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

Example 26 with KeplerianOrbit

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

the class PartialDerivativesTest method testWrongParametersDimension.

@Test
public void testWrongParametersDimension() throws OrekitException {
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    double dP = 0.001;
    ForceModel sunAttraction = new ThirdBodyAttraction(CelestialBodyFactory.getSun());
    sunAttraction.getParameterDriver("Sun attraction coefficient").setSelected(true);
    ForceModel moonAttraction = new ThirdBodyAttraction(CelestialBodyFactory.getMoon());
    NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE, sunAttraction, moonAttraction);
    PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
    try {
        partials.setInitialJacobians(new SpacecraftState(initialOrbit), new double[6][6], new double[6][3]);
        partials.computeDerivatives(new SpacecraftState(initialOrbit), new double[6]);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH, oe.getSpecifier());
    }
}

Example 27 with KeplerianOrbit

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

the class PartialDerivativesTest method testTooLargeDimension.

@Test(expected = OrekitException.class)
public void testTooLargeDimension() throws OrekitException {
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    double dP = 0.001;
    NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE);
    PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
    partials.setInitialJacobians(new SpacecraftState(initialOrbit), new double[8][6], new double[6][2]);
}

Example 28 with KeplerianOrbit

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

the class PartialDerivativesTest method testNotInitialized.

@Test(expected = OrekitException.class)
public void testNotInitialized() throws OrekitException {
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    double dP = 0.001;
    NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE);
    new PartialDerivativesEquations("partials", propagator).getMapper();
}

Example 29 with KeplerianOrbit

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

the class PartialDerivativesTest method testTooSmallDimension.

@Test(expected = OrekitException.class)
public void testTooSmallDimension() throws OrekitException {
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, Constants.EIGEN5C_EARTH_MU);
    double dP = 0.001;
    NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE);
    PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
    partials.setInitialJacobians(new SpacecraftState(initialOrbit), new double[5][6], new double[6][2]);
}

Example 30 with KeplerianOrbit

use of org.orekit.orbits.KeplerianOrbit 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);
}