Example usage for org.apache.commons.math3.ode.nonstiff GraggBulirschStoerIntegrator GraggBulirschStoerIntegrator

Introduction

In this page you can find the example usage for org.apache.commons.math3.ode.nonstiff GraggBulirschStoerIntegrator GraggBulirschStoerIntegrator.

Prototype

public GraggBulirschStoerIntegrator(final double minStep, final double maxStep,
        final double[] vecAbsoluteTolerance, final double[] vecRelativeTolerance) 

Source Link

Document

Simple constructor.

Usage

From source file:org.orekit.forces.gravity.ThirdBodyAttractionTest.java

@Test(expected = OrekitException.class)
public void testSunContrib() throws OrekitException {

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    Orbit orbit = new EquinoctialOrbit(42164000, 10e-3, 10e-3,
            FastMath.tan(0.001745329) * FastMath.cos(2 * FastMath.PI / 3),
            FastMath.tan(0.001745329) * FastMath.sin(2 * FastMath.PI / 3), 0.1, PositionAngle.TRUE,
            FramesFactory.getEME2000(), date, mu);
    double period = 2 * FastMath.PI * orbit.getA() * FastMath.sqrt(orbit.getA() / orbit.getMu());

    // set up propagator
    NumericalPropagator calc = new NumericalPropagator(
            new GraggBulirschStoerIntegrator(10.0, period, 0, 1.0e-5));
    calc.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getSun()));

    // set up step handler to perform checks
    calc.setMasterMode(FastMath.floor(period), new ReferenceChecker(date) {
        protected double hXRef(double t) {
            return -1.06757e-3 + 0.221415e-11 * t + 18.9421e-5 * FastMath.cos(3.9820426e-7 * t)
                    - 7.59983e-5 * FastMath.sin(3.9820426e-7 * t);
        }/* w  w w  .  j a v a2 s  .  co  m*/

        protected double hYRef(double t) {
            return 1.43526e-3 + 7.49765e-11 * t + 6.9448e-5 * FastMath.cos(3.9820426e-7 * t)
                    + 17.6083e-5 * FastMath.sin(3.9820426e-7 * t);
        }
    });
    AbsoluteDate finalDate = date.shiftedBy(365 * period);
    calc.setInitialState(new SpacecraftState(orbit));
    calc.propagate(finalDate);

}

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From source file:org.orekit.forces.gravity.ThirdBodyAttractionTest.java

@Test
public void testMoonContrib() throws OrekitException {

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(1970, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    Orbit orbit = new EquinoctialOrbit(42164000, 10e-3, 10e-3,
            FastMath.tan(0.001745329) * FastMath.cos(2 * FastMath.PI / 3),
            FastMath.tan(0.001745329) * FastMath.sin(2 * FastMath.PI / 3), 0.1, PositionAngle.TRUE,
            FramesFactory.getEME2000(), date, mu);
    double period = 2 * FastMath.PI * orbit.getA() * FastMath.sqrt(orbit.getA() / orbit.getMu());

    // set up propagator
    NumericalPropagator calc = new NumericalPropagator(
            new GraggBulirschStoerIntegrator(10.0, period, 0, 1.0e-5));
    calc.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));

    // set up step handler to perform checks
    calc.setMasterMode(FastMath.floor(period), new ReferenceChecker(date) {
        protected double hXRef(double t) {
            return -0.000906173 + 1.93933e-11 * t + 1.0856e-06 * FastMath.cos(5.30637e-05 * t)
                    - 1.22574e-06 * FastMath.sin(5.30637e-05 * t);
        }/*  w w  w .  j a  va 2 s .  c o m*/

        protected double hYRef(double t) {
            return 0.00151973 + 1.88991e-10 * t - 1.25972e-06 * FastMath.cos(5.30637e-05 * t)
                    - 1.00581e-06 * FastMath.sin(5.30637e-05 * t);
        }
    });
    AbsoluteDate finalDate = date.shiftedBy(31 * period);
    calc.setInitialState(new SpacecraftState(orbit));
    calc.propagate(finalDate);

}

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From source file:org.orekit.propagation.conversion.GraggBulirschStoerIntegratorBuilder.java

/** {@inheritDoc} */
public AbstractIntegrator buildIntegrator(final Orbit orbit) throws PropagationException {
    final double[][] tol = NumericalPropagator.tolerances(dP, orbit, OrbitType.CARTESIAN);
    return new GraggBulirschStoerIntegrator(minStep, maxStep, tol[0], tol[1]);
}

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From source file:ummisco.gaml.extensions.maths.ode.utils.solver.GraggBulirschStoerSolver.java

public GraggBulirschStoerSolver(final double minStep, final double maxStep, final double scalAbsoluteTolerance,
        final double scalRelativeTolerance, final GamaMap<String, IList<Double>> integrated_val) {
    super((minStep + maxStep) / 2,
            new GraggBulirschStoerIntegrator(minStep, maxStep, scalAbsoluteTolerance, scalRelativeTolerance),
            integrated_val);
}

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