Examples with LofOffset org.orekit.attitudes.LofOffset used on opensource projects

Example 11 with LofOffset

use of org.orekit.attitudes.LofOffset in project Orekit by CS-SI.

the class DSSTPropagatorTest method testIssue339WithAccelerations.

@Test
public void testIssue339WithAccelerations() throws OrekitException {
    final SpacecraftState osculatingState = getLEOStatePropagatedBy30Minutes();
    final CelestialBody sun = CelestialBodyFactory.getSun();
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final BoxAndSolarArraySpacecraft boxAndWing = new BoxAndSolarArraySpacecraft(5.0, 2.0, 2.0, sun, 50.0, Vector3D.PLUS_J, 2.0, 0.1, 0.2, 0.6);
    final Atmosphere atmosphere = new HarrisPriester(CelestialBodyFactory.getSun(), earth, 6);
    final AttitudeProvider attitudeProvider = new LofOffset(osculatingState.getFrame(), LOFType.VVLH, RotationOrder.XYZ, 0.0, 0.0, 0.0);
    // Surface force models that require an attitude provider
    final Collection<DSSTForceModel> forces = new ArrayList<DSSTForceModel>();
    forces.add(new DSSTAtmosphericDrag(atmosphere, boxAndWing));
    final SpacecraftState meanState = DSSTPropagator.computeMeanState(osculatingState, attitudeProvider, forces);
    final SpacecraftState computedOsculatingState = DSSTPropagator.computeOsculatingState(meanState, attitudeProvider, forces);
    Assert.assertEquals(0.0, Vector3D.distance(osculatingState.getPVCoordinates().getPosition(), computedOsculatingState.getPVCoordinates().getPosition()), 5.0e-6);
}

Example 12 with LofOffset

use of org.orekit.attitudes.LofOffset in project Orekit by CS-SI.

the class DSSTPropagatorTest method testIssue339.

@Test
public void testIssue339() throws OrekitException {
    final SpacecraftState osculatingState = getLEOState();
    final CelestialBody sun = CelestialBodyFactory.getSun();
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final BoxAndSolarArraySpacecraft boxAndWing = new BoxAndSolarArraySpacecraft(5.0, 2.0, 2.0, sun, 50.0, Vector3D.PLUS_J, 2.0, 0.1, 0.2, 0.6);
    final Atmosphere atmosphere = new HarrisPriester(CelestialBodyFactory.getSun(), earth, 6);
    final AttitudeProvider attitudeProvider = new LofOffset(osculatingState.getFrame(), LOFType.VVLH, RotationOrder.XYZ, 0.0, 0.0, 0.0);
    // Surface force models that require an attitude provider
    final Collection<DSSTForceModel> forces = new ArrayList<DSSTForceModel>();
    forces.add(new DSSTSolarRadiationPressure(sun, Constants.WGS84_EARTH_EQUATORIAL_RADIUS, boxAndWing));
    forces.add(new DSSTAtmosphericDrag(atmosphere, boxAndWing));
    final SpacecraftState meanState = DSSTPropagator.computeMeanState(osculatingState, attitudeProvider, forces);
    Assert.assertEquals(0.522, Vector3D.distance(osculatingState.getPVCoordinates().getPosition(), meanState.getPVCoordinates().getPosition()), 0.001);
    final SpacecraftState computedOsculatingState = DSSTPropagator.computeOsculatingState(meanState, attitudeProvider, forces);
    Assert.assertEquals(0.0, Vector3D.distance(osculatingState.getPVCoordinates().getPosition(), computedOsculatingState.getPVCoordinates().getPosition()), 5.0e-6);
}

Example 13 with LofOffset

use of org.orekit.attitudes.LofOffset in project Orekit by CS-SI.

the class TrackCorridor method createPropagator.

