Examples with OneAxisEllipsoid org.orekit.bodies.OneAxisEllipsoid used on opensource projects

Example 21 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class DSSTPropagation method setForceModel.

/**
 * Set DSST propagator force models
 *
 *  @param parser input file parser
 *  @param unnormalized spherical harmonics provider
 *  @param earthFrame Earth rotating frame
 *  @param rotationRate central body rotation rate (rad/s)
 *  @param dsstProp DSST propagator
 *  @throws IOException
 *  @throws OrekitException
 */
private void setForceModel(final KeyValueFileParser<ParameterKey> parser, final UnnormalizedSphericalHarmonicsProvider unnormalized, final Frame earthFrame, final double rotationRate, final DSSTPropagator dsstProp) throws IOException, OrekitException {
    final double ae = unnormalized.getAe();
    final int degree = parser.getInt(ParameterKey.CENTRAL_BODY_DEGREE);
    final int order = parser.getInt(ParameterKey.CENTRAL_BODY_ORDER);
    if (order > degree) {
        throw new IOException("Potential order cannot be higher than potential degree");
    }
    // Central Body Force Model with un-normalized coefficients
    dsstProp.addForceModel(new DSSTZonal(unnormalized, parser.getInt(ParameterKey.MAX_DEGREE_ZONAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_ECCENTRICITY_POWER_ZONAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_FREQUENCY_TRUE_LONGITUDE_ZONAL_SHORT_PERIODS)));
    dsstProp.addForceModel(new DSSTTesseral(earthFrame, rotationRate, unnormalized, parser.getInt(ParameterKey.MAX_DEGREE_TESSERAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_ORDER_TESSERAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_ECCENTRICITY_POWER_TESSERAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_FREQUENCY_MEAN_LONGITUDE_TESSERAL_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_DEGREE_TESSERAL_M_DAILIES_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_ORDER_TESSERAL_M_DAILIES_SHORT_PERIODS), parser.getInt(ParameterKey.MAX_ECCENTRICITY_POWER_TESSERAL_M_DAILIES_SHORT_PERIODS)));
    // 3rd body (SUN)
    if (parser.containsKey(ParameterKey.THIRD_BODY_SUN) && parser.getBoolean(ParameterKey.THIRD_BODY_SUN)) {
        dsstProp.addForceModel(new DSSTThirdBody(CelestialBodyFactory.getSun()));
    }
    // 3rd body (MOON)
    if (parser.containsKey(ParameterKey.THIRD_BODY_MOON) && parser.getBoolean(ParameterKey.THIRD_BODY_MOON)) {
        dsstProp.addForceModel(new DSSTThirdBody(CelestialBodyFactory.getMoon()));
    }
    // Drag
    if (parser.containsKey(ParameterKey.DRAG) && parser.getBoolean(ParameterKey.DRAG)) {
        final OneAxisEllipsoid earth = new OneAxisEllipsoid(ae, Constants.WGS84_EARTH_FLATTENING, earthFrame);
        final Atmosphere atm = new HarrisPriester(CelestialBodyFactory.getSun(), earth, 6);
        dsstProp.addForceModel(new DSSTAtmosphericDrag(atm, parser.getDouble(ParameterKey.DRAG_CD), parser.getDouble(ParameterKey.DRAG_SF)));
    }
    // Solar Radiation Pressure
    if (parser.containsKey(ParameterKey.SOLAR_RADIATION_PRESSURE) && parser.getBoolean(ParameterKey.SOLAR_RADIATION_PRESSURE)) {
        dsstProp.addForceModel(new DSSTSolarRadiationPressure(parser.getDouble(ParameterKey.SOLAR_RADIATION_PRESSURE_CR), parser.getDouble(ParameterKey.SOLAR_RADIATION_PRESSURE_SF), CelestialBodyFactory.getSun(), ae));
    }
}

Example 22 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class SolarRadiationPressureTest method testRoughOrbitalModifs.

