@Test
public void testEphemerisGenerationIssue14() throws OrekitException, IOException {
// Propagation of the initial at t + dt
final double dt = 3200;
propagator.getInitialState();
propagator.setOrbitType(OrbitType.CARTESIAN);
propagator.setEphemerisMode();
propagator.propagate(initDate.shiftedBy(dt));
final BoundedPropagator ephemeris1 = propagator.getGeneratedEphemeris();
Assert.assertEquals(initDate, ephemeris1.getMinDate());
Assert.assertEquals(initDate.shiftedBy(dt), ephemeris1.getMaxDate());
propagator.getPVCoordinates(initDate.shiftedBy(2 * dt), FramesFactory.getEME2000());
propagator.getPVCoordinates(initDate.shiftedBy(-2 * dt), FramesFactory.getEME2000());
// the new propagations should not have changed ephemeris1
Assert.assertEquals(initDate, ephemeris1.getMinDate());
Assert.assertEquals(initDate.shiftedBy(dt), ephemeris1.getMaxDate());
final BoundedPropagator ephemeris2 = propagator.getGeneratedEphemeris();
Assert.assertEquals(initDate.shiftedBy(-2 * dt), ephemeris2.getMinDate());
Assert.assertEquals(initDate.shiftedBy(2 * dt), ephemeris2.getMaxDate());
// generating ephemeris2 should not have changed ephemeris1
Assert.assertEquals(initDate, ephemeris1.getMinDate());
Assert.assertEquals(initDate.shiftedBy(dt), ephemeris1.getMaxDate());
}
@Test
public void testGroundToGroundIssue181() throws OrekitException {
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
Frame eme2000 = FramesFactory.getEME2000();
OneAxisEllipsoid model =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
TimeStampedPVCoordinates initPV =
new TimeStampedPVCoordinates(
AbsoluteDate.J2000_EPOCH.shiftedBy(584.),
new Vector3D(3220103., 69623., 6449822.),
new Vector3D(6414.7, -2006., -3180.),
Vector3D.ZERO);
TimeStampedPVCoordinates body =
itrf.getTransformTo(eme2000, initPV.getDate()).transformPVCoordinates(initPV);
TimeStampedPVCoordinates ground1 = model.projectToGround(body, itrf);
TimeStampedPVCoordinates ground2 = model.projectToGround(ground1, itrf);
Assert.assertEquals(
0.0, Vector3D.distance(ground1.getPosition(), ground2.getPosition()), 1.0e-12);
Assert.assertEquals(
0.0, Vector3D.distance(ground1.getVelocity(), ground2.getVelocity()), 1.0e-12);
Assert.assertEquals(
0.0, Vector3D.distance(ground1.getAcceleration(), ground2.getAcceleration()), 1.0e-12);
}
@Test
public void testPropagationTypesHyperbolic() throws OrekitException, ParseException, IOException {
SpacecraftState state =
new SpacecraftState(
new KeplerianOrbit(
-10000000.0,
2.5,
0.3,
0,
0,
0.0,
PositionAngle.TRUE,
FramesFactory.getEME2000(),
initDate,
mu));
ForceModel gravityField =
new HolmesFeatherstoneAttractionModel(
FramesFactory.getITRF(IERSConventions.IERS_2010, true),
GravityFieldFactory.getNormalizedProvider(5, 5));
propagator.addForceModel(gravityField);
// Propagation of the initial at t + dt
final PVCoordinates pv = state.getPVCoordinates();
final double dP = 0.001;
final double dV =
state.getMu() * dP / (pv.getPosition().getNormSq() * pv.getVelocity().getNorm());
final PVCoordinates pvcM = propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.MEAN);
final PVCoordinates pvkM = propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN);
final PVCoordinates pvcE =
propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC);
final PVCoordinates pvkE =
propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC);
final PVCoordinates pvcT = propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.TRUE);
final PVCoordinates pvkT = propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE);
Assert.assertEquals(0, pvcM.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
Assert.assertEquals(0, pvcM.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
