Examples with PositionAngle org.orekit.orbits.PositionAngle used on opensource projects

Example 16 with PositionAngle

use of org.orekit.orbits.PositionAngle in project Orekit by CS-SI.

the class PartialDerivativesTest method testPropagationTypesElliptical.

@Test
public void testPropagationTypesElliptical() throws OrekitException {
    NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(5, 5);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider);
    Orbit initialOrbit = new KeplerianOrbit(8000000.0, 0.01, 0.1, 0.7, 0, 1.2, PositionAngle.TRUE, FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, provider.getMu());
    double dt = 900;
    double dP = 0.001;
    for (OrbitType orbitType : OrbitType.values()) {
        for (PositionAngle angleType : PositionAngle.values()) {
            // compute state Jacobian using PartialDerivatives
            NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, orbitType, angleType, gravityField);
            PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
            final SpacecraftState initialState = partials.setInitialJacobians(new SpacecraftState(initialOrbit));
            propagator.setInitialState(initialState);
            final JacobiansMapper mapper = partials.getMapper();
            PickUpHandler pickUp = new PickUpHandler(mapper, null);
            propagator.setMasterMode(pickUp);
            propagator.propagate(initialState.getDate().shiftedBy(dt));
            double[][] dYdY0 = pickUp.getdYdY0();
            // compute reference state Jacobian using finite differences
            double[][] dYdY0Ref = new double[6][6];
            AbstractIntegratedPropagator propagator2 = setUpPropagator(initialOrbit, dP, orbitType, angleType, gravityField);
            double[] steps = NumericalPropagator.tolerances(1000000 * dP, initialOrbit, orbitType)[0];
            for (int i = 0; i < 6; ++i) {
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -4 * steps[i], i));
                SpacecraftState sM4h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -3 * steps[i], i));
                SpacecraftState sM3h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -2 * steps[i], i));
                SpacecraftState sM2h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -1 * steps[i], i));
                SpacecraftState sM1h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 1 * steps[i], i));
                SpacecraftState sP1h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 2 * steps[i], i));
                SpacecraftState sP2h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 3 * steps[i], i));
                SpacecraftState sP3h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 4 * steps[i], i));
                SpacecraftState sP4h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                fillJacobianColumn(dYdY0Ref, i, orbitType, angleType, steps[i], sM4h, sM3h, sM2h, sM1h, sP1h, sP2h, sP3h, sP4h);
            }
            for (int i = 0; i < 6; ++i) {
                for (int j = 0; j < 6; ++j) {
                    double error = FastMath.abs((dYdY0[i][j] - dYdY0Ref[i][j]) / dYdY0Ref[i][j]);
                    Assert.assertEquals(0, error, 6.0e-2);
                }
            }
        }
    }
}

Example 17 with PositionAngle

use of org.orekit.orbits.PositionAngle in project Orekit by CS-SI.

the class PartialDerivativesTest method testPropagationTypesHyperbolic.

