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

Example 31 with OrbitType

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

the class SolarRadiationPressureTest method testGlobalStateJacobianBox.

@Test
public void testGlobalStateJacobianBox() throws OrekitException {
    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 03, 01), new TimeComponents(13, 59, 27.816), TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN, FramesFactory.getEME2000(), date, Constants.EIGEN5C_EARTH_MU);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);
    NumericalPropagator propagator = new NumericalPropagator(new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    SolarRadiationPressure forceModel = new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.WGS84_EARTH_EQUATORIAL_RADIUS, new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0, Vector3D.PLUS_J, 1.2, 0.7, 0.2));
    propagator.addForceModel(forceModel);
    SpacecraftState state0 = new SpacecraftState(orbit);
    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 1e3, tolerances[0], 5.0e-4);
}

Example 32 with OrbitType

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

the class PropagatorsParallelizerTest method buildNotInitializedNumerical.

private NumericalPropagator buildNotInitializedNumerical() throws OrekitException {
    OrbitType type = OrbitType.CARTESIAN;
    double minStep = 0.001;
    double maxStep = 300;
    double[][] tolerances = NumericalPropagator.tolerances(10.0, orbit, type);
    ODEIntegrator integrator = new DormandPrince853Integrator(minStep, maxStep, tolerances[0], tolerances[1]);
    NumericalPropagator numericalPropagator = new NumericalPropagator(integrator);
    ForceModel gravity = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), normalizedGravityField);
    numericalPropagator.addForceModel(gravity);
    return numericalPropagator;
}

Example 33 with OrbitType

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

the class FieldIntegratedEphemerisTest method createPropagator.

private <T extends RealFieldElement<T>> FieldNumericalPropagator<T> createPropagator(Field<T> field) {
    double[] absTolerance = { 0.0001, 1.0e-11, 1.0e-11, 1.0e-8, 1.0e-8, 1.0e-8, 0.001 };
    double[] relTolerance = { 1.0e-8, 1.0e-8, 1.0e-8, 1.0e-9, 1.0e-9, 1.0e-9, 1.0e-7 };
    OrbitType type = OrbitType.EQUINOCTIAL;
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 500, absTolerance, relTolerance);
    integrator.setInitialStepSize(field.getZero().add(100));
    FieldNumericalPropagator<T> numericalPropagator = new FieldNumericalPropagator<>(field, integrator);
    numericalPropagator.setOrbitType(type);
    return numericalPropagator;
}

Example 34 with OrbitType

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

the class FieldNumericalPropagatorTest method doTestNoExtrapolation.

private <T extends RealFieldElement<T>> void doTestNoExtrapolation(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    // setup
    final FieldAbsoluteDate<T> initDate = FieldAbsoluteDate.getJ2000Epoch(field);
    FieldSpacecraftState<T> initialState;
    FieldNumericalPropagator<T> propagator;
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(7.0e6), zero.add(1.0e6), zero.add(4.0e6));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(-500.0), zero.add(8000.0), zero.add(1000.0));
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new FieldSpacecraftState<>(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit.toOrbit(), type);
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(zero.add(60));
    propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    // Propagate of the initial at the initial date
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate);
    // Initial orbit definition
    final FieldVector3D<T> initialPosition = initialState.getPVCoordinates().getPosition();
    final FieldVector3D<T> initialVelocity = initialState.getPVCoordinates().getVelocity();
    // Final orbit definition
    final FieldVector3D<T> finalPosition = finalState.getPVCoordinates().getPosition();
    final FieldVector3D<T> finalVelocity = finalState.getPVCoordinates().getVelocity();
    // Check results
    Assert.assertEquals(initialPosition.getX().getReal(), finalPosition.getX().getReal(), 1.0e-10);
    Assert.assertEquals(initialPosition.getY().getReal(), finalPosition.getY().getReal(), 1.0e-10);
    Assert.assertEquals(initialPosition.getZ().getReal(), finalPosition.getZ().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getX().getReal(), finalVelocity.getX().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getY().getReal(), finalVelocity.getY().getReal(), 1.0e-10);
    Assert.assertEquals(initialVelocity.getZ().getReal(), finalVelocity.getZ().getReal(), 1.0e-10);
}

Example 35 with OrbitType

use of org.orekit.orbits.OrbitType in project SpriteOrbits by ProjectPersephone.

the class SpriteProp method createPropagator.

/**
 * Create a numerical propagator for a state.
 * @param state state to propagate
 * @param attitudeProvider provider for the attitude
 * @param crossSection cross section of the object
 * @param dragCoeff drag coefficient
 */
private Propagator createPropagator(final SpacecraftState state, final AttitudeProvider attitudeProvider, final double crossSection, final double dragCoeff) throws OrekitException {
    // see https://www.orekit.org/static/architecture/propagation.html
    // steps limits
    final double minStep = 0.001;
    final double maxStep = 1000;
    final double initStep = 60;
    // error control parameters (absolute and relative)
    final double positionError = 10.0;
    // we will propagate in Cartesian coordinates
    final OrbitType orbitType = OrbitType.CARTESIAN;
    final double[][] tolerances = NumericalPropagator.tolerances(positionError, state.getOrbit(), orbitType);
    // set up mathematical integrator
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxStep, tolerances[0], tolerances[1]);
    integrator.setInitialStepSize(initStep);
    // set up space dynamics propagator
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.setOrbitType(orbitType);
    // add gravity field force model
    final NormalizedSphericalHarmonicsProvider gravityProvider = GravityFieldFactory.getNormalizedProvider(8, 8);
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(earth.getBodyFrame(), gravityProvider));
    // add atmospheric drag force model
    propagator.addForceModel(new DragForce(new HarrisPriester(sun, earth), new SphericalSpacecraft(crossSection, dragCoeff, 0.0, 0.0)));
    // set attitude mode
    propagator.setAttitudeProvider(attitudeProvider);
    propagator.setInitialState(state);
    return propagator;
}