Assert.assertEquals(0, pvkM.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.2);
Assert.assertEquals(0, pvkM.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.3);
Assert.assertEquals(0, pvcE.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
Assert.assertEquals(0, pvcE.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
Assert.assertEquals(0, pvkE.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.009);
Assert.assertEquals(0, pvkE.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.006);
Assert.assertEquals(0, pvcT.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
Assert.assertEquals(0, pvcT.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
}
@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 testMiss() throws OrekitException {
final CircularOrbit circ =
new CircularOrbit(
7178000.0,
0.5e-4,
-0.5e-4,
FastMath.toRadians(0.),
FastMath.toRadians(270.),
FastMath.toRadians(5.300),
PositionAngle.MEAN,
FramesFactory.getEME2000(),
date,
mu);
final LofOffset upsideDown =
new LofOffset(circ.getFrame(), LOFType.VVLH, RotationOrder.XYX, FastMath.PI, 0, 0);
final LofOffsetPointing pointing =
new LofOffsetPointing(earthSpheric, upsideDown, Vector3D.PLUS_K);
try {
pointing.getTargetPV(circ, date, circ.getFrame());
Assert.fail("an exception should have been thrown");
} catch (OrekitException oe) {
Assert.assertEquals(
OrekitMessages.ATTITUDE_POINTING_LAW_DOES_NOT_POINT_TO_GROUND, oe.getSpecifier());
}
}
private static List<GeodeticPoint> computeCircle(
double latitude,
double longitude,
double altitude,
String name,
double minElevation,
double radius,
int points)
throws OrekitException {
// define Earth shape, using WGS84 model
BodyShape earth =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, false));
// define an array of ground stations
TopocentricFrame station =
new TopocentricFrame(earth, new GeodeticPoint(latitude, longitude, altitude), name);
// compute the visibility circle
List<GeodeticPoint> circle = new ArrayList<GeodeticPoint>();
for (int i = 0; i < points; ++i) {
double azimuth = i * (2.0 * FastMath.PI / points);
circle.add(station.computeLimitVisibilityPoint(radius, azimuth, minElevation));
}
// return the computed points
return circle;
}
@Test
public void testFrance() throws OrekitException {
final BodyShape earth =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
GeographicZoneDetector d =
new GeographicZoneDetector(20.0, 1.e-3, earth, buildFrance(), FastMath.toRadians(0.5))
.withHandler(new ContinueOnEvent<GeographicZoneDetector>());
Assert.assertEquals(20.0, d.getMaxCheckInterval(), 1.0e-15);
Assert.assertEquals(1.0e-3, d.getThreshold(), 1.0e-15);
Assert.assertEquals(0.5, FastMath.toDegrees(d.getMargin()), 1.0e-15);
Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
final TimeScale utc = TimeScalesFactory.getUTC();
final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
final Orbit orbit =
new EquinoctialOrbit(
new PVCoordinates(position, velocity),
FramesFactory.getEME2000(),
date,
Constants.EIGEN5C_EARTH_MU);
Propagator propagator =
new EcksteinHechlerPropagator(
orbit,
Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS,
Constants.EIGEN5C_EARTH_MU,
Constants.EIGEN5C_EARTH_C20,
Constants.EIGEN5C_EARTH_C30,
Constants.EIGEN5C_EARTH_C40,
Constants.EIGEN5C_EARTH_C50,
Constants.EIGEN5C_EARTH_C60);
EventsLogger logger = new EventsLogger();
propagator.addEventDetector(logger.monitorDetector(d));
propagator.propagate(date.shiftedBy(10 * Constants.JULIAN_DAY));
Assert.assertEquals(26, logger.getLoggedEvents().size());
}
@Test
public void testEventDetectionBug() throws OrekitException, IOException, ParseException {
TimeScale utc = TimeScalesFactory.getUTC();
AbsoluteDate initialDate = new AbsoluteDate(2005, 1, 1, 0, 0, 0.0, utc);