@Test
public void testPropagationTypesHyperbolic() throws OrekitException {
    NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(5, 5);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider);
    Orbit initialOrbit = new KeplerianOrbit(new PVCoordinates(new Vector3D(-1551946.0, 708899.0, 6788204.0), new Vector3D(-9875.0, -3941.0, -1845.0)), FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, provider.getMu());
    double dt = 900;
    double dP = 0.001;
    for (OrbitType orbitType : new OrbitType[] { OrbitType.KEPLERIAN, OrbitType.CARTESIAN }) {
        for (PositionAngle angleType : PositionAngle.values()) {
            // compute state Jacobian using PartialDerivatives
            NumericalPropagator propagator = setUpPropagator(initialOrbit, dP, orbitType, angleType, gravityField);
            PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
            final SpacecraftState initialState = partials.setInitialJacobians(new SpacecraftState(initialOrbit));
            propagator.setInitialState(initialState);
            final JacobiansMapper mapper = partials.getMapper();
            PickUpHandler pickUp = new PickUpHandler(mapper, null);
            propagator.setMasterMode(pickUp);
            propagator.propagate(initialState.getDate().shiftedBy(dt));
            double[][] dYdY0 = pickUp.getdYdY0();
            // compute reference state Jacobian using finite differences
            double[][] dYdY0Ref = new double[6][6];
            AbstractIntegratedPropagator propagator2 = setUpPropagator(initialOrbit, dP, orbitType, angleType, gravityField);
            double[] steps = NumericalPropagator.tolerances(1000000 * dP, initialOrbit, orbitType)[0];
            for (int i = 0; i < 6; ++i) {
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -4 * steps[i], i));
                SpacecraftState sM4h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -3 * steps[i], i));
                SpacecraftState sM3h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -2 * steps[i], i));
                SpacecraftState sM2h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, -1 * steps[i], i));
                SpacecraftState sM1h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 1 * steps[i], i));
                SpacecraftState sP1h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 2 * steps[i], i));
                SpacecraftState sP2h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 3 * steps[i], i));
                SpacecraftState sP3h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                propagator2.resetInitialState(shiftState(initialState, orbitType, angleType, 4 * steps[i], i));
                SpacecraftState sP4h = propagator2.propagate(initialState.getDate().shiftedBy(dt));
                fillJacobianColumn(dYdY0Ref, i, orbitType, angleType, steps[i], sM4h, sM3h, sM2h, sM1h, sP1h, sP2h, sP3h, sP4h);
            }
            for (int i = 0; i < 6; ++i) {
                for (int j = 0; j < 6; ++j) {
                    double error = FastMath.abs((dYdY0[i][j] - dYdY0Ref[i][j]) / dYdY0Ref[i][j]);
                    Assert.assertEquals(0, error, 1.0e-3);
                }
            }
        }
    }
}

Example 18 with PositionAngle

use of org.orekit.orbits.PositionAngle in project Orekit by CS-SI.

the class OrbitDetermination method createOrbit.

/**
 * Create an orbit from input parameters
 * @param parser input file parser
 * @param mu     central attraction coefficient
 * @throws NoSuchElementException if input parameters are missing
 * @throws OrekitException if inertial frame cannot be created
 */
private Orbit createOrbit(final KeyValueFileParser<ParameterKey> parser, final double mu) throws NoSuchElementException, OrekitException {
    final Frame frame;
    if (!parser.containsKey(ParameterKey.INERTIAL_FRAME)) {
        frame = FramesFactory.getEME2000();
    } else {
        frame = parser.getInertialFrame(ParameterKey.INERTIAL_FRAME);
    }
    // Orbit definition
    PositionAngle angleType = PositionAngle.MEAN;
    if (parser.containsKey(ParameterKey.ORBIT_ANGLE_TYPE)) {
        angleType = PositionAngle.valueOf(parser.getString(ParameterKey.ORBIT_ANGLE_TYPE).toUpperCase());
    }
    if (parser.containsKey(ParameterKey.ORBIT_KEPLERIAN_A)) {
        return new KeplerianOrbit(parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_A), parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_E), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_I), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_PA), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_RAAN), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_ANOMALY), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_EQUINOCTIAL_A)) {
        return new EquinoctialOrbit(parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_A), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EY), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HY), parser.getAngle(ParameterKey.ORBIT_EQUINOCTIAL_LAMBDA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_CIRCULAR_A)) {
        return new CircularOrbit(parser.getDouble(ParameterKey.ORBIT_CIRCULAR_A), parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EX), parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EY), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_I), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_RAAN), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_ALPHA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_TLE_LINE_1)) {
        final String line1 = parser.getString(ParameterKey.ORBIT_TLE_LINE_1);
        final String line2 = parser.getString(ParameterKey.ORBIT_TLE_LINE_2);
        final TLE tle = new TLE(line1, line2);
        TLEPropagator propagator = TLEPropagator.selectExtrapolator(tle);
        // propagator.setEphemerisMode();
        AbsoluteDate initDate = tle.getDate();
        SpacecraftState initialState = propagator.getInitialState();
        // Transformation from TEME to frame.
        return new CartesianOrbit(initialState.getPVCoordinates(FramesFactory.getEME2000()), frame, initDate, mu);
    } else {
        final double[] pos = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PX), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PY), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PZ) };
        final double[] vel = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VX), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VY), parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VZ) };
        return new CartesianOrbit(new PVCoordinates(new Vector3D(pos), new Vector3D(vel)), frame, parser.getDate(ParameterKey.ORBIT_DATE, TimeScalesFactory.getUTC()), mu);
    }
}

