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

Example 86 with OneAxisEllipsoid

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

the class DSSTPropagatorTest method testShortPeriodCoefficients.

@Test
public void testShortPeriodCoefficients() throws OrekitException {
    Utils.setDataRoot("regular-data:potential/icgem-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new ICGEMFormatReader("^eigen-6s-truncated$", false));
    UnnormalizedSphericalHarmonicsProvider nshp = GravityFieldFactory.getUnnormalizedProvider(4, 4);
    Orbit orbit = new KeplerianOrbit(13378000, 0.05, 0, 0, FastMath.PI, 0, PositionAngle.MEAN, FramesFactory.getTOD(false), new AbsoluteDate(2003, 5, 6, TimeScalesFactory.getUTC()), nshp.getMu());
    double period = orbit.getKeplerianPeriod();
    double[][] tolerance = DSSTPropagator.tolerances(1.0, orbit);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(period / 100, period * 100, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(10 * period);
    DSSTPropagator propagator = new DSSTPropagator(integrator, false);
    OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getGTOD(false));
    CelestialBody sun = CelestialBodyFactory.getSun();
    CelestialBody moon = CelestialBodyFactory.getMoon();
    propagator.addForceModel(new DSSTZonal(nshp, 4, 3, 9));
    propagator.addForceModel(new DSSTTesseral(earth.getBodyFrame(), Constants.WGS84_EARTH_ANGULAR_VELOCITY, nshp, 4, 4, 4, 8, 4, 4, 2));
    propagator.addForceModel(new DSSTThirdBody(sun));
    propagator.addForceModel(new DSSTThirdBody(moon));
    propagator.addForceModel(new DSSTAtmosphericDrag(new HarrisPriester(sun, earth), 2.1, 180));
    propagator.addForceModel(new DSSTSolarRadiationPressure(1.2, 180, sun, earth.getEquatorialRadius()));
    final AbsoluteDate finalDate = orbit.getDate().shiftedBy(30 * Constants.JULIAN_DAY);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateNoConfig = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateNoConfig.getAdditionalStates().size());
    propagator.setSelectedCoefficients(new HashSet<String>());
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigEmpty = propagator.propagate(finalDate);
    Assert.assertEquals(234, stateConfigEmpty.getAdditionalStates().size());
    final Set<String> selected = new HashSet<String>();
    selected.add("DSST-3rd-body-Moon-s[7]");
    selected.add("DSST-central-body-tesseral-c[-2][3]");
    propagator.setSelectedCoefficients(selected);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigeSelected = propagator.propagate(finalDate);
    Assert.assertEquals(selected.size(), stateConfigeSelected.getAdditionalStates().size());
    propagator.setSelectedCoefficients(null);
    propagator.resetInitialState(new SpacecraftState(orbit, 45.0));
    final SpacecraftState stateConfigNull = propagator.propagate(finalDate);
    Assert.assertEquals(0, stateConfigNull.getAdditionalStates().size());
}

Example 87 with OneAxisEllipsoid

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

the class DSSTPropagatorTest method testPropagationWithDrag.

