Examples with PVCoordinates org.orekit.utils.PVCoordinates used on opensource projects

Example 66 with PVCoordinates

use of org.orekit.utils.PVCoordinates in project Orekit by CS-SI.

the class CircularOrbitTest method testCircularToEquinoctialCirc.

@Test
public void testCircularToEquinoctialCirc() {
    double ix = 1.200e-04;
    double iy = -1.16e-04;
    double i = 2 * FastMath.asin(FastMath.sqrt((ix * ix + iy * iy) / 4));
    double raan = FastMath.atan2(iy, ix);
    // circular orbit
    EquinoctialOrbit circCir = new EquinoctialOrbit(42166.712, 0.1e-10, -0.1e-10, i, raan, 5.300 - raan, PositionAngle.MEAN, FramesFactory.getEME2000(), date, mu);
    Vector3D posCir = circCir.getPVCoordinates().getPosition();
    Vector3D vitCir = circCir.getPVCoordinates().getVelocity();
    PVCoordinates pvCoordinates = new PVCoordinates(posCir, vitCir);
    EquinoctialOrbit paramCir = new EquinoctialOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    Assert.assertEquals(paramCir.getA(), circCir.getA(), Utils.epsilonTest * circCir.getA());
    Assert.assertEquals(paramCir.getEquinoctialEx(), circCir.getEquinoctialEx(), Utils.epsilonEcir * FastMath.abs(circCir.getE()));
    Assert.assertEquals(paramCir.getEquinoctialEy(), circCir.getEquinoctialEy(), Utils.epsilonEcir * FastMath.abs(circCir.getE()));
    Assert.assertEquals(paramCir.getHx(), circCir.getHx(), Utils.epsilonAngle * FastMath.abs(circCir.getI()));
    Assert.assertEquals(paramCir.getHy(), circCir.getHy(), Utils.epsilonAngle * FastMath.abs(circCir.getI()));
    Assert.assertEquals(MathUtils.normalizeAngle(paramCir.getLv(), circCir.getLv()), circCir.getLv(), Utils.epsilonAngle * FastMath.abs(circCir.getLv()));
}

Example 67 with PVCoordinates

use of org.orekit.utils.PVCoordinates in project Orekit by CS-SI.

the class CircularOrbitTest method testSymmetryCir.

@Test
public void testSymmetryCir() {
    // circular and equatorial orbit
    Vector3D position = new Vector3D(33051.2, 26184.9, -1.3E-5);
    Vector3D velocity = new Vector3D(-60376.2, 76208., 2.7E-4);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CircularOrbit p = new CircularOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    Vector3D positionOffset = p.getPVCoordinates().getPosition().subtract(position);
    Vector3D velocityOffset = p.getPVCoordinates().getVelocity().subtract(velocity);
    Assert.assertEquals(0.0, positionOffset.getNorm(), position.getNorm() * Utils.epsilonTest);
    Assert.assertEquals(0.0, velocityOffset.getNorm(), velocity.getNorm() * Utils.epsilonTest);
}

Example 68 with PVCoordinates

use of org.orekit.utils.PVCoordinates in project Orekit by CS-SI.

the class CircularOrbitTest method testEquatorialRetrograde.

@Test
public void testEquatorialRetrograde() {
    Vector3D position = new Vector3D(10000000.0, 0.0, 0.0);
    Vector3D velocity = new Vector3D(0.0, -6500.0, 0.0);
    double r2 = position.getNormSq();
    double r = FastMath.sqrt(r2);
    Vector3D acceleration = new Vector3D(-mu / (r * r2), position, 1, new Vector3D(-0.1, 0.2, 0.3));
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity, acceleration);
    CircularOrbit orbit = new CircularOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    Assert.assertEquals(10637829.465, orbit.getA(), 1.0e-3);
    Assert.assertEquals(-738.145, orbit.getADot(), 1.0e-3);
    Assert.assertEquals(0.05995861, orbit.getE(), 1.0e-8);
    Assert.assertEquals(-6.523e-5, orbit.getEDot(), 1.0e-8);
    Assert.assertEquals(FastMath.PI, orbit.getI(), 1.0e-15);
    Assert.assertEquals(-4.615e-5, orbit.getIDot(), 1.0e-8);
    Assert.assertTrue(Double.isNaN(orbit.getHx()));
    Assert.assertTrue(Double.isNaN(orbit.getHxDot()));
    Assert.assertTrue(Double.isNaN(orbit.getHy()));
    Assert.assertTrue(Double.isNaN(orbit.getHyDot()));
}

Example 69 with PVCoordinates

use of org.orekit.utils.PVCoordinates in project Orekit by CS-SI.

the class CircularOrbitTest method testSymmetryEll.

@Test
public void testSymmetryEll() {
    // elliptic and non equatorail orbit
    Vector3D position = new Vector3D(4512.9, 18260., -5127.);
    Vector3D velocity = new Vector3D(134664.6, 90066.8, 72047.6);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CircularOrbit p = new CircularOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    Vector3D positionOffset = p.getPVCoordinates().getPosition();
    Vector3D velocityOffset = p.getPVCoordinates().getVelocity();
    positionOffset = positionOffset.subtract(position);
    velocityOffset = velocityOffset.subtract(velocity);
    Assert.assertEquals(0.0, positionOffset.getNorm(), position.getNorm() * Utils.epsilonTest);
    Assert.assertEquals(0.0, velocityOffset.getNorm(), velocity.getNorm() * Utils.epsilonTest);
}

Example 70 with PVCoordinates

use of org.orekit.utils.PVCoordinates in project Orekit by CS-SI.

the class ConstantThrustManeuverTest method RealFieldTest.

