Example usage for org.apache.commons.math3.geometry.euclidean.threed Vector3D Vector3D

List of usage examples for org.apache.commons.math3.geometry.euclidean.threed Vector3D Vector3D

  1. HOME
  2. Java
  3. org.apache.commons
  4. org.apache.commons.math3.geometry.euclidean.threed.*
  5. Vector3D
  6. Vector3D

Introduction

In this page you can find the example usage for org.apache.commons.math3.geometry.euclidean.threed Vector3D Vector3D.

Prototype

public Vector3D(double x, double y, double z)

Source Link

Document

Simple constructor.

Usage

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test
public void testShiftCircular() {
    Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
    Vector3D velocity = new Vector3D(FastMath.sqrt(mu / position.getNorm()), position.orthogonal());
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    testShift(orbit, new CircularOrbit(orbit), 1.0e-15);
}

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test
public void testShiftHyperbolic() {
    Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
    Vector3D velocity = new Vector3D(3 * FastMath.sqrt(mu / position.getNorm()), position.orthogonal());
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    testShift(orbit, new KeplerianOrbit(orbit), 1.0e-15);
}

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test
public void testNumericalIssue135() throws OrekitException {
    Vector3D position = new Vector3D(-6.7884943832e7, -2.1423006112e7, -3.1603915377e7);
    Vector3D velocity = new Vector3D(-4732.55, -2472.086, -3022.177);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date,
            324858598826460.);/*from   w w  w .  j a va2s. c o m*/
    testShift(orbit, new KeplerianOrbit(orbit), 3.0e-15);
}

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test(expected = IllegalArgumentException.class)
public void testNonInertialFrame() throws IllegalArgumentException {

    Vector3D position = new Vector3D(-26655470.0, 29881667.0, -113657.0);
    Vector3D velocity = new Vector3D(-1125.0, -1122.0, 195.0);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    double mu = 3.9860047e14;
    new CartesianOrbit(pvCoordinates,
            new Frame(FramesFactory.getEME2000(), Transform.IDENTITY, "non-inertial", false), date, mu);
}

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test
public void testJacobianReference() throws OrekitException {

    Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
    Vector3D velocity = new Vector3D(-2194.0, -2141.0, -8.0);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);

    double[][] jacobian = new double[6][6];
    orbit.getJacobianWrtCartesian(PositionAngle.MEAN, jacobian);

    for (int i = 0; i < jacobian.length; i++) {
        double[] row = jacobian[i];
        for (int j = 0; j < row.length; j++) {
            Assert.assertEquals((i == j) ? 1 : 0, row[j], 1.0e-15);
        }/*from   w  ww .  jav a  2  s  . c o m*/
    }

}

From source file:org.orekit.orbits.CartesianParametersTest.java

@Test
public void testInterpolation() 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;

    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH.shiftedBy(584.);
    final Vector3D position = new Vector3D(3220103., 69623., 6449822.);
    final Vector3D velocity = new Vector3D(6414.7, -2006., -3180.);
    final CartesianOrbit initialOrbit = new CartesianOrbit(new PVCoordinates(position, velocity),
            FramesFactory.getEME2000(), date, ehMu);

    EcksteinHechlerPropagator propagator = new EcksteinHechlerPropagator(initialOrbit, ae, ehMu, c20, c30, c40,
            c50, c60);/*from  w ww  .ja  va 2 s . c o m*/

    // set up a 5 points sample
    List<Orbit> sample = new ArrayList<Orbit>();
    for (double dt = 0; dt < 251.0; dt += 60.0) {
        sample.add(propagator.propagate(date.shiftedBy(dt)).getOrbit());
    }

