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

Example 1 with FieldEquinoctialOrbit

use of org.orekit.orbits.FieldEquinoctialOrbit 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 FieldEquinoctialOrbit

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

the class FieldNumericalPropagatorTest method doTestStopEvent.

private <T extends RealFieldElement<T>> void doTestStopEvent(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);
    final FieldAbsoluteDate<T> stopDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.STOP);
    propagator.addEventDetector(new FieldDateDetector<>(stopDate).withHandler(checking));
    Assert.assertEquals(1, propagator.getEventsDetectors().size());
    checking.assertEvent(false);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(3200));
    checking.assertEvent(true);
    Assert.assertEquals(0, finalState.getDate().durationFrom(stopDate).getReal(), 1.0e-10);
    propagator.clearEventsDetectors();
    Assert.assertEquals(0, propagator.getEventsDetectors().size());
}

Example 3 with FieldEquinoctialOrbit

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

the class FieldNumericalPropagatorTest method doTestResetDerivativesEvent.

private <T extends RealFieldElement<T>> void doTestResetDerivativesEvent(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);
    final FieldAbsoluteDate<T> resetDate = initDate.shiftedBy(1000);
    CheckingHandler<FieldDateDetector<T>, T> checking = new CheckingHandler<FieldDateDetector<T>, T>(Action.RESET_DERIVATIVES);
    propagator.addEventDetector(new FieldDateDetector<>(resetDate).withHandler(checking));
    final double dt = 3200;
    checking.assertEvent(false);
    Assert.assertEquals(0.0, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    propagator.setResetAtEnd(true);
    final FieldSpacecraftState<T> finalState = propagator.propagate(initDate.shiftedBy(dt));
    Assert.assertEquals(dt, propagator.getInitialState().getDate().durationFrom(initDate).getReal(), 1.0e-10);
    checking.assertEvent(true);
    final double n = FastMath.sqrt(initialState.getMu() / initialState.getA().getReal()) / initialState.getA().getReal();
    Assert.assertEquals(initialState.getA().getReal(), finalState.getA().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEx().getReal(), finalState.getEquinoctialEx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getEquinoctialEy().getReal(), finalState.getEquinoctialEy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHx().getReal(), finalState.getHx().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getHy().getReal(), finalState.getHy().getReal(), 1.0e-10);
    Assert.assertEquals(initialState.getLM().getReal() + n * dt, finalState.getLM().getReal(), 6.0e-10);
}

Example 4 with FieldEquinoctialOrbit

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

the class FieldNumericalPropagatorTest method doTestException.

private <T extends RealFieldElement<T>> void doTestException(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);
    propagator.setMasterMode(new FieldOrekitStepHandler<T>() {

        private int countDown = 3;

        private FieldAbsoluteDate<T> previousCall = null;

        public void init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) {
        }

        public void handleStep(FieldOrekitStepInterpolator<T> interpolator, boolean isLast) throws OrekitException {
            if (previousCall != null) {
                System.out.println(interpolator.getCurrentState().getDate().compareTo(previousCall) < 0);
            }
            if (--countDown == 0) {
                throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "dummy error");
            }
        }
    });
    propagator.propagate(initDate.shiftedBy(-3600));
}

Example 5 with FieldEquinoctialOrbit

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

the class FieldEcksteinHechlerPropagatorTest method doPropagatedCartesian.

