C++ EngEphemeris类代码示例

      /* Method to really get the weight of a given satellite.
       *
       * @param sat       Satellite
       * @param time      Epoch
       * @param bcEph     Broadcast EphemerisStore object to be used
       */
   double ComputeIURAWeights::getWeight( const SatID& sat,
                                         const DayTime& time,
                                         const GPSEphemerisStore* bcEph )
      throw(InvalidWeights)
   {

         // Set by default a very big value
      int iura(1000000);

      double sigma(1000000.0);

      EngEphemeris engEph;

      try
      {
            // Look if this satellite is present in ephemeris
         engEph = bcEph->findEphemeris(sat, time);

            // If so, get the IURA
         iura = engEph.getAccFlag();

      }
      catch(...)
      {
         InvalidWeights eWeight("Satellite not found.");
         GPSTK_THROW(eWeight);
      }

         // Compute and return the weight
      sigma = gpstk::ura2nominalAccuracy(iura);

      return ( 1.0 / (sigma*sigma) );

   }  // End of method 'ComputeIURAWeights::getWeight()'

 bool operator() (const EngEphemeris& l, const EngEphemeris& r) const
    {
       if ( (l.getPRNID() == r.getPRNID()) && 
            (l.getIODC() == r.getIODC()) )
          return true;
       return false;
    }

int main(int argc, char* argv[])
{
      // Set time to Day 153, 2011 (6/2/2011) at noon
   CivilTime g( 2011, 6, 2, 12, 14, 44.0, TimeSystem::GPS );
   CommonTime dt = g.convertToCommonTime();

   short weeknum   = 1638;     // By rules of Kepler Orbit, this must be week of Toe
  
   // Test data from 06/02/2011

   long subframe1[10] = { 0x22C2663D, 0x1F0E29B8, 0x2664002B, 0x09FCC1B6, 0x0F60EB8A,
                          0x1299CE93, 0x29CD3DB6, 0x0597BB0F, 0x00000B68, 0x17B28E5C };
   long subframe2[10] = { 0x22C2663D, 0x1F0E4A28, 0x05809675, 0x0EBD8AF1, 0x00089344,
                          0x008081F8, 0x1330CC2C, 0x0461E855, 0x034F8045, 0x17BB1E68 };
   long subframe3[10] = { 0x22C2663D, 0x1F0E6BA0, 0x3FE129CD, 0x26E31837, 0x0006C96A,
                          0x35A74DFC, 0x065C8B0F, 0x1E4F400A, 0x3FE8966D, 0x05860C44 };
   

   //The dump from ee.dump() and ee_copy.dump() should be the same
   //    an EngEphemeris object is created, then used to create a Rinex3NavData
   EngEphemeris ee;
   ee.addSubframe(subframe1, weeknum, 3, 1);
   ee.addSubframe(subframe2, weeknum, 3, 1);
   ee.addSubframe(subframe3, weeknum, 3, 1);
   ee.dump();

   Rinex3NavData rnd = Rinex3NavData(ee); //constructor

   EngEphemeris ee_copy;
   ee_copy = EngEphemeris(rnd);           //cast
   ee_copy.dump();
}

   // Try to convert the given pages into an EngEphemeris object. Returns true
   // upon success.
   bool makeEngEphemeris(EngEphemeris& eph, const EphemerisPages& pages)
   {
      EphemerisPages::const_iterator sf[4];

      sf[1] = pages.find(1);
      if (sf[1] == pages.end())
         return false;
      
      sf[2] = pages.find(2);
      if (sf[2] == pages.end())
         return false;

      sf[3] = pages.find(3);
      if (sf[3] == pages.end())
         return false;

      long t1 = sf[1]->second.getHOWTime();
      long t2 = sf[2]->second.getHOWTime();
      long t3 = sf[3]->second.getHOWTime();
      if (t2 != t1+6 || t3 != t1+12)
         return false;

      int prn = sf[1]->second.prn;
      int week = sf[1]->second.time.GPSfullweek();
      long sfa[10];
      long long_sfa[10];

      for (int i=1; i<=3; i++)
      {
         sf[i]->second.fillArray(sfa);
         for( int j = 0; j < 10; j++ )
            long_sfa[j] = static_cast<long>( sfa[j] );
         if (!eph.addSubframe(long_sfa, week, prn, 0))
            return false;
      }

      if (eph.isData(1) && eph.isData(2) && eph.isData(3))
         return true;

      return false;
   }

   void processSubframes1to3(MDPNavSubframe& nav)
   {
         // For now, just look at L1 C/A navigation message
      if (nav.range != rcCA || nav.carrier != ccL1)
         return;