@Test
public void testPropagationWithDrag() throws OrekitException {
    // Central Body geopotential 2x0
    final UnnormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getUnnormalizedProvider(2, 0);
    final Frame earthFrame = CelestialBodyFactory.getEarth().getBodyOrientedFrame();
    DSSTForceModel zonal = new DSSTZonal(provider, 2, 0, 5);
    DSSTForceModel tesseral = new DSSTTesseral(earthFrame, Constants.WGS84_EARTH_ANGULAR_VELOCITY, provider, 2, 0, 0, 2, 2, 0, 0);
    // Drag Force Model
    final OneAxisEllipsoid earth = new OneAxisEllipsoid(provider.getAe(), Constants.WGS84_EARTH_FLATTENING, earthFrame);
    final Atmosphere atm = new HarrisPriester(CelestialBodyFactory.getSun(), earth, 6);
    final double cd = 2.0;
    final double area = 25.0;
    DSSTForceModel drag = new DSSTAtmosphericDrag(atm, cd, area);
    // LEO Orbit
    final AbsoluteDate initDate = new AbsoluteDate(2003, 7, 1, 0, 0, 00.000, TimeScalesFactory.getUTC());
    final Orbit orbit = new KeplerianOrbit(7204535.848109440, 0.0012402238462686, FastMath.toRadians(98.74341600466740), FastMath.toRadians(111.1990175076630), FastMath.toRadians(43.32990110790340), FastMath.toRadians(68.66852509725620), PositionAngle.MEAN, FramesFactory.getEME2000(), initDate, provider.getMu());
    // Set propagator with state and force model
    setDSSTProp(new SpacecraftState(orbit));
    dsstProp.addForceModel(zonal);
    dsstProp.addForceModel(tesseral);
    dsstProp.addForceModel(drag);
    // 5 days propagation
    final SpacecraftState state = dsstProp.propagate(initDate.shiftedBy(5. * 86400.));
    // Ref Standalone_DSST:
    // a    = 7204521.657141485 m
    // h/ey =  0.0007093755541595772
    // k/ex = -0.001016800430994036
    // p/hy =  0.8698955648709271
    // q/hx =  0.7757573478894775
    // lM   = 193°0939742953394
    Assert.assertEquals(7204521.657141485, state.getA(), 6.e-1);
    Assert.assertEquals(-0.001016800430994036, state.getEquinoctialEx(), 5.e-8);
    Assert.assertEquals(0.0007093755541595772, state.getEquinoctialEy(), 2.e-8);
    Assert.assertEquals(0.7757573478894775, state.getHx(), 5.e-8);
    Assert.assertEquals(0.8698955648709271, state.getHy(), 5.e-8);
    Assert.assertEquals(193.0939742953394, FastMath.toDegrees(MathUtils.normalizeAngle(state.getLM(), FastMath.PI)), 2.e-3);
    // Assert.assertEquals(((DSSTAtmosphericDrag)drag).getCd(), cd, 1e-9);
    // Assert.assertEquals(((DSSTAtmosphericDrag)drag).getArea(), area, 1e-9);
    Assert.assertEquals(((DSSTAtmosphericDrag) drag).getAtmosphere(), atm);
    // DSSTAtmosphericDrag.ATMOSPHERE_ALTITUDE_MAX
    final double atmosphericMaxConstant = 1000000.0;
    Assert.assertEquals(((DSSTAtmosphericDrag) drag).getRbar(), atmosphericMaxConstant + Constants.WGS84_EARTH_EQUATORIAL_RADIUS, 1e-9);
}

Example 88 with OneAxisEllipsoid

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

the class ElevationDetectorTest method testPresTemp.

public void testPresTemp() throws OrekitException {
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
    // Earth and frame
    // equatorial radius in meter
    double ae = 6378137.0;
    // flattening
    double f = 1.0 / 298.257223563;
    // terrestrial frame at an arbitrary date
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
    GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833), FastMath.toRadians(2.333), 0.0);
    TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
    EarthStandardAtmosphereRefraction refractionModel = new EarthStandardAtmosphereRefraction();
    ElevationDetector detector = new ElevationDetector(topo).withRefraction(refractionModel).withHandler(new StopOnIncreasing<ElevationDetector>());
    refractionModel.setPressure(101325);
    refractionModel.setTemperature(290);
    AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 20, 0, 0, utc);
    propagator.resetInitialState(propagator.propagate(startDate));
    propagator.addEventDetector(detector);
    final SpacecraftState fs = propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
    double elevation = topo.getElevation(fs.getPVCoordinates().getPosition(), fs.getFrame(), fs.getDate());
    Assert.assertEquals(FastMath.toRadians(1.7026104902251749), elevation, 2.0e-5);
}

Example 89 with OneAxisEllipsoid

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

the class ElevationDetectorTest method testIssue203.

