Examples with AdditionalEquations org.orekit.propagation.integration.AdditionalEquations used on opensource projects

Example 1 with AdditionalEquations

use of org.orekit.propagation.integration.AdditionalEquations in project Orekit by CS-SI.

the class NumericalPropagatorTest method testResetAdditionalStateEvent.

@Test
public void testResetAdditionalStateEvent() throws OrekitException {
    propagator.addAdditionalEquations(new AdditionalEquations() {

        public String getName() {
            return "linear";
        }

        public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
            pDot[0] = 1.0;
            return null;
        }
    });
    propagator.setInitialState(propagator.getInitialState().addAdditionalState("linear", 1.5));
    CheckingHandler<AdditionalStateLinearDetector> checking = new CheckingHandler<AdditionalStateLinearDetector>(Action.RESET_STATE) {

        public SpacecraftState resetState(AdditionalStateLinearDetector detector, SpacecraftState oldState) throws OrekitException {
            return oldState.addAdditionalState("linear", oldState.getAdditionalState("linear")[0] * 2);
        }
    };
    propagator.addEventDetector(new AdditionalStateLinearDetector(10.0, 1.0e-8).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    final SpacecraftState finalState = propagator.propagate(initDate.shiftedBy(dt));
    checking.assertEvent(true);
    Assert.assertEquals(dt + 4.5, finalState.getAdditionalState("linear")[0], 1.0e-8);
    Assert.assertEquals(dt, finalState.getDate().durationFrom(initDate), 1.0e-8);
}

Example 2 with AdditionalEquations

use of org.orekit.propagation.integration.AdditionalEquations in project Orekit by CS-SI.

the class NumericalPropagatorTest method testAdditionalStateEvent.

@Test
public void testAdditionalStateEvent() throws OrekitException {
    propagator.addAdditionalEquations(new AdditionalEquations() {

        public String getName() {
            return "linear";
        }

        public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
            pDot[0] = 1.0;
            return new double[7];
        }
    });
    try {
        propagator.addAdditionalEquations(new AdditionalEquations() {

            public String getName() {
                return "linear";
            }

            public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
                pDot[0] = 1.0;
                return new double[7];
            }
        });
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE);
    }
    try {
        propagator.addAdditionalStateProvider(new AdditionalStateProvider() {

            public String getName() {
                return "linear";
            }

            public double[] getAdditionalState(SpacecraftState state) {
                return null;
            }
        });
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.ADDITIONAL_STATE_NAME_ALREADY_IN_USE);
    }
    propagator.addAdditionalStateProvider(new AdditionalStateProvider() {

        public String getName() {
            return "constant";
        }

        public double[] getAdditionalState(SpacecraftState state) {
            return new double[] { 1.0 };
        }
    });
    Assert.assertTrue(propagator.isAdditionalStateManaged("linear"));
    Assert.assertTrue(propagator.isAdditionalStateManaged("constant"));
    Assert.assertFalse(propagator.isAdditionalStateManaged("non-managed"));
    Assert.assertEquals(2, propagator.getManagedAdditionalStates().length);
    propagator.setInitialState(propagator.getInitialState().addAdditionalState("linear", 1.5));
    CheckingHandler<AdditionalStateLinearDetector> checking = new CheckingHandler<AdditionalStateLinearDetector>(Action.STOP);
    propagator.addEventDetector(new AdditionalStateLinearDetector(10.0, 1.0e-8).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    final SpacecraftState finalState = propagator.propagate(initDate.shiftedBy(dt));
    checking.assertEvent(true);
    Assert.assertEquals(3.0, finalState.getAdditionalState("linear")[0], 1.0e-8);
    Assert.assertEquals(1.5, finalState.getDate().durationFrom(initDate), 1.0e-8);
}

Example 3 with AdditionalEquations

use of org.orekit.propagation.integration.AdditionalEquations in project Orekit by CS-SI.

the class NumericalPropagatorTest method testEphemerisAdditionalState.

@Test
public void testEphemerisAdditionalState() throws OrekitException, IOException {
    // Propagation of the initial at t + dt
    final double dt = -3200;
    final double rate = 2.0;
    propagator.addAdditionalStateProvider(new AdditionalStateProvider() {

        public String getName() {
            return "squaredA";
        }

        public double[] getAdditionalState(SpacecraftState state) {
            return new double[] { state.getA() * state.getA() };
        }
    });
    propagator.addAdditionalEquations(new AdditionalEquations() {

        public String getName() {
            return "extra";
        }

        public double[] computeDerivatives(SpacecraftState s, double[] pDot) {
            pDot[0] = rate;
            return null;
        }
    });
    propagator.setInitialState(propagator.getInitialState().addAdditionalState("extra", 1.5));
    propagator.setOrbitType(OrbitType.CARTESIAN);
    propagator.setEphemerisMode();
    propagator.propagate(initDate.shiftedBy(dt));
    final BoundedPropagator ephemeris1 = propagator.getGeneratedEphemeris();
    Assert.assertEquals(initDate.shiftedBy(dt), ephemeris1.getMinDate());
    Assert.assertEquals(initDate, ephemeris1.getMaxDate());
    try {
        ephemeris1.propagate(ephemeris1.getMinDate().shiftedBy(-10.0));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException pe) {
        Assert.assertEquals(OrekitMessages.OUT_OF_RANGE_EPHEMERIDES_DATE, pe.getSpecifier());
    }
    try {
        ephemeris1.propagate(ephemeris1.getMaxDate().shiftedBy(+10.0));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException pe) {
        Assert.assertEquals(OrekitMessages.OUT_OF_RANGE_EPHEMERIDES_DATE, pe.getSpecifier());
    }
    double shift = -60;
    SpacecraftState s = ephemeris1.propagate(initDate.shiftedBy(shift));
    Assert.assertEquals(2, s.getAdditionalStates().size());
    Assert.assertTrue(s.hasAdditionalState("squaredA"));
    Assert.assertTrue(s.hasAdditionalState("extra"));
    Assert.assertEquals(s.getA() * s.getA(), s.getAdditionalState("squaredA")[0], 1.0e-10);
    Assert.assertEquals(1.5 + shift * rate, s.getAdditionalState("extra")[0], 1.0e-10);
    try {
        ephemeris1.resetInitialState(s);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.NON_RESETABLE_STATE, oe.getSpecifier());
    }
}