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

Example 71 with PVCoordinates

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

the class ConstantThrustManeuverTest method RealFieldExpectErrorTest.

/**
 *Same test as the previous one but not adding the ForceModel to the NumericalPropagator
 *    it is a test to validate the previous test.
 *    (to test if the ForceModel it's actually
 *    doing something in the Propagator and the FieldPropagator)
 */
@Test
public void RealFieldExpectErrorTest() throws OrekitException {
    DSFactory factory = new DSFactory(6, 0);
    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.setInitialState(iSR);
    final ConstantThrustManeuver forceModel = new ConstantThrustManeuver(J2000.toAbsoluteDate().shiftedBy(100), 100.0, 400.0, 300.0, Vector3D.PLUS_K);
    FNP.addForceModel(forceModel);
    // NOT ADDING THE FORCE MODEL TO THE NUMERICAL PROPAGATOR   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.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getX() - finPVC_R.getPosition().getX()) < FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
    Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getY() - finPVC_R.getPosition().getY()) < FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
    Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getZ() - finPVC_R.getPosition().getZ()) < FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
}

Example 72 with PVCoordinates

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

the class SmallManeuverAnalyticalModelTest method testLowEarthOrbit1.

@Test
public void testLowEarthOrbit1() throws OrekitException {
    Orbit leo = new CircularOrbit(7200000.0, -1.0e-5, 2.0e-4, FastMath.toRadians(98.0), FastMath.toRadians(123.456), 0.0, PositionAngle.MEAN, FramesFactory.getEME2000(), new AbsoluteDate(new DateComponents(2004, 01, 01), new TimeComponents(23, 30, 00.000), TimeScalesFactory.getUTC()), Constants.EIGEN5C_EARTH_MU);
    double mass = 5600.0;
    AbsoluteDate t0 = leo.getDate().shiftedBy(1000.0);
    Vector3D dV = new Vector3D(-0.01, 0.02, 0.03);
    double f = 20.0;
    double isp = 315.0;
    BoundedPropagator withoutManeuver = getEphemeris(leo, mass, t0, Vector3D.ZERO, f, isp);
    BoundedPropagator withManeuver = getEphemeris(leo, mass, t0, dV, f, isp);
    SmallManeuverAnalyticalModel model = new SmallManeuverAnalyticalModel(withoutManeuver.propagate(t0), dV, isp);
    Assert.assertEquals(t0, model.getDate());
    for (AbsoluteDate t = withoutManeuver.getMinDate(); t.compareTo(withoutManeuver.getMaxDate()) < 0; t = t.shiftedBy(60.0)) {
        PVCoordinates pvWithout = withoutManeuver.getPVCoordinates(t, leo.getFrame());
        PVCoordinates pvWith = withManeuver.getPVCoordinates(t, leo.getFrame());
        PVCoordinates pvModel = model.apply(withoutManeuver.propagate(t)).getPVCoordinates(leo.getFrame());
        double nominalDeltaP = new PVCoordinates(pvWith, pvWithout).getPosition().getNorm();
        double modelError = new PVCoordinates(pvWith, pvModel).getPosition().getNorm();
        if (t.compareTo(t0) < 0) {
            // before maneuver, all positions should be equal
            Assert.assertEquals(0, nominalDeltaP, 1.0e-10);
            Assert.assertEquals(0, modelError, 1.0e-10);
        } else {
            // despite nominal deltaP exceeds 1 kilometer after less than 3 orbits
            if (t.durationFrom(t0) > 0.1 * leo.getKeplerianPeriod()) {
                Assert.assertTrue(modelError < 0.009 * nominalDeltaP);
            }
            Assert.assertTrue(modelError < 0.8);
        }
    }
}

Example 73 with PVCoordinates

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

the class SmallManeuverAnalyticalModelTest method testEccentricOrbit.