      NavIndex ni(RangeCarrierPair(nav.range, nav.carrier), nav.prn);
      ephData[ni] = nav;

      long sfa[10];
      nav.fillArray(sfa);
      uint32_t uint_sfa[10];
 
      for( int j = 0; j < 10; j++ )
         uint_sfa[j] = static_cast<uint32_t>( sfa[j] );

      numSubframesCollected++;
      if (gpstk::EngNav::checkParity(uint_sfa))
      {
         paritySuccessCount++;
         ephPageStore[ni][nav.getSFID()] = nav;
         EngEphemeris engEph;
         if (makeEngEphemeris(engEph, ephPageStore[ni]))
         {
            currentPRN = engEph.getPRNID();     // debug
            if (firstNavSF) 
            {
               earliestTime = engEph.getTransmitTime();
               firstNavSF = false;
            }
            latestTime = engEph.getTransmitTime();
            processEphemeris( engEph, ephPageStore[ni] );
         }
      }
      else parityFailCount++;
   } // end of process(MDPNavSubframe)

   RinexNavData::operator EngEphemeris() const throw()
   {
      EngEphemeris ee;

         // there's no TLM word in RinexNavData, so it's set to 0.
         // likewise, there's no AS alert or tracker.
         // Also, in Rinex, the accuracy is in meters, and setSF1 expects
         // the accuracy flag.  We'll give it zero and pass the accuracy
         // separately via the setAccuracy() method.
      ee.setSF1(0, HOWtime, 0, weeknum, codeflgs, 0, health,
                short(IODC), L2Pdata, Tgd, Toc, af2, af1, af0, 0, PRNID);
      ee.setSF2(0, HOWtime, 0, short(IODE), Crs, dn, M0, Cuc, ecc, Cus, Ahalf,
                Toe, (fitint > 4) ? 1 : 0);
      ee.setSF3(0, HOWtime, 0, Cic, OMEGA0, Cis, i0, Crc, w, OMEGAdot,
                idot);
      ee.setFIC(false);
      ee.setAccuracy(accuracy);

      return ee;
   }

void xBrcClockCorrectiongpsNavMsg::firstTest(void)
{
      // Set time to Day 153, 2011 (6/2/2011) at noon
   CivilTime g( 2011, 6, 2, 12, 14, 44.0, TimeSystem::GPS );
   CommonTime dt = g.convertToCommonTime();

      // Test data (copied from navdmp output for .....)
      // Generally, we'd load these data from the file
   std::string SysID = "G";
   ObsID obsID( ObsID::otUndefined, ObsID::cbL1, ObsID::tcCA );
   short PRNID     = 3;
   double Toc      = 388800.0;
   double Top      = 345600.0;
   short weeknum   = 1638;     // By rules of Clock Correction, this must be week of Toc
   short URAoc     = 5;
   short URAoc1    = 7;
   short URAoc2    = 7;
   bool healthy    = true;
   double af0      = 7.23189674E-04;
   double af1      = 5.11590770E-12;
   double af2      = 0.00000000E+00;
   CommonTime TocCT = GPSWeekSecond(weeknum, Toc, TimeSystem::GPS);
   CommonTime TopCT = GPSWeekSecond(weeknum, Top, TimeSystem::GPS);
  
      // Test Data copied from RINEX file	
   double rToc      = 388800.0;
   double rTop      = 345600.0;
   short rweeknum   = 1638;     // By rules of Clock Corection, this must be week of Toc
   short rURAoc     = 5;
   short rURAoc1    = 7;
   short rURAoc2    = 7;
   bool rhealthy    = true;
   double raf0      = 7.23189674318E-04;
   double raf1      = 5.11590769747E-12;
   double raf2      = 0.00000000000E+00;
   CommonTime rTocCT = GPSWeekSecond(rweeknum, rToc, TimeSystem::GPS);
   CommonTime rTopCT = GPSWeekSecond(rweeknum, rTop, TimeSystem::GPS);

   long subframe1[10] = { 0x22C2663D, 0x1F0E29B8, 0x2664002B, 0x09FCC1B6, 0x0F60EB8A,
                          0x1299CE93, 0x29CD3DB6, 0x0597BB0F, 0x00000B68, 0x17B28E5C };
   long subframe2[10] = { 0x22C2663D, 0x1F0E4A28, 0x05809675, 0x0EBD8AF1, 0x00089344,
                          0x008081F8, 0x1330CC2C, 0x0461E855, 0x034F8045, 0x17BB1E68 };
   long subframe3[10] = { 0x22C2663D, 0x1F0E6BA0, 0x3FE129CD, 0x26E31837, 0x0006C96A,
                          0x35A74DFC, 0x065C8B0F, 0x1E4F400A, 0x3FE8966D, 0x05860C44 };

   ofstream outf("Logs/BrcClkCorr_Output", ios::out);

