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《Aeronautical Computing Technique》 2015-06
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Inertial / Star / Vector Objects Integrated Navigation Algorithm Based on Particle Filter

LIN Ai-jun;XIONG Zhi;CHENG Jiao-jiao;YU Feng;LIU Jian-ye;Navigation Research Center,Nanjing University of Aeronautics and Astronautics;  
The GNSS is vulnerable to be disrupted by interference,and can not satisfy the requests of high reliability and high precision for the navigation system of vehicle. Integrating SINS,the attitude information provided by star sensor and the vector objects provided by the ultraviolet sensor is the assurance of realizing high precision in future vehicle. Because of the nonlinear nature and inaccuracy noise statistics in inertial / star / vector objects integrated navigation system,the performance of the existing Kalman filter seems to degrade significantly. Given this problem,this paper proposes an inertial / star / vector objects integrated navigation algorithm based on particle filter. The simulation results show that the proposed algorithm has higher navigation precision,which indicates this algorithm can effectively reduce the negative impact brought by system nonlinear and the inaccuracy noise statistics.
【Fund】: 国家自然科学基金项目资助(61374115 61533008 61533009 61203197 61203188);; 江苏省六大人才高峰项目资助(2013-JY-013);; 中央高校基本科研业务费专项资金项目资助(NZ2014406 NP2015406 NJ20150012 NP20152212 NS2014031);; 江苏高校优势学科建设工程项目和江苏省“物联网与控制技术”重点实验室基金项目资助;; 江苏省高校自然科学基金项目资助(13KJB590001);; 南京航空航天大学研究生创新基地(实验室)开放基金项目资助(kfjj201425 kfjj20150315)
【CateGory Index】: V448.2
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