Examples with IsotropicDrag org.orekit.forces.drag.IsotropicDrag used on opensource projects

Example 1 with IsotropicDrag

use of org.orekit.forces.drag.IsotropicDrag in project Orekit by CS-SI.

the class EstimationTestUtils method geoStationnaryContext.

public static Context geoStationnaryContext(final String dataRoot) throws OrekitException {
    Utils.setDataRoot(dataRoot);
    Context context = new Context();
    context.conventions = IERSConventions.IERS_2010;
    context.utc = TimeScalesFactory.getUTC();
    context.ut1 = TimeScalesFactory.getUT1(context.conventions, true);
    context.displacements = new StationDisplacement[0];
    String Myframename = "MyEarthFrame";
    final AbsoluteDate datedef = new AbsoluteDate(2000, 1, 1, 12, 0, 0.0, context.utc);
    final double omega = Constants.WGS84_EARTH_ANGULAR_VELOCITY;
    final Vector3D rotationRate = new Vector3D(0.0, 0.0, omega);
    TransformProvider MyEarthFrame = new TransformProvider() {

        private static final long serialVersionUID = 1L;

        public Transform getTransform(final AbsoluteDate date) {
            final double rotationduration = date.durationFrom(datedef);
            final Vector3D alpharot = new Vector3D(rotationduration, rotationRate);
            final Rotation rotation = new Rotation(Vector3D.PLUS_K, -alpharot.getZ(), RotationConvention.VECTOR_OPERATOR);
            return new Transform(date, rotation, rotationRate);
        }

        public <T extends RealFieldElement<T>> FieldTransform<T> getTransform(final FieldAbsoluteDate<T> date) {
            final T rotationduration = date.durationFrom(datedef);
            final FieldVector3D<T> alpharot = new FieldVector3D<>(rotationduration, rotationRate);
            final FieldRotation<T> rotation = new FieldRotation<>(FieldVector3D.getPlusK(date.getField()), alpharot.getZ().negate(), RotationConvention.VECTOR_OPERATOR);
            return new FieldTransform<>(date, rotation, new FieldVector3D<>(date.getField(), rotationRate));
        }
    };
    Frame FrameTest = new Frame(FramesFactory.getEME2000(), MyEarthFrame, Myframename, true);
    // Earth is spherical, rotating in one sidereal day
    context.earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, 0.0, FrameTest);
    context.sun = CelestialBodyFactory.getSun();
    context.moon = CelestialBodyFactory.getMoon();
    context.radiationSensitive = new IsotropicRadiationClassicalConvention(2.0, 0.2, 0.8);
    context.dragSensitive = new IsotropicDrag(2.0, 1.2);
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));
    AstronomicalAmplitudeReader aaReader = new AstronomicalAmplitudeReader("hf-fes2004.dat", 5, 2, 3, 1.0);
    DataProvidersManager.getInstance().feed(aaReader.getSupportedNames(), aaReader);
    Map<Integer, Double> map = aaReader.getAstronomicalAmplitudesMap();
    GravityFieldFactory.addOceanTidesReader(new FESCHatEpsilonReader("fes2004-7x7.dat", 0.01, FastMath.toRadians(1.0), OceanLoadDeformationCoefficients.IERS_2010, map));
    context.gravity = GravityFieldFactory.getNormalizedProvider(20, 20);
    // semimajor axis for a geostationnary satellite
    double da = FastMath.cbrt(context.gravity.getMu() / (omega * omega));
    // context.stations = Arrays.asList(context.createStation(  0.0,  0.0, 0.0, "Lat0_Long0"),
    // context.createStation( 62.29639,   -7.01250,  880.0, "Slættaratindur")
    // );
    context.stations = Arrays.asList(context.createStation(0.0, 0.0, 0.0, "Lat0_Long0"));
    // Station position & velocity in EME2000
    final Vector3D geovelocity = new Vector3D(0., 0., 0.);
    // Compute the frames transformation from station frame to EME2000
    Transform topoToEME = context.stations.get(0).getBaseFrame().getTransformTo(FramesFactory.getEME2000(), new AbsoluteDate(2000, 1, 1, 12, 0, 0.0, context.utc));
    // Station position in EME2000 at reference date
    Vector3D stationPositionEME = topoToEME.transformPosition(Vector3D.ZERO);
    // Satellite position and velocity in Station Frame
    final Vector3D sat_pos = new Vector3D(0., 0., da - stationPositionEME.getNorm());
    final Vector3D acceleration = new Vector3D(-context.gravity.getMu(), sat_pos);
    final PVCoordinates pv_sat_topo = new PVCoordinates(sat_pos, geovelocity, acceleration);
    // satellite position in EME2000
    final PVCoordinates pv_sat_iner = topoToEME.transformPVCoordinates(pv_sat_topo);
    // Geo-stationary Satellite Orbit, tightly above the station (l0-L0)
    context.initialOrbit = new KeplerianOrbit(pv_sat_iner, FramesFactory.getEME2000(), new AbsoluteDate(2000, 1, 1, 12, 0, 0.0, context.utc), context.gravity.getMu());
    context.stations = Arrays.asList(context.createStation(10.0, 45.0, 0.0, "Lat10_Long45"));
    // Turn-around range stations
    // Map entry = master station
    // Map value = slave station associated
    context.TARstations = new HashMap<GroundStation, GroundStation>();
    context.TARstations.put(context.createStation(41.977, 13.600, 671.354, "Fucino"), context.createStation(43.604, 1.444, 263.0, "Toulouse"));
    context.TARstations.put(context.createStation(49.867, 8.65, 144.0, "Darmstadt"), context.createStation(-25.885, 27.707, 1566.633, "Pretoria"));
    return context;
}