    // well inside the sample, interpolation should be much better than Keplerian shift
    // this is bacause we take the full non-Keplerian acceleration into account in
    // the Cartesian parameters, which in this case is preserved by the
    // Eckstein-Hechler propagator
    double maxShiftPError = 0;
    double maxInterpolationPError = 0;
    double maxShiftVError = 0;
    double maxInterpolationVError = 0;
    for (double dt = 0; dt < 240.0; dt += 1.0) {
        AbsoluteDate t = initialOrbit.getDate().shiftedBy(dt);
        PVCoordinates propagated = propagator.propagate(t).getPVCoordinates();
        PVCoordinates shiftError = new PVCoordinates(propagated, initialOrbit.shiftedBy(dt).getPVCoordinates());
        PVCoordinates interpolationError = new PVCoordinates(propagated,
                initialOrbit.interpolate(t, sample).getPVCoordinates());
        maxShiftPError = FastMath.max(maxShiftPError, shiftError.getPosition().getNorm());
        maxInterpolationPError = FastMath.max(maxInterpolationPError,
                interpolationError.getPosition().getNorm());
        maxShiftVError = FastMath.max(maxShiftVError, shiftError.getVelocity().getNorm());
        maxInterpolationVError = FastMath.max(maxInterpolationVError,
                interpolationError.getVelocity().getNorm());
    }
    Assert.assertTrue(maxShiftPError > 390.0);
    Assert.assertTrue(maxInterpolationPError < 3.0e-8);
    Assert.assertTrue(maxShiftVError > 3.0);
    Assert.assertTrue(maxInterpolationVError < 2.0e-9);

    // if we go far past sample end, interpolation becomes worse than Keplerian shift
    maxShiftPError = 0;
    maxInterpolationPError = 0;
    maxShiftVError = 0;
    maxInterpolationVError = 0;
    for (double dt = 500.0; dt < 650.0; dt += 1.0) {
        AbsoluteDate t = initialOrbit.getDate().shiftedBy(dt);
        PVCoordinates propagated = propagator.propagate(t).getPVCoordinates();
        PVCoordinates shiftError = new PVCoordinates(propagated, initialOrbit.shiftedBy(dt).getPVCoordinates());
        PVCoordinates interpolationError = new PVCoordinates(propagated,
                initialOrbit.interpolate(t, sample).getPVCoordinates());
        maxShiftPError = FastMath.max(maxShiftPError, shiftError.getPosition().getNorm());
        maxInterpolationPError = FastMath.max(maxInterpolationPError,
                interpolationError.getPosition().getNorm());
        maxShiftVError = FastMath.max(maxShiftVError, shiftError.getVelocity().getNorm());
        maxInterpolationVError = FastMath.max(maxInterpolationVError,
                interpolationError.getVelocity().getNorm());
    }
    Assert.assertTrue(maxShiftPError < 2500.0);
    Assert.assertTrue(maxInterpolationPError > 6000.0);
    Assert.assertTrue(maxShiftVError < 7.0);
    Assert.assertTrue(maxInterpolationVError > 170.0);

}

From source file:org.orekit.orbits.CircularOrbit.java

/** {@inheritDoc} */
protected TimeStampedPVCoordinates initPVCoordinates() {

    // get equinoctial parameters
    final double equEx = getEquinoctialEx();
    final double equEy = getEquinoctialEy();
    final double hx = getHx();
    final double hy = getHy();
    final double lE = getLE();

    // inclination-related intermediate parameters
    final double hx2 = hx * hx;
    final double hy2 = hy * hy;
    final double factH = 1. / (1 + hx2 + hy2);

    // reference axes defining the orbital plane
    final double ux = (1 + hx2 - hy2) * factH;
    final double uy = 2 * hx * hy * factH;
    final double uz = -2 * hy * factH;

    final double vx = uy;
    final double vy = (1 - hx2 + hy2) * factH;
    final double vz = 2 * hx * factH;

    // eccentricity-related intermediate parameters
    final double exey = equEx * equEy;
    final double ex2 = equEx * equEx;
    final double ey2 = equEy * equEy;
    final double e2 = ex2 + ey2;
    final double eta = 1 + FastMath.sqrt(1 - e2);
    final double beta = 1. / eta;

    // eccentric latitude argument
    final double cLe = FastMath.cos(lE);
    final double sLe = FastMath.sin(lE);
    final double exCeyS = equEx * cLe + equEy * sLe;

