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

Example 46 with TimeScale

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

the class KeplerianPropagatorTest method testIssue107.

@Test
public void testIssue107() 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) {

        private static final long serialVersionUID = 1L;

        AbsoluteDate lastDate = AbsoluteDate.PAST_INFINITY;

        protected SpacecraftState basicPropagate(final AbsoluteDate date) throws OrekitException {
            if (date.compareTo(lastDate) < 0) {
                throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "no backward propagation allowed");
            }
            lastDate = date;
            return super.basicPropagate(date);
        }
    };
    SpacecraftState finalState = propagator.propagate(date.shiftedBy(3600.0));
    Assert.assertEquals(3600.0, finalState.getDate().durationFrom(date), 1.0e-15);
}

Example 47 with TimeScale

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

the class KeplerianPropagatorTest method testIssue224.

@Test
public void testIssue224() throws OrekitException, IOException, ClassNotFoundException {
    // Inertial frame
    Frame inertialFrame = FramesFactory.getEME2000();
    // Initial date
    TimeScale utc = TimeScalesFactory.getUTC();
    AbsoluteDate initialDate = new AbsoluteDate(2004, 01, 01, 23, 30, 00.000, utc);
    // Central attraction coefficient
    double mu = 3.986004415e+14;
    // Initial orbit
    // semi major axis in meters
    double a = 42100;
    // eccentricity
    double e = 0.01;
    // inclination
    double i = FastMath.toRadians(6);
    // perigee argument
    double omega = FastMath.toRadians(180);
    // right ascention of ascending node
    double raan = FastMath.toRadians(261);
    // mean anomaly
    double lM = 0;
    Orbit initialOrbit = new KeplerianOrbit(a, e, i, omega, raan, lM, PositionAngle.MEAN, inertialFrame, initialDate, mu);
    // Initial state definition
    SpacecraftState initialState = new SpacecraftState(initialOrbit);
    // Propagator
    KeplerianPropagator propagator = new KeplerianPropagator(initialOrbit, new LofOffset(inertialFrame, LOFType.VVLH));
    propagator.addAdditionalStateProvider(new SevenProvider());
    propagator.setEphemerisMode();
    // Impulsive burn 1
    final AbsoluteDate burn1Date = initialState.getDate().shiftedBy(200);
    ImpulseManeuver<DateDetector> impulsiveBurn1 = new ImpulseManeuver<DateDetector>(new DateDetector(burn1Date), new Vector3D(1000, 0, 0), 320);
    propagator.addEventDetector(impulsiveBurn1);
    // Impulsive burn 2
    final AbsoluteDate burn2Date = initialState.getDate().shiftedBy(300);
    ImpulseManeuver<DateDetector> impulsiveBurn2 = new ImpulseManeuver<DateDetector>(new DateDetector(burn2Date), new Vector3D(1000, 0, 0), 320);
    propagator.addEventDetector(impulsiveBurn2);
    propagator.propagate(initialState.getDate().shiftedBy(400));
    ByteArrayOutputStream bos = new ByteArrayOutputStream();
    ObjectOutputStream oos = new ObjectOutputStream(bos);
    oos.writeObject(propagator.getGeneratedEphemeris());
    Assert.assertTrue(bos.size() > 2400);
    Assert.assertTrue(bos.size() < 2500);
    ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
    ObjectInputStream ois = new ObjectInputStream(bis);
    BoundedPropagator ephemeris = (BoundedPropagator) ois.readObject();
    ephemeris.setMasterMode(10, new OrekitFixedStepHandler() {

        public void handleStep(SpacecraftState currentState, boolean isLast) {
            if (currentState.getDate().durationFrom(burn1Date) < -0.001) {
                Assert.assertEquals(42100.0, currentState.getA(), 1.0e-3);
            } else if (currentState.getDate().durationFrom(burn1Date) > 0.001 && currentState.getDate().durationFrom(burn2Date) < -0.001) {
                Assert.assertEquals(42979.962, currentState.getA(), 1.0e-3);
            } else if (currentState.getDate().durationFrom(burn2Date) > 0.001) {
                Assert.assertEquals(43887.339, currentState.getA(), 1.0e-3);
            }
        }
    });
    ephemeris.propagate(ephemeris.getMaxDate());
}

Example 48 with TimeScale

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

the class KeplerianPropagatorTest method testIssue223.