      // First test case. Create an empty CC object, then load the data.
   outf << "Test Case 1: Creating an empty CC object and loading the data." << endl;
   BrcClockCorrection co1;
   co1.loadData( SysID, obsID, PRNID, TocCT, TopCT, URAoc, URAoc1, URAoc2, healthy, 
		           af0, af1, af2 ); 

   double ClkCorr1 = co1.svClockBias( dt );
   outf.precision(11); 
   outf << "Clock Correction co1: " << ClkCorr1 << endl << endl;

      // Second test case. Create an CC object with data available at time of construction.
   outf << "Test Case 2: Creating CC object with data." << endl;
   BrcClockCorrection co2( SysID, obsID, PRNID, TocCT, TopCT, URAoc, URAoc1, URAoc2, healthy, 
		                     af0, af1, af2 ); 

   double ClkCorr2 = co2.svClockBias( dt ); 
   outf << "ClockCorrection co2: " << ClkCorr2 << endl << endl;

      // Third test case. Create a CC object using raw legacy navigation message data
   outf << "Test Case 3: Creating CC object with raw legacy nav message data." << endl;
   BrcClockCorrection co3(obsID, PRNID, weeknum, subframe1 );

   double ClkCorr3 = co3.svClockBias( dt ); 
   outf << "Clock Correction co3: " << ClkCorr3 << endl << endl;

      // Fourth test case. Create a CC object using raw legacy navigation message data
   outf << "Test Case 4: Creating CC object with raw legacy nav message data." << endl;
   BrcClockCorrection co4;
   co4.loadData(obsID, PRNID, weeknum, subframe1 );

   double ClkCorr4 = co4.svClockBias( dt ); 
   outf << "Clock Correction co4: " << ClkCorr4 << endl << endl;

      // Fifth test case. Create an CC object with data available from RINEX file.
   outf << "Test Case 5: Creating CC object with data from RINEX file." << endl;
   BrcClockCorrection co5( SysID, obsID, PRNID, rTocCT, TopCT, URAoc, URAoc1, URAoc2, rhealthy, 
		                     raf0, raf1, raf2 ); 

   double ClkCorr5 = co5.svClockBias( dt ); 
   outf << "Clock Correction co5: " << ClkCorr5 << endl << endl;

      // Sixth test case. Compare against "classic" EngEphemeris
   outf << "Test Case 6: Calculated clock correction using 'classic' EngEphemeris." << endl;
   outf<< "Time= "<< g << endl;
   EngEphemeris EE;
   EE.addSubframe(subframe1, weeknum, 3, 1);
   EE.addSubframe(subframe2, weeknum, 3, 1);
   EE.addSubframe(subframe3, weeknum, 3, 1);

   Xvt xvt = EE.svXvt(dt);
   outf << "Clock Bias EE:  " << xvt.clkbias << endl;
	outf << "Clock Drift EE: " << xvt.clkdrift << endl;
 
//.........这里部分代码省略.........

 EphDiffFinder(const EngEphemeris& e)
       : PRN(e.getPRNID()), IODC(e.getIODC())
    {}

//.........这里部分代码省略.........

      // Set time to Day 156, 2011 (6/5/2011) at midnight
   CivilTime ct3( 2011, 6, 5, 0, 0, 0.0, TimeSystem::GPS );
   CommonTime dt3 = ct2.convertToCommonTime();

      // Test data (copied from navdmp output for PRN 9 Day 155, 2011 at 22:00:00 Transmit Time)
      // Generally, we'd load these data from the file
   short PRNID3     = 9;
   double Toc3      = 0.0;
   short TOWWeek3   = 1638;     // By rules of Clock Corection, this must be week of Toc
   double accuracy3 = 10.61;
   long TOWMsg_3    = 597600;
   long Top3        = 594000;
   double af0_3     = 8.43554735E-05;
   double af1_3     = 2.38742359E-12;
   double af2_3     = 0.0;
   short health3    = 0;
   long TOW3        = 597600; 
   short URAoc_3    = 1;
   short URAoc1_3   = 2;
   short URAoc2_3   = 3;

