基于XPNAV和SINS的容错组合导航系统  

Fault-tolerant integrated navigation system based on XPNAV and SINS

作　　者：苏哲[1] 许录平[1] 张华[1] 谢强[1] 

机构地区：[1]西安电子科技大学电子工程学院,陕西西安710071

出　　处：《华中科技大学学报（自然科学版）》2011年第6期19-23,共5页Journal of Huazhong University of Science and Technology(Natural Science Edition)

基　　金：国家高技术研究发展计划资助项目(2007AA12Z323);国家自然科学基金资助项目(60772139);中国卫星导航学术年会青年优秀论文获得者资助项目(CSNC2010-QY-014)

摘　　要：提出一种基于脉冲星导航和捷联惯导的容错组合导航系统.捷联惯导具有自主性和不间断性的优点,可弥补脉冲星导航滤波周期较长的缺陷;脉冲星导航的长期稳定度好,可抑制捷联惯导的误差随时间发散.该系统根据轨道动力学模型和SINS估计航天器的状态,利用脉冲星导航的观测量分别修正估计误差,通过相位残差检测天体遮挡等因素引起的故障,利用联邦扩展卡尔曼滤波融合导航信息.仿真实验结果表明:同脉冲星导航方法相比,该方法具有更高的精度和更短的滤波周期,且不受天体遮挡的影响.A fault-tolerant integrated navigation system based on X-ray pulsar-based navigation （XP- NAV） and strapdown inertial navigation system （SINS） was proposed. The defect of long filter period of XPNAV was remedied by the independency and uninterruptibility of SINS. The long term stability of XPNAV was used to restrain the divergence of SINS errors over time. This system estimates the states of spacecraft by trajectory dynamics model and SINS, corrects the estimation error by the measurement of XPNAV, introduces phase residual detection method to detect and isolate the breakdown of XPNAV system which is caused by the shelter from other celestial bodies, and used federated extended Kalman filter to fuse navigation information. The experimental results show that this method has higher navigation accuracy and shorter filter period than the pulsar navigation method, and is not affected by the shelter from other celestial bodies.

关 键 词：脉冲星 容错 组合导航 卡尔曼滤波 捷联惯性导航 

分 类 号：V249.23[航空宇航科学与技术—飞行器设计]