List of usage examples for java.util Formatter close
public void close()
From source file:Main.java
public static void main(String[] args) { StringBuffer buffer = new StringBuffer(); Formatter formatter = new Formatter(buffer, Locale.US); // format a new string String name = "from java2s.com"; formatter.format("Hello %s !", name); // print the formatted string System.out.println(formatter); // close the formatter formatter.close(); // attempt to access the formatter results in exception System.out.println(formatter); }
From source file:Main.java
public static void main(String[] args) { File file = new File("xyz.txt"); Formatter fm = null; try {//from w w w. jav a 2s .com // Create a Formatter that will write the output the file fm = new Formatter(file); // Formatting strings fm.format("%1$s, %2$s, and %3$s %n", "A", "B", "C"); fm.format("%3$s, %2$s, and %1$s %n", "A", "B", "C"); // Format more text here... } catch (FileNotFoundException e) { e.printStackTrace(); } finally { if (fm != null) { fm.close(); } } }
From source file:Main.java
public static void main(String[] argv) throws Exception { Formatter fmtCon = new Formatter(System.out); Formatter fmtFile = new Formatter(new FileOutputStream("test.fmt")); fmtCon.format("a negative number: %(.2f\n\n", -123.34); fmtCon.format("%8s %8s\n", "Value", "Square"); for (int i = 1; i < 20; i++) fmtCon.format("%8d %8d\n", i, i * i); // write to the file. fmtFile.format("This is a negative number: %(.2f\n\n", -123.34); fmtFile.format("%8s %8s\n", "Value", "Square"); for (int i = 1; i < 20; i++) fmtFile.format("%8d %8d\n", i, i * i); fmtFile.close(); if (fmtFile.ioException() != null) { System.out.println("File I/O Error Occurred"); }/*from w w w. ja v a 2 s . c om*/ }
From source file:Main.java
public static void main(String[] argv) throws Exception { Formatter fmtCon = new Formatter(System.out); Formatter fmtFile; fmtFile = new Formatter(new FileOutputStream("test.fmt")); fmtCon.format("a negative number: %(.2f\n\n", -123.34); fmtCon.format("%8s %8s\n", "Value", "Square"); for (int i = 1; i < 20; i++) fmtCon.format("%8d %8d\n", i, i * i); // write to the file. fmtFile.format("This is a negative number: %(.2f\n\n", -123.34); fmtFile.format("%8s %8s\n", "Value", "Square"); for (int i = 1; i < 20; i++) fmtFile.format("%8d %8d\n", i, i * i); fmtFile.close(); if (fmtFile.ioException() != null) { System.out.println("File I/O Error Occurred"); }//from ww w. j a va2 s . c o m }
From source file:gentracklets.Propagate.java
public static void main(String[] args) throws OrekitException { // load the data files File data = new File("/home/zittersteijn/Documents/java/libraries/orekit-data.zip"); DataProvidersManager DM = DataProvidersManager.getInstance(); ZipJarCrawler crawler = new ZipJarCrawler(data); DM.clearProviders();/*from ww w. j a v a2s. co m*/ DM.addProvider(crawler); // Read in TLE elements File tleFile = new File("/home/zittersteijn/Documents/TLEs/ASTRA20151207.tle"); FileReader TLEfr; Vector<TLE> tles = new Vector<>(); tles.setSize(30); try { // read and save TLEs to a vector TLEfr = new FileReader("/home/zittersteijn/Documents/TLEs/ASTRA20151207.tle"); BufferedReader readTLE = new BufferedReader(TLEfr); Scanner s = new Scanner(tleFile); String line1, line2; TLE2 tle = new TLE2(); int nrOfObj = 4; for (int ii = 1; ii < nrOfObj + 1; ii++) { System.out.println(ii); line1 = s.nextLine(); line2 = s.nextLine(); if (TLE.isFormatOK(line1, line2)) { tles.setElementAt(new TLE(line1, line2), ii); System.out.println(tles.get(ii).toString()); } else { System.out.println("format problem"); } } readTLE.close(); // define a groundstation Frame inertialFrame = FramesFactory.getEME2000(); TimeScale utc = TimeScalesFactory.getUTC(); double longitude = FastMath.toRadians(7.465); double latitude = FastMath.toRadians(46.87); double altitude = 950.; GeodeticPoint station = new GeodeticPoint(latitude, longitude, altitude); Frame earthFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true); BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, earthFrame); TopocentricFrame staF = new TopocentricFrame(earth, station, "station"); Vector<Orbit> eles = new Vector<>(); eles.setSize(tles.size()); for (int ii = 1; ii < nrOfObj + 1; ii++) { double a = FastMath.pow(Constants.WGS84_EARTH_MU / FastMath.pow(tles.get(ii).getMeanMotion(), 2), (1.0 / 3)); // convert them to orbits Orbit kep = new KeplerianOrbit(a, tles.get(ii).getE(), tles.get(ii).getI(), tles.get(ii).getPerigeeArgument(), tles.get(ii).getRaan(), tles.get(ii).getMeanAnomaly(), PositionAngle.MEAN, inertialFrame, tles.get(ii).getDate(), Constants.WGS84_EARTH_MU); eles.setElementAt(kep, ii); // set up propagators KeplerianPropagator kepler = new KeplerianPropagator(eles.get(ii)); System.out.println("a: " + a); // Initial state definition double mass = 1000.0; SpacecraftState initialState = new SpacecraftState(kep, mass); // Adaptive step integrator // with a minimum step of 0.001 and a maximum step of 1000 double minStep = 0.001; double maxstep = 1000.0; double positionTolerance = 10.0; OrbitType propagationType = OrbitType.KEPLERIAN; double[][] tolerances = NumericalPropagator.tolerances(positionTolerance, kep, propagationType); AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxstep, tolerances[0], tolerances[1]); NumericalPropagator propagator = new NumericalPropagator(integrator); propagator.setOrbitType(propagationType); // set up and add force models double AMR = 4.0; double crossSection = mass * AMR; double Cd = 0.01; double Cr = 0.5; double Co = 0.8; NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(4, 4); ForceModel holmesFeatherstone = new HolmesFeatherstoneAttractionModel( FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider); SphericalSpacecraft ssc = new SphericalSpacecraft(crossSection, Cd, Cr, Co); PVCoordinatesProvider sun = CelestialBodyFactory.getSun(); SolarRadiationPressure srp = new SolarRadiationPressure(sun, Constants.WGS84_EARTH_EQUATORIAL_RADIUS, ssc); // propagator.addForceModel(srp); // propagator.addForceModel(holmesFeatherstone); propagator.setInitialState(initialState); // propagate the orbits with steps size and tracklet lenght at several epochs (tracklets) Vector<AbsoluteDate> startDates = new Vector<>(); startDates.setSize(1); startDates.setElementAt(new AbsoluteDate(2016, 1, 26, 20, 00, 00, utc), 0); // set the step size [s] and total length double tstep = 100; double ld = 3; double ls = FastMath.floor(ld * (24 * 60 * 60) / tstep); System.out.println(ls); SpacecraftState currentStateKep = kepler.propagate(startDates.get(0)); SpacecraftState currentStatePer = propagator.propagate(startDates.get(0)); for (int tt = 0; tt < startDates.size(); tt++) { // set up output file String app = tles.get(ii).getSatelliteNumber() + "_" + startDates.get(tt) + ".txt"; // with formatted output File file1 = new