@Test
public void testIssue203() throws OrekitException {
    // Initial state definition : date, orbit
    AbsoluteDate initialDate = new AbsoluteDate("2012-01-26T07:00:00.000", TimeScalesFactory.getUTC());
    // inertial frame for orbit definition
    Frame inertialFrame = FramesFactory.getEME2000();
    Orbit initialOrbit = new KeplerianOrbit(6828137.5, 7.322641060181212E-8, 1.7082667003713938, 0.0, 1.658054062748353, 1.2231496082116026E-4, PositionAngle.TRUE, inertialFrame, initialDate, Constants.WGS84_EARTH_MU);
    Propagator propagator = new EcksteinHechlerPropagator(initialOrbit, Constants.EGM96_EARTH_EQUATORIAL_RADIUS, Constants.EGM96_EARTH_MU, Constants.EGM96_EARTH_C20, Constants.EGM96_EARTH_C30, Constants.EGM96_EARTH_C40, Constants.EGM96_EARTH_C50, Constants.EGM96_EARTH_C60);
    // Earth and frame
    Frame earthFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, earthFrame);
    // Station
    final double longitude = FastMath.toRadians(21.0);
    final double latitude = FastMath.toRadians(67.9);
    final double altitude = 300.0;
    final GeodeticPoint station1 = new GeodeticPoint(latitude, longitude, altitude);
    final TopocentricFrame sta1Frame = new TopocentricFrame(earth, station1, "station1");
    double[][] maskValues = { { -0.017453292519943098, 0.006981317007977318 }, { 0.0, 0.006981317007977318 }, { 0.017453292519943295, 0.006981317007977318 }, { 0.03490658503988659, 0.010471975511965976 }, { 0.05235987755982989, 0.012217304763960306 }, { 0.06981317007977318, 0.010471975511965976 }, { 0.08726646259971647, 0.010471975511965976 }, { 0.10471975511965978, 0.012217304763960306 }, { 0.12217304763960307, 0.010471975511965976 }, { 0.13962634015954636, 0.008726646259971648 }, { 0.15707963267948966, 0.008726646259971648 }, { 0.17453292519943295, 0.006981317007977318 }, { 0.19198621771937624, 0.006981317007977318 }, { 0.20943951023931956, 0.006981317007977318 }, { 0.22689280275926285, 0.005235987755982988 }, { 0.24434609527920614, 0.005235987755982988 }, { 0.2617993877991494, 0.003490658503988659 }, { 0.2792526803190927, 0.003490658503988659 }, { 0.29670597283903605, 0.0017453292519943296 }, { 0.3141592653589793, 0.003490658503988659 }, { 0.33161255787892263, 0.0017453292519943296 }, { 0.3490658503988659, 0.0 }, { 0.3665191429188092, 0.012217304763960306 }, { 0.3839724354387525, 0.012217304763960306 }, { 0.4014257279586958, 0.0 }, { 0.4188790204786391, 0.010471975511965976 }, { 0.4363323129985824, 0.029670597283903602 }, { 0.4537856055185257, 0.029670597283903602 }, { 0.47123889803846897, 0.017453292519943295 }, { 0.4886921905584123, 0.0 }, { 0.5061454830783556, 0.029670597283903602 }, { 0.5235987755982988, 0.015707963267948967 }, { 0.5410520681182421, 0.005235987755982988 }, { 0.5585053606381855, 0.024434609527920613 }, { 0.5759586531581288, 0.041887902047863905 }, { 0.5934119456780721, 0.06283185307179587 }, { 0.6108652381980153, 0.05235987755982989 }, { 0.6283185307179586, 0.05759586531581287 }, { 0.6457718232379019, 0.061086523819801536 }, { 0.6632251157578453, 0.05759586531581287 }, { 0.6806784082777885, 0.04363323129985824 }, { 0.6981317007977318, 0.059341194567807204 }, { 0.7155849933176751, 0.07504915783575616 }, { 0.7330382858376184, 0.08726646259971647 }, { 0.7504915783575618, 0.08726646259971647 }, { 0.767944870877505, 0.07330382858376185 }, { 0.7853981633974483, 0.07853981633974483 }, { 0.8028514559173916, 0.09075712110370514 }, { 0.8203047484373349, 0.0942477796076938 }, { 0.8377580409572782, 0.11519173063162574 }, { 0.8552113334772214, 0.11519173063162574 }, { 0.8726646259971648, 0.12566370614359174 }, { 0.8901179185171081, 0.12566370614359174 }, { 0.9075712110370514, 0.10122909661567112 }, { 0.9250245035569946, 0.11868238913561441 }, { 0.9424777960769379, 0.11868238913561441 }, { 0.9599310885968813, 0.11868238913561441 }, { 0.9773843811168246, 0.10821041362364843 }, { 0.9948376736367679, 0.12217304763960307 }, { 1.0122909661567112, 0.12740903539558607 }, { 1.0297442586766545, 0.11344640137963143 }, { 1.0471975511965976, 0.11344640137963143 }, { 1.064650843716541, 0.06632251157578452 }, { 1.0821041362364843, 0.12391837689159739 }, { 1.0995574287564276, 0.12391837689159739 }, { 1.117010721276371, 0.10995574287564276 }, { 1.1344640137963142, 0.09250245035569947 }, { 1.1519173063162575, 0.12740903539558607 }, { 1.1693705988362009, 0.1308996938995747 }, { 1.1868238913561442, 