Examples with FieldDateDetector org.orekit.propagation.events.FieldDateDetector used on opensource projects

Example 1 with FieldDateDetector

use of org.orekit.propagation.events.FieldDateDetector in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestStopEvent.

private <T extends RealFieldElement<T>> void doTestStopEvent(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    final FieldAbsoluteDate<T> stopDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.STOP);
    propagator.addEventDetector(new FieldDateDetector<>(stopDate).withHandler(checking));
    Assert.assertEquals(1, propagator.getEventsDetectors().size());
    checking.assertEvent(false);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(3200));
    checking.assertEvent(true);
    Assert.assertEquals(0, finalState.getDate().durationFrom(stopDate).getReal(), 1.0e-10);
    propagator.clearEventsDetectors();
    Assert.assertEquals(0, propagator.getEventsDetectors().size());
}

Example 2 with FieldDateDetector

use of org.orekit.propagation.events.FieldDateDetector in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestResetDerivativesEvent.

private <T extends RealFieldElement<T>> void doTestResetDerivativesEvent(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    final FieldAbsoluteDate<T> resetDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.RESET_DERIVATIVES);
    propagator.addEventDetector(new FieldDateDetector<>(resetDate).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    Assert.assertEquals(0.0, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    propagator.setResetAtEnd(true);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(dt));
    Assert.assertEquals(dt, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    checking.assertEvent(true);
    final double n = FastMath.sqrt(initialState.getMu() / initialState.getA().getReal()) / initialState.getA().getReal();
    Assert.assertEquals(initialState.getA().getReal(), finalState.getA().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEx().getReal(), finalState.getEquinoctialEx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEy().getReal(), finalState.getEquinoctialEy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHx().getReal(), finalState.getHx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHy().getReal(), finalState.getHy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getLM().getReal() + n * dt, finalState.getLM().getReal(), 6.0e-10);
}

Example 3 with FieldDateDetector

use of org.orekit.propagation.events.FieldDateDetector in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestResetStateEvent.

private <T extends RealFieldElement<T>> void doTestResetStateEvent(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    final FieldAbsoluteDate<T> resetDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.RESET_STATE) {

        public FieldSpacecraftState<T> resetState(FieldDateDetector<T> detector, FieldSpacecraftState<T> oldState) {
            return new FieldSpacecraftState<>(oldState.getOrbit(), oldState.getAttitude(), oldState.getMass().subtract(200.0));
        }
    };
    propagator.addEventDetector(new FieldDateDetector<>(resetDate).withHandler(checking));
    checking.assertEvent(false);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(3200));
    checking.assertEvent(true);
    Assert.assertEquals(initialState.getMass().getReal() - 200, finalState.getMass().getReal(), 1.0e-10);
}

Example 4 with FieldDateDetector

use of org.orekit.propagation.events.FieldDateDetector in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestContinueEvent.

private <T extends RealFieldElement<T>> void doTestContinueEvent(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    final FieldAbsoluteDate<T> resetDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.CONTINUE);
    propagator.addEventDetector(new FieldDateDetector<>(resetDate).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    Assert.assertEquals(0.0, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    propagator.setResetAtEnd(false);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(dt));
    Assert.assertEquals(0.0, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    checking.assertEvent(true);
    final double n = FastMath.sqrt(initialState.getMu() / initialState.getA().getReal()) / initialState.getA().getReal();
    Assert.assertEquals(initialState.getA().getReal(), finalState.getA().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEx().getReal(), finalState.getEquinoctialEx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEy().getReal(), finalState.getEquinoctialEy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHx().getReal(), finalState.getHx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHy().getReal(), finalState.getHy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getLM().getReal() + n * dt, finalState.getLM().getReal(), 6.0e-10);
}

Example 5 with FieldDateDetector

use of org.orekit.propagation.events.FieldDateDetector in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestShift.

private static <T extends RealFieldElement<T>> void doTestShift(final FieldCartesianOrbit<T> orbit, final OrbitType orbitType, final PositionAngle angleType, final boolean withDerivatives, final double error60s, final double error120s, final double error300s, final double error600s, final double error900s) throws OrekitException {
    T zero = orbit.getDate().getField().getZero();
    Utils.setDataRoot("regular-data:atmosphere:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));
    final FieldNumericalPropagator<T> np = createPropagator(new FieldSpacecraftState<>(orbit), orbitType, angleType);
    // the reference date for shifts is set at 60s, so the propagator can provide derivatives if needed
    // (derivatives are not available in the initial orbit)
    final FieldAbsoluteDate<T> reference = orbit.getDate().shiftedBy(60.0);
    final ShiftChecker<T> checker = new ShiftChecker<>(withDerivatives, orbitType, angleType, error60s, error120s, error300s, error600s, error900s);
    @SuppressWarnings("unchecked") FieldTimeStamped<T>[] dates = (FieldTimeStamped<T>[]) Array.newInstance(FieldTimeStamped.class, 6);
    dates[0] = reference;
    dates[1] = reference.shiftedBy(60.0);
    dates[2] = reference.shiftedBy(120.0);
    dates[3] = reference.shiftedBy(300.0);
    dates[4] = reference.shiftedBy(600.0);
    dates[5] = reference.shiftedBy(900.0);
    np.addEventDetector(new FieldDateDetector<T>(zero.add(30.0), zero.add(1.0e-9), (FieldTimeStamped<T>[]) dates).withHandler(checker));
    np.propagate(reference.shiftedBy(1000.0));
}