Examples with HolmesFeatherstoneAttractionModel org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel used on opensource projects

Example 1 with HolmesFeatherstoneAttractionModel

use of org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel in project Orekit by CS-SI.

the class FieldNumericalPropagatorTest method doTestPropagationTypesElliptical.

private <T extends RealFieldElement<T>> void doTestPropagationTypesElliptical(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);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(5, 5));
    propagator.addForceModel(gravityField);
    // Propagation of the initial at t + dt
    final FieldPVCoordinates<T> pv = initialState.getPVCoordinates();
    final T dP = zero.add(0.001);
    final T dV = pv.getPosition().getNormSq().multiply(pv.getVelocity().getNorm()).reciprocal().multiply(dP.multiply(initialState.getMu()));
    final FieldPVCoordinates<T> pvcM = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pviM = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pveM = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pvkM = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN, propagator);
    final FieldPVCoordinates<T> pvcE = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pviE = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pveE = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pvkE = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC, propagator);
    final FieldPVCoordinates<T> pvcT = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pviT = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pveT = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE, propagator);
    final FieldPVCoordinates<T> pvkT = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE, propagator);
    Assert.assertEquals(0, pvcM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.6);
    Assert.assertEquals(0, pviM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.4);
    Assert.assertEquals(0, pvkM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.5);
    Assert.assertEquals(0, pvkM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.3);
    Assert.assertEquals(0, pveM.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.2);
    Assert.assertEquals(0, pveM.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
    Assert.assertEquals(0, pvcE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.03);
    Assert.assertEquals(0, pviE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.04);
    Assert.assertEquals(0, pvkE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.4);
    Assert.assertEquals(0, pvkE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.3);
    Assert.assertEquals(0, pveE.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.2);
    Assert.assertEquals(0, pveE.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.07);
    Assert.assertEquals(0, pvcT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 3.0);
    Assert.assertEquals(0, pvcT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 2.0);
    Assert.assertEquals(0, pviT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.3);
    Assert.assertEquals(0, pviT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
    Assert.assertEquals(0, pvkT.getPosition().subtract(pveT.getPosition()).getNorm().getReal() / dP.getReal(), 0.4);
    Assert.assertEquals(0, pvkT.getVelocity().subtract(pveT.getVelocity()).getNorm().getReal() / dV.getReal(), 0.2);
}

Example 2 with HolmesFeatherstoneAttractionModel

use of org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel 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 3 with HolmesFeatherstoneAttractionModel

use of org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel in project Orekit by CS-SI.

the class NumericalPropagatorTest method testPropagationTypesElliptical.

@Test
public void testPropagationTypesElliptical() throws OrekitException, ParseException, IOException {
    // setup
    AbsoluteDate initDate = new AbsoluteDate();
    SpacecraftState initialState;
    final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
    final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
    initDate = AbsoluteDate.J2000_EPOCH;
    final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity), FramesFactory.getEME2000(), initDate, mu);
    initialState = new SpacecraftState(orbit);
    OrbitType type = OrbitType.EQUINOCTIAL;
    double[][] tolerance = NumericalPropagator.tolerances(0.001, orbit, type);
    AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
    integrator.setInitialStepSize(60);
    propagator = new NumericalPropagator(integrator);
    propagator.setOrbitType(type);
    propagator.setInitialState(initialState);
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(5, 5));
    propagator.addForceModel(gravityField);
    // Propagation of the initial at t + dt
    final PVCoordinates pv = initialState.getPVCoordinates();
    final double dP = 0.001;
    final double dV = initialState.getMu() * dP / (pv.getPosition().getNormSq() * pv.getVelocity().getNorm());
    final PVCoordinates pvcM = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.MEAN);
    final PVCoordinates pviM = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.MEAN);
    final PVCoordinates pveM = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.MEAN);
    final PVCoordinates pvkM = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN);
    final PVCoordinates pvcE = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pviE = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.ECCENTRIC);
    final PVCoordinates pveE = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.ECCENTRIC);
    final PVCoordinates pvkE = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pvcT = propagateInType(initialState, dP, OrbitType.CARTESIAN, PositionAngle.TRUE);
    final PVCoordinates pviT = propagateInType(initialState, dP, OrbitType.CIRCULAR, PositionAngle.TRUE);
    final PVCoordinates pveT = propagateInType(initialState, dP, OrbitType.EQUINOCTIAL, PositionAngle.TRUE);
    final PVCoordinates pvkT = propagateInType(initialState, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE);
    Assert.assertEquals(0, pvcM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.6);
    Assert.assertEquals(0, pviM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.4);
    Assert.assertEquals(0, pvkM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.5);
    Assert.assertEquals(0, pvkM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.3);
    Assert.assertEquals(0, pveM.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.2);
    Assert.assertEquals(0, pveM.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
    Assert.assertEquals(0, pvcE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.03);
    Assert.assertEquals(0, pviE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.04);
    Assert.assertEquals(0, pvkE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.4);
    Assert.assertEquals(0, pvkE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.3);
    Assert.assertEquals(0, pveE.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.2);
    Assert.assertEquals(0, pveE.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.07);
    Assert.assertEquals(0, pvcT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 3.0);
    Assert.assertEquals(0, pvcT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 2.0);
    Assert.assertEquals(0, pviT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.3);
    Assert.assertEquals(0, pviT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
    Assert.assertEquals(0, pvkT.getPosition().subtract(pveT.getPosition()).getNorm() / dP, 0.4);
    Assert.assertEquals(0, pvkT.getVelocity().subtract(pveT.getVelocity()).getNorm() / dV, 0.2);
}

