Exemplo n.º 1
0
 @Test
 public void testIssue157() throws OrekitException {
   try {
     Orbit orbit =
         new KeplerianOrbit(
             13378000,
             0.05,
             0,
             0,
             FastMath.PI,
             0,
             PositionAngle.MEAN,
             FramesFactory.getTOD(false),
             new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()),
             Constants.EIGEN5C_EARTH_MU);
     NumericalPropagator.tolerances(1.0, orbit, OrbitType.KEPLERIAN);
     Assert.fail("an exception should have been thrown");
   } catch (PropagationException pe) {
     Assert.assertEquals(OrekitMessages.SINGULAR_JACOBIAN_FOR_ORBIT_TYPE, pe.getSpecifier());
   }
 }
Exemplo n.º 2
0
  @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 (PropagationException 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 (PropagationException 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());
    }
  }