  
   long subframe1[10] = { 0x22C2663D, 0x1F0E29B8, 0x2664002B, 0x09FCC1B6, 0x0F60EB8A,
                          0x1299CE93, 0x29CD3DB6, 0x0597BB0F, 0x00000B68, 0x17B28E5C };
   long subframe2[10] = { 0x22C2663D, 0x1F0E4A28, 0x05809675, 0x0EBD8AF1, 0x00089344,
                         0x008081F8, 0x1330CC2C, 0x0461E855, 0x034F8045, 0x17BB1E68 };
   long subframe3[10] = { 0x22C2663D, 0x1F0E6BA0, 0x3FE129CD, 0x26E31837, 0x0006C96A,
                          0x35A74DFC, 0x065C8B0F, 0x1E4F400A, 0x3FE8966D, 0x05860C44 };

   ofstream outf("Logs/CNAVClock_Output", ios::out);
   outf.precision(11);

      // First test case.  Create an CC object with data available from RINEX file.
   outf << endl << "Test Case 1: Creating CC object with data from RINEX file." << endl;
   outf << "Time = " << g << endl;
   CNAVClock cc1;
   cc1.loadData( SysID, obsID, PRNID, AlertMsg, TOWMsg_1, rTOWWeek, Top,
                 rToc, raccuracy, URAoc_1, URAoc1_1, URAoc2_1, raf0, raf1, raf2 );

   double ClkCorr1 = cc1.svClockBias( dt );
   double ClkDrift1 = cc1.svClockDrift( dt ); 
   outf << "Clock Bias cc1:         " << ClkCorr1 << endl;
   outf << "Clock Drift cc1:        " << ClkDrift1 << endl;
   outf << "Time of Prediction cc1: " << GPSWeekSecond(cc1.getTimeOfPrediction()).printf("%F, %g") << endl;
   outf << "CNAV Accuracy Test:     " << SV_CNAV_ACCURACY_GPS_MAX_INDEX[URAoc_1+15] << endl;
   outf << "legacy Accuracy Test:   " << SV_ACCURACY_GPS_MAX_INDEX[URAoc_1] << endl;

      // Second test case.  Create an CC object with data available from navdump.
   outf << endl << "Test Case 2: Creating CC object with data from navdump." << endl;
   outf << "Time = " << ct2 << endl;
   CNAVClock cc2;
   cc2.loadData( SysID, obsID2, PRNID2, AlertMsg2, TOWMsg_2, TOWWeek2, Top2,
                 Toc2, accuracy2, URAoc_2, URAoc1_2, URAoc2_2, af0_2, af1_2, af2_2 );

   double ClkCorr2 = cc2.svClockBias( dt2 );
   double ClkDrift2 = cc2.svClockDrift( dt2 ); 
   outf << "Clock Bias cc2:  "        << ClkCorr2 << endl;
   outf << "Clock Drift cc2: "        << ClkDrift2 << endl; 
   outf << "Time of Prediction cc2: " << GPSWeekSecond(cc2.getTimeOfPrediction()).printf("%F, %g") << endl;

      // Third test case.  Create an CC object with data available from navdump.
   outf << endl << "Test Case 3: Creating CC object with data from navdump." << endl;
   outf << "Time = " << ct3 << endl;
   CNAVClock cc3;
   cc3.loadData( SysID, obsID, PRNID3, AlertMsg, TOWMsg_3, TOWWeek3, Top3,
                 Toc3, accuracy3, URAoc_3, URAoc1_3, URAoc2_3, af0_3, af1_3, af2_3 );

   double ClkCorr3 = cc3.svClockBias( dt3 );
   double ClkDrift3 = cc3.svClockDrift( dt3 ); 
   outf << "Clock Bias cc3:  "        << ClkCorr3 << endl;
   outf << "Clock Drift cc3: "        << ClkDrift3 << endl; 
   outf << "Time of Prediction cc3: " << GPSWeekSecond(cc3.getTimeOfPrediction()).printf("%F, %g") << endl;

      // Fourth test case.  Compare against "classic" EngEphemeris
   outf << endl << "Test Case 4: Calculated position using 'classic' EngEphemeris." << endl;
   outf<< "Time= "<< g << endl;
   EngEphemeris EE;
   EE.addSubframe(subframe1, TOWWeek, 3, 1);
   EE.addSubframe(subframe2, TOWWeek, 3, 1);
   EE.addSubframe(subframe3, TOWWeek, 3, 1);

