List of usage examples for java.util Formatter Formatter
public Formatter(OutputStream os)
From source file:MainClass.java
public static void main(String[] args) { String[] phrases = { "A", "B 1", "C 1.3" }; String dirname = "C:/test"; String filename = "Phrases.txt"; File dir = new File(dirname); File aFile = new File(dir, filename); FileOutputStream outputFile = null; try {//from ww w. ja v a 2s .c om outputFile = new FileOutputStream(aFile, true); } catch (FileNotFoundException e) { e.printStackTrace(System.err); } FileChannel outChannel = outputFile.getChannel(); ByteBuffer buf = ByteBuffer.allocate(1024); System.out.println(buf.position()); System.out.println(buf.limit()); System.out.println(buf.capacity()); CharBuffer charBuf = buf.asCharBuffer(); System.out.println(charBuf.position()); System.out.println(charBuf.limit()); System.out.println(charBuf.capacity()); Formatter formatter = new Formatter(charBuf); int number = 0; for (String phrase : phrases) { formatter.format("%n %s", ++number, phrase); System.out.println(charBuf.position()); System.out.println(charBuf.limit()); System.out.println(charBuf.capacity()); charBuf.flip(); System.out.println(charBuf.position()); System.out.println(charBuf.limit()); System.out.println(charBuf.length()); buf.limit(2 * charBuf.length()); // Set byte buffer limit System.out.println(buf.position()); System.out.println(buf.limit()); System.out.println(buf.remaining()); try { outChannel.write(buf); buf.clear(); charBuf.clear(); } catch (IOException e) { e.printStackTrace(System.err); } } try { outputFile.close(); } catch (IOException e) { e.printStackTrace(System.err); } }
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 w w w . j a va 2 s. c om*/ 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();//from ww w. j ava 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 hexEncode(byte[] in) { StringBuilder builder = new StringBuilder(in.length * 2); Formatter formatter = new Formatter(builder); for (byte inByte : in) { formatter.format("%02x", inByte); }// w w w . j a va2 s . co m return builder.toString(); }
From source file:Main.java
public static String byteArrayToHexString(byte[] paramArrayOfByte) { StringBuilder localStringBuilder = new StringBuilder(2 * paramArrayOfByte.length); Formatter localFormatter = new Formatter(localStringBuilder); int i = paramArrayOfByte.length; for (int j = 0; j < i; j++) { byte b = paramArrayOfByte[j]; Object[] arrayOfObject = new Object[1]; arrayOfObject[0] = Byte.valueOf(b); localFormatter.format("%02x", arrayOfObject); }// w w w. java 2 s . c o m localFormatter.close(); return localStringBuilder.toString(); }
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.j a va 2s . c om formatter.close(); return sb.toString(); }
From source file:Main.java
private static String encodeHex(byte[] data) { StringBuilder sb = new StringBuilder(data.length * 2); Formatter formatter = new Formatter(sb); for (byte b : data) { formatter.format("%02x", b); }//from ww w . j av a 2 s.c o m return sb.toString(); }
From source file:Main.java
private static String mBytesToHexString(byte[] bytes) { StringBuilder sb = new StringBuilder(bytes.length * 2); Formatter formatter = new Formatter(sb); for (byte b : bytes) { formatter.format("%02x", b); }// ww w. j a va 2s .c o m return "0x" + sb.toString().toUpperCase(); }
From source file:Main.java
public static String toUUIDFormat(byte[] bytes) { byte[] switched = new byte[] { bytes[3], bytes[2], bytes[1], bytes[0], bytes[5], bytes[4], bytes[7], bytes[6], bytes[8], bytes[9], bytes[10], bytes[11], bytes[12], bytes[13], bytes[14], bytes[15] }; StringBuilder sb = new StringBuilder(bytes.length * 2); Formatter formatter = new Formatter(sb); for (byte b : switched) { formatter.format("%02x", b); }// www .j ava2 s. c o m sb.insert(8, "-"); sb.insert(13, "-"); sb.insert(18, "-"); sb.insert(23, "-"); String temp = sb.toString().toUpperCase(); formatter.close(); return temp; }
From source file:Main.java
/** * Returns the Md5 hash for the given text. * //from www . j av a2s .com * @param text * String whose Md5 hash should be returned. * @return Returns the Md5 hash for the given text. */ public static String getMd5Hash(String text) { StringBuffer result = new StringBuffer(32); try { MessageDigest md5 = MessageDigest.getInstance("MD5"); md5.update(text.getBytes()); Formatter f = new Formatter(result); byte[] digest = md5.digest(); for (int i = 0; i < digest.length; i++) { f.format("%02x", new Object[] { new Byte(digest[i]) }); } } catch (NoSuchAlgorithmException ex) { ex.printStackTrace(); } return result.toString(); }