File("/home/zittersteijn/Documents/propagate/keplerian/MEO/" + app); File file2 = new File("/home/zittersteijn/Documents/propagate/perturbed/MEO/" + app); file1.createNewFile(); file2.createNewFile(); Formatter fmt1 = new Formatter(file1); Formatter fmt2 = new Formatter(file2); for (int kk = 0; kk < (int) ls; kk++) { AbsoluteDate propDate = startDates.get(tt).shiftedBy(tstep * kk); currentStateKep = kepler.propagate(propDate); currentStatePer = propagator.propagate(propDate); System.out.println(currentStateKep.getPVCoordinates().getPosition() + "\t" + currentStateKep.getDate()); // convert to RADEC coordinates double[] radecKep = conversions.geo2radec(currentStateKep.getPVCoordinates(), staF, inertialFrame, propDate); double[] radecPer = conversions.geo2radec(currentStatePer.getPVCoordinates(), staF, inertialFrame, propDate); // write the orbit to seperate files with the RA, DEC, epoch and fence given AbsoluteDate year = new AbsoluteDate(YEAR, utc); fmt1.format("%.12f %.12f %.12f %d%n", radecKep[0], radecKep[2], (currentStateKep.getDate().durationFrom(year) / (24 * 3600)), (tt + 1)); fmt2.format("%.12f %.12f %.12f %d%n", radecPer[0], radecPer[2], (currentStateKep.getDate().durationFrom(year) / (24 * 3600)), (tt + 1)); } fmt1.flush(); fmt1.close(); fmt2.flush(); fmt2.close(); } double[] radecKep = conversions.geo2radec(currentStateKep.getPVCoordinates(), staF, inertialFrame, new AbsoluteDate(startDates.get(0), ls * tstep)); double[] radecPer = conversions.geo2radec(currentStatePer.getPVCoordinates(), staF, inertialFrame, new AbsoluteDate(startDates.get(0), ls * tstep)); double sig0 = 1.0 / 3600.0 / 180.0 * FastMath.PI; double dRA = radecKep[0] - radecPer[0] / (sig0 * sig0); double dDEC = radecKep[2] - radecPer[2] / (sig0 * sig0); System.out.println(dRA + "\t" + dDEC); } } catch (FileNotFoundException ex) { Logger.getLogger(GenTracklets.class.getName()).log(Level.SEVERE, null, ex); } catch (IOException iox) { Logger.getLogger(GenTracklets.class.getName()).log(Level.SEVERE, null, iox); } }
From source file:gentracklets.GenTracklets.java
public static void main(String[] args) throws OrekitException { // load the data files File data = new File("/home/zittersteijn/Documents/java/libraries/orekit-data.zip"); DataProvidersManager DM = DataProvidersManager.getInstance(); ZipJarCrawler crawler = new ZipJarCrawler(data); DM.clearProviders();// ww w .j a v a 2 s. c o m DM.addProvider(crawler); // Read in TLE elements File tleFile = new File("/home/zittersteijn/Documents/TLEs/ASTRA20151207.tle"); FileReader TLEfr; Vector<TLE> tles = new Vector<>(); tles.setSize(30); try { // read and save TLEs to a vector TLEfr = new FileReader("/home/zittersteijn/Documents/TLEs/ASTRA20151207.tle"); BufferedReader readTLE = new BufferedReader(TLEfr); Scanner s = new Scanner(tleFile); String line1, line2; TLE2 tle = new TLE2(); int nrOfObj = 4; for (int ii = 1; ii < nrOfObj + 1; ii++) { System.out.println(ii); line1 = s.nextLine(); line2 = s.nextLine(); if (TLE.isFormatOK(line1, line2)) { tles.setElementAt(new TLE(line1, line2), ii); System.out.println(tles.get(ii).toString()); } else { System.out.println("format problem"); } } readTLE.close(); // define a groundstation Frame inertialFrame = FramesFactory.getEME2000(); TimeScale utc = TimeScalesFactory.getUTC(); double longitude = FastMath.toRadians(7.465); double latitude = FastMath.toRadians(46.87); double altitude = 950.; GeodeticPoint station = new