/**
 * Create an orbit propagator for a circular orbit
 * @param a  semi-major axis (m)
 * @param ex e cos(ω), first component of circular eccentricity vector
 * @param ey e sin(ω), second component of circular eccentricity vector
 * @param i inclination (rad)
 * @param raan right ascension of ascending node (Ω, rad)
 * @param alpha  an + ω, mean latitude argument (rad)
 * @param date date of the orbital parameters
 * @return an orbit propagator
 * @exception OrekitException if propagator cannot be built
 */
private Propagator createPropagator(final AbsoluteDate date, final double a, final double ex, final double ey, final double i, final double raan, final double alpha) throws OrekitException {
    // create orbit
    Orbit initialOrbit = new CircularOrbit(a, ex, ey, i, raan, alpha, PositionAngle.MEAN, FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    // create propagator
    Propagator propagator = new EcksteinHechlerPropagator(initialOrbit, new LofOffset(initialOrbit.getFrame(), LOFType.TNW), 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);
    return propagator;
}

Example 14 with LofOffset

use of org.orekit.attitudes.LofOffset in project Orekit by CS-SI.

the class SolidTidesTest method testStateJacobianVs80ImplementationNoPoleTide.

@Test
public void testStateJacobianVs80ImplementationNoPoleTide() throws OrekitException {
    Frame eme2000 = FramesFactory.getEME2000();
    TimeScale utc = TimeScalesFactory.getUTC();
    AbsoluteDate date = new AbsoluteDate(2964, 8, 12, 11, 30, 00.000, utc);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, FastMath.toRadians(98.7), FastMath.toRadians(93.0), FastMath.toRadians(15.0 * 22.5), 0, PositionAngle.MEAN, eme2000, date, Constants.EIGEN5C_EARTH_MU);
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    UT1Scale ut1 = TimeScalesFactory.getUT1(IERSConventions.IERS_2010, true);
    NormalizedSphericalHarmonicsProvider gravityField = GravityFieldFactory.getConstantNormalizedProvider(5, 5);
    ForceModel forceModel = new SolidTides(itrf, gravityField.getAe(), gravityField.getMu(), gravityField.getTideSystem(), false, SolidTides.DEFAULT_STEP, SolidTides.DEFAULT_POINTS, IERSConventions.IERS_2010, ut1, CelestialBodyFactory.getSun(), CelestialBodyFactory.getMoon());
    Assert.assertTrue(forceModel.dependsOnPositionOnly());
    checkStateJacobianVs80Implementation(new SpacecraftState(orbit), forceModel, new LofOffset(orbit.getFrame(), LOFType.VVLH), 2.0e-15, false);
}

Example 15 with LofOffset

use of org.orekit.attitudes.LofOffset in project Orekit by CS-SI.

the class ConstantThrustManeuverTest method testJacobianVs80Implementation.

@Test
public void testJacobianVs80Implementation() throws OrekitException {
    final double isp = 318;
    final double mass = 2500;
    final double a = 24396159;
    final double e = 0.72831215;
    final double i = FastMath.toRadians(7);
    final double omega = FastMath.toRadians(180);
    final double OMEGA = FastMath.toRadians(261);
    final double lv = 0;
    final double duration = 3653.99;
    final double f = 420;
    final AbsoluteDate initDate = new AbsoluteDate(new DateComponents(2004, 01, 01), new TimeComponents(23, 30, 00.000), TimeScalesFactory.getUTC());
    final Orbit orbit = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), initDate, mu);
    final AttitudeProvider law = new LofOffset(orbit.getFrame(), LOFType.VVLH);
    final SpacecraftState initialState = new SpacecraftState(orbit, law.getAttitude(orbit, orbit.getDate(), orbit.getFrame()), mass);
    final AbsoluteDate fireDate = new AbsoluteDate(new DateComponents(2004, 01, 02), new TimeComponents(04, 15, 34.080), TimeScalesFactory.getUTC());
    final ConstantThrustManeuver maneuver = new ConstantThrustManeuver(fireDate, duration, f, isp, Vector3D.PLUS_I);
    // before maneuver (Jacobian wrt. state is zero)
    checkStateJacobianVs80Implementation(initialState, maneuver, law, 1.0e-50, false);
    // in maneuver
    SpacecraftState startState = initialState.shiftedBy(fireDate.durationFrom(initDate));
    maneuver.getEventsDetectors().findFirst().get().eventOccurred(startState, true);
    SpacecraftState midState = startState.shiftedBy(duration / 2.0);
    checkStateJacobianVs80Implementation(midState, maneuver, law, 1.0e-20, false);
}