@Test
public void testIssue223() throws OrekitException, IOException, ClassNotFoundException {
    // Inertial frame
    Frame inertialFrame = FramesFactory.getEME2000();
    // Initial date
    TimeScale utc = TimeScalesFactory.getUTC();
    AbsoluteDate initialDate = new AbsoluteDate(2004, 01, 01, 23, 30, 00.000, utc);
    // Central attraction coefficient
    double mu = 3.986004415e+14;
    // Initial orbit
    // semi major axis in meters
    double a = 42100;
    // eccentricity
    double e = 0.01;
    // inclination
    double i = FastMath.toRadians(6);
    // perigee argument
    double omega = FastMath.toRadians(180);
    // right ascention of ascending node
    double raan = FastMath.toRadians(261);
    // mean anomaly
    double lM = 0;
    Orbit initialOrbit = new KeplerianOrbit(a, e, i, omega, raan, lM, PositionAngle.MEAN, inertialFrame, initialDate, mu);
    // Initial state definition
    SpacecraftState initialState = new SpacecraftState(initialOrbit);
    // Propagator
    KeplerianPropagator propagator = new KeplerianPropagator(initialOrbit);
    propagator.addAdditionalStateProvider(new SevenProvider());
    propagator.setEphemerisMode();
    propagator.propagate(initialState.getDate().shiftedBy(40000));
    BoundedPropagator ephemeris = propagator.getGeneratedEphemeris();
    Assert.assertSame(inertialFrame, ephemeris.getFrame());
    ByteArrayOutputStream bos = new ByteArrayOutputStream();
    ObjectOutputStream oos = new ObjectOutputStream(bos);
    oos.writeObject(ephemeris);
    Assert.assertTrue(bos.size() > 2250);
    Assert.assertTrue(bos.size() < 2350);
    ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
    ObjectInputStream ois = new ObjectInputStream(bis);
    BoundedPropagator deserialized = (BoundedPropagator) ois.readObject();
    Assert.assertEquals(initialOrbit.getA(), deserialized.getInitialState().getA(), 1.0e-10);
    Assert.assertEquals(initialOrbit.getEquinoctialEx(), deserialized.getInitialState().getEquinoctialEx(), 1.0e-10);
    SpacecraftState s = deserialized.propagate(initialState.getDate().shiftedBy(20000));
    Map<String, double[]> additional = s.getAdditionalStates();
    Assert.assertEquals(1, additional.size());
    Assert.assertEquals(1, additional.get("seven").length);
    Assert.assertEquals(7, additional.get("seven")[0], 1.0e-15);
}

Example 49 with TimeScale

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

the class TabulatedEphemerisTest method testPiWraping.

@Test
public void testPiWraping() throws OrekitException {
    TimeScale utc = TimeScalesFactory.getUTC();
    Frame frame = FramesFactory.getEME2000();
    double mu = CelestialBodyFactory.getEarth().getGM();
    AbsoluteDate t0 = new AbsoluteDate(2009, 10, 29, 0, 0, 0, utc);
    AbsoluteDate t1 = new AbsoluteDate(t0, 1320.0);
    Vector3D p1 = new Vector3D(-0.17831296727974E+08, 0.67919502669856E+06, -0.16591008368477E+07);
    Vector3D v1 = new Vector3D(-0.38699705630724E+04, -0.36209408682762E+04, -0.16255053872347E+03);
    SpacecraftState s1 = new SpacecraftState(new EquinoctialOrbit(new PVCoordinates(p1, v1), frame, t1, mu));
    AbsoluteDate t2 = new AbsoluteDate(t0, 1440.0);
    Vector3D p2 = new Vector3D(-0.18286942572033E+08, 0.24442124296930E+06, -0.16777961761695E+07);
    Vector3D v2 = new Vector3D(-0.37252897467918E+04, -0.36246628128896E+04, -0.14917724596280E+03);
    SpacecraftState s2 = new SpacecraftState(new EquinoctialOrbit(new PVCoordinates(p2, v2), frame, t2, mu));
    AbsoluteDate t3 = new AbsoluteDate(t0, 1560.0);
    Vector3D p3 = new Vector3D(-0.18725635245837E+08, -0.19058407701834E+06, -0.16949352249614E+07);
    Vector3D v3 = new Vector3D(-0.35873348682393E+04, -0.36248828501784E+04, -0.13660045394149E+03);
    SpacecraftState s3 = new SpacecraftState(new EquinoctialOrbit(new PVCoordinates(p3, v3), frame, t3, mu));
    Ephemeris ephem = new Ephemeris(Arrays.asList(s1, s2, s3), 2);
    AbsoluteDate tA = new AbsoluteDate(t0, 24 * 60);
    Vector3D pA = ephem.propagate(tA).getPVCoordinates(frame).getPosition();
    Assert.assertEquals(1.766, Vector3D.distance(pA, s1.shiftedBy(tA.durationFrom(s1.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(0.000, Vector3D.distance(pA, s2.shiftedBy(tA.durationFrom(s2.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(1.556, Vector3D.distance(pA, s3.shiftedBy(tA.durationFrom(s3.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    AbsoluteDate tB = new AbsoluteDate(t0, 25 * 60);
    Vector3D pB = ephem.propagate(tB).getPVCoordinates(frame).getPosition();
    Assert.assertEquals(2.646, Vector3D.distance(pB, s1.shiftedBy(tB.durationFrom(s1.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(2.619, Vector3D.distance(pB, s2.shiftedBy(tB.durationFrom(s2.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(2.632, Vector3D.distance(pB, s3.shiftedBy(tB.durationFrom(s3.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    AbsoluteDate tC = new AbsoluteDate(t0, 26 * 60);
    Vector3D pC = ephem.propagate(tC).getPVCoordinates(frame).getPosition();
    Assert.assertEquals(6.851, Vector3D.distance(pC, s1.shiftedBy(tC.durationFrom(s1.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(1.605, Vector3D.distance(pC, s2.shiftedBy(tC.durationFrom(s2.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
    Assert.assertEquals(0.000, Vector3D.distance(pC, s3.shiftedBy(tC.durationFrom(s3.getDate())).getPVCoordinates(frame).getPosition()), 1.0e-3);
}

Example 50 with TimeScale

use of org.orekit.time.TimeScale 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);
}