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 = 2100841 hand over word subframe 2 how = 2100874 hand over word subframe 3 how = 2100907 user range accuracy index ura = 1 issue of date, clock iodc = 41 issue of date, ephemeris iode = 0 satellite group delay differential [sec] tgd = 1.1595e-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 = 1.705303e-12 clock polynomial correction parameter 0 [sec] af0 = 2.31734477e-04 mean motion correction [semi-circles/sec] dn = 4.013381e-09 rate of right ascension [semi-circles/sec] omegadot = -7.759966e-09 rate of inclination angle [semi-circles/sec] idot = 2.334669e-08 cosine harm. corr. to arg. of latitude [rad] cuc = 1.167525e-04 sine harm. corr. to arg. of latitude [rad] cus = 7.225201e-06 cosine harm. corr. to orbit radius [m] crc = 2.427188e+02 sine harm. corr. to orbit radius [m] crs = 1.947625e+03 cosine harm. corr. to angle of incl. [rad] cic = 8.568168e-08 sine harm. corr. to angle of inclination [rad] cis = 1.220200e-04 mean anomaly at reference time [semi-circles] ma = 2.2170667764e+00 eccentricity e = 5.2214065799e-03 square root of semi-major axis [m^1/2] sqra = 5.1536374683e+03 lon. asc. node of orbit plane at weekly epoch omega0 = 3.477840212e+00 inclination angle at reference time [semi-circles] inc0 = 9.6940477768e-01 argument of perigee [semi-circles] w = -1.6894510492e+00 [end subframe 1-3] [subframe 4 : support data] page number pageno = 1 hand over word how = 2100940 reserved [end subframe 4] [subframe 5 : support data] page number pageno = 6 hand over word how = 2100973 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]