本文選題：測(cè)碼偽距　切入點(diǎn)：超快速星歷　出處：《計(jì)算機(jī)仿真》2017年07期 　論文類型：期刊論文

【摘要】：目前越來(lái)越多的應(yīng)用需要依賴高精度的實(shí)時(shí)衛(wèi)星軌道數(shù)據(jù),由于目前GPS接收機(jī)所使用的廣播星歷精度不高和星上處理器性能有限等原因,實(shí)時(shí)定軌的精度不是很理想。針對(duì)這種情況,提出了一種新的星載GPS實(shí)時(shí)定軌方法。上述方法采用工程應(yīng)用背景,使用IGS發(fā)布的超快速星歷代替廣播星歷,以相位平滑后的測(cè)碼偽距作為主要觀測(cè)量,結(jié)合簡(jiǎn)化的動(dòng)力學(xué)模型,通過(guò)擴(kuò)展卡爾曼濾波器進(jìn)行低軌衛(wèi)星軌道的實(shí)時(shí)解算。為了驗(yàn)證其性能,使用上述算法對(duì)CHAMP衛(wèi)星的在軌實(shí)際觀測(cè)數(shù)據(jù)進(jìn)行模擬實(shí)時(shí)處理,結(jié)果表明,改進(jìn)方法不僅計(jì)算量小,而且定軌精度高。
[Abstract]:At present, more and more applications need to rely on real-time satellite orbit data with high accuracy. Due to the low accuracy of broadcast ephemeris and limited performance of on-board processors used in GPS receivers, The accuracy of real-time orbit determination is not ideal. In view of this situation, a new real-time orbit determination method for spaceborne GPS is proposed. Using the background of engineering application, the super-fast ephemeris issued by IGS is used to replace the broadcast ephemeris. Taking the pseudo-range of the measured code after phase smoothing as the main observation quantity and combining the simplified dynamic model, the real time calculation of Leo satellite orbit is carried out by extended Kalman filter. In order to verify its performance, The above algorithm is used to simulate the real time observation data of CHAMP satellite in orbit. The results show that the improved method not only has a small amount of calculation, but also has high orbit determination accuracy.
【作者單位】： 上海衛(wèi)星工程研究所;
【分類號(hào)】：P228.4

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