@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());
}
}
@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());
}
}
