Examples with Frame org.orekit.frames.Frame used on opensource projects

Example 81 with Frame

use of org.orekit.frames.Frame in project Orekit by CS-SI.

the class FieldKeplerianOrbitTest method doTestNonKeplerianHyperbolicDerivatives.

private <T extends RealFieldElement<T>> void doTestNonKeplerianHyperbolicDerivatives(final Field<T> field) throws OrekitException {
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, "2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final FieldVector3D<T> position = new FieldVector3D<>(field.getZero().add(224267911.905821), field.getZero().add(290251613.109399), field.getZero().add(45534292.777492));
    final FieldVector3D<T> velocity = new FieldVector3D<>(field.getZero().add(-1494.068165293), field.getZero().add(1124.771027677), field.getZero().add(526.915286134));
    final FieldVector3D<T> acceleration = new FieldVector3D<>(field.getZero().add(-0.001295920501), field.getZero().add(-0.002233045187), field.getZero().add(-0.000349906292));
    final TimeStampedFieldPVCoordinates<T> pv = new TimeStampedFieldPVCoordinates<>(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(pv, frame, mu);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getA()), orbit.getADot().getReal(), 9.6e-8);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEx()), orbit.getEquinoctialExDot().getReal(), 2.8e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEy()), orbit.getEquinoctialEyDot().getReal(), 3.6e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHx()), orbit.getHxDot().getReal(), 1.4e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHy()), orbit.getHyDot().getReal(), 9.4e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLv()), orbit.getLvDot().getReal(), 5.6e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLE()), orbit.getLEDot().getReal(), 9.0e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLM()), orbit.getLMDot().getReal(), 1.8e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getE()), orbit.getEDot().getReal(), 1.8e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getI()), orbit.getIDot().getReal(), 3.6e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getPerigeeArgument()), orbit.getPerigeeArgumentDot().getReal(), 9.4e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getRightAscensionOfAscendingNode()), orbit.getRightAscensionOfAscendingNodeDot().getReal(), 1.1e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getTrueAnomaly()), orbit.getTrueAnomalyDot().getReal(), 1.4e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEccentricAnomaly()), orbit.getEccentricAnomalyDot().getReal(), 9.2e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getMeanAnomaly()), orbit.getMeanAnomalyDot().getReal(), 1.4e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.TRUE)), orbit.getAnomalyDot(PositionAngle.TRUE).getReal(), 1.4e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.ECCENTRIC)), orbit.getAnomalyDot(PositionAngle.ECCENTRIC).getReal(), 9.2e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.MEAN)), orbit.getAnomalyDot(PositionAngle.MEAN).getReal(), 1.4e-15);
}

Example 82 with Frame

use of org.orekit.frames.Frame in project Orekit by CS-SI.

the class KeplerianOrbitTest method testNonInertialFrame.

@Test(expected = IllegalArgumentException.class)
public void testNonInertialFrame() throws IllegalArgumentException {
    Vector3D position = new Vector3D(-4947831., -3765382., -3708221.);
    Vector3D velocity = new Vector3D(-2079., 5291., -7842.);
    PVCoordinates pvCoordinates = new PVCoordinates(position, velocity);
    new KeplerianOrbit(pvCoordinates, new Frame(FramesFactory.getEME2000(), Transform.IDENTITY, "non-inertial", false), date, mu);
}

Example 83 with Frame

use of org.orekit.frames.Frame in project Orekit by CS-SI.

the class KeplerianOrbitTest method testPositionAngleDerivatives.

@Test
public void testPositionAngleDerivatives() 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 Vector3D acceleration = new Vector3D(-7.466182457944, -2.118153357345, 0.160004048437);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final KeplerianOrbit orbit = new KeplerianOrbit(pv, frame, mu);
    for (PositionAngle type : PositionAngle.values()) {
        final KeplerianOrbit rebuilt = new KeplerianOrbit(orbit.getA(), orbit.getE(), orbit.getI(), orbit.getPerigeeArgument(), orbit.getRightAscensionOfAscendingNode(), orbit.getAnomaly(type), orbit.getADot(), orbit.getEDot(), orbit.getIDot(), orbit.getPerigeeArgumentDot(), orbit.getRightAscensionOfAscendingNodeDot(), orbit.getAnomalyDot(type), type, orbit.getFrame(), orbit.getDate(), orbit.getMu());
        Assert.assertThat(rebuilt.getA(), relativelyCloseTo(orbit.getA(), 1));
        Assert.assertThat(rebuilt.getE(), relativelyCloseTo(orbit.getE(), 1));
        Assert.assertThat(rebuilt.getI(), relativelyCloseTo(orbit.getI(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgument(), relativelyCloseTo(orbit.getPerigeeArgument(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNode(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNode(), 1));
        Assert.assertThat(rebuilt.getADot(), relativelyCloseTo(orbit.getADot(), 1));
        Assert.assertThat(rebuilt.getEDot(), relativelyCloseTo(orbit.getEDot(), 1));
        Assert.assertThat(rebuilt.getIDot(), relativelyCloseTo(orbit.getIDot(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgumentDot(), relativelyCloseTo(orbit.getPerigeeArgumentDot(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNodeDot(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNodeDot(), 1));
        for (PositionAngle type2 : PositionAngle.values()) {
            Assert.assertThat(rebuilt.getAnomaly(type2), relativelyCloseTo(orbit.getAnomaly(type2), 1));
            Assert.assertThat(rebuilt.getAnomalyDot(type2), relativelyCloseTo(orbit.getAnomalyDot(type2), 1));
        }
    }
}

Example 84 with Frame

use of org.orekit.frames.Frame in project Orekit by CS-SI.

the class KeplerianOrbitTest method testPositionAngleHyperbolicDerivatives.