Example 2 with IsotropicDrag

use of org.orekit.forces.drag.IsotropicDrag in project Orekit by CS-SI.

the class EstimationTestUtils method eccentricContext.

public static Context eccentricContext(final String dataRoot) throws OrekitException {
    Utils.setDataRoot(dataRoot);
    Context context = new Context();
    context.conventions = IERSConventions.IERS_2010;
    context.earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(context.conventions, true));
    context.sun = CelestialBodyFactory.getSun();
    context.moon = CelestialBodyFactory.getMoon();
    context.radiationSensitive = new IsotropicRadiationClassicalConvention(2.0, 0.2, 0.8);
    context.dragSensitive = new IsotropicDrag(2.0, 1.2);
    final EOPHistory eopHistory = FramesFactory.getEOPHistory(context.conventions, true);
    context.utc = TimeScalesFactory.getUTC();
    context.ut1 = TimeScalesFactory.getUT1(eopHistory);
    context.displacements = new StationDisplacement[] { new TidalDisplacement(Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS, Constants.JPL_SSD_SUN_EARTH_PLUS_MOON_MASS_RATIO, Constants.JPL_SSD_EARTH_MOON_MASS_RATIO, context.sun, context.moon, context.conventions, false) };
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));
    AstronomicalAmplitudeReader aaReader = new AstronomicalAmplitudeReader("hf-fes2004.dat", 5, 2, 3, 1.0);
    DataProvidersManager.getInstance().feed(aaReader.getSupportedNames(), aaReader);
    Map<Integer, Double> map = aaReader.getAstronomicalAmplitudesMap();
    GravityFieldFactory.addOceanTidesReader(new FESCHatEpsilonReader("fes2004-7x7.dat", 0.01, FastMath.toRadians(1.0), OceanLoadDeformationCoefficients.IERS_2010, map));
    context.gravity = GravityFieldFactory.getNormalizedProvider(20, 20);
    context.initialOrbit = new KeplerianOrbit(15000000.0, 0.125, 1.25, 0.250, 1.375, 0.0625, PositionAngle.TRUE, FramesFactory.getEME2000(), new AbsoluteDate(2000, 2, 24, 11, 35, 47.0, context.utc), context.gravity.getMu());
    context.stations = // context.createStation(-18.59146, -173.98363,   76.0, "Leimatu`a"),
    Arrays.asList(context.createStation(-53.05388, -75.01551, 1750.0, "Isla Desolación"), context.createStation(62.29639, -7.01250, 880.0, "Slættaratindur"));
    // Turn-around range stations
    // Map entry = master station
    // Map value = slave station associated
    context.TARstations = new HashMap<GroundStation, GroundStation>();
    context.TARstations.put(context.createStation(-53.05388, -75.01551, 1750.0, "Isla Desolación"), context.createStation(-54.815833, -68.317778, 6.0, "Ushuaïa"));
    context.TARstations.put(context.createStation(62.29639, -7.01250, 880.0, "Slættaratindur"), context.createStation(61.405833, -6.705278, 470.0, "Sumba"));
    return context;
}

