Examples with FieldVector3D org.hipparchus.geometry.euclidean.threed.FieldVector3D used on opensource projects

Example 46 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FieldEcksteinHechlerPropagatorTest method doPropagatedKeplerian.

private <T extends RealFieldElement<T>> void doPropagatedKeplerian(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    // Definition of initial conditions with Keplerian parameters
    // -----------------------------------------------------------
    FieldAbsoluteDate<T> initDate = date.shiftedBy(584.);
    FieldOrbit<T> initialOrbit = new FieldKeplerianOrbit<>(zero.add(7209668.0), zero.add(0.5e-4), zero.add(1.7), zero.add(2.1), zero.add(2.9), zero.add(6.2), PositionAngle.TRUE, FramesFactory.getEME2000(), initDate, provider.getMu());
    // Extrapolator definition
    // -----------------------
    FieldEcksteinHechlerPropagator<T> extrapolator = new FieldEcksteinHechlerPropagator<>(initialOrbit, new LofOffset(initialOrbit.getFrame(), LOFType.VNC), zero.add(2000.0), 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);
    // 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)
    // with ex and ey the same for initial and final orbit
    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(beta.negate().multiply(ey2).add(1).multiply(LE.cos())).add(beta.multiply(ex).multiply(ey).multiply(LE.sin()));
    T y3 = ey.negate().add(beta.negate().multiply(ex2).add(1).multiply(LE.sin())).add(beta.multiply(ex).multiply(ey).multiply(LE.cos()));
    FieldVector3D<T> U = new FieldVector3D<>(hx2.subtract(hy2).add(1.).divide(h2p1), hx.multiply(2).multiply(hy).divide(h2p1), hy.multiply(-2.).divide(h2p1));
    FieldVector3D<T> V = new FieldVector3D<>(hx.multiply(2.).multiply(hy).divide(h2p1), hy2.subtract(hx2).add(1.).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());
}

Example 47 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D 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());
}

Example 48 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FieldKeplerianPropagatorTest method doTestIssue107.

private <T extends RealFieldElement<T>> void doTestIssue107(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<T>(orbit) {

        FieldAbsoluteDate<T> lastDate = FieldAbsoluteDate.getPastInfinity(field);

        protected FieldSpacecraftState<T> basicPropagate(final FieldAbsoluteDate<T> date) throws OrekitException {
            if (date.compareTo(lastDate) < 0) {
                throw new OrekitException(LocalizedCoreFormats.SIMPLE_MESSAGE, "no backward propagation allowed");
            }
            lastDate = date;
            return super.basicPropagate(date);
        }
    };
    FieldSpacecraftState<T> finalState = propagator.propagate(date.shiftedBy(3600.0));
    Assert.assertEquals(3600.0, finalState.getDate().durationFrom(date).getReal(), 1.0e-15);
}

Example 49 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FieldEventDetectorTest method doTestIssue108Numerical.

private <T extends RealFieldElement<T>> void doTestIssue108Numerical(Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    final TimeScale utc = TimeScalesFactory.getUTC();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.56), zero.add(-25767.257));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.848), zero.add(942.781), zero.add(7435.922));
    final FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, 2003, 9, 16, utc);
    final FieldOrbit<T> orbit = new FieldCircularOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getEME2000(), date, mu);
    final T step = zero.add(60.0);
    final int n = 100;
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, new ClassicalRungeKuttaFieldIntegrator<>(field, step));
    propagator.setOrbitType(OrbitType.EQUINOCTIAL);
    propagator.resetInitialState(new FieldSpacecraftState<>(orbit));
    GCallsCounter<T> counter = new GCallsCounter<>(zero.add(100000.0), zero.add(1.0e-6), 20, new FieldStopOnEvent<GCallsCounter<T>, T>());
    propagator.addEventDetector(counter);
    propagator.propagate(date.shiftedBy(step.multiply(n)));
    Assert.assertEquals(n + 1, counter.getCount());
}

Example 50 with FieldVector3D

use of org.hipparchus.geometry.euclidean.threed.FieldVector3D in project Orekit by CS-SI.

the class FieldEclipseDetectorTest method doTestInsideOcculted.

private <T extends RealFieldElement<T>> void doTestInsideOcculted(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    final FieldVector3D<T> position = new FieldVector3D<>(zero.add(-6142438.668), zero.add(3492467.560), zero.add(-25767.25680));
    final FieldVector3D<T> velocity = new FieldVector3D<>(zero.add(505.8479685), zero.add(942.7809215), zero.add(7435.922231));
    FieldAbsoluteDate<T> iniDate = new FieldAbsoluteDate<>(field, 1969, 7, 28, 4, 0, 0.0, TimeScalesFactory.getTT());
    final FieldOrbit<T> orbit = new FieldEquinoctialOrbit<>(new FieldPVCoordinates<>(position, velocity), FramesFactory.getGCRF(), iniDate, mu);
    FieldSpacecraftState<T> initialState = new FieldSpacecraftState<>(orbit);
    double[] absTolerance = { 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001 };
    double[] relTolerance = { 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7 };
    AdaptiveStepsizeFieldIntegrator<T> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 1000, absTolerance, relTolerance);
    integrator.setInitialStepSize(field.getZero().add(60));
    FieldNumericalPropagator<T> propagator = new FieldNumericalPropagator<>(field, integrator);
    propagator.setOrbitType(OrbitType.EQUINOCTIAL);
    propagator.setInitialState(initialState);
    sun = CelestialBodyFactory.getSun();
    earth = CelestialBodyFactory.getEarth();
    sunRadius = 696000000.;
    earthRadius = 6400000.;
    FieldEclipseDetector<T> e = new FieldEclipseDetector<>(field.getZero().add(60.), field.getZero().add(1.e-3), sun, sunRadius, earth, earthRadius);
    Vector3D p = sun.getPVCoordinates(AbsoluteDate.J2000_EPOCH, FramesFactory.getGCRF()).getPosition();
    FieldSpacecraftState<T> s = new FieldSpacecraftState<>(new FieldCartesianOrbit<>(new TimeStampedFieldPVCoordinates<>(FieldAbsoluteDate.getJ2000Epoch(field), new FieldPVCoordinates<>(new FieldVector3D<>(field.getOne(), field.getZero(), field.getZero()).add(p), new FieldVector3D<>(field.getZero(), field.getZero(), field.getOne()))), FramesFactory.getGCRF(), mu));
    Assert.assertEquals(FastMath.PI, e.g(s).getReal(), 1.0e-15);
}