double duration = 100000.;
AbsoluteDate endDate = new AbsoluteDate(initialDate, duration);
// Initialization of the frame EME2000
Frame EME2000 = FramesFactory.getEME2000();
// Initial orbit
double a = 35786000. + 6378137.0;
double e = 0.70;
double rApogee = a * (1 + e);
double vApogee = FastMath.sqrt(mu * (1 - e) / (a * (1 + e)));
Orbit geo =
new CartesianOrbit(
new PVCoordinates(new Vector3D(rApogee, 0., 0.), new Vector3D(0., vApogee, 0.)),
EME2000,
initialDate,
mu);
duration = geo.getKeplerianPeriod();
endDate = new AbsoluteDate(initialDate, duration);
// Numerical Integration
final double minStep = 0.001;
final double maxStep = 1000;
final double initStep = 60;
final double[] absTolerance = {0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001};
final double[] relTolerance = {1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7};
AdaptiveStepsizeIntegrator integrator =
new DormandPrince853Integrator(minStep, maxStep, absTolerance, relTolerance);
integrator.setInitialStepSize(initStep);
// Numerical propagator based on the integrator
propagator = new NumericalPropagator(integrator);
double mass = 1000.;
SpacecraftState initialState = new SpacecraftState(geo, mass);
propagator.setInitialState(initialState);
propagator.setOrbitType(OrbitType.CARTESIAN);
// Set the events Detectors
ApsideDetector event1 = new ApsideDetector(geo);
propagator.addEventDetector(event1);
// Set the propagation mode
propagator.setSlaveMode();
// Propagate
SpacecraftState finalState = propagator.propagate(endDate);
// we should stop long before endDate
Assert.assertTrue(endDate.durationFrom(finalState.getDate()) > 40000.0);
}
@Test
public void testFarPoint() throws OrekitException {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
OneAxisEllipsoid model = new OneAxisEllipsoid(90.0, 5.0 / 9.0, frame);
Vector3D point = new Vector3D(1.0e15, 2.0e15, -1.0e12);
GeodeticPoint gp = model.transform(point, frame, date);
Vector3D rebuilt = model.transform(gp);
Assert.assertEquals(0.0, rebuilt.distance(point), 1.0e-15 * point.getNorm());
}
@Test
public void testNoLineIntersection() throws OrekitException {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
OneAxisEllipsoid model = new OneAxisEllipsoid(100.0, 0.9, frame);
Vector3D point = new Vector3D(0.0, 93.7139699, 3.5930796);
Vector3D direction = new Vector3D(0.0, 9.0, -2.0);
Line line = new Line(point, point.add(direction), 1.0e-10);
Assert.assertNull(model.getIntersectionPoint(line, point, frame, date));
}
@Test
public void testSpin() throws OrekitException {
AbsoluteDate date =
new AbsoluteDate(
new DateComponents(1970, 01, 01),
new TimeComponents(3, 25, 45.6789),
TimeScalesFactory.getUTC());
KeplerianOrbit orbit =
new KeplerianOrbit(
7178000.0,
1.e-4,
FastMath.toRadians(50.),
FastMath.toRadians(10.),
FastMath.toRadians(20.),
FastMath.toRadians(30.),
PositionAngle.MEAN,
FramesFactory.getEME2000(),
date,
3.986004415e14);
final AttitudeProvider law =
new LofOffsetPointing(
earthSpheric,
new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYX, 0.1, 0.2, 0.3),
Vector3D.PLUS_K);
Propagator propagator = new KeplerianPropagator(orbit, law);
double h = 0.01;
SpacecraftState sMinus = propagator.propagate(date.shiftedBy(-h));
SpacecraftState s0 = propagator.propagate(date);
SpacecraftState sPlus = propagator.propagate(date.shiftedBy(h));
// check spin is consistent with attitude evolution
double errorAngleMinus =
Rotation.distance(
sMinus.shiftedBy(h).getAttitude().getRotation(), s0.getAttitude().getRotation());
double evolutionAngleMinus =
Rotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation());
Assert.assertEquals(0.0, errorAngleMinus, 1.0e-6 * evolutionAngleMinus);
double errorAnglePlus =
Rotation.distance(
