@Test
public void testUnsupportedParameter() 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 ThirdBodyAttraction(CelestialBodyFactory.getSun()),
new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
partials.selectParamAndStep("non-existent", 1.0);
try {
partials.computeDerivatives(new SpacecraftState(initialOrbit), new double[6]);
Assert.fail("an exception should have been thrown");
} catch (OrekitException oe) {
Assert.assertEquals(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, oe.getSpecifier());
}
}
@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;
NumericalPropagator propagator =
setUpPropagator(
initialOrbit,
dP,
OrbitType.EQUINOCTIAL,
PositionAngle.TRUE,
new ThirdBodyAttraction(CelestialBodyFactory.getSun()),
new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
partials.setInitialJacobians(
new SpacecraftState(initialOrbit), new double[6][6], new double[6][3]);
partials.selectParameters("Sun attraction coefficient");
try {
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());
}
}
