Example usage for org.apache.commons.math3.linear RealMatrix getEntry

Introduction

In this page you can find the example usage for org.apache.commons.math3.linear RealMatrix getEntry.

Prototype

double getEntry(int row, int column) throws OutOfRangeException;

Source Link

Document

Get the entry in the specified row and column.

Usage

From source file:lambertmrev.LambertMRev.java

/**
 * @param args the command line arguments
 *///from w w  w  .  j  av a  2 s.  c om
public static void main(String[] args) {
    // Want to test the Lambert class so you can specify the number of revs for which to compute
    //System.out.print("this is the frames tutorial \n");
    try {
        Frame inertialFrame = FramesFactory.getEME2000();
        TimeScale utc = TimeScalesFactory.getTAI();
        AbsoluteDate initialDate = new AbsoluteDate(2004, 01, 01, 23, 30, 00.000, utc);
        double mu = 3.986004415e+14;

        double a = 24396159; // semi major axis in meters
        double e = 0.72831215; // eccentricity
        double i = Math.toRadians(7); // inclination
        double omega = Math.toRadians(180); // perigee argument
        double raan = Math.toRadians(261); // right ascension of ascending node
        double lM = 0; // mean anomaly

        Orbit initialOrbit = new KeplerianOrbit(a, e, i, omega, raan, lM, PositionAngle.MEAN, inertialFrame,
                initialDate, mu);
        //KeplerianPropagator kepler = new KeplerianPropagator(initialOrbit);

        // set geocentric positions
        Vector3D r1 = new Vector3D(-6.88999e3, 3.92763e4, 2.67053e3);
        Vector3D r2 = new Vector3D(-3.41458e4, 2.05328e4, 3.44315e3);
        Vector3D r1_site = new Vector3D(4.72599e3, 1.26633e3, 4.07799e3);
        Vector3D r2_site = new Vector3D(4.70819e3, 1.33099e3, 4.07799e3);

        // get the topocentric positions
        Vector3D top1 = Transform.geo2radec(r1.scalarMultiply(1000), r1_site.scalarMultiply(1000));
        Vector3D top2 = Transform.geo2radec(r2.scalarMultiply(1000), r2_site.scalarMultiply(1000));

        // time of flight in seconds
        double tof = 3 * 3600;

        // propagate to 0 and tof
        Lambert test = new Lambert();

        boolean cw = false;
        int multi_revs = 1;
        RealMatrix v1_mat;
        Random randomGenerator = new Random();

        PrintWriter out_a = new PrintWriter("out_java_a.txt");
        PrintWriter out_e = new PrintWriter("out_java_e.txt");
        PrintWriter out_rho1 = new PrintWriter("out_java_rho1.txt");
        PrintWriter out_rho2 = new PrintWriter("out_java_rho2.txt");

        // start the loop
        double A, Ecc, rho1, rho2, tof_hyp;

        long time1 = System.nanoTime();
        for (int ll = 0; ll < 1e6; ll++) {

            rho1 = top1.getZ() / 1000 + 1e-3 * randomGenerator.nextGaussian() * top1.getZ() / 1000;
            rho2 = top2.getZ() / 1000 + 1e-3 * randomGenerator.nextGaussian() * top2.getZ() / 1000;
            //tof_hyp = FastMath.abs(tof + 0.1*3600 * randomGenerator.nextGaussian());
            // from topo to geo
            Vector3D r1_hyp = Transform.radec2geo(top1.getX(), top1.getY(), rho1, r1_site);
            Vector3D r2_hyp = Transform.radec2geo(top2.getX(), top2.getY(), rho2, r2_site);
            //            System.out.println(r1_hyp.scalarMultiply(1000).getNorm());
            //            System.out.println(r2_hyp.scalarMultiply(1000).getNorm());
            //            System.out.println(tof/3600);
            test.lambert_problem(r1_hyp.scalarMultiply(1000), r2_hyp.scalarMultiply(1000), tof, mu, cw,
                    multi_revs);

            v1_mat = test.get_v1();

            Vector3D v1 = new Vector3D(v1_mat.getEntry(0, 0), v1_mat.getEntry(0, 1), v1_mat.getEntry(0, 2));
            //            System.out.println(v1);
            PVCoordinates rv1 = new PVCoordinates(r1_hyp.scalarMultiply(1000), v1);
            Orbit orbit_out = new KeplerianOrbit(rv1, inertialFrame, initialDate, mu);
            A = orbit_out.getA();
            Ecc = orbit_out.getE();

            //            System.out.println(ll + " - " +A);
            out_a.println(A);
            out_e.println(Ecc);
            out_rho1.println(rho1);
            out_rho2.println(rho2);
        }
        long time2 = System.nanoTime();
        long timeTaken = time2 - time1;

        out_a.close();
        out_e.close();
        out_rho1.close();
        out_rho2.close();