/**
 *Testing if the propagation between the FieldPropagation and the propagation
 * is equivalent.
 * Also testing if propagating X+dX with the propagation is equivalent to
 * propagation X with the FieldPropagation and then applying the taylor
 * expansion of dX to the result.
 */
@Test
public void RealFieldTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 5);
    DerivativeStructure a_0 = factory.variable(0, 7e7);
    DerivativeStructure e_0 = factory.variable(1, 0.4);
    DerivativeStructure i_0 = factory.variable(2, 85 * FastMath.PI / 180);
    DerivativeStructure R_0 = factory.variable(3, 0.7);
    DerivativeStructure O_0 = factory.variable(4, 0.5);
    DerivativeStructure n_0 = factory.variable(5, 0.1);
    Field<DerivativeStructure> field = a_0.getField();
    DerivativeStructure zero = field.getZero();
    FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<>(field);
    Frame EME = FramesFactory.getEME2000();
    FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<>(a_0, e_0, i_0, R_0, O_0, n_0, PositionAngle.MEAN, EME, J2000, Constants.EIGEN5C_EARTH_MU);
    FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<>(FKO);
    SpacecraftState iSR = initialState.toSpacecraftState();
    final OrbitType type = OrbitType.KEPLERIAN;
    double[][] tolerance = NumericalPropagator.tolerances(10.0, FKO.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<DerivativeStructure> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    AdaptiveStepsizeIntegrator RIntegrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    RIntegrator.setInitialStepSize(60);
    FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
    FNP.setOrbitType(type);
    FNP.setInitialState(initialState);
    NumericalPropagator NP = new NumericalPropagator(RIntegrator);
    NP.setOrbitType(type);
    NP.setInitialState(iSR);
    final ConstantThrustManeuver forceModel = new ConstantThrustManeuver(J2000.toAbsoluteDate().shiftedBy(100), 100.0, 400.0, 300.0, Vector3D.PLUS_K);
    FNP.addForceModel(forceModel);
    NP.addForceModel(forceModel);
    FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1000.);
    FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
    SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
    FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
    PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getX(), finPVC_R.getPosition().getX(), FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getY(), finPVC_R.getPosition().getY(), FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
    Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getZ(), finPVC_R.getPosition().getZ(), FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
    long number = 23091991;
    RandomGenerator RG = new Well19937a(number);
    GaussianRandomGenerator NGG = new GaussianRandomGenerator(RG);
    UncorrelatedRandomVectorGenerator URVG = new UncorrelatedRandomVectorGenerator(new double[] { 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 }, new double[] { 1e3, 0.01, 0.01, 0.01, 0.01, 0.01 }, NGG);
    double a_R = a_0.getReal();
    double e_R = e_0.getReal();
    double i_R = i_0.getReal();
    double R_R = R_0.getReal();
    double O_R = O_0.getReal();
    double n_R = n_0.getReal();
    for (int ii = 0; ii < 1; ii++) {
        double[] rand_next = URVG.nextVector();
        double a_shift = a_R + rand_next[0];
        double e_shift = e_R + rand_next[1];
        double i_shift = i_R + rand_next[2];
        double R_shift = R_R + rand_next[3];
        double O_shift = O_R + rand_next[4];
        double n_shift = n_R + rand_next[5];
        KeplerianOrbit shiftedOrb = new KeplerianOrbit(a_shift, e_shift, i_shift, R_shift, O_shift, n_shift, PositionAngle.MEAN, EME, J2000.toAbsoluteDate(), Constants.EIGEN5C_EARTH_MU);
        SpacecraftState shift_iSR = new SpacecraftState(shiftedOrb);
        NumericalPropagator shift_NP = new NumericalPropagator(RIntegrator);
        shift_NP.setInitialState(shift_iSR);
        shift_NP.addForceModel(forceModel);
        SpacecraftState finalState_shift = shift_NP.propagate(target.toAbsoluteDate());
        PVCoordinates finPVC_shift = finalState_shift.getPVCoordinates();
        // position check
        FieldVector3D<DerivativeStructure> pos_DS = finPVC_DS.getPosition();
        double x_DS = pos_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double y_DS = pos_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double z_DS = pos_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        // System.out.println(pos_DS.getX().getPartialDerivative(1));
        double x = finPVC_shift.getPosition().getX();
        double y = finPVC_shift.getPosition().getY();
        double z = finPVC_shift.getPosition().getZ();
        Assert.assertEquals(x_DS, x, FastMath.abs(x - pos_DS.getX().getReal()) * 1e-8);
        Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 1e-8);
        Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 1e-8);
        // velocity check
        FieldVector3D<DerivativeStructure> vel_DS = finPVC_DS.getVelocity();
        double vx_DS = vel_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vy_DS = vel_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vz_DS = vel_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double vx = finPVC_shift.getVelocity().getX();
        double vy = finPVC_shift.getVelocity().getY();
        double vz = finPVC_shift.getVelocity().getZ();
        Assert.assertEquals(vx_DS, vx, FastMath.abs(vx) * 1e-9);
        Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 1e-9);
        Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 1e-9);
        // acceleration check
        FieldVector3D<DerivativeStructure> acc_DS = finPVC_DS.getAcceleration();
        double ax_DS = acc_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ay_DS = acc_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double az_DS = acc_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
        double ax = finPVC_shift.getAcceleration().getX();
        double ay = finPVC_shift.getAcceleration().getY();
        double az = finPVC_shift.getAcceleration().getZ();
        Assert.assertEquals(ax_DS, ax, FastMath.abs(ax) * 1e-8);
        Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 1e-8);
        Assert.assertEquals(az_DS, az, FastMath.abs(az) * 1e-8);
    }
}