s0.getAttitude().getRotation(), sPlus.shiftedBy(-h).getAttitude().getRotation());
double evolutionAnglePlus =
Rotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation());
Assert.assertEquals(0.0, errorAnglePlus, 1.0e-6 * evolutionAnglePlus);
Vector3D spin0 = s0.getAttitude().getSpin();
Vector3D reference =
AngularCoordinates.estimateRate(
sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), 2 * h);
Assert.assertTrue(spin0.getNorm() > 1.0e-3);
Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 1.0e-10);
}
@Test
public void testGeoCar() throws OrekitException {
OneAxisEllipsoid model =
new OneAxisEllipsoid(
6378137.0, 1.0 / 298.257222101, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
GeodeticPoint nsp = new GeodeticPoint(0.852479154923577, 0.0423149994747243, 111.6);
Vector3D p = model.transform(nsp);
Assert.assertEquals(4201866.69291890, p.getX(), 1.0e-6);
Assert.assertEquals(177908.184625686, p.getY(), 1.0e-6);
Assert.assertEquals(4779203.64408617, p.getZ(), 1.0e-6);
}
@Test
public void testOnSurface() throws OrekitException {
Vector3D surfacePoint =
new Vector3D(-1092200.775949484, -3944945.7282234835, 4874931.946956173);
OneAxisEllipsoid earthShape =
new OneAxisEllipsoid(
6378136.460, 1 / 298.257222101, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
GeodeticPoint gp =
earthShape.transform(surfacePoint, earthShape.getBodyFrame(), AbsoluteDate.J2000_EPOCH);
Vector3D rebuilt = earthShape.transform(gp);
Assert.assertEquals(0, rebuilt.distance(surfacePoint), 3.0e-9);
}
@Test
public void testEquatorialInside() throws OrekitException {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
OneAxisEllipsoid model = new OneAxisEllipsoid(90.0, 5.0 / 9.0, frame);
for (double rho = 0; rho < model.getEquatorialRadius(); rho += 0.01) {
Vector3D point = new Vector3D(rho, 0.0, 0.0);
GeodeticPoint gp = model.transform(point, frame, date);
Vector3D rebuilt = model.transform(gp);
Assert.assertEquals(0.0, rebuilt.distance(point), 1.0e-10);
}
}
@Test
public void testGroundProjectionDerivatives() throws OrekitException {
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
Frame eme2000 = FramesFactory.getEME2000();
OneAxisEllipsoid model =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
TimeStampedPVCoordinates initPV =
new TimeStampedPVCoordinates(
AbsoluteDate.J2000_EPOCH.shiftedBy(584.),
new Vector3D(3220103., 69623., 6449822.),
new Vector3D(6414.7, -2006., -3180.),
Vector3D.ZERO);
Orbit orbit = new EquinoctialOrbit(initPV, eme2000, Constants.EIGEN5C_EARTH_MU);
double[] errors = derivativesErrors(orbit, orbit.getDate(), eme2000, model);
Assert.assertEquals(0, errors[0], 1.0e-16);
Assert.assertEquals(0, errors[1], 1.0e-12);
Assert.assertEquals(0, errors[2], 2.0e-4);
}
@Before
public void setUp() throws OrekitException {
Utils.setDataRoot("regular-data");
earth =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
gp = new GeodeticPoint(FastMath.toRadians(51.0), FastMath.toRadians(66.6), 300.0);
final TimeScale utc = TimeScalesFactory.getUTC();
final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
orbit =
new EquinoctialOrbit(
new PVCoordinates(position, velocity),
FramesFactory.getEME2000(),
date,
Constants.EIGEN5C_EARTH_MU);
}
@Test
public void testIssue141() throws OrekitException {
AbsoluteDate date =
new AbsoluteDate("2002-03-06T20:50:20.44188731559965033", TimeScalesFactory.getUTC());
Frame frame = FramesFactory.getGTOD(IERSConventions.IERS_1996, true);
OneAxisEllipsoid model =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, frame);
Vector3D point = new Vector3D(-6838696.282102453, -2148321.403361013, -0.011907944179711194);
GeodeticPoint gp = model.transform(point, frame, date);
Vector3D rebuilt = model.transform(gp);
