Examples with TimeScale org.orekit.time.TimeScale used on opensource projects

Example 81 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestEventDetectionBug.

private <T extends RealFieldElement<T>> void doTestEventDetectionBug(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    TimeScale utc = TimeScalesFactory.getUTC();
    FieldAbsoluteDate<T> initialDate = new FieldAbsoluteDate<>(field, 2005, 1, 1, 0, 0, 0.0, utc);
    T duration = zero.add(100000.0);
    FieldAbsoluteDate<T> endDate = new FieldAbsoluteDate<>(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)));
    FieldOrbit<T> geo = new FieldCartesianOrbit<>(new FieldPVCoordinates<>(new FieldVector3D<>(zero.add(rApogee), zero, zero), new FieldVector3D<>(zero, zero.add(vApogee), zero)), EME2000, initialDate, mu);
    duration = geo.getKeplerianPeriod();
    endDate = new FieldAbsoluteDate<>(initialDate, duration);
    // Numerical Integration
    final double minStep = 0.001;
    final double maxStep = 1000;
    final double initStep = 60;
    final OrbitType type = OrbitType.EQUINOCTIAL;
    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 };
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, minStep, maxStep, absTolerance, relTolerance);
    integrator.setInitialStepSize(zero.add(initStep));
    // Numerical propagator based on the integrator
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    T mass = field.getZero().add(1000.0);
    FieldSpacecraftState<T> initialState = new FieldSpacecraftState<>(geo, mass);
    propagator.setInitialState(initialState);
    propagator.setOrbitType(OrbitType.CARTESIAN);
    // Set the events Detectors
    FieldApsideDetector<T> event1 = new FieldApsideDetector<>(geo);
    propagator.addEventDetector(event1);
    // Set the propagation mode
    propagator.setSlaveMode();
    // Propagate
    FieldSpacecraftState<T> finalState = propagator.propagate(endDate);
    // we should stop long before endDate
    Assert.assertTrue(endDate.durationFrom(finalState.getDate()).getReal() > 40000.0);
}

Example 82 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class ElevationDetectorTest method testPresTemp.

public void testPresTemp() 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");
    EarthStandardAtmosphereRefraction refractionModel = new EarthStandardAtmosphereRefraction();
    ElevationDetector detector = new ElevationDetector(topo).withRefraction(refractionModel).withHandler(new StopOnIncreasing<ElevationDetector>());
    refractionModel.setPressure(101325);
    refractionModel.setTemperature(290);
    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(FastMath.toRadians(1.7026104902251749), elevation, 2.0e-5);
}

Example 83 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class ElevationDetectorTest method testAgata.

@Test
public void testAgata() 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");
    Checking checking = new Checking(topo);
    ElevationDetector detector = new ElevationDetector(topo).withConstantElevation(FastMath.toRadians(5.0)).withHandler(checking);
    Assert.assertNull(detector.getElevationMask());
    Assert.assertNull(detector.getRefractionModel());
    Assert.assertSame(topo, detector.getTopocentricFrame());
    Assert.assertEquals(FastMath.toRadians(5.0), detector.getMinElevation(), 1.0e-15);
    AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 12, 0, 0, utc);
    propagator.resetInitialState(propagator.propagate(startDate));
    propagator.addEventDetector(detector);
    propagator.setMasterMode(10.0, checking);
    propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
}

Example 84 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class ElevationDetectorTest method testHorizon.

@Test
public void testHorizon() 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");
    AtmosphericRefractionModel refractionModel = new EarthStandardAtmosphereRefraction();
    ElevationDetector detector = new ElevationDetector(topo).withRefraction(refractionModel).withHandler(new StopOnIncreasing<ElevationDetector>());
    Assert.assertSame(refractionModel, detector.getRefractionModel());
    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(FastMath.toRadians(-0.5746255623877098), elevation, 2.0e-5);
}

Example 85 with TimeScale

use of org.orekit.time.TimeScale in project Orekit by CS-SI.

the class EventDetectorTest method testIssue108Analytical.

@Test
public void testIssue108Analytical() 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;
    KeplerianPropagator propagator = new KeplerianPropagator(orbit);
    GCallsCounter counter = new GCallsCounter(100000.0, 1.0e-6, 20, new StopOnEvent<GCallsCounter>());
    propagator.addEventDetector(counter);
    propagator.setMasterMode(step, new OrekitFixedStepHandler() {

        public void handleStep(SpacecraftState currentState, boolean isLast) {
        }
    });
    propagator.propagate(date.shiftedBy(n * step));
    Assert.assertEquals(n + 1, counter.getCount());
}