Example 19 with PositionAngle

use of org.orekit.orbits.PositionAngle in project Orekit by CS-SI.

the class DSSTPropagation method createOrbit.

/**
 * Create an orbit from input parameters
 * @param parser input file parser
 * @param scale  time scale
 * @param mu     central attraction coefficient
 * @throws OrekitException if inertial frame cannot be retrieved
 * @throws NoSuchElementException if input parameters are missing
 * @throws IOException if input parameters are invalid
 */
private Orbit createOrbit(final KeyValueFileParser<ParameterKey> parser, final TimeScale scale, final double mu) throws OrekitException, NoSuchElementException, IOException {
    final Frame frame;
    if (!parser.containsKey(ParameterKey.INERTIAL_FRAME)) {
        frame = FramesFactory.getEME2000();
    } else {
        frame = parser.getInertialFrame(ParameterKey.INERTIAL_FRAME);
    }
    // Orbit definition
    Orbit orbit;
    PositionAngle angleType = PositionAngle.MEAN;
    if (parser.containsKey(ParameterKey.ORBIT_ANGLE_TYPE)) {
        angleType = PositionAngle.valueOf(parser.getString(ParameterKey.ORBIT_ANGLE_TYPE).toUpperCase());
    }
    if (parser.containsKey(ParameterKey.ORBIT_KEPLERIAN_A)) {
        orbit = new KeplerianOrbit(parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_A) * 1000., parser.getDouble(ParameterKey.ORBIT_KEPLERIAN_E), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_I), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_PA), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_RAAN), parser.getAngle(ParameterKey.ORBIT_KEPLERIAN_ANOMALY), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, scale), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_EQUINOCTIAL_A)) {
        orbit = new EquinoctialOrbit(parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_A) * 1000., parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_EY), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HX), parser.getDouble(ParameterKey.ORBIT_EQUINOCTIAL_HY), parser.getAngle(ParameterKey.ORBIT_EQUINOCTIAL_LAMBDA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, scale), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_CIRCULAR_A)) {
        orbit = new CircularOrbit(parser.getDouble(ParameterKey.ORBIT_CIRCULAR_A) * 1000., parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EX), parser.getDouble(ParameterKey.ORBIT_CIRCULAR_EY), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_I), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_RAAN), parser.getAngle(ParameterKey.ORBIT_CIRCULAR_ALPHA), angleType, frame, parser.getDate(ParameterKey.ORBIT_DATE, scale), mu);
    } else if (parser.containsKey(ParameterKey.ORBIT_CARTESIAN_PX)) {
        final double[] pos = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PX) * 1000., parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PY) * 1000., parser.getDouble(ParameterKey.ORBIT_CARTESIAN_PZ) * 1000. };
        final double[] vel = { parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VX) * 1000., parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VY) * 1000., parser.getDouble(ParameterKey.ORBIT_CARTESIAN_VZ) * 1000. };
        orbit = new CartesianOrbit(new PVCoordinates(new Vector3D(pos), new Vector3D(vel)), frame, parser.getDate(ParameterKey.ORBIT_DATE, scale), mu);
    } else {
        throw new IOException("Orbit definition is incomplete.");
    }
    return orbit;
}