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

Example 71 with Frame

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

the class TidalDisplacementTest method doTestDehant.

private void doTestDehant(final IERSConventions conventions, final boolean removePermanentDeformation, final boolean replaceModels, final double expectedDx, final double expectedDy, final double expectedDz, final double tolerance) throws OrekitException {
    Frame itrf = FramesFactory.getITRF(conventions, false);
    TimeScale ut1 = TimeScalesFactory.getUT1(conventions, false);
    final double re;
    final double sunEarthSystemMassRatio;
    final double earthMoonMassRatio;
    if (replaceModels) {
        // constants consistent with DEHANTTIDEINEL.F reference program
        // available at <ftp://tai.bipm.org/iers/conv2010/chapter7/dehanttideinel/>
        // and Copyright (C) 2008 IERS Conventions Center
        re = 6378136.6;
        final double massRatioSun = 332946.0482;
        final double massRatioMoon = 0.0123000371;
        sunEarthSystemMassRatio = massRatioSun * (1.0 / (1.0 + massRatioMoon));
        earthMoonMassRatio = 1.0 / massRatioMoon;
    } else {
        // constants consistent with IERS and JPL
        re = Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS;
        sunEarthSystemMassRatio = Constants.JPL_SSD_SUN_EARTH_PLUS_MOON_MASS_RATIO;
        earthMoonMassRatio = Constants.JPL_SSD_EARTH_MOON_MASS_RATIO;
    }
    // fake providers generating only the positions from the reference program test
    PVCoordinatesProvider fakeSun = (date, frame) -> new TimeStampedPVCoordinates(date, new Vector3D(137859926952.015, 54228127881.435, 23509422341.6960), Vector3D.ZERO, Vector3D.ZERO);
    PVCoordinatesProvider fakeMoon = (date, frame) -> new TimeStampedPVCoordinates(date, new Vector3D(-179996231.920342, -312468450.131567, -169288918.592160), Vector3D.ZERO, Vector3D.ZERO);
    TidalDisplacement td = new TidalDisplacement(re, sunEarthSystemMassRatio, earthMoonMassRatio, fakeSun, fakeMoon, conventions, removePermanentDeformation);
    FundamentalNutationArguments arguments = null;
    if (replaceModels) {
        try {
            // we override the official IERS conventions 2010 arguments with fake arguments matching DEHANTTIDEINEL.F code
            String regularArguments = "/assets/org/orekit/IERS-conventions/2010/nutation-arguments.txt";
            arguments = new FundamentalNutationArguments(conventions, ut1, IERSConventions.class.getResourceAsStream(regularArguments), regularArguments) {

                private static final long serialVersionUID = 20170913L;

                @Override
                public BodiesElements evaluateAll(final AbsoluteDate date) {
                    BodiesElements base = super.evaluateAll(date);
                    double fhr = date.getComponents(ut1).getTime().getSecondsInUTCDay() / 3600.0;
                    double t = base.getTC();
                    // Doodson fundamental arguments as per DEHANTTIDEINEL.F code
                    double s = 218.31664563 + (481267.88194 + (-0.0014663889 + (0.00000185139) * t) * t) * t;
                    double tau = fhr * 15 + 280.4606184 + (36000.7700536 + (0.00038793 + (-0.0000000258) * t) * t) * t - s;
                    double pr = (1.396971278 + (0.000308889 + (0.000000021 + (0.000000007) * t) * t) * t) * t;
                    double h = 280.46645 + (36000.7697489 + (0.00030322222 + (0.000000020 + (-0.00000000654) * t) * t) * t) * t;
                    double p = 83.35324312 + (4069.01363525 + (-0.01032172222 + (-0.0000124991 + (0.00000005263) * t) * t) * t) * t;
                    double zns = 234.95544499 + (1934.13626197 + (-0.00207561111 + (-0.00000213944 + (0.00000001650) * t) * t) * t) * t;
                    double ps = 282.93734098 + (1.71945766667 + (0.00045688889 + (-0.00000001778 + (-0.00000000334) * t) * t) * t) * t;
                    s += pr;
                    // rebuild Delaunay arguments from Doodson arguments, ignoring derivatives
                    return new BodiesElements(date, base.getTC(), FastMath.toRadians(s + tau), 0.0, FastMath.toRadians(s - p), 0.0, FastMath.toRadians(h - ps), 0.0, FastMath.toRadians(s + zns), 0.0, FastMath.toRadians(s - h), 0.0, FastMath.toRadians(-zns), 0.0, base.getLMe(), 0.0, base.getLVe(), 0.0, base.getLE(), 0.0, base.getLMa(), 0.0, base.getLJu(), 0.0, base.getLSa(), 0.0, base.getLUr(), 0.0, base.getLNe(), 0.0, base.getPa(), 0.0);
                }
            };
            // we override the official IERS conventions 2010 tides displacements with tides displacements matching DEHANTTIDEINEL.F code
            String table73a = "/tides/tab7.3a-Dehant.txt";
            Field diurnalCorrectionField = td.getClass().getDeclaredField("frequencyCorrectionDiurnal");
            diurnalCorrectionField.setAccessible(true);
            Method diurnalCorrectionGetter = IERSConventions.class.getDeclaredMethod("getTidalDisplacementFrequencyCorrectionDiurnal", String.class, Integer.TYPE, Integer.TYPE, Integer.TYPE, Integer.TYPE, Integer.TYPE);
            diurnalCorrectionGetter.setAccessible(true);
            diurnalCorrectionField.set(td, diurnalCorrectionGetter.invoke(null, table73a, 18, 15, 16, 17, 18));
        } catch (SecurityException | NoSuchMethodException | NoSuchFieldException | InvocationTargetException | IllegalArgumentException | IllegalAccessException e) {
            Assert.fail(e.getLocalizedMessage());
        }
    } else {
        arguments = conventions.getNutationArguments(ut1);
    }
    Vector3D fundamentalStationWettzell = new Vector3D(4075578.385, 931852.890, 4801570.154);
    AbsoluteDate date = new AbsoluteDate(2009, 4, 13, 0, 0, 0.0, ut1);
    Vector3D displacement = td.displacement(arguments.evaluateAll(date), itrf, fundamentalStationWettzell);
    Assert.assertEquals(expectedDx, displacement.getX(), tolerance);
    Assert.assertEquals(expectedDy, displacement.getY(), tolerance);
    Assert.assertEquals(expectedDz, displacement.getZ(), tolerance);
}