   Xvt xvt = EE.svXvt(dt);
   outf<< "Clock Bias EE:  " << xvt.clkbias << endl;
   outf<< "Clocl Drift EE: " << xvt.clkdrift << endl;

   outf << endl;
   outf << "CC1 Object Dump:" << endl;
   outf << cc1 << endl;

   outf << endl;
   outf << "CC2 Object Dump:" << endl;
   outf << cc2 << endl;

   outf << endl;
   outf << "CC3 Object Dump:" << endl;
   outf << cc3 << endl;

   CPPUNIT_ASSERT(fileEqualTest((char*)"Logs/CNAVClock_Truth",(char*)"Logs/CNAVClock_Output"));
}

AlmOrbit ConvertEEtoAO(EngEphemeris& ee)
{
   AlmOrbit ao(
      ee.getPRNID()   , ee.getEcc()   , ee.getI0()-0.3*PI, ee.getOmegaDot()      ,
      ee.getAhalf()   , ee.getOmega0(), ee.getW()        , ee.getM0()            ,
      ee.getAf0()     , ee.getAf1()   , long(ee.getToe()), long(ee.getHOWTime(1)),
      ee.getFullWeek(), ee.getHealth()
      );

   return ao;
}

void MinSfTest::process()
{
   if (debugLevel)
      cout << "Setting up input file: " 
           <<  inputOption.getValue().front() << endl;
   FileFilterFrame<FICStream, FICData>
      input(inputOption.getValue().front());
   
   printf(" input.getDataCount() after init: %d\n", input.getDataCount());
   if(debugLevel)
      cout << "Setting up output file: "
           << outputOption.getValue().front() << endl;
           
   fp.open( outputOption.getValue().front().c_str() );
   if ( !fp.is_open() )
   {
      printf(" Failed to open output file.\n");
      exit(1);
   }
           
      // filter the FIC data for the requested vlock(s)
   std::list<long> blockList;
   blockList.push_back(109);
   input.filter(FICDataFilterBlock(blockList));
   input.sort(FICDataOperatorLessThanBlock109());
   input.unique(FICDataUniqueBlock109());
   
      //some hand waving for the data conversion
   if(debugLevel)
      cout << "Reading the input data." << endl;
   list<FICData>& ficList = input.getData();
   list<FICData>::iterator itr = ficList.begin();
   
   DayTime earliest( DayTime::END_OF_TIME );
   DayTime latest( DayTime::BEGINNING_OF_TIME );
   int count = 0;
   int numMismatches = 0;
   int numMismatchEph = 0; 
   while (itr != ficList.end())
   {
      EngEphemeris ee(*itr);

      bc109.addEphemeris( ee );

      DayTime ct = ee.getEpochTime();
      if (ct>latest) latest = ct;
      if (ct<earliest) earliest = ct;
      
         // Following code simulates a situation where only words 3-10
         // and the estimated time of receipt are available.
      DayTime timeOfReceipt = ee.getTransmitTime();
      FICData& fic = *itr;
      long sf1min[8];
      long sf2min[8];
      long sf3min[8];
      int wrdCnt = 8;
      int i;
      for (i=0; i<wrdCnt; ++i) sf1min[i] = fic.i[4+i];   
      for (i=0; i<wrdCnt; ++i) sf2min[i] = fic.i[14+i];   
      for (i=0; i<wrdCnt; ++i) sf3min[i] = fic.i[24+i];  

      EngEphemeris eeMin;
      short PRNID = (short) fic.i[1];
      eeMin.addIncompleteSF1Thru3( sf1min, sf2min, sf3min,
             (long) timeOfReceipt.GPSsecond(), timeOfReceipt.GPSfullweek(),
             PRNID, 0 );
      minRaw.addEphemeris( eeMin );
      
         // Compare non-orbit portions of the two objects
      bool mismatch = false;
      for (int i=1; i<=3; ++i)
      {
         if (!ee.isData(i) || !eeMin.isData(i))
         {
            mismatch = true;
            fp << "ERROR: not all subframes are claimed available.";
         }
      }
      
      if (ee.getIODC()!=eeMin.getIODC()) 
      {
         mismatch = true;
         fp << "ERROR: IODCs do not match."; 
      }
      if (ee.getIODE()!=eeMin.getIODE()) 
      {
         mismatch = true;
         fp << "ERROR: IODCs do not match."; 
      }
      if (ee.getFitInterval() != eeMin.getFitInterval() )
      {
         mismatch = true;
         fp << "ERROR: fit intervals do not match.";
      }
      if (ee.getCodeFlags()!=eeMin.getCodeFlags() )
      {
         mismatch = true;
         fp << "ERROR: code flags do not match.";
      }
      if (ee.getL2Pdata()!=eeMin.getL2Pdata() )
//.........这里部分代码省略.........

