@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());
}
}
public static void clearFactories() {
OrekitUtils.clearFactoryMaps(CelestialBodyFactory.class);
CelestialBodyFactory.clearCelestialBodyLoaders();
OrekitUtils.clearFactoryMaps(FramesFactory.class);
OrekitUtils.clearFactoryMaps(TimeScalesFactory.class);
OrekitUtils.clearFactory(TimeScalesFactory.class, TimeScale.class);
OrekitUtils.clearFactoryMaps(JacobiPolynomials.class);
OrekitUtils.clearFactoryMaps(NewcombOperators.class);
for (final Class<?> c : NewcombOperators.class.getDeclaredClasses()) {
if (c.getName().endsWith("PolynomialsGenerator")) {
OrekitUtils.clearFactoryMaps(c);
}
}
// FramesFactory.setEOPContinuityThreshold(5 * Constants.JULIAN_DAY);
// TimeScalesFactory.clearUTCTAILoaders();
OrekitUtils.clearJPLEphemeridesConstants();
GravityFieldFactory.clearPotentialCoefficientsReaders();
GravityFieldFactory.clearOceanTidesReaders();
DataProvidersManager.getInstance().clearProviders();
DataProvidersManager.getInstance().clearLoadedDataNames();
}
@Test
public void testWithOriginalTestsCases() throws OrekitException, ParseException {
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
OneAxisEllipsoid earth = new OneAxisEllipsoid(6378136.460, 1.0 / 298.257222101, itrf);
SolarInputs97to05 in = SolarInputs97to05.getInstance();
earth.setAngularThreshold(1e-10);
DTM2000 atm = new DTM2000(in, sun, earth);
double roTestCase;
double tzTestCase;
double tinfTestCase;
double myRo;
// Inputs :
// alt=800.
// lat=40.
// day=185.
// hl=16.
// xlon=0.
// fm(1)=150.
// f(1) =fm(1)
// fm(2)=0.
// f(2)=0.
// akp(1)=0.
// akp(2)=0.
// akp(3)=0.
// akp(4)=0.
// Outputs :
roTestCase = 1.8710001353820e-17 * 1000;
tzTestCase = 1165.4839828984;
tinfTestCase = 1165.4919505608;
// Computation and results
myRo =
atm.getDensity(
185, 800 * 1000, 0, FastMath.toRadians(40), 16 * FastMath.PI / 12, 150, 150, 0, 0);
Assert.assertEquals(0, (roTestCase - myRo) / roTestCase, 1e-14);
Assert.assertEquals(0, (tzTestCase - atm.getT()) / tzTestCase, 1e-13);
Assert.assertEquals(0, (tinfTestCase - atm.getTinf()) / tinfTestCase, 1e-13);
// IDEM., day=275
roTestCase = 2.8524195214905e-17 * 1000;
tzTestCase = 1157.1872001392;
tinfTestCase = 1157.1933514185;
myRo =
atm.getDensity(
275, 800 * 1000, 0, FastMath.toRadians(40), 16 * FastMath.PI / 12, 150, 150, 0, 0);
Assert.assertEquals(0, (roTestCase - myRo) / roTestCase, 1e-14);
Assert.assertEquals(0, (tzTestCase - atm.getT()) / tzTestCase, 1e-13);
Assert.assertEquals(0, (tinfTestCase - atm.getTinf()) / tinfTestCase, 1e-13);
// IDEM., day=355
roTestCase = 1.7343324462212e-17 * 1000;
tzTestCase = 1033.0277846356;
tinfTestCase = 1033.0282703200;
myRo =
atm.getDensity(
355, 800 * 1000, 0, FastMath.toRadians(40), 16 * FastMath.PI / 12, 150, 150, 0, 0);
Assert.assertEquals(0, (roTestCase - myRo) / roTestCase, 2e-14);
Assert.assertEquals(0, (tzTestCase - atm.getT()) / tzTestCase, 1e-13);
Assert.assertEquals(0, (tinfTestCase - atm.getTinf()) / tinfTestCase, 1e-13);
// IDEM., day=85
roTestCase = 2.9983740796297e-17 * 1000;
tzTestCase = 1169.5405086196;
tinfTestCase = 1169.5485768345;
myRo =
atm.getDensity(
85, 800 * 1000, 0, FastMath.toRadians(40), 16 * FastMath.PI / 12, 150, 150, 0, 0);
Assert.assertEquals(0, (roTestCase - myRo) / roTestCase, 1e-14);
Assert.assertEquals(0, (tzTestCase - atm.getT()) / tzTestCase, 1e-13);
Assert.assertEquals(0, (tinfTestCase - atm.getTinf()) / tinfTestCase, 1e-13);
// alt=500.
// lat=-70. NB: the subroutine requires latitude in rad
// day=15.
// hl=16. NB: the subroutine requires local time in rad (0hr=0 rad)
// xlon=0.
// fm(1)=70.
// f(1) =fm(1)
// fm(2)=0.
// f(2)=0.
// akp(1)=0.
// akp(2)=0.
// akp(3)=0.
// akp(4)=0.
// ro= 1.3150282384722D-16
// tz= 793.65487014559
// tinf= 793.65549802348
// roTestCase = 1.3150282384722E-16;
// tzTestCase= 793.65487014559;
// tinfTestCase= 793.65549802348;
atm.getDensity(15, 500 * 1000, 0, FastMath.toRadians(-70), 16 * FastMath.PI / 12, 70, 70, 0, 0);
// IDEM., alt=800.
// ro= 1.9556768571305D-18
// tz= 793.65549797919
// tinf= 793.65549802348
atm.getDensity(15, 800 * 1000, 0, FastMath.toRadians(-70), 16 * FastMath.PI / 12, 70, 70, 0, 0);
}