GeodeticPoint(latitude, longitude, altitude); Frame earthFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, true); BodyShape earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, earthFrame); TopocentricFrame staF = new TopocentricFrame(earth, station, "station"); Vector<Orbit> eles = new Vector<>(); eles.setSize(tles.size()); for (int ii = 1; ii < nrOfObj + 1; ii++) { double a = FastMath.pow(Constants.WGS84_EARTH_MU / FastMath.pow(tles.get(ii).getMeanMotion(), 2), (1.0 / 3)); // convert them to orbits Orbit kep = new KeplerianOrbit(a, tles.get(ii).getE(), tles.get(ii).getI(), tles.get(ii).getPerigeeArgument(), tles.get(ii).getRaan(), tles.get(ii).getMeanAnomaly(), PositionAngle.MEAN, inertialFrame, tles.get(ii).getDate(), Constants.WGS84_EARTH_MU); eles.setElementAt(kep, ii); // set up propagators KeplerianPropagator kepler = new KeplerianPropagator(eles.get(ii)); System.out.println("a: " + a); // Initial state definition double mass = 1000.0; SpacecraftState initialState = new SpacecraftState(kep, mass); // Adaptive step integrator // with a minimum step of 0.001 and a maximum step of 1000 double minStep = 0.001; double maxstep = 1000.0; double positionTolerance = 10.0; OrbitType propagationType = OrbitType.KEPLERIAN; double[][] tolerances = NumericalPropagator.tolerances(positionTolerance, kep, propagationType); AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxstep, tolerances[0], tolerances[1]); NumericalPropagator propagator = new NumericalPropagator(integrator); propagator.setOrbitType(propagationType); // set up and add force models double AMR = 0.4; double crossSection = mass * AMR; double Cd = 0.01; double Cr = 0.5; double Co = 0.8; NormalizedSphericalHarmonicsProvider provider = GravityFieldFactory.getNormalizedProvider(4, 4); ForceModel holmesFeatherstone = new HolmesFeatherstoneAttractionModel( FramesFactory.getITRF(IERSConventions.IERS_2010, true), provider); SphericalSpacecraft ssc = new SphericalSpacecraft(crossSection, Cd, Cr, Co); PVCoordinatesProvider sun = CelestialBodyFactory.getSun(); SolarRadiationPressure srp = new SolarRadiationPressure(sun, Constants.WGS84_EARTH_EQUATORIAL_RADIUS, ssc); propagator.addForceModel(srp); propagator.addForceModel(holmesFeatherstone); propagator.setInitialState(initialState); // propagate the orbits with steps size and tracklet lenght at several epochs (tracklets) Vector<AbsoluteDate> startDates = new Vector<>(); startDates.setSize(3); startDates.setElementAt(new AbsoluteDate(2015, 12, 8, 20, 00, 00, utc), 0); startDates.setElementAt(new AbsoluteDate(2015, 12, 9, 21, 00, 00, utc), 1); startDates.setElementAt(new AbsoluteDate(2015, 12, 10, 22, 00, 00, utc), 2); double tstep = 30; int l = 7; for (int tt = 0; tt < startDates.size(); tt++) { // set up output file String app = "S_" + tles.get(ii).getSatelliteNumber() + "_" + startDates.get(tt) + ".txt"; // FileWriter trackletsOutKep = new FileWriter("/home/zittersteijn/Documents/tracklets/simulated/keplerian/ASTRA/dt1h/AMR040/" + app); // FileWriter trackletsOutPer = new FileWriter("/home/zittersteijn/Documents/tracklets/simulated/perturbed/ASTRA/dt1h/AMR040/" + app); // BufferedWriter trackletsKepBW = new BufferedWriter(trackletsOutKep); // BufferedWriter trackletsPerBW = new BufferedWriter(trackletsOutPer); // with formatted output File file1 = new File( "/home/zittersteijn/Documents/tracklets/simulated/keplerian/ASTRA/dt1d/AMR040/" + app); File