Example 4 with HolmesFeatherstoneAttractionModel

use of org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel in project Orekit by CS-SI.

the class NumericalPropagatorTest method testPropagationTypesHyperbolic.

@Test
public void testPropagationTypesHyperbolic() throws OrekitException, ParseException, IOException {
    SpacecraftState state = new SpacecraftState(new KeplerianOrbit(-10000000.0, 2.5, 0.3, 0, 0, 0.0, PositionAngle.TRUE, FramesFactory.getEME2000(), initDate, mu));
    ForceModel gravityField = new HolmesFeatherstoneAttractionModel(FramesFactory.getITRF(IERSConventions.IERS_2010, true), GravityFieldFactory.getNormalizedProvider(5, 5));
    propagator.addForceModel(gravityField);
    // Propagation of the initial at t + dt
    final PVCoordinates pv = state.getPVCoordinates();
    final double dP = 0.001;
    final double dV = state.getMu() * dP / (pv.getPosition().getNormSq() * pv.getVelocity().getNorm());
    final PVCoordinates pvcM = propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.MEAN);
    final PVCoordinates pvkM = propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.MEAN);
    final PVCoordinates pvcE = propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pvkE = propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.ECCENTRIC);
    final PVCoordinates pvcT = propagateInType(state, dP, OrbitType.CARTESIAN, PositionAngle.TRUE);
    final PVCoordinates pvkT = propagateInType(state, dP, OrbitType.KEPLERIAN, PositionAngle.TRUE);
    Assert.assertEquals(0, pvcM.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
    Assert.assertEquals(0, pvcM.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
    Assert.assertEquals(0, pvkM.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.2);
    Assert.assertEquals(0, pvkM.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.3);
    Assert.assertEquals(0, pvcE.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
    Assert.assertEquals(0, pvcE.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
    Assert.assertEquals(0, pvkE.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.009);
    Assert.assertEquals(0, pvkE.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.006);
    Assert.assertEquals(0, pvcT.getPosition().subtract(pvkT.getPosition()).getNorm() / dP, 0.3);
    Assert.assertEquals(0, pvcT.getVelocity().subtract(pvkT.getVelocity()).getNorm() / dV, 0.4);
}

Example 5 with HolmesFeatherstoneAttractionModel

use of org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel in project Orekit by CS-SI.

the class SecularAndHarmonicTest method createPropagator.

private NumericalPropagator createPropagator(CircularOrbit orbit) throws OrekitException {
    OrbitType type = OrbitType.CIRCULAR;
    double[][] tolerances = NumericalPropagator.tolerances(0.1, orbit, type);
    DormandPrince853Integrator integrator = new DormandPrince853Integrator(1.0, 600, tolerances[0], tolerances[1]);
    integrator.setInitialStepSize(60.0);
    NumericalPropagator propagator = new NumericalPropagator(integrator);
    propagator.addForceModel(new HolmesFeatherstoneAttractionModel(earth.getBodyFrame(), gravityField));
    propagator.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getSun()));
    propagator.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
    propagator.setOrbitType(type);
    propagator.resetInitialState(new SpacecraftState(orbit));
    return propagator;
}