Example 3 with IsotropicDrag

use of org.orekit.forces.drag.IsotropicDrag in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method createPropagator.

private static <T extends RealFieldElement<T>> FieldNumericalPropagator<T> createPropagator(FieldSpacecraftState<T> spacecraftState, OrbitType orbitType, PositionAngle angleType) throws OrekitException {
    final Field<T> field = spacecraftState.getDate().getField();
    final T zero = field.getZero();
    final double minStep = 0.001;
    final double maxStep = 120.0;
    final T positionTolerance = zero.add(0.1);
    final int degree = 20;
    final int order = 20;
    final double spacecraftArea = 1.0;
    final double spacecraftDragCoefficient = 2.0;
    final double spacecraftReflectionCoefficient = 2.0;
    // propagator main configuration
    final double[][] tol = FieldNumericalPropagator.tolerances(positionTolerance, spacecraftState.getOrbit(), orbitType);
    final FieldODEIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, minStep, maxStep, tol[0], tol[1]);
    final FieldNumericalPropagator<T> np = new FieldNumericalPropagator<>(field, integrator);
    np.setOrbitType(orbitType);
    np.setPositionAngleType(angleType);
    np.setInitialState(spacecraftState);
    // Earth gravity field
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    final NormalizedSphericalHarmonicsProvider harmonicsGravityProvider = GravityFieldFactory.getNormalizedProvider(degree, order);
    np.addForceModel(new HolmesFeatherstoneAttractionModel(earth.getBodyFrame(), harmonicsGravityProvider));
    // Sun and Moon attraction
    np.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getSun()));
    np.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
    // atmospheric drag
    MarshallSolarActivityFutureEstimation msafe = new MarshallSolarActivityFutureEstimation("Jan2000F10-edited-data\\.txt", MarshallSolarActivityFutureEstimation.StrengthLevel.AVERAGE);
    DataProvidersManager.getInstance().feed(msafe.getSupportedNames(), msafe);
    DTM2000 atmosphere = new DTM2000(msafe, CelestialBodyFactory.getSun(), earth);
    np.addForceModel(new DragForce(atmosphere, new IsotropicDrag(spacecraftArea, spacecraftDragCoefficient)));
    // solar radiation pressure
    np.addForceModel(new SolarRadiationPressure(CelestialBodyFactory.getSun(), earth.getEquatorialRadius(), new IsotropicRadiationSingleCoefficient(spacecraftArea, spacecraftReflectionCoefficient)));
    return np;
}

Example 4 with IsotropicDrag

use of org.orekit.forces.drag.IsotropicDrag in project Orekit by CS-SI.

the class JacobianPropagatorConverterTest method setUp.

@Before
public void setUp() throws OrekitException, IOException, ParseException {
    Utils.setDataRoot("regular-data:potential/shm-format");
    gravity = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(2, 0));
    mu = gravity.getParameterDriver(NewtonianAttraction.CENTRAL_ATTRACTION_COEFFICIENT).getValue();
    dP = 1.0;
    // use a orbit that comes close to Earth so the drag coefficient has an effect
    final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6).normalize().scalarMultiply(Constants.WGS84_EARTH_EQUATORIAL_RADIUS + 300e3);
    final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    final AbsoluteDate initDate = new AbsoluteDate(2010, 10, 10, 10, 10, 10.0, TimeScalesFactory.getUTC());
    orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
    earth.setAngularThreshold(1.e-7);
    atmosphere = new SimpleExponentialAtmosphere(earth, 0.0004, 42000.0, 7500.0);
    final double dragCoef = 2.0;
    crossSection = 25.0;
    drag = new DragForce(atmosphere, new IsotropicDrag(crossSection, dragCoef));
}

Example 5 with IsotropicDrag

use of org.orekit.forces.drag.IsotropicDrag in project Orekit by CS-SI.

the class KalmanOrbitDeterminationTest method createPropagatorBuilder.