Assert.assertEquals(0.0, rebuilt.distance(point), 1.0e-15 * point.getNorm());
}
@Test
public void testGroundProjectionTaylor() throws OrekitException {
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
Frame eme2000 = FramesFactory.getEME2000();
OneAxisEllipsoid model =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
TimeStampedPVCoordinates initPV =
new TimeStampedPVCoordinates(
AbsoluteDate.J2000_EPOCH.shiftedBy(584.),
new Vector3D(3220103., 69623., 6449822.),
new Vector3D(6414.7, -2006., -3180.),
Vector3D.ZERO);
Orbit orbit = new EquinoctialOrbit(initPV, eme2000, Constants.EIGEN5C_EARTH_MU);
TimeStampedPVCoordinates pv0 = orbit.getPVCoordinates(orbit.getDate(), model.getBodyFrame());
PVCoordinatesProvider groundTaylor =
model.projectToGround(pv0, model.getBodyFrame()).toTaylorProvider(model.getBodyFrame());
TimeStampedPVCoordinates g0 =
groundTaylor.getPVCoordinates(orbit.getDate(), model.getBodyFrame());
Vector3D zenith = pv0.getPosition().subtract(g0.getPosition()).normalize();
Vector3D acrossTrack = Vector3D.crossProduct(zenith, g0.getVelocity()).normalize();
Vector3D alongTrack = Vector3D.crossProduct(acrossTrack, zenith).normalize();
for (double dt = -1; dt < 1; dt += 0.01) {
AbsoluteDate date = orbit.getDate().shiftedBy(dt);
Vector3D taylorP = groundTaylor.getPVCoordinates(date, model.getBodyFrame()).getPosition();
Vector3D refP =
model.projectToGround(
orbit.getPVCoordinates(date, model.getBodyFrame()).getPosition(),
date,
model.getBodyFrame());
Vector3D delta = taylorP.subtract(refP);
Assert.assertEquals(0.0, Vector3D.dotProduct(delta, alongTrack), 0.0015);
Assert.assertEquals(0.0, Vector3D.dotProduct(delta, acrossTrack), 0.0007);
Assert.assertEquals(0.0, Vector3D.dotProduct(delta, zenith), 0.00002);
}
}
public static void setLoaders(final IERSConventions conventions, final List<EOPEntry> eop) {
OrekitUtils.clearFactoryMaps(FramesFactory.class);
OrekitUtils.clearFactoryMaps(TimeScalesFactory.class);
FramesFactory.addEOPHistoryLoader(
conventions,
new EOPHistoryLoader() {
public void fillHistory(
IERSConventions.NutationCorrectionConverter converter, SortedSet<EOPEntry> history) {
history.addAll(eop);
}
});
}
@Test
public void testGroundProjectionPosition() throws OrekitException {
OneAxisEllipsoid model =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
TimeStampedPVCoordinates initPV =
new TimeStampedPVCoordinates(
AbsoluteDate.J2000_EPOCH.shiftedBy(584.),
new Vector3D(3220103., 69623., 6449822.),
new Vector3D(6414.7, -2006., -3180.),
Vector3D.ZERO);
Frame eme2000 = FramesFactory.getEME2000();
Orbit orbit = new EquinoctialOrbit(initPV, eme2000, Constants.EIGEN5C_EARTH_MU);
for (double dt = 0; dt < 3600.0; dt += 60.0) {
TimeStampedPVCoordinates pv = orbit.getPVCoordinates(orbit.getDate().shiftedBy(dt), eme2000);
TimeStampedPVCoordinates groundPV = model.projectToGround(pv, eme2000);
Vector3D groundP = model.projectToGround(pv.getPosition(), pv.getDate(), eme2000);
// check methods projectToGround and transform are consistent with each other
Assert.assertEquals(
model.transform(pv.getPosition(), eme2000, pv.getDate()).getLatitude(),
model.transform(groundPV.getPosition(), eme2000, pv.getDate()).getLatitude(),
1.0e-10);
Assert.assertEquals(
model.transform(pv.getPosition(), eme2000, pv.getDate()).getLongitude(),
model.transform(groundPV.getPosition(), eme2000, pv.getDate()).getLongitude(),
1.0e-10);
Assert.assertEquals(
0.0, Vector3D.distance(groundP, groundPV.getPosition()), 1.0e-15 * groundP.getNorm());
}
}
@Test
public void testLineIntersection() throws OrekitException {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
OneAxisEllipsoid model = new OneAxisEllipsoid(100.0, 0.9, frame);
Vector3D point = new Vector3D(0.0, 93.7139699, 3.5930796);
