摘要
高轨飞行器可用卫星数目较少,信号空间链路损耗大,使用伪距进行测量的精度较低.提出基于GNSS(Global Navigation Satellite System)卫星载波相位与捷联惯导紧组合方法对高轨机动飞行器进行自主导航.该方法将连续跟踪的卫星初次可用时的整周模糊度的浮点解作为状态变量,通过平方根UKF建立了组合导航非线性滤波模型,提出了基于整周浮点解交集的滤波器故障检测方法.研究表明,提出的组合导航方法充分利用了载波相位高测量精度和系统性误差缓变的特点,提高了系统的可靠性和精度.
Because of the fewer available satellites and the greater wastage of signal on space link, the measurement accuracy is lower using pseudo-distance. The method of autonomous navigation using carrier phase of global navigation satellite system（GNSS） and strapdown inertial navigation system （SINS） was pres- ented for the high earth orbit automotive spacecraft. The float solutions of initial integer ambiguity were used as states variable in this method, and the nonlinear filter was established by square-root unscented Kalman filter （SRUKF）. The method of cycle slips faults detection and isolation was presented based on the intersections of the float solutions. The method of integrated navigation makes full use of the high measurement accuracy of carrier phase and slowly varying characteristic of systematic errors, and it can increase the reliability and the precision of the navigation system.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2012年第6期726-730,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
载波相位
捷联惯导
组合导航
故障检测与隔离
carrier phase
strapdown inertial navigation system（SINS）
integrated navigation
fault detection and isolation