/**
 * Create a propagator builder from input parameters
 * @param parser input file parser
 * @param conventions IERS conventions to use
 * @param gravityField gravity field
 * @param body central body
 * @param orbit first orbit estimate
 * @return propagator builder
 * @throws NoSuchElementException if input parameters are missing
 * @throws OrekitException if body frame cannot be created
 */
private NumericalPropagatorBuilder createPropagatorBuilder(final KeyValueFileParser<ParameterKey> parser, final IERSConventions conventions, final NormalizedSphericalHarmonicsProvider gravityField, final OneAxisEllipsoid body, final Orbit orbit) throws NoSuchElementException, OrekitException {
    final double minStep;
    if (!parser.containsKey(ParameterKey.PROPAGATOR_MIN_STEP)) {
        minStep = 0.001;
    } else {
        minStep = parser.getDouble(ParameterKey.PROPAGATOR_MIN_STEP);
    }
    final double maxStep;
    if (!parser.containsKey(ParameterKey.PROPAGATOR_MAX_STEP)) {
        maxStep = 300;
    } else {
        maxStep = parser.getDouble(ParameterKey.PROPAGATOR_MAX_STEP);
    }
    final double dP;
    if (!parser.containsKey(ParameterKey.PROPAGATOR_POSITION_ERROR)) {
        dP = 10.0;
    } else {
        dP = parser.getDouble(ParameterKey.PROPAGATOR_POSITION_ERROR);
    }
    final double positionScale;
    if (!parser.containsKey(ParameterKey.ESTIMATOR_ORBITAL_PARAMETERS_POSITION_SCALE)) {
        positionScale = dP;
    } else {
        positionScale = parser.getDouble(ParameterKey.ESTIMATOR_ORBITAL_PARAMETERS_POSITION_SCALE);
    }
    final NumericalPropagatorBuilder propagatorBuilder = new NumericalPropagatorBuilder(orbit, new DormandPrince853IntegratorBuilder(minStep, maxStep, dP), PositionAngle.MEAN, positionScale);
    // initial mass
    final double mass;
    if (!parser.containsKey(ParameterKey.MASS)) {
        mass = 1000.0;
    } else {
        mass = parser.getDouble(ParameterKey.MASS);
    }
    propagatorBuilder.setMass(mass);
    // gravity field force model
    propagatorBuilder.addForceModel(new HolmesFeatherstoneAttractionModel(body.getBodyFrame(), gravityField));
    // ocean tides force model
    if (parser.containsKey(ParameterKey.OCEAN_TIDES_DEGREE) && parser.containsKey(ParameterKey.OCEAN_TIDES_ORDER)) {
        final int degree = parser.getInt(ParameterKey.OCEAN_TIDES_DEGREE);
        final int order = parser.getInt(ParameterKey.OCEAN_TIDES_ORDER);
        if (degree > 0 && order > 0) {
            propagatorBuilder.addForceModel(new OceanTides(body.getBodyFrame(), gravityField.getAe(), gravityField.getMu(), degree, order, conventions, TimeScalesFactory.getUT1(conventions, true)));
        }
    }
    // solid tides force model
    List<CelestialBody> solidTidesBodies = new ArrayList<CelestialBody>();
    if (parser.containsKey(ParameterKey.SOLID_TIDES_SUN) && parser.getBoolean(ParameterKey.SOLID_TIDES_SUN)) {
        solidTidesBodies.add(CelestialBodyFactory.getSun());
    }
    if (parser.containsKey(ParameterKey.SOLID_TIDES_MOON) && parser.getBoolean(ParameterKey.SOLID_TIDES_MOON)) {
        solidTidesBodies.add(CelestialBodyFactory.getMoon());
    }
    if (!solidTidesBodies.isEmpty()) {
        propagatorBuilder.addForceModel(new SolidTides(body.getBodyFrame(), gravityField.getAe(), gravityField.getMu(), gravityField.getTideSystem(), conventions, TimeScalesFactory.getUT1(conventions, true), solidTidesBodies.toArray(new CelestialBody[solidTidesBodies.size()])));
    }
    // third body attraction
    if (parser.containsKey(ParameterKey.THIRD_BODY_SUN) && parser.getBoolean(ParameterKey.THIRD_BODY_SUN)) {
        propagatorBuilder.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getSun()));
    }
    if (parser.containsKey(ParameterKey.THIRD_BODY_MOON) && parser.getBoolean(ParameterKey.THIRD_BODY_MOON)) {
