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

Example 71 with TimeComponents

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

the class LofOffsetPointingTest method testSpin.

@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(orbit.getFrame(), 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);
}

Example 72 with TimeComponents

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

the class LofOffsetTest method testSpin.

@Test
public void testSpin() throws OrekitException {
    final AttitudeProvider law = new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYX, 0.1, 0.2, 0.3);
    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);
    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.assertEquals(0.0, spin0.subtract(reference).getNorm(), 1.0e-10);
}

Example 73 with TimeComponents

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

the class LofOffsetTest method testAnglesSign.

@Test
public void testAnglesSign() 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-8, FastMath.toRadians(50.), FastMath.toRadians(10.), FastMath.toRadians(20.), FastMath.toRadians(0.), PositionAngle.MEAN, FramesFactory.getEME2000(), date, 3.986004415e14);
    double alpha = 0.1;
    double cos = FastMath.cos(alpha);
    double sin = FastMath.sin(alpha);
    // Roll
    Attitude attitude = new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYZ, alpha, 0.0, 0.0).getAttitude(orbit, date, orbit.getFrame());
    checkSatVector(orbit, attitude, Vector3D.PLUS_I, 1.0, 0.0, 0.0, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_J, 0.0, cos, sin, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_K, 0.0, -sin, cos, 1.0e-8);
    // Pitch
    attitude = new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYZ, 0.0, alpha, 0.0).getAttitude(orbit, date, orbit.getFrame());
    checkSatVector(orbit, attitude, Vector3D.PLUS_I, cos, 0.0, -sin, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_J, 0.0, 1.0, 0.0, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_K, sin, 0.0, cos, 1.0e-8);
    // Yaw
    attitude = new LofOffset(orbit.getFrame(), LOFType.VVLH, RotationOrder.XYZ, 0.0, 0.0, alpha).getAttitude(orbit, date, orbit.getFrame());
    checkSatVector(orbit, attitude, Vector3D.PLUS_I, cos, sin, 0.0, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_J, -sin, cos, 0.0, 1.0e-8);
    checkSatVector(orbit, attitude, Vector3D.PLUS_K, 0.0, 0.0, 1.0, 1.0e-8);
}

Example 74 with TimeComponents

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

the class CelestialBodyPointingTest method testSunPointing.

@Test
public void testSunPointing() throws OrekitException {
    PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
    final Frame frame = FramesFactory.getGCRF();
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getTAI());
    AttitudeProvider sunPointing = new CelestialBodyPointed(frame, sun, Vector3D.PLUS_K, Vector3D.PLUS_I, Vector3D.PLUS_K);
    PVCoordinates pv = new PVCoordinates(new Vector3D(28812595.32120171334, 5948437.45881852374, 0.0), new Vector3D(0, 0, 3680.853673522056));
    Orbit orbit = new KeplerianOrbit(pv, frame, date, 3.986004415e14);
    Attitude attitude = sunPointing.getAttitude(orbit, date, frame);
    checkField(Decimal64Field.getInstance(), sunPointing, orbit, date, frame);
    Vector3D xDirection = attitude.getRotation().applyInverseTo(Vector3D.PLUS_I);
    Vector3D zDirection = attitude.getRotation().applyInverseTo(Vector3D.PLUS_K);
    Assert.assertEquals(0, Vector3D.dotProduct(zDirection, Vector3D.crossProduct(xDirection, Vector3D.PLUS_K)), 1.0e-15);
    // the following statement checks we take parallax into account
    // Sun-Earth-Sat are in quadrature, with distance (Earth, Sat) == distance(Sun, Earth) / 5000
    Assert.assertEquals(FastMath.atan(1.0 / 5000.0), Vector3D.angle(xDirection, sun.getPVCoordinates(date, frame).getPosition()), 1.0e-15);
    double h = 0.1;
    Attitude aMinus = sunPointing.getAttitude(orbit.shiftedBy(-h), date.shiftedBy(-h), frame);
    Attitude a0 = sunPointing.getAttitude(orbit, date, frame);
    Attitude aPlus = sunPointing.getAttitude(orbit.shiftedBy(h), date.shiftedBy(h), frame);
    // check spin is consistent with attitude evolution
    double errorAngleMinus = Rotation.distance(aMinus.shiftedBy(h).getRotation(), a0.getRotation());
    double evolutionAngleMinus = Rotation.distance(aMinus.getRotation(), a0.getRotation());
    Assert.assertEquals(0.0, errorAngleMinus, 1.0e-6 * evolutionAngleMinus);
    double errorAnglePlus = Rotation.distance(a0.getRotation(), aPlus.shiftedBy(-h).getRotation());
    double evolutionAnglePlus = Rotation.distance(a0.getRotation(), aPlus.getRotation());
    Assert.assertEquals(0.0, errorAnglePlus, 1.0e-6 * evolutionAnglePlus);
}

Example 75 with TimeComponents

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

the class FixedRateTest method testNonZeroRate.

@Test
public void testNonZeroRate() throws OrekitException {
    final AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 3, 2), new TimeComponents(13, 17, 7.865), TimeScalesFactory.getUTC());
    final double rate = 2 * FastMath.PI / (12 * 60);
    final Frame frame = FramesFactory.getEME2000();
    FixedRate law = new FixedRate(new Attitude(date, frame, new Rotation(0.48, 0.64, 0.36, 0.48, false), new Vector3D(rate, Vector3D.PLUS_K), Vector3D.ZERO));
    PVCoordinates pv = new PVCoordinates(new Vector3D(28812595.32012577, 5948437.4640250085, 0), new Vector3D(0, 0, 3680.853673522056));
    Orbit orbit = new KeplerianOrbit(pv, FramesFactory.getEME2000(), date, 3.986004415e14);
    Rotation attitude0 = law.getAttitude(orbit, date, frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude0, law.getReferenceAttitude().getRotation()), 1.0e-10);
    Rotation attitude1 = law.getAttitude(orbit.shiftedBy(10.0), date.shiftedBy(10.0), frame).getRotation();
    Assert.assertEquals(10 * rate, Rotation.distance(attitude1, law.getReferenceAttitude().getRotation()), 1.0e-10);
    Rotation attitude2 = law.getAttitude(orbit.shiftedBy(-20.0), date.shiftedBy(-20.0), frame).getRotation();
    Assert.assertEquals(20 * rate, Rotation.distance(attitude2, law.getReferenceAttitude().getRotation()), 1.0e-10);
    Assert.assertEquals(30 * rate, Rotation.distance(attitude2, attitude1), 1.0e-10);
    Rotation attitude3 = law.getAttitude(orbit.shiftedBy(0.0), date, frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude3, law.getReferenceAttitude().getRotation()), 1.0e-10);
}