Examples with TimeScale org.orekit.time.TimeScale used on opensource projects

Example 11 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestEphemerisDatesBackward.

private <T extends RealFieldElement<T>> void doTestEphemerisDatesBackward(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    TimeScale tai = TimeScalesFactory.getTAI();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, "2015-07-05", tai);
    FieldAbsoluteDate<T> startDate = new FieldAbsoluteDate<>(field, "2015-07-03", tai).shiftedBy(-0.1);
    FieldAbsoluteDate<T> endDate = new FieldAbsoluteDate<>(field, "2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS), zero, zero, zero, zero, zero, PositionAngle.TRUE, eci, initialDate, mu);
    OrbitType type = OrbitType.CARTESIAN;
    double[][] tol = NumericalPropagator.tolerances(1e-3, orbit.toOrbit(), type);
    FieldNumericalPropagator<T> prop = new FieldNumericalPropagator<>(field, new DormandPrince853FieldIntegrator<>(field, 0.1, 500, tol[0], tol[1]));
    prop.setOrbitType(type);
    prop.resetInitialState(new FieldSpacecraftState<>(new FieldCartesianOrbit<>(orbit)));
    // action
    prop.setEphemerisMode();
    prop.propagate(endDate, startDate);
    FieldBoundedPropagator<T> ephemeris = prop.getGeneratedEphemeris();
    // verify
    TimeStampedFieldPVCoordinates<T> actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedFieldPVCoordinates<T> expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getPosition().toVector3D(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getVelocity().toVector3D(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate).getReal(), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate).getReal(), OrekitMatchers.closeTo(0, 0));
    // test date
    FieldAbsoluteDate<T> date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date).getReal(), 0, 0);
}

Example 12 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestEphemerisDates.

private <T extends RealFieldElement<T>> void doTestEphemerisDates(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    TimeScale tai = TimeScalesFactory.getTAI();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, "2015-07-01", tai);
    FieldAbsoluteDate<T> startDate = new FieldAbsoluteDate<>(field, "2015-07-03", tai).shiftedBy(-0.1);
    FieldAbsoluteDate<T> endDate = new FieldAbsoluteDate<>(field, "2015-07-04", tai);
    Frame eci = FramesFactory.getGCRF();
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(600e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS), zero, zero, zero, zero, zero, PositionAngle.TRUE, eci, initialDate, mu);
    OrbitType type = OrbitType.CARTESIAN;
    double[][] tol = NumericalPropagator.tolerances(1e-3, orbit.toOrbit(), type);
    FieldNumericalPropagator<T> prop = new FieldNumericalPropagator<>(field, new DormandPrince853FieldIntegrator<>(field, 0.1, 500, tol[0], tol[1]));
    prop.setOrbitType(type);
    prop.resetInitialState(new FieldSpacecraftState<>(new FieldCartesianOrbit<>(orbit)));
    // action
    prop.setEphemerisMode();
    prop.propagate(startDate, endDate);
    FieldBoundedPropagator<T> ephemeris = prop.getGeneratedEphemeris();
    // verify
    TimeStampedFieldPVCoordinates<T> actualPV = ephemeris.getPVCoordinates(startDate, eci);
    TimeStampedFieldPVCoordinates<T> expectedPV = orbit.getPVCoordinates(startDate, eci);
    MatcherAssert.assertThat(actualPV.getPosition().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getPosition().toVector3D(), 1.0));
    MatcherAssert.assertThat(actualPV.getVelocity().toVector3D(), OrekitMatchers.vectorCloseTo(expectedPV.getVelocity().toVector3D(), 1.0));
    MatcherAssert.assertThat(ephemeris.getMinDate().durationFrom(startDate).getReal(), OrekitMatchers.closeTo(0, 0));
    MatcherAssert.assertThat(ephemeris.getMaxDate().durationFrom(endDate).getReal(), OrekitMatchers.closeTo(0, 0));
    // test date
    FieldAbsoluteDate<T> date = endDate.shiftedBy(-0.11);
    Assert.assertEquals(ephemeris.propagate(date).getDate().durationFrom(date).getReal(), 0, 0);
}

Example 13 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class NumericalPropagatorTest 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, mu);
    OrbitType type = OrbitType.CARTESIAN;
    double[][] tol = NumericalPropagator.tolerances(1e-3, orbit, type);
    NumericalPropagator prop = new NumericalPropagator(new DormandPrince853Integrator(0.1, 500, tol[0], tol[1]));
    prop.setOrbitType(type);
    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 TimeScale

use of org.orekit.time.TimeScale 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 15 with TimeScale

use of org.orekit.time.TimeScale 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);
}