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

Example 61 with FieldAbsoluteDate

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

the class LofOffsetPointingTest method checkField.

private <T extends RealFieldElement<T>> void checkField(final Field<T> field, final GroundPointing provider, final Orbit orbit, final AbsoluteDate date, final Frame frame) throws OrekitException {
    final Attitude attitudeD = provider.getAttitude(orbit, date, frame);
    final FieldOrbit<T> orbitF = new FieldSpacecraftState<>(field, new SpacecraftState(orbit)).getOrbit();
    final FieldAbsoluteDate<T> dateF = new FieldAbsoluteDate<>(field, date);
    final FieldAttitude<T> attitudeF = provider.getAttitude(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Rotation.distance(attitudeD.getRotation(), attitudeF.getRotation().toRotation()), 1.0e-15);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getSpin(), attitudeF.getSpin().toVector3D()), 1.0e-15);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getRotationAcceleration(), attitudeF.getRotationAcceleration().toVector3D()), 1.0e-15);
    final TimeStampedPVCoordinates pvD = provider.getTargetPV(orbit, date, frame);
    final TimeStampedFieldPVCoordinates<T> pvF = provider.getTargetPV(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getPosition(), pvF.getPosition().toVector3D()), 9.0e-9);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getVelocity(), pvF.getVelocity().toVector3D()), 5.0e-9);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getAcceleration(), pvF.getAcceleration().toVector3D()), 4.0e-5);
}

Example 62 with FieldAbsoluteDate

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

the class NadirPointingTest method checkField.

private <T extends RealFieldElement<T>> void checkField(final Field<T> field, final GroundPointing provider, final Orbit orbit, final AbsoluteDate date, final Frame frame) throws OrekitException {
    final Attitude attitudeD = provider.getAttitude(orbit, date, frame);
    final FieldOrbit<T> orbitF = new FieldSpacecraftState<>(field, new SpacecraftState(orbit)).getOrbit();
    final FieldAbsoluteDate<T> dateF = new FieldAbsoluteDate<>(field, date);
    final FieldAttitude<T> attitudeF = provider.getAttitude(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Rotation.distance(attitudeD.getRotation(), attitudeF.getRotation().toRotation()), 1.0e-15);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getSpin(), attitudeF.getSpin().toVector3D()), 2.0e-14);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getRotationAcceleration(), attitudeF.getRotationAcceleration().toVector3D()), 4.0e-12);
    final TimeStampedPVCoordinates pvD = provider.getTargetPV(orbit, date, frame);
    final TimeStampedFieldPVCoordinates<T> pvF = provider.getTargetPV(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getPosition(), pvF.getPosition().toVector3D()), 1.0e-15);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getVelocity(), pvF.getVelocity().toVector3D()), 2.0e-8);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getAcceleration(), pvF.getAcceleration().toVector3D()), 3.0e-5);
}

Example 63 with FieldAbsoluteDate

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

the class BodyCenterPointingTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final double ehMu = 3.9860047e14;
    final double ae = 6.378137e6;
    final double c20 = -1.08263e-3;
    final double c30 = 2.54e-6;
    final double c40 = 1.62e-6;
    final double c50 = 2.3e-7;
    final double c60 = -5.5e-7;
    // Satellite position as circular parameters
    final T zero = field.getZero();
    final T a = zero.add(7178000.0);
    final T e = zero.add(7e-5);
    final T i = zero.add(FastMath.toRadians(50.));
    final T pa = zero.add(FastMath.toRadians(45.));
    final T raan = zero.add(FastMath.toRadians(270.));
    final T m = zero.add(FastMath.toRadians(5.3 - 270));
    // Computation date
    FieldAbsoluteDate<T> date_R = new FieldAbsoluteDate<>(field, new DateComponents(2008, 04, 07), TimeComponents.H00, TimeScalesFactory.getUTC());
    // Orbit
    FieldKeplerianOrbit<T> circ = new FieldKeplerianOrbit<>(a, e, i, pa, raan, m, PositionAngle.MEAN, FramesFactory.getEME2000(), date_R, ehMu);
    // WGS84 Earth model
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    // Earth center pointing attitude provider
    BodyCenterPointing earthCenterAttitudeLaw = new BodyCenterPointing(circ.getFrame(), earth);
    final FieldAbsoluteDate<T> date = FieldAbsoluteDate.getJ2000Epoch(field).shiftedBy(584.);
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(3220103.), zero.add(69623.), zero.add(6449822.));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(6414.7), zero.add(-2006.), zero.add(-3180.));
    final FieldCircularOrbit<T> initialOrbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, ehMu);
    FieldEcksteinHechlerPropagator<T> propagator = new FieldEcksteinHechlerPropagator<>(initialOrbit, ae, ehMu, c20, c30, c40, c50, c60);
    propagator.setAttitudeProvider(earthCenterAttitudeLaw);
    double h = 0.01;
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(-h));
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    T errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(zero.add(h)).getAttitude().getRotation(), s0.getAttitude().getRotation());
    T evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAngleMinus.getReal(), 1.0e-6 * evolutionAngleMinus.getReal());
    T errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(zero.add(-h)).getAttitude().getRotation());
    T evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation());
    Assert.assertEquals(0.0, errorAnglePlus.getReal(), 1.0e-6 * evolutionAnglePlus.getReal());
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), 2 * h);
    Assert.assertTrue(spin0.getNorm().getReal() > 1.0e-3);
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-13);
}