        System.out.println("Time taken " + timeTaken / 1000 / 1000 + " milli secs");

        // get the truth
        test.lambert_problem(r1.scalarMultiply(1000), r2.scalarMultiply(1000), tof, mu, cw, multi_revs);
        v1_mat = test.get_v1();
        Vector3D v1 = new Vector3D(v1_mat.getEntry(0, 0), v1_mat.getEntry(0, 1), v1_mat.getEntry(0, 2));
        PVCoordinates rv1 = new PVCoordinates(r1.scalarMultiply(1000), v1);
        Orbit orbit_out = new KeplerianOrbit(rv1, inertialFrame, initialDate, mu);
        //System.out.println(orbit_out.getA());
    } catch (FileNotFoundException ex) {
        Logger.getLogger(LambertMRev.class.getName()).log(Level.SEVERE, null, ex);
    }
}

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From source file:lsafunctions.LSA.java

private static int calcDf(int nRow, RealMatrix M) {
    int df = 0;//from  www  . ja  v  a  2s .  c om
    for (int j = 0; j < M.getColumnDimension(); j++) {
        if (M.getEntry(nRow, j) != 0) {
            df++;
        }
    }
    return df;
}

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From source file:com.analog.lyric.math.LyricSingularValueDecomposition.java

private static RealMatrix checkMatrix(RealMatrix m) {
    for (int i = 0; i < m.getRowDimension(); i++) {
        for (int j = 0; j < m.getColumnDimension(); j++) {
            if (Double.isNaN(m.getEntry(i, j)) || Double.isInfinite(m.getEntry(i, j))) {
                throw new DimpleException("cannot do SVD on matrix that contains NaN or infinite");
            }//www  . java  2 s.c o m
        }
    }
    return m;
}

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From source file:com.google.location.lbs.gnss.gps.pseudorange.Ecef2EnuConverter.java

/**
 * Converts a vector represented by coordinates ecefX, ecefY, ecefZ in an
 * Earth-Centered Earth-Fixed (ECEF) Cartesian system into a vector in a
 * local east-north-up (ENU) Cartesian system.
 *
 * <p> For example it can be used to rotate a speed vector or position offset vector to ENU.
 *
 * @param ecefX X coordinates in ECEF//from   w  ww .j av a 2  s .c o m
 * @param ecefY Y coordinates in ECEF
 * @param ecefZ Z coordinates in ECEF
 * @param refLat Latitude in Radians of the Reference Position
 * @param refLng Longitude in Radians of the Reference Position
 * @return the converted values in {@code EnuValues}
 */
public static EnuValues convertEcefToEnu(double ecefX, double ecefY, double ecefZ, double refLat,
        double refLng) {

    RealMatrix rotationMatrix = getRotationMatrix(refLat, refLng);
    RealMatrix ecefCoordinates = new Array2DRowRealMatrix(new double[] { ecefX, ecefY, ecefZ });

    RealMatrix enuResult = rotationMatrix.multiply(ecefCoordinates);
    return new EnuValues(enuResult.getEntry(0, 0), enuResult.getEntry(1, 0), enuResult.getEntry(2, 0));
}

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From source file:edu.oregonstate.eecs.mcplan.ml.HilbertSpace.java

public static double inner_prod(final double[] x, final RealMatrix M, final double[] y) {
    double s = 0.0;
    for (int i = 0; i < M.getRowDimension(); ++i) {
        for (int j = 0; j < M.getColumnDimension(); ++j) {
            s += x[i] * M.getEntry(i, j) * y[j];
        }// w  w  w  .  j a va  2 s.c  o m
    }
    return s;
}

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From source file:com.itemanalysis.psychometrics.factoranalysis.MatrixUtils.java

public static double sumMatrix(RealMatrix X) {
    double sum = 0.0;
    for (int i = 0; i < X.getRowDimension(); i++) {
        for (int j = 0; j < X.getColumnDimension(); j++) {
            sum += X.getEntry(i, j);
        }/*from   ww  w.ja v  a 2  s . c  o  m*/
    }
    return sum;
}

---

From source file:lambertmrev.conversions.java

public static CartesianOrbit hyp2ele(double[] hyp, Vector<Tracklet> subSet, constraints set,
        TopocentricFrame staF, Frame inertialFrame, TimeScale utc) {
    int N = subSet.size();
    AbsoluteDate year = new AbsoluteDate(Main.YEAR, utc);
    double tof = FastMath.abs(subSet.elementAt(0).getDOY() - subSet.elementAt(N - 1).getDOY()) * 24 * 3600;

    //        System.out.println("RA\t:" + subSet.elementAt(0).getRA() + "\tDEC:\t" + subSet.elementAt(0).getDEC() + "\thyp:\t" + hyp[0]);