file2 = new File( "/home/zittersteijn/Documents/tracklets/simulated/perturbed/ASTRA/dt1d/AMR040/" + app); file1.createNewFile(); file2.createNewFile(); Formatter fmt1 = new Formatter(file1); Formatter fmt2 = new Formatter(file2); for (int kk = 0; kk < l; kk++) { AbsoluteDate propDate = startDates.get(tt).shiftedBy(tstep * kk); SpacecraftState currentStateKep = kepler.propagate(propDate); SpacecraftState currentStatePer = propagator.propagate(propDate); System.out.println(currentStateKep.getPVCoordinates().getPosition() + "\t" + currentStateKep.getDate()); // convert to RADEC coordinates double[] radecKep = conversions.geo2radec(currentStateKep.getPVCoordinates(), staF, inertialFrame, propDate); double[] radecPer = conversions.geo2radec(currentStatePer.getPVCoordinates(), staF, inertialFrame, propDate); // write the tracklets to seperate files with the RA, DEC, epoch and fence given // System.out.println(tles.get(kk).getSatelliteNumber() + "\t" + radec[0] / (2 * FastMath.PI) * 180 + "\t" + currentState.getDate()); AbsoluteDate year = new AbsoluteDate(YEAR, utc); fmt1.format("%.12f %.12f %.12f %d%n", radecKep[0], radecKep[2], (currentStateKep.getDate().durationFrom(year) / (24 * 3600)), (tt + 1)); fmt2.format("%.12f %.12f %.12f %d%n", radecPer[0], radecPer[2], (currentStateKep.getDate().durationFrom(year) / (24 * 3600)), (tt + 1)); } fmt1.flush(); fmt1.close(); fmt2.flush(); fmt2.close(); } } } catch (FileNotFoundException ex) { Logger.getLogger(GenTracklets.class.getName()).log(Level.SEVERE, null, ex); } catch (IOException iox) { Logger.getLogger(GenTracklets.class.getName()).log(Level.SEVERE, null, iox); } }
From source file:Main.java
public static String toHexString(byte[] bytes) { // Used to parse byte array and return as string StringBuilder sb = new StringBuilder(bytes.length * 2); Formatter formatter = new Formatter(sb); for (byte b : bytes) { formatter.format("%02x", b); }//from w w w . java 2 s.c o m formatter.close(); return sb.toString(); }
From source file:ch.unibe.cde.geonet.kernel.security.Md5PasswordEncoder.java
/** * * @param hash//from w ww. j ava 2 s . co m * @return * * Copied from http://stackoverflow.com/a/9071224/1829038 */ private static String byteToHex(final byte[] hash) { Formatter formatter = new Formatter(); for (byte b : hash) { formatter.format("%02x", b); } String result = formatter.toString(); formatter.close(); return result; }
From source file:sturesy.util.Crypt.java
public static String toHex(byte[] bytes) { Formatter formatter = new Formatter(); for (byte b : bytes) { formatter.format("%02x", b); }/*from w w w . j av a 2 s.c om*/ String result = formatter.toString(); formatter.close(); return result; }
From source file:edu.smc.mediacommons.modules.Md5Module.java
public static String getSHA1(final File file) { String sha1 = null;/*w ww .j av a2s. co m*/ try { final MessageDigest messageDigest = MessageDigest.getInstance("SHA1"); InputStream is = new BufferedInputStream(new FileInputStream(file)); final byte[] buffer = new byte[1024]; for (int read = 0; (read = is.read(buffer)) != -1;) { messageDigest.update(buffer, 0, read); } // Convert the byte to hex format Formatter formatter = new Formatter(); for (final byte b : messageDigest.digest()) { formatter.format("%02x", b); } sha1 = formatter.toString(); formatter.close(); is.close(); } catch (IOException | NoSuchAlgorithmException e) { e.printStackTrace(); } finally { } return sha1; }