@Test
public void testRoughOrbitalModifs() throws ParseException, OrekitException, FileNotFoundException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 7, 1), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    Orbit orbit = new EquinoctialOrbit(42164000, 10e-3, 10e-3, FastMath.tan(0.001745329) * FastMath.cos(2 * FastMath.PI / 3), FastMath.tan(0.001745329) * FastMath.sin(2 * FastMath.PI / 3), 0.1, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    final double period = orbit.getKeplerianPeriod();
    Assert.assertEquals(86164, period, 1);
    PVCoordinatesProvider sun = CelestialBodyFactory.getSun();
    // creation of the force model
    OneAxisEllipsoid earth = new OneAxisEllipsoid(6378136.46, 1.0 / 298.25765, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    SolarRadiationPressure SRP = new SolarRadiationPressure(sun, earth.getEquatorialRadius(), new IsotropicRadiationCNES95Convention(500.0, 0.7, 0.7));
    // creation of the propagator
    double[] absTolerance = { 0.1, 1.0e-9, 1.0e-9, 1.0e-5, 1.0e-5, 1.0e-5, 0.001 };
    double[] relTolerance = { 1.0e-4, 1.0e-4, 1.0e-4, 1.0e-6, 1.0e-6, 1.0e-6, 1.0e-7 };
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(900.0, 60000, absTolerance, relTolerance);
    integrator.setInitialStepSize(3600);
    final NumericalPropagator calc = new NumericalPropagator(integrator);
    calc.addForceModel(SRP);
    // Step Handler
    calc.setMasterMode(FastMath.floor(period), new SolarStepHandler());
    AbsoluteDate finalDate = date.shiftedBy(10 * period);
    calc.setInitialState(new SpacecraftState(orbit, 1500.0));
    calc.propagate(finalDate);
    Assert.assertTrue(calc.getCalls() < 7100);
}

Example 23 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class TopocentricFrameTest method testIssue145.

@Test
public void testIssue145() throws OrekitException {
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
    TopocentricFrame staFrame = new TopocentricFrame(earth, new GeodeticPoint(0.0, 0.0, 0.0), "test");
    GeodeticPoint gp = staFrame.computeLimitVisibilityPoint(Constants.WGS84_EARTH_EQUATORIAL_RADIUS + 600000, 0.0, FastMath.toRadians(5.0));
    Assert.assertEquals(0.0, gp.getLongitude(), 1.0e-15);
    Assert.assertTrue(gp.getLatitude() > 0);
    Assert.assertEquals(0.0, staFrame.getNorth().distance(Vector3D.PLUS_K), 1.0e-15);
}

Example 24 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class TopocentricFrameTest method testPointAtDistance.

@Test
public void testPointAtDistance() throws OrekitException {
    RandomGenerator random = new Well1024a(0xa1e6bd5cd0578779l);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
    final AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
    for (int i = 0; i < 20; ++i) {
        // we don't need uniform point on the sphere, just a few different test configurations
        double latitude = FastMath.PI * (0.5 - random.nextDouble());
        double longitude = 2 * FastMath.PI * random.nextDouble();
        TopocentricFrame topo = new TopocentricFrame(earth, new GeodeticPoint(latitude, longitude, 0.0), "topo");
        Transform transform = earth.getBodyFrame().getTransformTo(topo, date);
        for (int j = 0; j < 20; ++j) {
            double elevation = FastMath.PI * (0.5 - random.nextDouble());
            double azimuth = 2 * FastMath.PI * random.nextDouble();
            double range = 500000.0 * (1.0 + random.nextDouble());
            Vector3D absolutePoint = earth.transform(topo.pointAtDistance(azimuth, elevation, range));
            Vector3D relativePoint = transform.transformPosition(absolutePoint);
            double rebuiltElevation = topo.getElevation(relativePoint, topo, AbsoluteDate.J2000_EPOCH);
            double rebuiltAzimuth = topo.getAzimuth(relativePoint, topo, AbsoluteDate.J2000_EPOCH);
            double rebuiltRange = topo.getRange(relativePoint, topo, AbsoluteDate.J2000_EPOCH);
            Assert.assertEquals(elevation, rebuiltElevation, 1.0e-12);
            Assert.assertEquals(azimuth, MathUtils.normalizeAngle(rebuiltAzimuth, azimuth), 1.0e-12);
            Assert.assertEquals(range, rebuiltRange, 1.0e-12 * range);
        }
    }
}

Example 25 with OneAxisEllipsoid

use of org.orekit.bodies.OneAxisEllipsoid in project Orekit by CS-SI.

the class TopocentricFrameTest method testEllipticEarth.

