nav-11-template-01-06.txt

C写的用软件无线电实现的GPS模拟程序

[subframe 1-3 : satellite clock, health data and ephemeris data]
hand over word subframe 1                              how = 65651
hand over word subframe 2                              how = 65652
hand over word subframe 3                              how = 65653
user range accuracy index                              ura = 0
issue of date, clock                                  iodc = 15
issue of date, ephemeris                              iode = 0
satellite group delay differential [sec]               tgd = 1.0803e-07
clock data reference time [sec]                        toc = 3.960000e+05
reference time ephemeris [sec]                         toe = 3.960000e+05
clock polynomial correction parameter 2 [sec/sec^2]    af2 = 0.0000e+00
clock polynomial correction parameter 1 [sec/sec]      af1 = 6.821210e-13
clock polynomial correction parameter 0 [sec]          af0 = 1.33668073e-05
mean motion correction [semi-circles/sec]               dn = 5.479871e-09
rate of right ascension [semi-circles/sec]        omegadot = -8.476782e-09
rate of inclination angle [semi-circles/sec]          idot = 1.000042e-11
cosine harm. corr. to arg. of latitude [rad]           cuc = 5.207956e-06
sine harm. corr. to arg. of latitude [rad]             cus = 6.191432e-06
cosine harm. corr. to orbit radius [m]                 crc = 2.369688e+02
sine harm. corr. to orbit radius [m]                   crs = 9.934375e+01
cosine harm. corr. to angle of incl. [rad]             cic = 1.220368e-04
sine harm. corr. to angle of inclination [rad]         cis = 1.490116e-08
mean anomaly at reference time [semi-circles]           ma = -2.5232076418e+00
eccentricity                                             e = 5.3939700592e-04
square root of semi-major axis [m^1/2]                sqra = 5.1536808434e+03
lon. asc. node of orbit plane at weekly epoch       omega0 = 1.297162851e+00
inclination angle at reference time [semi-circles]    inc0 = 9.1741797222e-01
argument of perigee [semi-circles]                       w = -9.0614362831e-01
[end subframe 1-3]
[subframe 4 : support data]
page number                                         pageno = 1
hand over word                                         how = 65654
reserved
[end subframe 4]
[subframe 5 : support data]
page number                                         pageno = 6
hand over word                                         how = 65655
satellite health                                    health = 0
satellite id number                                     id = 14
eccentricity                                             e = 2.0008087158e-03
almanac reference time                                 toa = 5.8982e+05
incl. angle at ref. time rel. to 0.3 of RA             inc = 9.6824389696e-01
rate of right ascension [semi-circles/sec]        omegadot = 7.410823e-07
square root of semi-major axis [m^1/2]                sqra = 5.153535645e+03
lon. asc. node of orbit plane at weekly epoch       omega0 = -2.832504988e+00
argument of perigee [semi-circles]                       w = -6.611225009e-01
mean anomaly at reference time [semi-circles]           ma = -1.333806813e-01
clock polyn. corr. parameter [sec/sec]                 af1 = 3.63798e-12
clock polyn. corr. parameter [sec]                     af0 = 6.24352e-02
[end subframe 5]