基于LQ/RHO多回路技术的变体飞机控制器设计

陈伟; 卢京潮; 章卫国

基于LQ/RHO多回路技术的变体飞机控制器设计

西北工业大学自动化学院, 西安 710129

基金项目: 航空科学基金资助项目(20100753009)

详细信息

作者简介:
陈伟(1986-),男,湖北随州人,博士生,chenwei1298@mail.nwpu.edu.cn.

中图分类号: TP273
计量
- 文章访问数: 1704
- HTML全文浏览量: 222
- PDF下载量: 701
- 被引次数: 0
出版历程
- 收稿日期: 2012-02-27
- 网络出版日期: 2013-03-31

Design of a controller for morphing aircraft based on the LQ/RHO multi-loop technology

College of Automation, Northwestern Polytechnical University, Xi'an 710129, China

摘要

摘要: 为了确保变体飞机在变体过程中的飞行稳定性,提出了一种多回路控制器设计方案.采用线性二次(LQ, Linear Quadratic)输出反馈方法进行内回路控制器设计,确保在机翼固定状态下飞行稳定性.在变体过程中,用一不确定项来描述变体过程中存在的干扰噪声和未建模的动态特性.采用基于参考模型的滚动时域优化(RHO, Receding Horizon Optimal)方法进行外回路修正控制器设计.仿真结果表明:实际系统的输出响应较好地跟随参考模型的输出,不受变体速率的影响,满足实时性和鲁棒性的要求.
- 线性二次 /
- 输出反馈 /
- 滚动时域优化 /
- 变体飞机 /
- 多回路
Abstract: In order to ensure the flight stability of morphing aircraft under the morph state, a multi-loop controller was proposed. The inner-loop controller was designed by the linear quadratic (LQ) output feedback approach, which was used to ensure stability under the fixed-wing state. In the process of morphing, an indeterminate term was introduced to describe the interferences and unmodeled dynamics. The outer-loop controller was designed by the receding horizon optimal (RHO) algorithm, which was used to calculate the real-time control correction value within a finite horizon. The simulation results show that the proposed controller is able to yield a consistent response regardless of morph rate, and that it satisfies the requirements of real-time and robustness.
- linear quadratic /
- output feedback /
- receding horizon optimal /
- morphing aircraft /
- multi-loop

HTML全文

参考文献(1)

[1] 毕胜.变结构飞行器的多刚体建模和姿态控制[D].合肥:中国科学技术大学自动化系,2010 Bi Sheng.Multi-rigid-body modeling and attitude control of variable structure aircraft [D].Hefei:Department of Automation,University of Science and Technology of China,2010(in Chinese) [2] 张平,周丽,邱涛.一种新的柔性蜂窝结构及其在变体飞机中的应用[J].航空学报,2011,32(1):156-163 Zhang Ping,Zhou Li,Qiu Tao.A new flexible honeycomb structure and its application in structure design of morphing aircraft[J].Acta Aeronautica et Astronautica Sinica,2011,32(1):156-163(in Chinese) [3] Du Sha,Ang Haisong.Design and feasibility analyses of morphing airfoil used to control flight attitude[J].Journal of Mechanical Engineering,2012,58(1):46-55 [4] Abdulrahim M,Lind R.Control and simulation of a multi-role morphing micro air vehicle[C]//AIAA Guidance,Navigation,and Control Conference.San Francisco:American Institute of Aeronautics and Astronautics,2005:6408-6426 [5] Baldelli D H,Lee D H,Pena R S,et al.Practical modeling,control and simulation of an aeroelastic morphing uav[C]//AIAA Structures,Structural Dynamics,and Materials Conference.Hawaii:American Institute of Aeronautics and Astronautics,2007:6481-6499 [6] Seigler T M,Neal D A.Analysis of transition stability for morphing aircraft[J].Journal of Guidance,Control,and Dynamics,2009,32(6):1947-1953 [7] Ward D G,Monaco J F.System identification for retrofit reconfigurable control of an F/A-18[J].Journal of Aircraft,2005,42(1):63-72 [8] Ward D G,Barron R L.A self-designing receding horizon optimal flight controller[C]//Proceedings of the 1995 American Control Conference.Washington:Barron Associates,1995:3490-3494 [9] Seigler T M,Neal D A,Bae J S,et al.Modeling and flight control of large-scale morphing aircraft[J].Journal of Aircraft,2007,44(4):1077-1084 [10] Stevens B L,Lewis F L.Aircraft control and simulation[M].New York:Wiley-Interscience,2003:385-386 [11] 高金源,李陆豫,冯亚昌,等.飞机飞行品质[M].北京:国防工业出版社,2003:65-68 Gao Jinyuan,Li Luyu,Feng Yachang,et al.Aircraft handling qualities[M].Beijing:National Defense Industry Press,2003:65-68(in Chinese)

施引文献

资源附件(0)

访问统计