Examples with Vector3D org.hipparchus.geometry.euclidean.threed.Vector3D used on opensource projects

Example 71 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class HarrisPriester method getDensity.

/**
 * Get the local density at some position.
 * @param date current date
 * @param position current position
 * @param <T> implements a RealFieldElement
 * @param frame the frame in which is defined the position
 * @return local density (kg/m³)
 * @exception OrekitException if some frame conversion cannot be performed
 *            or if altitude is below the model minimal altitude
 */
public <T extends RealFieldElement<T>> T getDensity(final FieldAbsoluteDate<T> date, final FieldVector3D<T> position, final Frame frame) throws OrekitException {
    // Sun position in earth frame
    final Vector3D sunInEarth = sun.getPVCoordinates(date.toAbsoluteDate(), earth.getBodyFrame()).getPosition();
    // Target position in earth frame
    final FieldVector3D<T> posInEarth = frame.getTransformTo(earth.getBodyFrame(), date.toAbsoluteDate()).transformPosition(position);
    return getDensity(sunInEarth, posInEarth);
}

Example 72 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class NumericalPropagatorTest method setUp.

@Before
public void setUp() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/shm-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new SHMFormatReader("^eigen_cg03c_coef$", false));
    mu = GravityFieldFactory.getUnnormalizedProvider(0, 0).getMu();
    final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    initDate = AbsoluteDate.J2000_EPOCH;
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new SpacecraftState(orbit);
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit, OrbitType.EQUINOCTIAL);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(60);
    propagator = new NumericalPropagator(integrator);
    propagator.setInitialState(initialState);
}

Example 73 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class NumericalPropagatorTest method createEllipticOrbit.

private CartesianOrbit createEllipticOrbit() throws OrekitException {
    final AbsoluteDate date = new AbsoluteDate("2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final Vector3D position = new Vector3D(6896874.444705, 1956581.072644, -147476.245054);
    final Vector3D velocity = new Vector3D(166.816407662, -1106.783301861, -7372.745712770);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    return new CartesianOrbit(pv, frame, mu);
}

Example 74 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class NumericalPropagatorTest method testPropagationTypesElliptical.

@Test
public void testPropagationTypesElliptical() throws OrekitException, ParseException, IOException {
    // setup
    AbsoluteDate initDate = new AbsoluteDate();
    SpacecraftState initialState;
    final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    initDate = AbsoluteDate.J2000_EPOCH;
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new SpacecraftState(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit, type);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(60);
    propagator = new NumericalPropagator(integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(5, 5));
    propagator.addForceModel(gravityField);
    // Propagation of the initial at t + dt
    final PVCoordinates pv = initialState.getPVCoordinates();
    final double dP = 0.001;
    final double dV = initialState.getMu() * dP / (pv.getPosition().getNormSq() * pv.getVelocity().getNorm());
    final PVCoordinates pvcM = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.MEAN);
    final PVCoordinates pviM = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.MEAN);
    final PVCoordinates pveM = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.MEAN);
    final PVCoordinates pvkM = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN);
    final PVCoordinates pvcE = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pviE = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.ECCENTRIC);
    final PVCoordinates pveE = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.ECCENTRIC);
    final PVCoordinates pvkE = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pvcT = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.TRUE);
    final PVCoordinates pviT = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.TRUE);
    final PVCoordinates pveT = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE);
    final PVCoordinates pvkT = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE);
    Assert.assertEquals(0, pvcM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.6);
    Assert.assertEquals(0, pviM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.4);
    Assert.assertEquals(0, pvkM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.5);
    Assert.assertEquals(0, pvkM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.3);
    Assert.assertEquals(0, pveM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.2);
    Assert.assertEquals(0, pveM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
    Assert.assertEquals(0, pvcE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.03);
    Assert.assertEquals(0, pviE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.04);
    Assert.assertEquals(0, pvkE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.4);
    Assert.assertEquals(0, pvkE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.3);
    Assert.assertEquals(0, pveE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.2);
    Assert.assertEquals(0, pveE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.07);
    Assert.assertEquals(0, pvcT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.3);
    Assert.assertEquals(0, pviT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
    Assert.assertEquals(0, pvkT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.4);
    Assert.assertEquals(0, pvkT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
}

Example 75 with Vector3D

use of org.hipparchus.geometry.euclidean.threed.Vector3D in project Orekit by CS-SI.

the class DSSTPropagatorTest method getLEOState.

private SpacecraftState getLEOState() throws IllegalArgumentException, OrekitException {
    final Vector3D position = new Vector3D(-6142438.668, 3492467.560, -25767.25680);
    final Vector3D velocity = new Vector3D(505.8479685, 942.7809215, 7435.922231);
    // Spring equinoxe 21st mars 2003 1h00m
    final AbsoluteDate initDate = new AbsoluteDate(new DateComponents(2003, 03, 21), new TimeComponents(1, 0, 0.), TimeScalesFactory.getUTC());
    return new SpacecraftState(new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, 3.986004415E14));
}