Vector3D direction = new Vector3D(0.0, 1.0, 1.0);
Line line = new Line(point, point.add(direction), 1.0e-10);
GeodeticPoint gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertEquals(gp.getAltitude(), 0.0, 1.0e-12);
Assert.assertTrue(line.contains(model.transform(gp)));
model = new OneAxisEllipsoid(100.0, 0.9, frame);
point = new Vector3D(0.0, -93.7139699, -3.5930796);
direction = new Vector3D(0.0, -1.0, -1.0);
line = new Line(point, point.add(direction), 1.0e-10).revert();
gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertTrue(line.contains(model.transform(gp)));
model = new OneAxisEllipsoid(100.0, 0.9, frame);
point = new Vector3D(0.0, -93.7139699, 3.5930796);
direction = new Vector3D(0.0, -1.0, 1.0);
line = new Line(point, point.add(direction), 1.0e-10);
gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertTrue(line.contains(model.transform(gp)));
model = new OneAxisEllipsoid(100.0, 0.9, frame);
point = new Vector3D(-93.7139699, 0.0, 3.5930796);
direction = new Vector3D(-1.0, 0.0, 1.0);
line = new Line(point, point.add(direction), 1.0e-10);
gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertTrue(line.contains(model.transform(gp)));
Assert.assertFalse(line.contains(new Vector3D(0, 0, 7000000)));
point = new Vector3D(0.0, 0.0, 110);
direction = new Vector3D(0.0, 0.0, 1.0);
line = new Line(point, point.add(direction), 1.0e-10);
gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertEquals(gp.getLatitude(), FastMath.PI / 2, 1.0e-12);
point = new Vector3D(0.0, 110, 0);
direction = new Vector3D(0.0, 1.0, 0.0);
line = new Line(point, point.add(direction), 1.0e-10);
gp = model.getIntersectionPoint(line, point, frame, date);
Assert.assertEquals(gp.getLatitude(), 0, 1.0e-12);
}
public Tracker(final BoundedPropagator prop) throws OrekitException {
this.prop = prop;
earth =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF2005());
// setup an arbitrary station on the surface of the earth
double longitude = Math.toRadians(45.);
double latitude = Math.toRadians(25.);
double altitude = 0.;
final GeodeticPoint station = new GeodeticPoint(latitude, longitude, altitude);
stationFrame = new TopocentricFrame(earth, station, "ground location");
}
@Test
public void testEphemerisDatesBackward() throws OrekitException {
// setup
TimeScale tai = TimeScalesFactory.getTAI();
AbsoluteDate initialDate = new AbsoluteDate("2015-07-05", 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,
mu);
double[][] tol = NumericalPropagator.tolerances(1, orbit, OrbitType.CARTESIAN);
Propagator prop =
new NumericalPropagator(new DormandPrince853Integrator(0.1, 500, tol[0], tol[1]));
prop.resetInitialState(new SpacecraftState(new CartesianOrbit(orbit)));
// action
prop.setEphemerisMode();
prop.propagate(endDate, startDate);
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);
}
@Test
public void testSerialization()
throws IOException, ClassNotFoundException, NoSuchFieldException, IllegalAccessException,
OrekitException {
final double r = Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
final BodyShape earth =
new OneAxisEllipsoid(
r,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
GeographicZoneDetector d =
new GeographicZoneDetector(20.0, 1.e-3, earth, buildFrance(), FastMath.toRadians(0.5))
.withMargin(FastMath.toRadians(0.75))
.withHandler(new ContinueOnEvent<GeographicZoneDetector>());
Assert.assertEquals(r, ((OneAxisEllipsoid) d.getBody()).getEquatorialRadius(), 1.0e-12);
Assert.assertEquals(0.75, FastMath.toDegrees(d.getMargin()), 1.0e-12);
Assert.assertEquals(5.6807e11, d.getZone().getSize() * r * r, 1.0e9);
Assert.assertEquals(4.0289e6, d.getZone().getBoundarySize() * r, 1.0e3);
ByteArrayOutputStream bos = new ByteArrayOutputStream();