    // coordinates of position and velocity in the orbital plane
    final double x = a * ((1 - beta * ey2) * cLe + beta * exey * sLe - equEx);
    final double y = a * ((1 - beta * ex2) * sLe + beta * exey * cLe - equEy);

    final double factor = FastMath.sqrt(getMu() / a) / (1 - exCeyS);
    final double xdot = factor * (-sLe + beta * equEy * exCeyS);
    final double ydot = factor * (cLe - beta * equEx * exCeyS);

    final Vector3D position = new Vector3D(x * ux + y * vx, x * uy + y * vy, x * uz + y * vz);
    final double r2 = position.getNormSq();
    final Vector3D velocity = new Vector3D(xdot * ux + ydot * vx, xdot * uy + ydot * vy, xdot * uz + ydot * vz);
    final Vector3D acceleration = new Vector3D(-getMu() / (r2 * FastMath.sqrt(r2)), position);
    return new TimeStampedPVCoordinates(getDate(), position, velocity, acceleration);

}

From source file:org.orekit.orbits.CircularParametersTest.java

@Test
public void testAnomalyEll() {

    // elliptic orbit
    Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);

    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);

    CircularOrbit p = new CircularOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    KeplerianOrbit kep = new KeplerianOrbit(p);

    double e = p.getE();
    double eRatio = FastMath.sqrt((1 - e) / (1 + e));
    double raan = kep.getRightAscensionOfAscendingNode();
    double paPraan = kep.getPerigeeArgument() + raan;

    double lv = 1.1;
    // formulations for elliptic case
    double lE = 2 * FastMath.atan(eRatio * FastMath.tan((lv - paPraan) / 2)) + paPraan;
    double lM = lE - e * FastMath.sin(lE - paPraan);

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lv - raan, PositionAngle.TRUE, p.getFrame(), date, mu);
    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));
    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), 0, PositionAngle.TRUE, p.getFrame(), date, mu);

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lE - raan, PositionAngle.ECCENTRIC, p.getFrame(), date, mu);
    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));
    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), 0, PositionAngle.TRUE, p.getFrame(), date, mu);

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lM - raan, PositionAngle.MEAN, p.getFrame(), date, mu);
    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));

}

From source file:org.orekit.orbits.CircularParametersTest.java

@Test
public void testAnomalyCirc() {

    Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    CircularOrbit p = new CircularOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
    double raan = p.getRightAscensionOfAscendingNode();

    // circular orbit
    p = new CircularOrbit(p.getA(), 0, 0, p.getRightAscensionOfAscendingNode(), p.getAlphaV(), p.getAlphaV(),
            PositionAngle.TRUE, p.getFrame(), date, mu);

    double lv = 1.1;
    double lE = lv;
    double lM = lE;

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lv - raan, PositionAngle.TRUE, p.getFrame(), date, mu);
    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));
    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), 0, PositionAngle.TRUE, p.getFrame(), date, mu);

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lE - raan, PositionAngle.ECCENTRIC, p.getFrame(), date, mu);

    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));
    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), 0, PositionAngle.TRUE, p.getFrame(), date, mu);

    p = new CircularOrbit(p.getA(), p.getCircularEx(), p.getCircularEy(), p.getRightAscensionOfAscendingNode(),
            p.getAlphaV(), lM - raan, PositionAngle.MEAN, p.getFrame(), date, mu);
    Assert.assertEquals(p.getAlphaV() + raan, lv, Utils.epsilonAngle * FastMath.abs(lv));
    Assert.assertEquals(p.getAlphaE() + raan, lE, Utils.epsilonAngle * FastMath.abs(lE));
    Assert.assertEquals(p.getAlphaM() + raan, lM, Utils.epsilonAngle * FastMath.abs(lM));

}

From source file:org.orekit.orbits.CircularParametersTest.java

@Test
public void testNumericalIssue25() throws OrekitException {
    Vector3D position = new Vector3D(3782116.14107698, 416663.11924914, 5875541.62103057);
    Vector3D velocity = new Vector3D(-6349.7848910501, 288.4061811651, 4066.9366759691);
    CircularOrbit orbit = new CircularOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(),
            new AbsoluteDate("2004-01-01T23:00:00.000", TimeScalesFactory.getUTC()), 3.986004415E14);
    Assert.assertEquals(0.0, orbit.getE(), 2.0e-14);
}