Example 64 with FieldAbsoluteDate

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

the class YawSteeringTest method checkField.

private <T extends RealFieldElement<T>> void checkField(final Field<T> field, final GroundPointing provider, final Orbit orbit, final AbsoluteDate date, final Frame frame) throws OrekitException {
    final Attitude attitudeD = provider.getAttitude(orbit, date, frame);
    final FieldOrbit<T> orbitF = new FieldSpacecraftState<>(field, new SpacecraftState(orbit)).getOrbit();
    final FieldAbsoluteDate<T> dateF = new FieldAbsoluteDate<>(field, date);
    final FieldAttitude<T> attitudeF = provider.getAttitude(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Rotation.distance(attitudeD.getRotation(), attitudeF.getRotation().toRotation()), 1.0e-15);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getSpin(), attitudeF.getSpin().toVector3D()), 4.0e-14);
    Assert.assertEquals(0.0, Vector3D.distance(attitudeD.getRotationAcceleration(), attitudeF.getRotationAcceleration().toVector3D()), 3.0e-12);
    final TimeStampedPVCoordinates pvD = provider.getTargetPV(orbit, date, frame);
    final TimeStampedFieldPVCoordinates<T> pvF = provider.getTargetPV(orbitF, dateF, frame);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getPosition(), pvF.getPosition().toVector3D()), 2.0e-9);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getVelocity(), pvF.getVelocity().toVector3D()), 7.0e-8);
    Assert.assertEquals(0.0, Vector3D.distance(pvD.getAcceleration(), pvF.getAcceleration().toVector3D()), 4.0e-5);
}

Example 65 with FieldAbsoluteDate

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

the class OneAxisEllipsoidTest method checkCartesianToEllipsoidic.

private void checkCartesianToEllipsoidic(double ae, double f, double x, double y, double z, double longitude, double latitude, double altitude) throws OrekitException {
    AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    Frame frame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    OneAxisEllipsoid model = new OneAxisEllipsoid(ae, f, frame);
    GeodeticPoint gp = model.transform(new Vector3D(x, y, z), frame, date);
    Assert.assertEquals(longitude, MathUtils.normalizeAngle(gp.getLongitude(), longitude), 1.0e-10);
    Assert.assertEquals(latitude, gp.getLatitude(), 1.0e-10);
    Assert.assertEquals(altitude, gp.getAltitude(), 1.0e-10 * FastMath.abs(ae));
    Vector3D rebuiltNadir = Vector3D.crossProduct(gp.getSouth(), gp.getWest());
    Assert.assertEquals(0, rebuiltNadir.subtract(gp.getNadir()).getNorm(), 1.0e-15);
    FieldGeodeticPoint<Decimal64> gp64 = model.transform(new FieldVector3D<Decimal64>(new Decimal64(x), new Decimal64(y), new Decimal64(z)), frame, new FieldAbsoluteDate<>(Decimal64Field.getInstance(), date));
    Assert.assertEquals(longitude, MathUtils.normalizeAngle(gp64.getLongitude().getReal(), longitude), 1.0e-10);
    Assert.assertEquals(latitude, gp64.getLatitude().getReal(), 1.0e-10);
    Assert.assertEquals(altitude, gp64.getAltitude().getReal(), 1.0e-10 * FastMath.abs(ae));
    FieldVector3D<Decimal64> rebuiltNadir64 = FieldVector3D.crossProduct(gp64.getSouth(), gp64.getWest());
    Assert.assertEquals(0, rebuiltNadir64.subtract(gp64.getNadir()).getNorm().getReal(), 1.0e-15);
}