[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]
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C写的用软件无线电实现的GPS模拟程序,包括捕获和跟踪,以后后续的PVT解算,对于初学GPS有很大的帮助
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C写的用软件无线电实现的GPS模拟程序,包括捕获和跟踪,以后后续的PVT解算,对于初学GPS有很大的帮助
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C写的用软件无线电实现的GPS模拟程序,包括捕获和跟踪,以后后续的PVT解算,对于初学GPS有很大的帮助.zip (53个子文件)
www.pudn.com.txt 218B
opengpssim
bin
gpsrcvr.log 48B
current.eph 5KB
xmit_par.dat 590B
rcvr_par.dat 2KB
changelog 216B
warranty 1KB
rcvr
ogsoptions.c 5KB
gp2021.c 11KB
current.eph 5KB
warranty 1KB
correlator.c 25KB
ogsrcvr.c 6KB
gpsrcvr.c 79KB
copying 18KB
ogsinout.c 10KB
Makefile 2KB
gpsfuncs.c 64KB
include
ogsnavdecode.h 4KB
ogslibrary.h 4KB
ogsnavencode.h 4KB
ogsdefine.h 6KB
ogsprototypes.h 7KB
ogsextern.h 9KB
boxmuller.h 472B
ogsstructs.h 14KB
copying 18KB
doc
dataformats.txt 1KB
readme 8KB
data
current.eph 5KB
curloc.dat 48B
nav-01-template-01-06.txt 3KB
current.alm 16KB
ion_utc.dat 625B
393540x36.g12 90KB
nav-11-template-01-06.txt 3KB
lib
ogsnavascii.c 24KB
ogsnavencode.c 19KB
ogsionavasc.c 20KB
ogslibrary.c 41KB
ogsnavdecode.c 27KB
getopt.c 18KB
encdec
ogsoptions.c 5KB
ogsencdec.c 20KB
ogsgar2rnx.c 20KB
ogsinout.c 17KB
Makefile 2KB
xmit
ogsoptions.c 5KB
warranty 1KB
boxmuller.c 2KB
copying 18KB
ogsxmit.c 19KB
Makefile 1KB
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