基于GPS的低轨伴飞卫星自主导航轨道确定

对基于EKF算法的相对导航滤波器和基于全球卫星定位系统(GPS)伪距测量的伴飞星定轨进行了研究。用几何法与相对动力学方法联合获得目标星轨道信息,给出了伴飞卫星伪距测量定位的模型。仿真结果表明:该定轨方法可用于低轨卫星实时定位导航,定轨精度较高。     

单颗导航卫星的轨道确定

讨论在导航星座只有一颗卫星时，不依赖于时间同步系统的卫星定轨策略和精度分析。采用历元间差分算法，在消除钟差的主项（低频）误差后，将伪距和相位数据转化为等价的积分Doppler数据，并对其建立测量模型。仿真分析表明，此时不需要知道钟差参数而定轨算法收敛。为进一步验证此定轨方案的可行性及其定轨精度，利用实测的GPS数据进行轨道确定计算，计算结果表明，采用历元间差分算法，利用国内观测台站3天弧段的观测资料对单颗GPS卫星进行定轨，其径向精度优于10m，利用其对国内定位用户的用户距离误差URE可达13．8m。     

Preliminary analysis of the quality and positioning performance of BDS-3 global interoperable signal B1C&B2a

BeiDou-3 Navigation Satellite System (BDS-3) satellites are equipped with the new generation GNSS signals B1C and B2a, which support the interoperability with GPS and Galileo systems. In this study, the pseudo-range multipath error and carrier phase observation noise of the BDS-3 B1C and B2a signals were evaluated based on zero baseline measurements from the day of year (DOY) 113 to 116, 2020. Further, the precision and performance of the single point positioning (SPP) and precise point positioning (PPP) are assessed at 9 stations. This assessment manifests that the standard deviations (STDs) of the pseudo-range multipath error are about 0.09 ~ 0.22 m, while STDs of the carrier phase observation noise are about 0.075 mm. For the single-frequency SPP, its positioning precision is about 2.03 ~ 4.85 m and 3.29 ~ 10.73 m at the 99.99% confidence level in horizontal and vertical directions, respectively, while the dual-frequency SPP precision is about 1.92 ~ 8.02 m and 4.81 ~ 12.77 m in horizontal and vertical directions, respectively. For the daily static PPP, the convergence time is about 20 ~ 30 min, while the daily positioning precision can reach 1.38 ~ 4.42 cm and -1.31 ~ 4.34 cm in horizontal and vertical directions, respectively. In general, the quality and the SPP and PPP performance of the BDS-3 B1C&B2a signals are comparable to the GPS and Galileo.     

基于Hatch滤波法的GPS伪距差分定位分析

利用Hatch滤波法对导航数据进行伪距差分定位研究,对单频接收机采用Hatch滤波法时电离层的影响做进一步研究,分析电离层风暴对定位精度的影响。为了提高定位精度,采用Hatch滤波法辅助的差分定位技术,对解算过程进行详细分析,并通过MATLAB软件对数据进行处理仿真,验证利用差分Hatch滤波法提高定位精度的可行性。     

惯性卫星紧组合导航系统仿真分析

针对SINS/Satellites进行松组合的不足,直接利用卫星信号接收机原始测量信息(伪距、伪距率),实现紧组合,来提高组合导航系统的精度和抗干扰性。文中详细推导了紧组合导航系统的伪距、伪距率误差模型,以伪距、伪距率差作为输入进行反馈,不仅当可见星数目小于4颗的时候,可以进行反馈,保证了一定的导航精度,而且可以用INS提供导航信息辅助接收机快速捕获卫星信号,这就提高了组合导航系统的容错能力。设计了SINS卫星紧组合导航系统的Kalman滤波器,并进行仿真验证,结果表明,SINS卫星紧组合较松组合有明显优势。