    Vector3D geoPos1 = conversions.radec2geo(subSet.elementAt(0), hyp[0], staF, inertialFrame, utc);
    Vector3D geoPos2 = conversions.radec2geo(subSet.elementAt(N - 1), hyp[1], staF, inertialFrame, utc);

    //        System.out.println("x1:\t" + geoPos1.getX() + "\ty1:\t" + geoPos1.getY() + "\tz1:\t" + geoPos1.getZ());

    // define epoch of first tracklet
    AbsoluteDate epoch0 = new AbsoluteDate(year, subSet.elementAt(0).getDOY() * 24 * 3600);

    // perform lambert solver
    Lambert solve = new Lambert();
    solve.lambert_problem(geoPos1, geoPos2, tof, Constants.EIGEN5C_EARTH_MU, Boolean.FALSE, 1);
    RealMatrix v1 = solve.get_v1();

    // get the orbital elements at epoch 0
    Vector3D v1vec = new Vector3D(v1.getEntry(0, 0), v1.getEntry(0, 1), v1.getEntry(0, 2));
    PVCoordinates PVgeo1 = new PVCoordinates(geoPos1, v1vec);
    CartesianOrbit orbit = new CartesianOrbit(PVgeo1, inertialFrame, epoch0, Constants.EIGEN5C_EARTH_MU);

    //        System.out.println("a:\t" + orbit.getA() + "\ti:\t" + orbit.getI() + "\te:\t" + orbit.getE());
    return orbit;
}

---

From source file:lsafunctions.LSA.java

public static double cosinSim(int v1, int v2, RealMatrix Vt) {
    double sim = 0.0;
    double sumNum = 0.0;
    double fdenom = 0.0;
    double sdenom = 0.0;

    for (int j = 0; j < Vt.getRowDimension(); j++) {
        sumNum += Vt.getEntry(j, v1) * Vt.getEntry(j, v2);
        fdenom += Math.pow(Vt.getEntry(j, v1), 2);
        sdenom += Math.pow(Vt.getEntry(j, v2), 2);
    }//from   w  w w.  j  a  v  a 2  s .  c  o m
    sim = sumNum / (Math.sqrt(fdenom) * Math.sqrt(sdenom));

    return sim;
}

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From source file:edu.oregonstate.eecs.mcplan.ml.MatrixAlgorithms.java

public static RealMatrix makePositiveDefinite(final RealMatrix M, final double eps) {
    assert (eps > 0.0);
    final SingularValueDecomposition svd = new SingularValueDecomposition(M);
    final RealMatrix Sigma = svd.getS().copy();
    final int N = Math.min(Sigma.getColumnDimension(), Sigma.getRowDimension());
    for (int i = 0; i < N; ++i) {
        final double lambda = Sigma.getEntry(i, i);
        System.out.println("lambda_" + i + " = " + lambda);
        if (Math.abs(lambda) < eps) {
            System.out.println("Corrected " + i);
            Sigma.setEntry(i, i, eps);//  ww w  . j  av a2s.  c om
        } else if (lambda < 0.0) {
            throw new NonPositiveDefiniteMatrixException(lambda, i, eps);
        } else {
            Sigma.setEntry(i, i, lambda);
        }
    }
    return svd.getU().multiply(Sigma).multiply(svd.getVT());
}

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From source file:edu.oregonstate.eecs.mcplan.ml.MatrixAlgorithms.java

/**
 * Computes the inverse of a matrix using the singular value decomposition.
 * // w ww.  ja  v a  2  s  .c o m
 * The input matrix M is assumed to be positive definite up to numerical
 * precision 'eps'. That is, for all eigenvalues lambda of M, it must be
 * the case that lambda + eps > 0. For eigenvalues with |lambda| < eps, the
 * eigenvalue is set to 'eps' before inverting. Throws an exception if
 * any lambda < -eps.
 * @param M
 * @param eps
 * @return
 */
public static RealMatrix robustInversePSD(final RealMatrix M, final double eps) {
    assert (eps > 0.0);
    final SingularValueDecomposition svd = new SingularValueDecomposition(M);
    final RealMatrix Sigma = svd.getS().copy();
    final int N = Math.min(Sigma.getColumnDimension(), Sigma.getRowDimension());
    for (int i = 0; i < N; ++i) {
        final double lambda = Sigma.getEntry(i, i);
        System.out.println("lambda_" + i + " = " + lambda);
        if (Math.abs(lambda) < eps) {
            System.out.println("Corrected " + i);
            Sigma.setEntry(i, i, 1.0 / eps);
        } else if (lambda < 0.0) {
            throw new IllegalArgumentException("Negative eigenvalue " + lambda);
        } else {
            Sigma.setEntry(i, i, 1.0 / lambda);
        }
    }
    return svd.getV().multiply(Sigma.transpose()).multiply(svd.getUT());
}

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