Examples with FieldAbsoluteDate org.orekit.time.FieldAbsoluteDate used on opensource projects

Example 51 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class FieldEcksteinHechlerPropagatorTest method doStopAtTargetDate.

private <T extends RealFieldElement<T>> void doStopAtTargetDate(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field);
    final FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(7.8e6), zero.add(0.032), zero.add(0.4), zero.add(0.1), zero.add(0.2), zero.add(0.3), PositionAngle.TRUE, FramesFactory.getEME2000(), date, 3.986004415e14);
    FieldEcksteinHechlerPropagator<T> propagator = new FieldEcksteinHechlerPropagator<>(orbit, provider);
    Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
    propagator.addEventDetector(new FieldNodeDetector<>(orbit, itrf).withHandler(new FieldContinueOnEvent<FieldNodeDetector<T>, T>()));
    FieldAbsoluteDate<T> farTarget = orbit.getDate().shiftedBy(10000.0);
    FieldSpacecraftState<T> propagated = propagator.propagate(farTarget);
    Assert.assertEquals(0.0, FastMath.abs(farTarget.durationFrom(propagated.getDate()).getReal()), 1.0e-3);
}

Example 52 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate 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 53 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate 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 54 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate in project Orekit by CS-SI.

the class FieldKeplerianPropagatorTest method doTestWrappedAttitudeException.

private <T extends RealFieldElement<T>> void doTestWrappedAttitudeException(Field<T> field) throws OrekitException {
    T zero = field.getZero();
    final FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(7.8e6), zero.add(0.032), zero.add(0.4), zero.add(0.1), zero.add(0.2), zero.add(0.3), PositionAngle.TRUE, FramesFactory.getEME2000(), new FieldAbsoluteDate<>(field), 3.986004415e14);
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, new AttitudeProvider() {

        private static final long serialVersionUID = 1L;

        public Attitude getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) throws OrekitException {
            throw new OrekitException((Throwable) null, new DummyLocalizable("dummy error"));
        }

        public <Q extends RealFieldElement<Q>> FieldAttitude<Q> getAttitude(FieldPVCoordinatesProvider<Q> pvProv, FieldAbsoluteDate<Q> date, Frame frame) throws OrekitException {
            throw new OrekitException((Throwable) null, new DummyLocalizable("dummy error"));
        }
    });
    propagator.propagate(orbit.getDate().shiftedBy(10.09));
}

Example 55 with FieldAbsoluteDate

use of org.orekit.time.FieldAbsoluteDate 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);
}