首页 | 本学科首页   官方微博 | 高级检索  
     

基于简化FXLMS算法的磁悬浮控制力矩陀螺动框架效应精确补偿方法实验研究
引用本文:霍甲,魏彤,房建成. 基于简化FXLMS算法的磁悬浮控制力矩陀螺动框架效应精确补偿方法实验研究[J]. 宇航学报, 2010, 31(3): 786-792. DOI: 10.3873/j.issn.1000-1328.2010.03.027
作者姓名:霍甲  魏彤  房建成
作者单位:“新型惯性仪表与导航系统技术”国防重点学科实验室,北京航空航天大学仪器科学与光电工程学院,北京 100191
基金项目:国家自然科学基金资助 
摘    要:
磁悬浮控制力矩陀螺(MSCMG)是一种用于航天器姿态控制的高精度长寿命惯性执行机 构,动框架效应补偿是MSCMG实现高精度性能的关键技术之一。然而现有的FXLMS补偿算法由 于模型复杂、计算量大而难以实际应用。通过分析MSCMG磁轴承对象特性,提出一种简化FXL MS算法,将对象滤波器简化为常数对角阵,大幅度减少了算法计算量。对简化算法进行了仿 真,并在MSCMG样机上面进行了动框架效应补偿实验。实验结果表明:简化后的自适应控制 系统,收敛性好,跟踪速度快,具有理想的精度和较强的鲁棒性。


关 键 词:磁轴承  控制力矩陀螺  动框架效应  FXLMS  收敛性  
收稿时间:2009-02-16

Experimental Research on Accurate Compensation of Moving-Gimbal Effects Based on Simplified FXLMS Algorithm in Magnetically Suspended Control Moment Gyroscope
HUO Jia,WEI Tong,FANG Jian-cheng. Experimental Research on Accurate Compensation of Moving-Gimbal Effects Based on Simplified FXLMS Algorithm in Magnetically Suspended Control Moment Gyroscope[J]. Journal of Astronautics, 2010, 31(3): 786-792. DOI: 10.3873/j.issn.1000-1328.2010.03.027
Authors:HUO Jia  WEI Tong  FANG Jian-cheng
Abstract:
Magnetically Suspended Control Moment Gyroscope (MSCMG) is a kind of high precision long life torque producing actuator which is usually used in spacecraft. Accurate compensation of moving-gimbal effects is one of the key technologies in high precision MSCMG. But complex model and much higher computation cost has limited its application. Through analyzing object properties, this paper presents a simplified FXLMS algorithm. In this algorithm, the object filter is replaced by constant diagonal matrix. As a result, the computation cost decreases greatly. The simulation and experiment are presented to verify the method. The experimental results indicate that the adaptive control system based on simplified FXLMS algorithm has the property of good convergence, fast response, enough precision and strong robustness.
Keywords:FXLMS  Magnetic bearing  Control moment gyroscope  Moving gimbal effects  FXLMS  Convergence
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《宇航学报》浏览原始摘要信息
点击此处可从《宇航学报》下载全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号