List of usage examples for java.util Vector setElementAt
public synchronized void setElementAt(E obj, int index)
From source file:Main.java
public static void main(String[] args) { Vector<Integer> vec = new Vector<Integer>(4); vec.add(4);/* w ww .j ava 2 s. c o m*/ vec.add(3); vec.add(2); vec.add(1); vec.setElementAt(11, 2); for (Integer number : vec) { System.out.println("Number = " + number); } }
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 w w w.j a v a 2s .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: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 ww . j a va2 s.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:Main.java
public static void swap(Vector v, int i, int j) { Object o = v.elementAt(i);//from ww w . jav a 2 s .c o m v.setElementAt(v.elementAt(j), i); v.setElementAt(o, j); }
From source file:Main.java
public static <K> K setElementAt(Vector<K> vec, int index, K value) { K retVal;//from w w w.j a va 2s . c o m if (vec.size() <= index) { vec.setSize(index + 10); retVal = null; } else retVal = vec.elementAt(index); vec.setElementAt(value, index); return retVal; }
From source file:Sort.java
private static void swap(Vector v, int i, int j) { Object o;// www. ja va 2 s . c om o = v.elementAt(i); v.setElementAt(v.elementAt(j), i); v.setElementAt(o, j); }
From source file:com.greenpepper.repository.FileSystemRepository.java
/** * <p>listDocumentsInHierarchy.</p> * * @return a {@link java.util.List} object. * @throws java.lang.Exception if any.// w w w . j av a 2 s.com */ @Override public List<Object> listDocumentsInHierarchy() throws Exception { Vector<Object> hierarchy = toHierarchyNodeVector(root); hierarchy.setElementAt(root.getName(), 0); hierarchy.setElementAt(false, 1); hierarchy.setElementAt(false, 2); return hierarchy; }
From source file:org.apache.axis.encoding.ser.VectorDeserializer.java
/** * The registerValueTarget code above causes this set function to be invoked when * each value is known.// w w w. j a va2 s .c o m * @param value is the value of an element * @param hint is an Integer containing the index */ public void setChildValue(Object value, Object hint) throws SAXException { if (log.isDebugEnabled()) { log.debug(Messages.getMessage("gotValue00", "VectorDeserializer", "" + value)); } int offset = ((Integer) hint).intValue(); Vector v = (Vector) this.value; // If the vector is too small, grow it if (offset >= v.size()) { v.setSize(offset + 1); } v.setElementAt(value, offset); }
From source file:org.talend.core.model.metadata.MetadataToolHelper.java
/** * /*www . j a v a 2 s . com*/ * qli Comment method "mapSpecialChar". * * */ private static String mapSpecialChar(String columnName) { if (GlobalServiceRegister.getDefault().isServiceRegistered(IRoutinesService.class)) { IRoutinesService service = (IRoutinesService) GlobalServiceRegister.getDefault() .getService(IRoutinesService.class); if (service != null) { Vector map = service.getAccents(); map.setElementAt("AE", 4);//$NON-NLS-1$ map.setElementAt("OE", 22);//$NON-NLS-1$ map.setElementAt("UE", 28);//$NON-NLS-1$ map.setElementAt("ss", 31);//$NON-NLS-1$ map.setElementAt("ae", 36);//$NON-NLS-1$ map.setElementAt("oe", 54);//$NON-NLS-1$ map.setElementAt("ue", 60);//$NON-NLS-1$ Vector addedMap = new Vector(); for (int i = 257; i < 304; i++) { addedMap.add(String.valueOf((char) i)); } map.addAll(addedMap); map.add("I");//$NON-NLS-1$ return initSpecificMapping(columnName, map); } } return columnName; }
From source file:org.kchine.rpf.PoolUtils.java
public static Vector<String> tokenizeWindowsCommand(String command) throws Exception { String command_t = ""; boolean changeSpaces = false; for (int i = 0; i < command.length(); ++i) { if (command.charAt(i) == '\"') { changeSpaces = !changeSpaces; } else {/* www .j a v a 2 s . c o m*/ if (command.charAt(i) == ' ' && changeSpaces) command_t += pattern; else command_t += command.charAt(i); } } Vector<String> result = tokenize(command_t, " "); for (int i = 0; i < result.size(); ++i) result.setElementAt(PoolUtils.replaceAll(result.elementAt(i).trim(), pattern, " "), i); return result; }