//.........这里部分代码省略.........

   ofstream outf("Logs/CNAVEphemeris_Output", ios::out);
   outf.precision(11);

      // First test case.  Create an CE object with data available from RINEX file.
   outf << endl << "Test Case 1: Creating CE object with data from RINEX file." << endl;
   outf << "Time = " << g << endl;
   CNAVEphemeris ce1;
   ce1.loadData(SysID, obsID, PRNID, AlertMsg10, TOWMsg10_1, AlertMsg11,
                TOWMsg11_1, rTOWWeek, Top, URAoe, L1Health, L2Health, 
		          L5Health, rToe, raccuracy, rCuc, rCus, rCrc, rCrs, rCic,
                rCis, rM0, rdn, rdnDot, recc, deltaA, rAdot, rOMEGA0, 
                ri0, rw, deltaOMEGAdot1, ridot );

   Xv  xv1 = ce1.svXv( dt ); 
   outf << "Position ce1: "           << xv1.x << endl;
   outf << "Velocity ce1: "           << xv1.v << endl;
   outf << "RelCorr ce1:  "           << ce1.svRelativity(dt) << endl;
   outf << "Time of Prediction ce1: " << GPSWeekSecond(ce1.getTimeOfPrediction()).printf("%F, %g") << endl;
   outf << "CNAV Accuracy Test:  "    << SV_CNAV_ACCURACY_GPS_MAX_INDEX[URAoe+15] << endl;
   outf << "legacy Accuracy Test: "   << SV_ACCURACY_GPS_MAX_INDEX[URAoe] << endl;

      // Second test case.  Create an CE object with data available from navdump.
   outf << endl << "Test Case 2: Creating CE object with data from navdump." << endl;
   outf << "Time = " << ct2 << endl;
   CNAVEphemeris ce2;
   ce2.loadData( SysID, obsID2, PRNID2, AlertMsg10, TOWMsg10_2, AlertMsg11,
                TOWMsg11_2, TOWWeek2, Top2, URAoe2, L1Health, L2Health, 
		          L5Health, Toe2, accuracy2, Cuc2, Cus2, Crc2, Crs2, Cic2,
                Cis2, M02, dn2, dnDot2, ecc2, deltaA2, Adot2, OMEGA02, 
                i02, w2, deltaOMEGAdot2, idot2 );

   Xv  xv2 = ce2.svXv( dt2 ); 
   outf << "Position ce2: "           << xv2.x << endl;
   outf << "Velocity ce2: "           << xv2.v << endl;
   outf << "RelCorr ce2:  "           << ce2.svRelativity(dt2) << endl;
   outf << "Time of Prediction ce2: " << GPSWeekSecond(ce2.getTimeOfPrediction()).printf("%F, %g") << endl;

      // Third test case.  Create an CE object with data available from navdump.
   outf << endl << "Test Case 3: Creating CE object with data from navdump." << endl;
   outf << "Time = " << ct3 << endl;
   CNAVEphemeris ce3;
   ce3.loadData( SysID, obsID, PRNID3, AlertMsg10, TOWMsg10_3, AlertMsg11,
                TOWMsg11_3, TOWWeek3, Top3, URAoe3, L1Health, L2Health, 
		          L5Health, Toe3, accuracy3, Cuc3, Cus3, Crc3, Crs3, Cic3,
                Cis3, M03, dn3, dnDot3, ecc3, deltaA3, Adot3, OMEGA03, 
                i03, w3, deltaOMEGAdot3, idot3 );

   Xv  xv3 = ce3.svXv( dt3 ); 
   outf << "Position ce3: "           << xv3.x << endl;
   outf << "Velocity ce3: "           << xv3.v << endl;
   outf << "RelCorr ce3:  "           << ce3.svRelativity(dt3) << endl;
   outf << "Time of Prediction ce3: " << GPSWeekSecond(ce3.getTimeOfPrediction()).printf("%F, %g") << endl;

      // Fourth test case.  Compare against "classic" EngEphemeris
   outf << endl << "Test Case 4: Calculated position using 'classic' EngEphemeris." << endl;
   outf<< "Time= "<< g << endl;
   EngEphemeris EE;
   EE.addSubframe(subframe1, TOWWeek, 3, 1);
   EE.addSubframe(subframe2, TOWWeek, 3, 1);
   EE.addSubframe(subframe3, TOWWeek, 3, 1);