@Test
public void testEllipticEarth() throws OrekitException {
    // Elliptic earth shape
    final OneAxisEllipsoid earthElliptic = new OneAxisEllipsoid(6378136.460, 1 / 298.257222101, itrf);
    // Satellite point
    // Caution !!! Sat point target shall be the same whatever earth shape chosen !!
    final GeodeticPoint satPointGeo = new GeodeticPoint(FastMath.toRadians(30.), FastMath.toRadians(15.), 800000.);
    final Vector3D satPoint = earthElliptic.transform(satPointGeo);
    // ****************************
    // Test at equatorial position
    // ****************************
    GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(0.), FastMath.toRadians(5.), 0.);
    TopocentricFrame topoElliptic = new TopocentricFrame(earthElliptic, point, "elliptic, equatorial lon 5");
    TopocentricFrame topoSpheric = new TopocentricFrame(earthSpheric, point, "spheric, equatorial lon 5");
    // Compare azimuth/elevation/range of satellite point : shall be strictly identical
    // ***************************************************
    double aziElli = topoElliptic.getAzimuth(satPoint, earthElliptic.getBodyFrame(), date);
    double aziSphe = topoSpheric.getAzimuth(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(aziElli, aziSphe, Utils.epsilonAngle);
    double eleElli = topoElliptic.getElevation(satPoint, earthElliptic.getBodyFrame(), date);
    double eleSphe = topoSpheric.getElevation(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(eleElli, eleSphe, Utils.epsilonAngle);
    double disElli = topoElliptic.getRange(satPoint, earthElliptic.getBodyFrame(), date);
    double disSphe = topoSpheric.getRange(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(disElli, disSphe, Utils.epsilonTest);
    // Infinite point separated by -20 deg in longitude
    // *************************************************
    GeodeticPoint infPointGeo = new GeodeticPoint(FastMath.toRadians(0.), FastMath.toRadians(-15.), 1000000000.);
    Vector3D infPoint = earthElliptic.transform(infPointGeo);
    // Azimuth = pi/2
    aziElli = topoElliptic.getAzimuth(infPoint, earthElliptic.getBodyFrame(), date);
    Assert.assertEquals(3 * FastMath.PI / 2., aziElli, Utils.epsilonAngle);
    // Site = pi/2 - longitude difference
    eleElli = topoElliptic.getElevation(infPoint, earthElliptic.getBodyFrame(), date);
    Assert.assertEquals(FastMath.PI / 2. - FastMath.abs(point.getLongitude() - infPointGeo.getLongitude()), eleElli, 1.e-2);
    // Infinite point separated by +20 deg in longitude
    // *************************************************
    infPointGeo = new GeodeticPoint(FastMath.toRadians(0.), FastMath.toRadians(25.), 1000000000.);
    infPoint = earthElliptic.transform(infPointGeo);
    // Azimuth = pi/2
    aziElli = topoElliptic.getAzimuth(infPoint, earthElliptic.getBodyFrame(), date);
    Assert.assertEquals(FastMath.PI / 2., aziElli, Utils.epsilonAngle);
    // Site = pi/2 - longitude difference
    eleElli = topoElliptic.getElevation(infPoint, earthElliptic.getBodyFrame(), date);
    Assert.assertEquals(FastMath.PI / 2. - FastMath.abs(point.getLongitude() - infPointGeo.getLongitude()), eleElli, 1.e-2);
    // ************************
    // Test at polar position
    // ************************
    point = new GeodeticPoint(FastMath.toRadians(89.999), FastMath.toRadians(0.), 0.);
    topoSpheric = new TopocentricFrame(earthSpheric, point, "lon 0 lat 90");
    topoElliptic = new TopocentricFrame(earthElliptic, point, "lon 0 lat 90");
    // Compare azimuth/elevation/range of satellite point : slight difference due to earth flatness
    // ***************************************************
    aziElli = topoElliptic.getAzimuth(satPoint, earthElliptic.getBodyFrame(), date);
    aziSphe = topoSpheric.getAzimuth(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(aziElli, aziSphe, 1.e-7);
    eleElli = topoElliptic.getElevation(satPoint, earthElliptic.getBodyFrame(), date);
    eleSphe = topoSpheric.getElevation(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(eleElli, eleSphe, 1.e-2);
    disElli = topoElliptic.getRange(satPoint, earthElliptic.getBodyFrame(), date);
    disSphe = topoSpheric.getRange(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(disElli, disSphe, 20.e+3);
    // *********************
    // Test at any position
    // *********************
    point = new GeodeticPoint(FastMath.toRadians(60), FastMath.toRadians(30.), 0.);
    topoSpheric = new TopocentricFrame(earthSpheric, point, "lon 10 lat 45");
    topoElliptic = new TopocentricFrame(earthElliptic, point, "lon 10 lat 45");
    // Compare azimuth/elevation/range of satellite point : slight difference
    // ***************************************************
    aziElli = topoElliptic.getAzimuth(satPoint, earthElliptic.getBodyFrame(), date);
    aziSphe = topoSpheric.getAzimuth(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(aziElli, aziSphe, 1.e-2);
    eleElli = topoElliptic.getElevation(satPoint, earthElliptic.getBodyFrame(), date);
    eleSphe = topoSpheric.getElevation(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(eleElli, eleSphe, 1.e-2);
    disElli = topoElliptic.getRange(satPoint, earthElliptic.getBodyFrame(), date);
    disSphe = topoSpheric.getRange(satPoint, earthSpheric.getBodyFrame(), date);
    Assert.assertEquals(disElli, disSphe, 20.e+3);
}