate.getJ2000Epoch(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();
    final OrbitType type = OrbitType.KEPLERIAN;
    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);
    PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
    // creation of the force model
    OneAxisEllipsoid earth = new OneAxisEllipsoid(6378136.46, 1.0 / 298.25765, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    SolarRadiationPressure forceModel = new SolarRadiationPressure(sun, earth.getEquatorialRadius(), new IsotropicRadiationCNES95Convention(500.0, 0.7, 0.7));
    FNP.addForceModel(forceModel);
    NP.addForceModel(forceModel);
    FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1000.);
    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(0, Vector3D.distance(finPVC_DS.toPVCoordinates().getPosition(), finPVC_R.getPosition()), 4.0e-9);
    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[] { 1e3, 0.01, 0.01, 0.01, 0.01, 0.01 }, 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]);
        // System.out.println(pos_DS.getX().getPartialDerivative(1));
        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()) * 4e-9);
        Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 5e-9);
        Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 6e-10);
        // 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) * 5e-11);
        Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 3e-10);
        Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 5e-11);
        // 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) * 2e-10);
        Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 4e-10);
        Assert.assertEquals(az_DS, az, FastMath.abs(az) * 7e-10);
    }
}