private <T extends RealFieldElement<T>> void doPropagatedCartesian(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    // Definition of initial conditions with position and velocity
    // ------------------------------------------------------------
    // with e around e = 1.4e-4 and i = 1.7 rad
    FieldVector3D<T> position = new FieldVector3D<>(zero.add(3220103.), zero.add(69623.), zero.add(6449822.));
    FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(6414.7), zero.add(-2006.), zero.add(-3180.));
    FieldAbsoluteDate<T> initDate = date.shiftedBy(584.);
    FieldOrbit<T> initialOrbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), initDate, provider.getMu());
    // Extrapolator definition
    // -----------------------
    FieldEcksteinHechlerPropagator<T> extrapolator = new FieldEcksteinHechlerPropagator<>(initialOrbit, new LofOffset(initialOrbit.getFrame(), LOFType.VNC, RotationOrder.XYZ, 0, 0, 0), provider);
    // Extrapolation at a final date different from initial date
    // ---------------------------------------------------------
    // extrapolation duration in seconds
    double delta_t = 100000.0;
    FieldAbsoluteDate<T> extrapDate = initDate.shiftedBy(delta_t);
    FieldSpacecraftState<T> finalOrbit = extrapolator.propagate(extrapDate);
    Assert.assertEquals(0.0, finalOrbit.getDate().durationFrom(extrapDate).getReal(), 1.0e-9);
    // computation of M final orbit
    T LM = finalOrbit.getLE().subtract(finalOrbit.getEquinoctialEx().multiply(finalOrbit.getLE().sin())).add(finalOrbit.getEquinoctialEy().multiply(finalOrbit.getLE().cos()));
    Assert.assertEquals(LM.getReal(), finalOrbit.getLM().getReal(), Utils.epsilonAngle * FastMath.abs(finalOrbit.getLM().getReal()));
    // test of tan ((LE - Lv)/2) :
    Assert.assertEquals(FastMath.tan((finalOrbit.getLE().getReal() - finalOrbit.getLv().getReal()) / 2.), tangLEmLv(finalOrbit.getLv(), finalOrbit.getEquinoctialEx(), finalOrbit.getEquinoctialEy()).getReal(), Utils.epsilonAngle);
    // test of evolution of M vs E: LM = LE - ex*sin(LE) + ey*cos(LE)
    T deltaM = finalOrbit.getLM().subtract(initialOrbit.getLM());
    T deltaE = finalOrbit.getLE().subtract(initialOrbit.getLE());
    T delta = finalOrbit.getEquinoctialEx().multiply(finalOrbit.getLE().sin()).subtract(initialOrbit.getEquinoctialEx().multiply(initialOrbit.getLE().sin())).subtract(finalOrbit.getEquinoctialEy().multiply(finalOrbit.getLE().cos())).add(initialOrbit.getEquinoctialEy().multiply(initialOrbit.getLE().cos()));
    Assert.assertEquals(deltaM.getReal(), deltaE.getReal() - delta.getReal(), Utils.epsilonAngle * FastMath.abs(deltaE.getReal() - delta.getReal()));
    // for final orbit
    T ex = finalOrbit.getEquinoctialEx();
    T ey = finalOrbit.getEquinoctialEy();
    T hx = finalOrbit.getHx();
    T hy = finalOrbit.getHy();
    T LE = finalOrbit.getLE();
    T ex2 = ex.multiply(ex);
    T ey2 = ey.multiply(ey);
    T hx2 = hx.multiply(hx);
    T hy2 = hy.multiply(hy);
    T h2p1 = hx2.add(1.).add(hy2);
    T beta = ex2.negate().add(1.).subtract(ey2).sqrt().add(1.).reciprocal();
    T x3 = ex.negate().add(ey2.multiply(beta).negate().add(1.).multiply(LE.cos())).add(beta.multiply(ex).multiply(ey).multiply(LE.sin()));
    T y3 = ey.negate().add(ex2.negate().multiply(beta).add(1).multiply(LE.sin())).add(beta.multiply(ex).multiply(ey).multiply(LE.cos()));
    FieldVector3D<T> U = new FieldVector3D<>(hx2.add(1).subtract(hy2).divide(h2p1), hx.multiply(hy).multiply(2).divide(h2p1), hy.multiply(-2).divide(h2p1));
    FieldVector3D<T> V = new FieldVector3D<>(hx.multiply(2).multiply(hy).divide(h2p1), hy2.add(1).subtract(hx2).divide(h2p1), hx.multiply(2).divide(h2p1));
    FieldVector3D<T> r = new FieldVector3D<>(finalOrbit.getA(), new FieldVector3D<>(x3, U, y3, V));
    Assert.assertEquals(finalOrbit.getPVCoordinates().getPosition().getNorm().getReal(), r.getNorm().getReal(), Utils.epsilonTest * r.getNorm().getReal());
}