   Xvt xvt = EE.svXvt(dt);
   outf<< "Position EE: " << xvt.x << endl;
   outf<< "Velocity EE: " << xvt.v << endl;
   outf<< "RelCorr EE:  " << EE.svRelativity(dt) << endl;

   outf << endl;
   outf << "CE Object Dump:" << endl;
   outf << ce1 << endl;
   if ( ce1.getOrbit().isHealthy()) outf << "CE.orbit is healthy." << endl;
   else outf << "CE.orbit is NOT healthy." << endl;

   outf << endl;
   outf << "CE2 Object Dump:" << endl;
   outf << ce2 << endl;
   if ( ce2.getOrbit().isHealthy()) outf << "CE2.orbit is healthy." << endl;
   else outf << "CE2.orbit is NOT healthy." << endl;

   outf << endl;
   outf << "CE3 Object Dump:" << endl;
   outf << ce3 << endl;
   if ( ce3.getOrbit().isHealthy()) outf << "CE3.orbit is healthy." << endl;
   else outf << "CE3.orbit is NOT healthy." << endl;

   outf << endl;
   outf << "Fit Interval Tests" << endl;
   outf << "BeginFit ce1:  "    << GPSWeekSecond(ce1.getOrbit().getBeginningOfFitInterval()).printf("%F, %g") << endl;
   outf << "BeginFit EE:   "    << GPSWeekSecond(EE.getOrbit().getBeginningOfFitInterval()).printf("%F, %g") << endl;

   outf << endl;
   outf << "EndFit ce1:   " << GPSWeekSecond(ce1.getOrbit().getEndOfFitInterval()).printf("%F, %g") << endl;
   outf << "EndFit EE  :  " << GPSWeekSecond(EE.getOrbit().getEndOfFitInterval()).printf("%F, %g") << endl;

   outf << endl;
   outf << "Within Fit Interval: " << ce1.getOrbit().withinFitInterval(dt) << endl;
   outf << "Within Fit Interval: " << EE.getOrbit().withinFitInterval(dt) << endl;

   CPPUNIT_ASSERT(fileEqualTest((char*)"Logs/CNAVEphemeris_Truth",(char*)"Logs/CNAVEphemeris_Output"));
}

      // Deprecated; use GPSEphemeris.
      // Converts this Rinex3NavData to an EngEphemeris object.
   Rinex3NavData::operator EngEphemeris() const throw()
   {
      EngEphemeris ee;

      // There's no TLM word in Rinex3NavData, so it's set to 0.
      // Likewise, there's no AS alert or tracker.
      // Also, in RINEX, the accuracy is in meters, and setSF1 expects
      // the accuracy flag.  We'll give it zero and pass the accuracy
      // separately via the setAccuracy() method.

      ee.tlm_message[0] = 0;           
      ee.tlm_message[1] = 0;
      ee.tlm_message[2] = 0;
      ee.HOWtime[0] = HOWtime;  // RINEX does not actually specify 
      ee.HOWtime[1] = HOWtime;  // how the transmit time is derived.  Therefore,
      ee.HOWtime[2] = HOWtime;  // These values may be misleading.  
      ee.ASalert[0] = 1;               //AS and alert flags set to 1 (default)
      ee.ASalert[1] = 1;
      ee.ASalert[2] = 1;

      ee.weeknum    = weeknum;
      ee.codeflags  = codeflgs;
      ee.health     = health;  
      ee.IODC       = short(IODC);
      ee.L2Pdata    = L2Pdata;
      ee.Tgd        = Tgd;
      ee.tracker    = 0;
      ee.PRNID      = PRNID;
      ee.satSys     = satSys;
      bool healthy = false;
      if (health == 0) healthy = true;
      short accFlag = 0; //will be set later.
          //BrcClockCorrection takes a flag, while EngEphemeris takes a double.
      double toc    = Toc;

      double timeDiff =toc - ee.HOWtime[0];
      short epochWeek = ee.weeknum;
      if (timeDiff < -HALFWEEK) epochWeek++;
      else if (timeDiff > HALFWEEK) epochWeek--;

      CommonTime tocCT = GPSWeekSecond(epochWeek, Toc, TimeSystem::GPS);

         // The observation ID has a type of navigation, but the
         // carrier and code types are undefined.  They could be
         // L1/L2 C/A, P, Y,.....
      ObsID obsID(ObsID::otNavMsg, ObsID::cbUndefined, ObsID::tcUndefined);
      ee.bcClock.loadData( satSys, obsID, PRNID, tocCT,
                        accFlag, healthy, af0, af1, af2);

      ee.IODE    = short(IODE);      
      ee.fitint  = (fitint > 4) ? 1 : 0;
      //double toe = Toe; //?????
      