0.1117010721276371 }, { 1.2042771838760873, 0.1117010721276371 }, { 1.2217304763960306, 0.0942477796076938 }, { 1.239183768915974, 0.10821041362364843 }, { 1.2566370614359172, 0.09599310885968812 }, { 1.2740903539558606, 0.09948376736367678 }, { 1.2915436464758039, 0.09773843811168245 }, { 1.3089969389957472, 0.08726646259971647 }, { 1.3264502315156905, 0.09250245035569947 }, { 1.3439035240356338, 0.10122909661567112 }, { 1.361356816555577, 0.09250245035569947 }, { 1.3788101090755203, 0.08552113334772216 }, { 1.3962634015954636, 0.08726646259971647 }, { 1.413716694115407, 0.08028514559173916 }, { 1.4311699866353502, 0.05759586531581287 }, { 1.4486232791552935, 0.054105206811824215 }, { 1.4660765716752369, 0.06632251157578452 }, { 1.4835298641951802, 0.08028514559173916 }, { 1.5009831567151235, 0.061086523819801536 }, { 1.5184364492350666, 0.048869219055841226 }, { 1.53588974175501, 0.0715584993317675 }, { 1.5533430342749532, 0.07504915783575616 }, { 1.5707963267948966, 0.05235987755982989 }, { 1.5882496193148399, 0.05235987755982989 }, { 1.6057029118347832, 0.06981317007977318 }, { 1.6231562043547265, 0.054105206811824215 }, { 1.6406094968746698, 0.0645771823237902 }, { 1.6580627893946132, 0.059341194567807204 }, { 1.6755160819145565, 0.029670597283903602 }, { 1.6929693744344996, 0.03316125578789226 }, { 1.710422666954443, 0.059341194567807204 }, { 1.7278759594743862, 0.0645771823237902 }, { 1.7453292519943295, 0.06283185307179587 }, { 1.7627825445142729, 0.061086523819801536 }, { 1.7802358370342162, 0.06806784082777885 }, { 1.7976891295541595, 0.06632251157578452 }, { 1.8151424220741028, 0.059341194567807204 }, { 1.8325957145940461, 0.05759586531581287 }, { 1.8500490071139892, 0.05759586531581287 }, { 1.8675022996339325, 0.0471238898038469 }, { 1.8849555921538759, 0.059341194567807204 }, { 1.9024088846738192, 0.05061454830783556 }, { 1.9198621771937625, 0.05061454830783556 }, { 1.9373154697137058, 0.024434609527920613 }, { 1.9547687622336491, 0.027925268031909273 }, { 1.9722220547535925, 0.041887902047863905 }, { 1.9896753472735358, 0.024434609527920613 }, { 2.007128639793479, 0.029670597283903602 }, { 2.0245819323134224, 0.03316125578789226 }, { 2.0420352248333655, 0.03665191429188092 }, { 2.059488517353309, 0.04537856055185257 }, { 2.076941809873252, 0.041887902047863905 }, { 2.0943951023931953, 0.05759586531581287 }, { 2.111848394913139, 0.06283185307179587 }, { 2.129301687433082, 0.06806784082777885 }, { 2.1467549799530254, 0.05759586531581287 }, { 2.1642082724729685, 0.059341194567807204 }, { 2.181661564992912, 0.06806784082777885 }, { 2.199114857512855, 0.06283185307179587 }, { 2.2165681500327987, 0.054105206811824215 }, { 2.234021442552742, 0.05235987755982989 }, { 2.251474735072685, 0.059341194567807204 }, { 2.2689280275926285, 0.07330382858376185 }, { 2.2863813201125716, 0.06283185307179587 }, { 2.303834612632515, 0.05235987755982989 }, { 2.321287905152458, 0.061086523819801536 }, { 2.3387411976724017, 0.048869219055841226 }, { 2.356194490192345, 0.06632251157578452 }, { 2.3736477827122884, 0.05061454830783556 }, { 2.3911010752322315, 0.07679448708775051 }, { 2.4085543677521746, 0.06283185307179587 }, { 2.426007660272118, 0.05585053606381855 }, { 2.443460952792061, 0.061086523819801536 }, { 2.4609142453120048, 0.06806784082777885 }, { 2.478367537831948, 0.0645771823237902 }, { 2.4958208303518914, 0.06283185307179587 }, { 2.5132741228718345, 0.06283185307179587 }, { 2.530727415391778, 0.0645771823237902 }, { 2.548180707911721, 0.07504915783575616 }, { 2.5656340004316642, 0.0715584993317675 }, { 2.5830872929516078, 0.0645771823237902 }, { 2.600540585471551, 0.059341194567807204 }, { 2.6179938779914944, 0.06283185307179587 }, { 2.6354471705114375, 0.06632251157578452 }, { 2.652900463031381, 0.06283185307179587 }, { 2.670353755551324, 0.06632251157578452 }, { 2.6878070480712677, 0.0645771823237902 } };
    ElevationMask mask = new ElevationMask(maskValues);
    final AbsoluteDate start = new AbsoluteDate("2012-02-10T22:00:00.000", TimeScalesFactory.getUTC());
    final AbsoluteDate end = initialDate.shiftedBy(1000 * Constants.JULIAN_DAY);
    // Event definition
    final double maxcheck = 60.0;
    // 0.001;
    final double threshold = 2.0;
    final EventDetector sta1Visi = new ElevationDetector(maxcheck, threshold, sta1Frame).withElevationMask(mask).withHandler(new EventHandler<ElevationDetector>() {

