基于可靠性分析的最优冗余配置数量确定方法

富立; 王新玲; 岳亚洲

基于可靠性分析的最优冗余配置数量确定方法

1.
北京航空航天大学自动化科学与电气工程学院, 北京 100191
2. 中国航空工业集团公司西安飞行自动控制研究所, 西安 710065

基金项目: 航空科学基金资助项目(20080851021)

详细信息

中图分类号: V 214.6
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出版历程
- 收稿日期: 2009-08-06
- 网络出版日期: 2010-09-30

Method for investigation of the optimal redundant gyros number based on reliability analysis

1.
School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Xi-an Flight Automation Control Research Institute, Aviation Industry Corporation of China, Xi-an 710065, China

摘要

摘要: 针对基于传感器级冗余的捷联惯性导航系统中陀螺仪的冗余配置问题,设计了一种确定最优冗余配置陀螺仪数量的方法,综合考虑了系统的可靠性和成本代价.在各陀螺仪故障的发生为相互独立的前提下,以可靠性函数为工具,提出了确定最优冗余配置数量的性能指标.以该性能指标为依据,分析了斜置冗余配置的陀螺仪数量改变时该指标值的变化情况.结果表明:确定最优冗余配置数量的性能指标的值最大时,所对应的最优斜置冗余配置陀螺仪数量为6.
- 惯性导航系统 /
- 陀螺仪 /
- 冗余 /
- 可靠性分析
Abstract: To solve redundant gyros configuration problem of the strapdown inertial navigation system with redundancy technique in sensor level, a method to determine the optimal number of gyros that compose the redundant system was proposed with a view to the system reliability and cost. It was assumed that the fault of each gyro should be independent of others. To obtain the optimal gyros number, a new criterion was developed by proposing reliability function and the number making the criterion value come to maximum is the optimal gyros number. The change of criterion value was analyzed when the gyros number of redundant system was different. The results show that the redundant system reliability increases with the gyro number increasing. The system reliability improvement is limited but the cost of system increases greatly from some number of gyros. Finally, the optimal gyros number of redundant configuration is given and it is 6.
- inertial navigation system /
- gyroscopes /
- redundancy /
- reliability analysis

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参考文献(1)

[1] Osder S.Practical view of redundancy management application and theory[J].Joural of Guidance,Control and Dynamics,1999,22(1):12-21 [2] 高飞,张洪钺.带马尔可夫参数容错控制系统的可靠性分析[J].北京航空航天大学学报,2007,33(3):302-306 Gao Fei,Zhang Hongyue.Reliability fault tolerant control system with Markovian parameters[J].Journal of Bejing University of Aeronautics and Astronautics,2007,33(3):302-306(in Chinese) [3] 张树侠,孙静.捷联式惯性导航系统[M].北京:国防工业出版社,1992:107-113 Zhang Shuxia,Sun Jing.Strapdown inertial navigation system[M].Beijing: National Defense Industry Press,1992:107-113(in Chinese) [4] Evans F A.Experimental strapdown redundant sensor inertial navigation system[J].J Spacecraft,1970,7(9):1070-1074 [5] Gilmore J P.A redundant strapdown inertial reference unit(SIRU)[J].J Spacecraft,1972,9(1):39-47 [6] Wilcox J C.Competitive evaluation of failure detection algorithms for strapdown redundant inertial instruments[J].J Spacecraft,1974,11(7): 525-530 [7] Seong Yun Cho,Chan Gook Park.Calibration of a redundant IMU .AIAA 2004-5123,2004(in Korea) [8] Vanderwerf K,Wefald K.Fault tolerant inertial navigation system .AIAA 88-4024-CP,1988 [9] Goodstein R.Failure detection technique for the inertial upper stage inertial navigation system .AIAA-1982-1622,1982 [10] Itzhack Y,Itzhack B,Harman R R.In-space calibration of a skewed gyro quadruplet .AIAA-2001-4152,2001 [11] 夏克寒,牟建华,夏至寒.多惯性仪表冗余系统方案设计及其关键技术 [J].导弹与航天运载技术,2007(6):21-24 Xia Kehan,Mu Jianhua,Xia Zhihan.Design of redundant system with multiple inertial measurement units and its key technologies[J].Missile And Space Vehcile,2007(6):21-24(in Chinese) [12] 王珍熙.可靠性、冗余及容错技术[M].北京:航空工业出版社,1991:1-5 Wang Zhenxi.Reliability,redundancy and fault tolerant techniques[M].Beijing:Aviation Industry Press,1991:1-5(in Chinese)

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