        propagatorBuilder.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
    }
    // drag
    if (parser.containsKey(ParameterKey.DRAG) && parser.getBoolean(ParameterKey.DRAG)) {
        final double cd = parser.getDouble(ParameterKey.DRAG_CD);
        final double area = parser.getDouble(ParameterKey.DRAG_AREA);
        final boolean cdEstimated = parser.getBoolean(ParameterKey.DRAG_CD_ESTIMATED);
        MarshallSolarActivityFutureEstimation msafe = new MarshallSolarActivityFutureEstimation("(?:Jan|Feb|Mar|Apr|May|Jun|Jul|Aug|Sep|Oct|Nov|Dec)\\p{Digit}\\p{Digit}\\p{Digit}\\p{Digit}F10\\.(?:txt|TXT)", MarshallSolarActivityFutureEstimation.StrengthLevel.AVERAGE);
        DataProvidersManager manager = DataProvidersManager.getInstance();
        manager.feed(msafe.getSupportedNames(), msafe);
        Atmosphere atmosphere = new DTM2000(msafe, CelestialBodyFactory.getSun(), body);
        propagatorBuilder.addForceModel(new DragForce(atmosphere, new IsotropicDrag(area, cd)));
        if (cdEstimated) {
            for (final ParameterDriver driver : propagatorBuilder.getPropagationParametersDrivers().getDrivers()) {
                if (driver.getName().equals(DragSensitive.DRAG_COEFFICIENT)) {
                    driver.setSelected(true);
                }
            }
        }
    }
    // solar radiation pressure
    if (parser.containsKey(ParameterKey.SOLAR_RADIATION_PRESSURE) && parser.getBoolean(ParameterKey.SOLAR_RADIATION_PRESSURE)) {
        final double cr = parser.getDouble(ParameterKey.SOLAR_RADIATION_PRESSURE_CR);
        final double area = parser.getDouble(ParameterKey.SOLAR_RADIATION_PRESSURE_AREA);
        final boolean cREstimated = parser.getBoolean(ParameterKey.SOLAR_RADIATION_PRESSURE_CR_ESTIMATED);
        propagatorBuilder.addForceModel(new SolarRadiationPressure(CelestialBodyFactory.getSun(), body.getEquatorialRadius(), new IsotropicRadiationSingleCoefficient(area, cr)));
        if (cREstimated) {
            for (final ParameterDriver driver : propagatorBuilder.getPropagationParametersDrivers().getDrivers()) {
                if (driver.getName().equals(RadiationSensitive.REFLECTION_COEFFICIENT)) {
                    driver.setSelected(true);
                }
            }
        }
    }
    // post-Newtonian correction force due to general relativity
    if (parser.containsKey(ParameterKey.GENERAL_RELATIVITY) && parser.getBoolean(ParameterKey.GENERAL_RELATIVITY)) {
        propagatorBuilder.addForceModel(new Relativity(gravityField.getMu()));
    }
    // extra polynomial accelerations
    if (parser.containsKey(ParameterKey.POLYNOMIAL_ACCELERATION_NAME)) {
        final String[] names = parser.getStringArray(ParameterKey.POLYNOMIAL_ACCELERATION_NAME);
        final Vector3D[] directions = parser.getVectorArray(ParameterKey.POLYNOMIAL_ACCELERATION_DIRECTION_X, ParameterKey.POLYNOMIAL_ACCELERATION_DIRECTION_Y, ParameterKey.POLYNOMIAL_ACCELERATION_DIRECTION_Z);
        final List<String>[] coefficients = parser.getStringsListArray(ParameterKey.POLYNOMIAL_ACCELERATION_COEFFICIENTS, ',');
        final boolean[] estimated = parser.getBooleanArray(ParameterKey.POLYNOMIAL_ACCELERATION_ESTIMATED);
        for (int i = 0; i < names.length; ++i) {
            final PolynomialParametricAcceleration ppa = new PolynomialParametricAcceleration(directions[i], true, names[i], null, coefficients[i].size() - 1);
            for (int k = 0; k < coefficients[i].size(); ++k) {
                final ParameterDriver driver = ppa.getParameterDriver(names[i] + "[" + k + "]");
                driver.setValue(Double.parseDouble(coefficients[i].get(k)));
                driver.setSelected(estimated[i]);
            }
            propagatorBuilder.addForceModel(ppa);
        }
    }
    return propagatorBuilder;
}