        private int count = 6;

        @Override
        public Action eventOccurred(SpacecraftState s, ElevationDetector detector, boolean increasing) {
            return (--count > 0) ? Action.CONTINUE : Action.STOP;
        }
    });
    // Add event to be detected
    EventsLogger logger = new EventsLogger();
    propagator.addEventDetector(logger.monitorDetector(sta1Visi));
    // Propagate until the sixth event
    propagator.propagate(start, end);
    List<LoggedEvent> events = logger.getLoggedEvents();
    Assert.assertEquals(6, events.size());
    // despite the events 2 and 3 are closer to each other than the convergence threshold
    // the second one is not merged into the first one
    AbsoluteDate d2 = events.get(2).getState().getDate();
    AbsoluteDate d3 = events.get(3).getState().getDate();
    Assert.assertEquals(1.529, d3.durationFrom(d2), 0.01);
}

Example 90 with OneAxisEllipsoid

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

the class ElevationDetectorTest method testAgata.

@Test
public void testAgata() throws OrekitException {
    final TimeScale utc = TimeScalesFactory.getUTC();
    final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
    final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
    final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), date, mu);
    Propagator propagator = new EcksteinHechlerPropagator(orbit, ae, mu, c20, c30, c40, c50, c60);
    // Earth and frame
    // equatorial radius in meter
    double ae = 6378137.0;
    // flattening
    double f = 1.0 / 298.257223563;
    // terrestrial frame at an arbitrary date
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    BodyShape earth = new OneAxisEllipsoid(ae, f, itrf);
    GeodeticPoint point = new GeodeticPoint(FastMath.toRadians(48.833), FastMath.toRadians(2.333), 0.0);
    TopocentricFrame topo = new TopocentricFrame(earth, point, "Gstation");
    Checking checking = new Checking(topo);
    ElevationDetector detector = new ElevationDetector(topo).withConstantElevation(FastMath.toRadians(5.0)).withHandler(checking);
    Assert.assertNull(detector.getElevationMask());
    Assert.assertNull(detector.getRefractionModel());
    Assert.assertSame(topo, detector.getTopocentricFrame());
    Assert.assertEquals(FastMath.toRadians(5.0), detector.getMinElevation(), 1.0e-15);
    AbsoluteDate startDate = new AbsoluteDate(2003, 9, 15, 12, 0, 0, utc);
    propagator.resetInitialState(propagator.propagate(startDate));
    propagator.addEventDetector(detector);
    propagator.setMasterMode(10.0, checking);
    propagator.propagate(startDate.shiftedBy(Constants.JULIAN_DAY));
}