ObjectOutputStream oos = new ObjectOutputStream(bos);
oos.writeObject(d);
Assert.assertTrue(bos.size() > 2100);
Assert.assertTrue(bos.size() < 2200);
ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
ObjectInputStream ois = new ObjectInputStream(bis);
GeographicZoneDetector deserialized = (GeographicZoneDetector) ois.readObject();
Assert.assertEquals(d.getZone().getSize(), deserialized.getZone().getSize(), 1.0e-3);
Assert.assertEquals(
d.getZone().getBoundarySize(), deserialized.getZone().getBoundarySize(), 1.0e-3);
Assert.assertEquals(d.getZone().getTolerance(), deserialized.getZone().getTolerance(), 1.0e-15);
Assert.assertEquals(d.getMaxCheckInterval(), deserialized.getMaxCheckInterval(), 1.0e-15);
Assert.assertEquals(d.getThreshold(), deserialized.getThreshold(), 1.0e-15);
Assert.assertEquals(d.getMaxIterationCount(), deserialized.getMaxIterationCount());
Assert.assertTrue(
new RegionFactory<Sphere2D>().difference(d.getZone(), deserialized.getZone()).isEmpty());
}
@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();
}
@Before
public void setUp() throws OrekitException {
Utils.setDataRoot("regular-data:potential/shm-format");
GravityFieldFactory.addPotentialCoefficientsReader(
new SHMFormatReader("^eigen_cg03c_coef$", false));
mu = GravityFieldFactory.getUnnormalizedProvider(0, 0).getMu();
final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
initDate = AbsoluteDate.J2000_EPOCH;
final Orbit orbit =
new EquinoctialOrbit(
new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
initialState = new SpacecraftState(orbit);
double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit, OrbitType.EQUINOCTIAL);
AdaptiveStepsizeIntegrator integrator =
new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
integrator.setInitialStepSize(60);
propagator = new NumericalPropagator(integrator);
propagator.setInitialState(initialState);
}
@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());
}
}
private void checkCartesianToEllipsoidic(
double ae,
double f,
double x,
double y,
double z,
double longitude,
double latitude,
double altitude)
throws OrekitException {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
OneAxisEllipsoid model = new OneAxisEllipsoid(ae, f, frame);
GeodeticPoint gp = model.transform(new Vector3D(x, y, z), frame, date);
Assert.assertEquals(longitude, MathUtils.normalizeAngle(gp.getLongitude(), longitude), 1.0e-10);
Assert.assertEquals(latitude, gp.getLatitude(), 1.0e-10);
Assert.assertEquals(altitude, gp.getAltitude(), 1.0e-10 * FastMath.abs(ae));
Vector3D rebuiltNadir = Vector3D.crossProduct(gp.getSouth(), gp.getWest());
Assert.assertEquals(0, rebuiltNadir.subtract(gp.getNadir()).getNorm(), 1.0e-15);
}
@Test
public void testSerialization() throws OrekitException, IOException, ClassNotFoundException {
OneAxisEllipsoid original =
new OneAxisEllipsoid(
Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRFEquinox(IERSConventions.IERS_1996, true));
original.setAngularThreshold(1.0e-3);
ByteArrayOutputStream bos = new ByteArrayOutputStream();
ObjectOutputStream oos = new ObjectOutputStream(bos);
oos.writeObject(original);
Assert.assertTrue(bos.size() > 250);
Assert.assertTrue(bos.size() < 350);
ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
ObjectInputStream ois = new ObjectInputStream(bis);
OneAxisEllipsoid deserialized = (OneAxisEllipsoid) ois.readObject();
Assert.assertEquals(
original.getEquatorialRadius(), deserialized.getEquatorialRadius(), 1.0e-12);
Assert.assertEquals(original.getFlattening(), deserialized.getFlattening(), 1.0e-12);
}
@Test(expected = OrekitException.class)
public void testMismatchedDimensions() 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[6][6], new double[7][2]);
}