@Test
public void testEccentricOrbit() throws OrekitException {
    Orbit heo = new KeplerianOrbit(90000000.0, 0.92, FastMath.toRadians(98.0), FastMath.toRadians(12.3456), FastMath.toRadians(123.456), FastMath.toRadians(1.23456), PositionAngle.MEAN, FramesFactory.getEME2000(), new AbsoluteDate(new DateComponents(2004, 01, 01), new TimeComponents(23, 30, 00.000), TimeScalesFactory.getUTC()), Constants.EIGEN5C_EARTH_MU);
    double mass = 5600.0;
    AbsoluteDate t0 = heo.getDate().shiftedBy(1000.0);
    Vector3D dV = new Vector3D(-0.01, 0.02, 0.03);
    double f = 20.0;
    double isp = 315.0;
    BoundedPropagator withoutManeuver = getEphemeris(heo, mass, t0, Vector3D.ZERO, f, isp);
    BoundedPropagator withManeuver = getEphemeris(heo, mass, t0, dV, f, isp);
    SmallManeuverAnalyticalModel model = new SmallManeuverAnalyticalModel(withoutManeuver.propagate(t0), dV, isp);
    Assert.assertEquals(t0, model.getDate());
    for (AbsoluteDate t = withoutManeuver.getMinDate(); t.compareTo(withoutManeuver.getMaxDate()) < 0; t = t.shiftedBy(600.0)) {
        PVCoordinates pvWithout = withoutManeuver.getPVCoordinates(t, heo.getFrame());
        PVCoordinates pvWith = withManeuver.getPVCoordinates(t, heo.getFrame());
        PVCoordinates pvModel = model.apply(withoutManeuver.propagate(t)).getPVCoordinates(heo.getFrame());
        double nominalDeltaP = new PVCoordinates(pvWith, pvWithout).getPosition().getNorm();
        double modelError = new PVCoordinates(pvWith, pvModel).getPosition().getNorm();
        if (t.compareTo(t0) < 0) {
            // before maneuver, all positions should be equal
            Assert.assertEquals(0, nominalDeltaP, 1.0e-10);
            Assert.assertEquals(0, modelError, 1.0e-10);
        } else {
            // despite nominal deltaP exceeds 300 kilometers at perigee, after 3 orbits
            if (t.durationFrom(t0) > 0.01 * heo.getKeplerianPeriod()) {
                Assert.assertTrue(modelError < 0.005 * nominalDeltaP);
            }
            Assert.assertTrue(modelError < 1700);
        }
    }
}

Example 74 with PVCoordinates

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

the class SolarRadiationPressureTest method testParameterDerivativeIsotropicSingle.

@Test
public void testParameterDerivativeIsotropicSingle() throws OrekitException {
    final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
    final Vector3D vel = new Vector3D(2.14718074509906819e+03, 7.38239351251748485e+03, -1.14097953925384523e+01);
    final SpacecraftState state = new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel), FramesFactory.getGCRF(), new AbsoluteDate(2003, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()), Constants.EIGEN5C_EARTH_MU));
    RadiationSensitive rs = new IsotropicRadiationSingleCoefficient(2.5, 0.7);
    SolarRadiationPressure forceModel = new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, rs);
    checkParameterDerivative(state, forceModel, RadiationSensitive.REFLECTION_COEFFICIENT, 1.0, 2.0e-15);
    try {
        rs.radiationPressureAcceleration(state.getDate(), state.getFrame(), state.getPVCoordinates().getPosition(), state.getAttitude().getRotation(), state.getMass(), Vector3D.ZERO, new double[2], RadiationSensitive.ABSORPTION_COEFFICIENT);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, oe.getSpecifier());
    }
    for (ParameterDriver driver : rs.getRadiationParametersDrivers()) {
        Assert.assertEquals(RadiationSensitive.REFLECTION_COEFFICIENT, driver.getName());
    }
}

Example 75 with PVCoordinates

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

the class TIRFProviderTest method testAASReferenceGEO.

@Test
public void testAASReferenceGEO() throws OrekitException {
    // this reference test has been extracted from the following paper:
    // Implementation Issues Surrounding the New IAU Reference Systems for Astrodynamics
    // David A. Vallado, John H. Seago, P. Kenneth Seidelmann
    // http://www.centerforspace.com/downloads/files/pubs/AAS-06-134.pdf
    Utils.setLoaders(IERSConventions.IERS_2010, Utils.buildEOPList(IERSConventions.IERS_2010, ITRFVersion.ITRF_2008, new double[][] { { 53153, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53154, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53155, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53156, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53157, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53158, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53159, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 }, { 53160, -0.4709050, 0.0000000, -0.083853, 0.467217, Double.NaN, Double.NaN, -0.000199, -0.000252 } }));
    AbsoluteDate t0 = new AbsoluteDate(new DateComponents(2004, 06, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    // Positions GEO
    Frame itrfA = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    PVCoordinates pvITRF = new PVCoordinates(new Vector3D(24796919.2915, -34115870.9234, 10226.0621), new Vector3D(-0.979178, -1.476538, -0.928776));
    Frame tirf = FramesFactory.getTIRF(IERSConventions.IERS_2010);
    PVCoordinates pvTIRF = new PVCoordinates(new Vector3D(24796919.2953, -34115870.9004, 10293.2583), new Vector3D(-0.979178, -1.476540, -0.928772));
    checkPV(pvTIRF, itrfA.getTransformTo(tirf, t0).transformPVCoordinates(pvITRF), 5.697e-5, 4.69e-7);
    Frame cirf = FramesFactory.getCIRF(IERSConventions.IERS_2010, true);
    PVCoordinates pvCIRF = new PVCoordinates(new Vector3D(-40588158.1236, -11462167.0709, 10293.2583), new Vector3D(834.787843, -2958.305669, -0.928772));
    checkPV(pvCIRF, tirf.getTransformTo(cirf, t0).transformPVCoordinates(pvTIRF), 0.0505, 3.60e-6);
}