期刊文献+

滑块机构下高旋弹头的逆系统设计方法 被引量:1

Inverse System Design Method of High-rolling Ball Based on Moving-mass Framework
下载PDF
导出
摘要 建立了滑块机构下高旋弹的姿态方程,采用逆系统方法对非线性模型进行了解耦控制研究,得到了完整的状态方程,分析了基于逆系统理论解耦的可行性,推导出状态反馈后的a阶伪线性系统和内环控制算法,而后用极点配置原理设计了外环PID(Proportional Integral Derivative)控制律,形成了完整的闭环控制结构,最后的仿真表明:滑块机构和逆系统方法对高旋弹的姿态控制是有效的,且PID控制律的引入使得此方法更易于工程实现。 The attitude model of high-rolling ball is found under inner moving-mass framework,a decoupling control approach based on dynamic inverse system theory has been developed for the nonlinear system,then feasibility of decoupling control based on dynamic inversion theory is discussed,α-th pseudo linear model and the dynamic decoupling control arithmetic is deduced,the further system synthesized by pole assignment theory to get PID(Proportional Integral Derivative) parameters is presented,so obtained the integrated closed-loop structure,the simulation results have showed that moving-mass framework and inverse system method is effective for attitude control of high-rolling ball and it is easy to engineering by PID controller.
作者 李永博 郭治
出处 《火力与指挥控制》 CSCD 北大核心 2011年第7期190-194,199,共6页 Fire Control & Command Control
关键词 高旋弹 滑块机构 逆系统方法 解耦控制 伪线性系统 PID控制器 high-rolling ball moving-mass framework inverse system theory decoupling control pseudo linear system PID controller
  • 相关文献

参考文献15

  • 1杨少宇,秦峰.防空高炮现状与发展趋势分析[J].四川兵工学报,2003,24(6):3-6. 被引量:9
  • 2薄煜明,郭治,杜国平,杨少宇.高炮与防空导弹在近程防空反导中的互补性[J].兵工学报,2002,23(2):164-166. 被引量:21
  • 3RD RI,BR S, SA K. Moving Mass Trim Control for Aerospace Vehicles[J]. Journal of Guidance Control and Dynamics, 1996,19 (5) : 1064-1070. 被引量:1
  • 4Petsopoulos T,Regan F. Moving Mass Roll Control System for Fixed-Trim Re-Entry Vehicle [J]. Journal of Spacecraft and Rockets, 1996,33 (1) : 54- 60. 被引量:1
  • 5Menon P K, Swerduk G D, Ohlmeyer E J. Integrated Guidance and Control of Moving Mass Actuated Kinetic Warheads [J ]. Journal of Guidance Control and Dynamics, 2004,27 ( 1 ) : 118- 126. 被引量:1
  • 6Snell S A,Enns D F,Jr WLG. Nonlinear Inversion Flight Control for a Supermaneuverable Aircraft [J]. Journal of Guidance, Control, and Dynamics, 1992,15(4) :976-984. 被引量:1
  • 7Lane S H,Stengel R F. Flight Control Design Using Nonlinear Inverse Dynamics[J]. Automatic, 1988, 24(4):471-483. 被引量:1
  • 8McFarland M B, Hoque S M. Robustness of a Nonlinear Missile Autopilot Designed using Dynamic Inversion [C ]//AIAA Guidance, Navigation, and Control Conference and Exhibit 14-17,2000. 被引量:1
  • 9Juliana S, Chu Q P, Mulder J A, et al. The Analytical Derivation of Non-linear Dynamic Inversion Control for Parametric Uncertain System [C]//AIAA Guidance, Navigation, and Control Conference and Exhibit, 2005. 被引量:1
  • 10Sadraey M, Colgren R. Robust Nonlinear Controller Design for a Complete UAV Mission [C]//AIAA Guidance, Navigation, and Control Conference and Exhibit, 2006. 被引量:1

共引文献27

同被引文献6

引证文献1

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部