Examples with FieldCircularOrbit org.orekit.orbits.FieldCircularOrbit used on opensource projects

Example 1 with FieldCircularOrbit

use of org.orekit.orbits.FieldCircularOrbit in project Orekit by CS-SI.

the class FieldKeplerianPropagatorTest method doTestIssue107.

private <T extends RealFieldElement<T>> void doTestIssue107(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<T>(orbit) {

        FieldAbsoluteDate<T> lastDate = FieldAbsoluteDate.getPastInfinity(field);

        protected FieldSpacecraftState<T> basicPropagate(final FieldAbsoluteDate<T> date) throws OrekitException {
            if (date.compareTo(lastDate) < 0) {
                throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "no backward propagation allowed");
            }
            lastDate = date;
            return super.basicPropagate(date);
        }
    };
    FieldSpacecraftState<T> finalState = propagator.propagate(date.shiftedBy(3600.0));
    Assert.assertEquals(3600.0, finalState.getDate().durationFrom(date).getReal(), 1.0e-15);
}

Example 2 with FieldCircularOrbit

use of org.orekit.orbits.FieldCircularOrbit in project Orekit by CS-SI.

the class FieldEventDetectorTest method doTestIssue108Numerical.

private <T extends RealFieldElement<T>> void doTestIssue108Numerical(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    final T step = zero.add(60.0);
    final int n = 100;
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, new ClassicalRungeKuttaFieldIntegrator<>(field, step));
    propagator.setOrbitType(OrbitType.EQUINOCTIAL);
    propagator.resetInitialState(new FieldSpacecraftState<>(orbit));
    GCallsCounter<T> counter = new GCallsCounter<>(zero.add(100000.0), zero.add(1.0e-6), 20, new FieldStopOnEvent<GCallsCounter<T>, T>());
    propagator.addEventDetector(counter);
    propagator.propagate(date.shiftedBy(step.multiply(n)));
    Assert.assertEquals(n + 1, counter.getCount());
}

Example 3 with FieldCircularOrbit

use of org.orekit.orbits.FieldCircularOrbit in project Orekit by CS-SI.

the class BodyCenterPointingTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final double ehMu = 3.9860047e14;
    final double ae = 6.378137e6;
    final double c20 = -1.08263e-3;
    final double c30 = 2.54e-6;
    final double c40 = 1.62e-6;
    final double c50 = 2.3e-7;
    final double c60 = -5.5e-7;
    // Satellite position as circular parameters
    final T zero = field.getZero();
    final T a = zero.add(7178000.0);
    final T e = zero.add(7e-5);
    final T i = zero.add(FastMath.toRadians(50.));
    final T pa = zero.add(FastMath.toRadians(45.));
    final T raan = zero.add(FastMath.toRadians(270.));
    final T m = zero.add(FastMath.toRadians(5.3 - 270));
    // Computation date
    FieldAbsoluteDate<T> date_R = new FieldAbsoluteDate<>(field, new DateComponents(2008, 04, 07), TimeComponents.H00, TimeScalesFactory.getUTC());
    // Orbit
    FieldKeplerianOrbit<T> circ = new FieldKeplerianOrbit<>(a, e, i, pa, raan, m, PositionAngle.MEAN, FramesFactory.getEME2000(), date_R, ehMu);
    // WGS84 Earth model
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    // Earth center pointing attitude provider
    BodyCenterPointing earthCenterAttitudeLaw = new BodyCenterPointing(circ.getFrame(), earth);
    final FieldAbsoluteDate<T> date = FieldAbsoluteDate.getJ2000Epoch(field).shiftedBy(584.);
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(3220103.), zero.add(69623.), zero.add(6449822.));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(6414.7), zero.add(-2006.), zero.add(-3180.));
    final FieldCircularOrbit<T> initialOrbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, ehMu);
    FieldEcksteinHechlerPropagator<T> propagator = new FieldEcksteinHechlerPropagator<>(initialOrbit, ae, ehMu, c20, c30, c40, c50, c60);
    propagator.setAttitudeProvider(earthCenterAttitudeLaw);
    double h = 0.01;
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(-h));
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    T errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(zero.add(h)).getAttitude().getRotation(), s0.getAttitude().getRotation());
    T evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAngleMinus.getReal(), 1.0e-6 * evolutionAngleMinus.getReal());
    T errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(zero.add(-h)).getAttitude().getRotation());
    T evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAnglePlus.getReal(), 1.0e-6 * evolutionAnglePlus.getReal());
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), 2 * h);
    Assert.assertTrue(spin0.getNorm().getReal() > 1.0e-3);
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-13);
}

Example 4 with FieldCircularOrbit

use of org.orekit.orbits.FieldCircularOrbit in project Orekit by CS-SI.

the class FieldEventDetectorTest method doTestIssue108Analytical.

private <T extends RealFieldElement<T>> void doTestIssue108Analytical(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    final T step = zero.add(60.0);
    final int n = 100;
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit);
    GCallsCounter<T> counter = new GCallsCounter<>(zero.add(100000.0), zero.add(1.0e-6), 20, new FieldStopOnEvent<GCallsCounter<T>, T>());
    propagator.addEventDetector(counter);
    propagator.setMasterMode(step, new FieldOrekitFixedStepHandler<T>() {

        public void handleStep(FieldSpacecraftState<T> currentState, boolean isLast) {
        }
    });
    propagator.propagate(date.shiftedBy(step.multiply(n)));
    Assert.assertEquals(n + 1, counter.getCount());
}

Example 5 with FieldCircularOrbit

use of org.orekit.orbits.FieldCircularOrbit in project Orekit by CS-SI.

the class FieldEventDetectorTest method doTestBasicScheduling.

private <T extends RealFieldElement<T>> void doTestBasicScheduling(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit);
    T stepSize = zero.add(60.0);
    OutOfOrderChecker<T> checker = new OutOfOrderChecker<>(stepSize);
    propagator.addEventDetector(new FieldDateDetector<>(date.shiftedBy(stepSize.multiply(5.25))).withHandler(checker));
    propagator.setMasterMode(stepSize, checker);
    propagator.propagate(date.shiftedBy(stepSize.multiply(10)));
    Assert.assertTrue(checker.outOfOrderCallDetected());
}