High Accuracy and Reliability Integrated Navigation Method for Longendurance Aircraft
A method of high accuracy and reliability integrated navigation for long-endurance aircraft is researched in this paper. Strapdown inertial navigation system (SINS), star sensor and global positioning system (GPS) are chosen as navigation equipments. In order to match the direction cosine matrix output of star sensor, a special matrix is constructed cleverly by outputs of SINS, and the difference between the above two matrixes is chosen as measurement of SINS/star sensor integrated navigation. Then Kalman filtering algorithm of SINS/star sensor integrated navigation is designed. At the same time, position and velocity outputs of SINS and GPS are taken to construct measurements of SINS/GPS integrated navigation, and its Kalman filtering algorithm is also designed. By designing the federated Kalman filter, local optimal estimations of system states from SINS/star sensor and SINS/GPS local filters are independently sent to the master filter, and global optimal estimations of system states are given by the master filter through global optimal fusion algorithm. Simulation results showed that, attitude accuracy of this integrated navigation method up to 0.25 , position accuracy up to 2.4m, and the reliability is satisfying when some navigation equipment is out of order.
integrated navigation long-endurance strapdown inertial navigation system star sensor global positioning system
Yang Bo Wang Yuegang Chai Yan
Department of Automation Xian Research Inst. Of High-Tech Xian, 710025, China College of Materials Northwestern Polytechnical University Xi’an, 710072, China
国际会议
2009 Ninth International Conference on Hybrid Intelligent Systems(第九届混合智能系统国际会议 HIS 2009)
沈阳
英文
1-4
2009-08-12（万方平台首次上网日期，不代表论文的发表时间）