摘要
由于空天飞行器特殊的飞行任务和复杂的飞行环境,单一的导航系统难以完全独立地为其提供高精度的导航参数。天文导航作为一种完全自主的导航技术,可以提供误差不随时间积累的高精度姿态信息,与惯性导航系统组合可以提高空天飞行器长时间导航精度。同时针对复杂空天环境下,实际导航系统噪声统计特性难以精确获得而导致传统卡尔曼滤波器性能下降的问题,提出了一种基于H_∞滤波的空天飞行器惯性/天文组合导航方法,建立了发射惯性系下组合导航系统的数学模型和H_∞滤波模型。仿真结果表明,该方法可有效解决系统噪声建模不准确的问题,提高空天飞行器组合导航系统的精度和可靠性。
The Aerospace vehicle has the characteristics that its flight mission is special and its flight environment is complex. Thus, a single navigation system can not independently provide high -precision parameters for the ASV. As a completely autonomous navigation technology, celestial navigation system can provide high -precision attitude information and its error do not accumulate over time. The navigation accuracy of aerospace vehicle can be improved by using celestial navigation system aided inertial navigation. Due to the complex flight environment, it is hard to obtain an accurate error model of actual navigation system which can cause a decline in the performance of traditional Kalman filter. An INS/CNS integrated nayigation method of aerospace vehicle based on the H∞ filter is proposed in this paper. The mathematical model of integrated navigation system under launch inertial coordinate and H∞ filter model are also established. The simulation results show that the problem of inaccurate noise modeling of system can be effectively solved by using the proposed method and the accuracy and reliability of integrated navigation system of ASV can be improved as well.
出处
《航天控制》
CSCD
北大核心
2016年第5期46-51,58,共7页
Aerospace Control
基金
国家自然科学基金项目(61533009
61374115)
江苏省六大人才高峰资助项目(2013-JY-013)
江苏高校优势学科建设工程资助项目
中央高校基本科研业务费专项资金资助(NP2015406
NP20152212)
南京航空航天大学研究生创新基地(实验室)开放基金资助(kfjj20150315)
关键词
空天飞行器
组合导航
发射惯性系
H∞滤波
Aerospace vehicle
Integrated navigation
Launch inertial coordinate
H∞ filter
