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

Example 11 with FieldKeplerianOrbit

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

the class FieldSpacecraftStateTest method doTestTransform.

private <T extends RealFieldElement<T>> void doTestTransform(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    T mass = zero.add(2500);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
    double maxDP = 0;
    double maxDV = 0;
    double maxDA = 0;
    for (double t = 0; t < orbit.getKeplerianPeriod().getReal(); t += 60) {
        final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(zero.add(t)));
        final Transform transform = state.toSpacecraftState().toTransform().getInverse();
        PVCoordinates pv = transform.transformPVCoordinates(PVCoordinates.ZERO);
        PVCoordinates dPV = new PVCoordinates(pv, state.getPVCoordinates().toPVCoordinates());
        Vector3D mZDirection = transform.transformVector(Vector3D.MINUS_K);
        double alpha = Vector3D.angle(mZDirection, state.getPVCoordinates().toPVCoordinates().getPosition());
        maxDP = FastMath.max(maxDP, dPV.getPosition().getNorm());
        maxDV = FastMath.max(maxDV, dPV.getVelocity().getNorm());
        maxDA = FastMath.max(maxDA, FastMath.toDegrees(alpha));
    }
    Assert.assertEquals(0.0, maxDP, 1.0e-6);
    Assert.assertEquals(0.0, maxDV, 1.0e-9);
    Assert.assertEquals(0.0, maxDA, 1.0e-12);
}

Example 12 with FieldKeplerianOrbit

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

the class FieldSpacecraftStateTest method doTestAdditionalStates.

private <T extends RealFieldElement<T>> void doTestAdditionalStates(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    T mass = zero.add(2500);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
    final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(60));
    T[] add = MathArrays.buildArray(field, 2);
    add[0] = zero.add(1.);
    add[1] = zero.add(2.);
    final FieldSpacecraftState<T> extended = state.addAdditionalState("test-1", add).addAdditionalState("test-2", zero.add(42.0));
    Assert.assertEquals(0, state.getAdditionalStates().size());
    Assert.assertFalse(state.hasAdditionalState("test-1"));
    try {
        state.getAdditionalState("test-1");
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertEquals(oe.getParts()[0], "test-1");
    }
    try {
        state.ensureCompatibleAdditionalStates(extended);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
    }
    try {
        extended.ensureCompatibleAdditionalStates(state);
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
        Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
    }
    try {
        T[] kk = MathArrays.buildArray(field, 7);
        extended.ensureCompatibleAdditionalStates(extended.addAdditionalState("test-2", kk));
        Assert.fail("an exception should have been thrown");
    } catch (MathIllegalStateException mise) {
        Assert.assertEquals(LocalizedCoreFormats.DIMENSIONS_MISMATCH, mise.getSpecifier());
        Assert.assertEquals(7, ((Integer) mise.getParts()[0]).intValue());
    }
    Assert.assertEquals(2, extended.getAdditionalStates().size());
    Assert.assertTrue(extended.hasAdditionalState("test-1"));
    Assert.assertTrue(extended.hasAdditionalState("test-2"));
    Assert.assertEquals(1.0, extended.getAdditionalState("test-1")[0].getReal(), 1.0e-15);
    Assert.assertEquals(2.0, extended.getAdditionalState("test-1")[1].getReal(), 1.0e-15);
    Assert.assertEquals(42.0, extended.getAdditionalState("test-2")[0].getReal(), 1.0e-15);
    // test various constructors
    T[] dd = MathArrays.buildArray(field, 1);
    dd[0] = zero.add(-6.0);
    Map<String, T[]> map = new HashMap<String, T[]>();
    map.put("test-3", dd);
    FieldSpacecraftState<T> sO = new FieldSpacecraftState<>(state.getOrbit(), map);
    Assert.assertEquals(-6.0, sO.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOA = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), map);
    Assert.assertEquals(-6.0, sOA.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOM = new FieldSpacecraftState<>(state.getOrbit(), state.getMass(), map);
    Assert.assertEquals(-6.0, sOM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sOAM = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), state.getMass(), map);
    Assert.assertEquals(-6.0, sOAM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
    FieldSpacecraftState<T> sFromDouble = new FieldSpacecraftState<>(field, sOAM.toSpacecraftState());
    Assert.assertEquals(-6.0, sFromDouble.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
}

Example 13 with FieldKeplerianOrbit

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

the class FieldSpacecraftStateTest method doTestDatesConsistency.

private <T extends RealFieldElement<T>> void doTestDatesConsistency(final Field<T> field) throws OrekitException {
    T zero = field.getZero();
    T a = zero.add(rOrbit.getA());
    T e = zero.add(rOrbit.getE());
    T i = zero.add(rOrbit.getI());
    T pa = zero.add(1.9674147913622104);
    T raan = zero.add(FastMath.toRadians(261));
    T lv = zero.add(0);
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
    BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
    new FieldSpacecraftState<>(orbit, attitudeLaw.getAttitude(orbit.shiftedBy(zero.add(10.0)), orbit.getDate().shiftedBy(10.0), orbit.getFrame()));
}

Example 14 with FieldKeplerianOrbit

use of org.orekit.orbits.FieldKeplerianOrbit 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 15 with FieldKeplerianOrbit

use of org.orekit.orbits.FieldKeplerianOrbit 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());
}