Example 72 with Frame

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

the class CartesianOrbitTest method testNonInertialFrame.

@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);
}

Example 73 with Frame

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

the class AngularIonosphericDelayModifier method modify.

@Override
public void modify(final EstimatedMeasurement<AngularAzEl> estimated) throws OrekitException {
    final AngularAzEl measure = estimated.getObservedMeasurement();
    final GroundStation station = measure.getStation();
    final SpacecraftState state = estimated.getStates()[0];
    final double delay = angularErrorIonosphericModel(station, state);
    // Delay is taken into account to shift the spacecraft position
    final double dt = delay / Constants.SPEED_OF_LIGHT;
    // Position of the spacecraft shifted of dt
    final SpacecraftState transitState = state.shiftedBy(-dt);
    // Update estimated value taking into account the ionospheric delay.
    final AbsoluteDate date = transitState.getDate();
    final Vector3D position = transitState.getPVCoordinates().getPosition();
    final Frame inertial = transitState.getFrame();
    // Elevation and azimuth in radians
    final double elevation = station.getBaseFrame().getElevation(position, inertial, date);
    final double baseAzimuth = station.getBaseFrame().getAzimuth(position, inertial, date);
    final double twoPiWrap = MathUtils.normalizeAngle(baseAzimuth, measure.getObservedValue()[0]) - baseAzimuth;
    final double azimuth = baseAzimuth + twoPiWrap;
    // Update estimated value taking into account the ionospheric delay.
    // Azimuth - elevation values
    estimated.setEstimatedValue(azimuth, elevation);
}

Example 74 with Frame

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

the class AngularTroposphericDelayModifier method modify.

@Override
public void modify(final EstimatedMeasurement<AngularAzEl> estimated) throws OrekitException {
    final AngularAzEl measure = estimated.getObservedMeasurement();
    final GroundStation station = measure.getStation();
    final SpacecraftState state = estimated.getStates()[0];
    final double delay = angularErrorTroposphericModel(station, state);
    // Delay is taken into account to shift the spacecraft position
    final double dt = delay / Constants.SPEED_OF_LIGHT;
    // Position of the spacecraft shifted of dt
    final SpacecraftState transitState = state.shiftedBy(-dt);
    // Update measurement value taking into account the ionospheric delay.
    final AbsoluteDate date = transitState.getDate();
    final Vector3D position = transitState.getPVCoordinates().getPosition();
    final Frame inertial = transitState.getFrame();
    // Elevation and azimuth in radians
    final double elevation = station.getBaseFrame().getElevation(position, inertial, date);
    final double baseAzimuth = station.getBaseFrame().getAzimuth(position, inertial, date);
    final double twoPiWrap = MathUtils.normalizeAngle(baseAzimuth, measure.getObservedValue()[0]) - baseAzimuth;
    final double azimuth = baseAzimuth + twoPiWrap;
    // Update estimated value taking into account the tropospheric delay.
    // Azimuth - elevation values
    estimated.setEstimatedValue(azimuth, elevation);
}

Example 75 with Frame

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

the class FieldEquinoctialOrbitTest method doTestNonInertialFrame.

private <T extends RealFieldElement<T>> void doTestNonInertialFrame(Field<T> field) throws IllegalArgumentException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    FieldVector3D<T> position = new FieldVector3D<>(zero.add(4512.9), zero.add(18260.), zero.add(-5127.));
    FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(134664.6), zero.add(90066.8), zero.add(72047.6));
    FieldPVCoordinates<T> FieldPVCoordinates = new FieldPVCoordinates<>(position, velocity);
    new FieldEquinoctialOrbit<>(FieldPVCoordinates, new Frame(FramesFactory.getEME2000(), Transform.IDENTITY, "non-inertial", false), date, mu);
}