      //Needed for modernized nav quatities
      double A = Ahalf * Ahalf;
      double dndot = 0.0;
      double Adot = 0.0;

      short fitHours = getLegacyFitInterval(ee.IODC, ee.fitint);
      long beginFitSOW = Toe - (fitHours/2)*3600.0;
      long endFitSOW = Toe + (fitHours/2)*3600.0;
      short beginFitWk = ee.weeknum;
      short endFitWk = ee.weeknum;

      if (beginFitSOW < 0)
      {
         beginFitSOW += FULLWEEK;
         beginFitWk--;
      }
      CommonTime beginFit = GPSWeekSecond(beginFitWk, beginFitSOW, TimeSystem::GPS);
      if (endFitSOW >= FULLWEEK)
      {
         endFitSOW += FULLWEEK;
         endFitWk++;
      }

      CommonTime endFit = GPSWeekSecond(endFitWk, endFitSOW, TimeSystem::GPS);
      CommonTime toeCT = GPSWeekSecond(epochWeek, Toe, TimeSystem::GPS);

      ee.orbit.loadData( satSys, obsID, PRNID, beginFit, endFit, toeCT,
                      accFlag, healthy, Cuc, Cus, Crc, Crs, Cic, Cis, 
                      M0, dn, dndot, ecc, A, Ahalf, Adot, OMEGA0, i0, 
                      w, OMEGAdot, idot);

      ee.haveSubframe[0] = true;    // need to be true to perform certain EngEphemeris functions
      ee.haveSubframe[1] = true;    // examples: ee.dump(), ee.setAccuracy()
      ee.haveSubframe[2] = true;

      ee.setAccuracy(accuracy);

     return ee;

   }  // End of 'Rinex3NavData::operator EngEphemeris()'

   // Deprecated; used GPSEphemeris.
   // This routine uses EngEphemeris, so is for GPS data only.
   // The comments about GPS v. Galileo next to each elements are just notes
   // from sorting out the ICDs in the RINEX 3 documentation. Please leave
   // them there until we add a routine for handling GalRecord or similar.
   Rinex3NavData::Rinex3NavData(const EngEphemeris& ee) // GPS only
   {
      // epoch info
      satSys = ee.getSatSys();
      PRNID  = ee.getPRNID();
      sat    = RinexSatID(PRNID,SatID::systemGPS);
      time   = ee.getEpochTime();

      Toc     = ee.getToc();
      HOWtime = long(ee.getHOWTime(1));
      weeknum = ee.getFullWeek();

      accuracy = ee.getAccuracy();
      health   = ee.getHealth();

      // GPS or Galileo data

      af0 = ee.getAf0(); // GPS and Galileo only
      af1 = ee.getAf1(); // GPS and Galileo only
      af2 = ee.getAf2(); // GPS and Galileo only

      Crs = ee.getCrs(); // GPS and Galileo only
      dn  = ee.getDn();  // GPS and Galileo only
      M0  = ee.getM0();  // GPS and Galileo only

      Cuc   = ee.getCuc();   // GPS and Galileo only
      ecc   = ee.getEcc();   // GPS and Galileo only
      Cus   = ee.getCus();   // GPS and Galileo only
      Ahalf = ee.getAhalf(); // GPS and Galileo only

      Toe    = ee.getToe();    // GPS and Galileo only
      Cic    = ee.getCic();    // GPS and Galileo only
      OMEGA0 = ee.getOmega0(); // GPS and Galileo only
      Cis    = ee.getCis();    // GPS and Galileo only

      i0       = ee.getI0();       // GPS and Galileo only
      Crc      = ee.getCrc();      // GPS and Galileo only
      w        = ee.getW();        // GPS and Galileo only
      OMEGAdot = ee.getOmegaDot(); // GPS and Galileo only

      idot = ee.getIDot(); // GPS and Galileo only

      // GPS-only data

      IODE = ee.getIODE(); // GPS only

      codeflgs = ee.getCodeFlags(); // GPS only
      L2Pdata  = ee.getL2Pdata();   // GPS only

      Tgd  = ee.getTgd();  // GPS only
      IODC = ee.getIODC(); // GPS only

      fitint = ee.getFitInterval(); // GPS only
   }  // End of 'Rinex3NavData::Rinex3NavData(const EngEphemeris& ee)'