use of org.orekit.orbits.Orbit in project Orekit by CS-SI.
the class ElevationDetectorTest method testEventForMask.
@Test
public void testEventForMask() throws OrekitException {
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, mu);
Propagator propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
// Earth and frame
// equatorial radius in meter
double ae = 6378137.0;
// flattening
double f = 1.0 / 298.257223563;
// terrestrial frame at an arbitrary date
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833), FastMath.toRadians(2.333), 0.0);
TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
double[][] maskValues = { { FastMath.toRadians(0), FastMath.toRadians(5) }, { FastMath.toRadians(30), FastMath.toRadians(4) }, { FastMath.toRadians(60), FastMath.toRadians(3) }, { FastMath.toRadians(90), FastMath.toRadians(2) }, { FastMath.toRadians(120), FastMath.toRadians(3) }, { FastMath.toRadians(150), FastMath.toRadians(4) }, { FastMath.toRadians(180), FastMath.toRadians(5) }, { FastMath.toRadians(210), FastMath.toRadians(6) }, { FastMath.toRadians(240), FastMath.toRadians(5) }, { FastMath.toRadians(270), FastMath.toRadians(4) }, { FastMath.toRadians(300), FastMath.toRadians(3) }, { FastMath.toRadians(330), FastMath.toRadians(4) } };
ElevationMask mask = new ElevationMask(maskValues);
ElevationDetector detector = new ElevationDetector(topo).withElevationMask(mask).withHandler(new StopOnIncreasing<ElevationDetector>());
Assert.assertSame(mask, detector.getElevationMask());
AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
propagator.resetInitialState(propagator.propagate(startDate));
propagator.addEventDetector(detector);
final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
double elevation = topo.getElevation(fs.getPVCoordinates().getPosition(), fs.getFrame(), fs.getDate());
Assert.assertEquals(0.065, elevation, 2.0e-5);
}
use of org.orekit.orbits.Orbit in project Orekit by CS-SI.
the class EventDetectorTest method testIssue108Numerical.
@Test
public void testIssue108Numerical() throws OrekitException {
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 CircularOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
final double step = 60.0;
final int n = 100;
NumericalPropagator propagator = new NumericalPropagator(new ClassicalRungeKuttaIntegrator(step));
propagator.resetInitialState(new SpacecraftState(orbit));
GCallsCounter counter = new GCallsCounter(100000.0, 1.0e-6, 20, new StopOnEvent<GCallsCounter>());
propagator.addEventDetector(counter);
propagator.propagate(date.shiftedBy(n * step));
Assert.assertEquals(n + 1, counter.getCount());
}
use of org.orekit.orbits.Orbit in project Orekit by CS-SI.
the class EventDetectorTest method testBasicScheduling.
@Test
public void testBasicScheduling() throws OrekitException {
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 CircularOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
Propagator propagator = new KeplerianPropagator(orbit);
double stepSize = 60.0;
OutOfOrderChecker checker = new OutOfOrderChecker(stepSize);
propagator.addEventDetector(new DateDetector(date.shiftedBy(5.25 * stepSize)).withHandler(checker));
propagator.setMasterMode(stepSize, checker);
propagator.propagate(date.shiftedBy(10 * stepSize));
Assert.assertTrue(checker.outOfOrderCallDetected());
}
use of org.orekit.orbits.Orbit in project Orekit by CS-SI.
the class EventShifterTest method setUp.
@Before
public void setUp() {
try {
Utils.setDataRoot("regular-data");
mu = 3.9860047e14;
double ae = 6.378137e6;
double c20 = -1.08263e-3;
double c30 = 2.54e-6;
double c40 = 1.62e-6;
double c50 = 2.3e-7;
double c60 = -5.5e-7;
final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getGCRF(), iniDate, mu);
propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
log = new ArrayList<EventEntry>();
} catch (OrekitException oe) {
Assert.fail(oe.getLocalizedMessage());
}
}
use of org.orekit.orbits.Orbit in project Orekit by CS-SI.
the class AlignmentDetectorTest method setUp.
@Before
public void setUp() {
try {
Utils.setDataRoot("regular-data");
double mu = 3.9860047e14;
final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
iniDate = new AbsoluteDate(1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), iniDate, mu);
initialState = new SpacecraftState(orbit);
double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
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(0.001, 1000, absTolerance, relTolerance);
integrator.setInitialStepSize(60);
propagator = new NumericalPropagator(integrator);
propagator.setInitialState(initialState);
} catch (OrekitException oe) {
Assert.fail(oe.getLocalizedMessage());
}
}
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