Abstract According to the data structure of JPL’s Development Ephemeris (DE) series, a simplified method is presented to facilitate the computation of autonomous orbit determination onboard GNSS satellite. The storage size of DE406 ephemeris in a period of 20 years is reduced to 369kb with this method. This simplified DE406 is verified with an experiment of longterm orbit integration of GPS satellites. The results show that the maximum prediction error in the normal direction is less than 3.0 meters during 60 days. This simplified method could not only ensure the accuracy and computational efficiency of autonomous orbit determination algorithm, but also decrease the data storage space onboard GNSS satellite.
$author.xingMing_EN,$author.xingMing_EN,$author.xingMing_EN et al. SIMPLIFICATION OF JPL’S DE AND ITS APPLICATION ON
AUTONOMOUS ORBIT DETERMINATION OF GLOBAL
NAVIGATION CONSTELLATION[J]. jgg, 2013, 33(6): 107-111.
$author.xingMing_EN,$author.xingMing_EN,$author.xingMing_EN et al. SIMPLIFICATION OF JPL’S DE AND ITS APPLICATION ON
AUTONOMOUS ORBIT DETERMINATION OF GLOBAL
NAVIGATION CONSTELLATION[J]. jgg, 2013, 33(6): 107-111.