@Test
public void testPositionAngleHyperbolicDerivatives() throws OrekitException {
    final AbsoluteDate date = new AbsoluteDate("2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final Vector3D position = new Vector3D(224267911.905821, 290251613.109399, 45534292.777492);
    final Vector3D velocity = new Vector3D(-1494.068165293, 1124.771027677, 526.915286134);
    final Vector3D acceleration = new Vector3D(-0.001295920501, -0.002233045187, -0.000349906292);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final KeplerianOrbit orbit = new KeplerianOrbit(pv, frame, mu);
    for (PositionAngle type : PositionAngle.values()) {
        final KeplerianOrbit rebuilt = new KeplerianOrbit(orbit.getA(), orbit.getE(), orbit.getI(), orbit.getPerigeeArgument(), orbit.getRightAscensionOfAscendingNode(), orbit.getAnomaly(type), orbit.getADot(), orbit.getEDot(), orbit.getIDot(), orbit.getPerigeeArgumentDot(), orbit.getRightAscensionOfAscendingNodeDot(), orbit.getAnomalyDot(type), type, orbit.getFrame(), orbit.getDate(), orbit.getMu());
        Assert.assertThat(rebuilt.getA(), relativelyCloseTo(orbit.getA(), 1));
        Assert.assertThat(rebuilt.getE(), relativelyCloseTo(orbit.getE(), 1));
        Assert.assertThat(rebuilt.getI(), relativelyCloseTo(orbit.getI(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgument(), relativelyCloseTo(orbit.getPerigeeArgument(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNode(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNode(), 1));
        Assert.assertThat(rebuilt.getADot(), relativelyCloseTo(orbit.getADot(), 1));
        Assert.assertThat(rebuilt.getEDot(), relativelyCloseTo(orbit.getEDot(), 1));
        Assert.assertThat(rebuilt.getIDot(), relativelyCloseTo(orbit.getIDot(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgumentDot(), relativelyCloseTo(orbit.getPerigeeArgumentDot(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNodeDot(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNodeDot(), 1));
        for (PositionAngle type2 : PositionAngle.values()) {
            Assert.assertThat(rebuilt.getAnomaly(type2), relativelyCloseTo(orbit.getAnomaly(type2), 2));
            Assert.assertThat(rebuilt.getAnomalyDot(type2), relativelyCloseTo(orbit.getAnomalyDot(type2), 4));
        }
    }
}

Example 85 with Frame

use of org.orekit.frames.Frame in project Orekit by CS-SI.

the class KeplerianOrbitTest method testNonKeplerianEllipticDerivatives.

@Test
public void testNonKeplerianEllipticDerivatives() 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 Vector3D acceleration = new Vector3D(-7.466182457944, -2.118153357345, 0.160004048437);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final KeplerianOrbit orbit = new KeplerianOrbit(pv, frame, mu);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getA()), orbit.getADot(), 4.3e-8);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEx()), orbit.getEquinoctialExDot(), 2.1e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEquinoctialEy()), orbit.getEquinoctialEyDot(), 5.3e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHx()), orbit.getHxDot(), 1.6e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getHy()), orbit.getHyDot(), 7.3e-17);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLv()), orbit.getLvDot(), 1.1e-14);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLE()), orbit.getLEDot(), 7.2e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getLM()), orbit.getLMDot(), 4.7e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getE()), orbit.getEDot(), 6.9e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getI()), orbit.getIDot(), 5.8e-16);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getPerigeeArgument()), orbit.getPerigeeArgumentDot(), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getRightAscensionOfAscendingNode()), orbit.getRightAscensionOfAscendingNodeDot(), 1.5e-15);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getTrueAnomaly()), orbit.getTrueAnomalyDot(), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getEccentricAnomaly()), orbit.getEccentricAnomalyDot(), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getMeanAnomaly()), orbit.getMeanAnomalyDot(), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.TRUE)), orbit.getAnomalyDot(PositionAngle.TRUE), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.ECCENTRIC)), orbit.getAnomalyDot(PositionAngle.ECCENTRIC), 1.5e-12);
    Assert.assertEquals(differentiate(pv, frame, mu, shifted -> shifted.getAnomaly(PositionAngle.MEAN)), orbit.getAnomalyDot(PositionAngle.MEAN), 1.5e-12);
}