基于高阶奇异值分解的LPV鲁棒控制器设计

孙斌; 杨凌宇; 张晶

doi:10.13700/j.bh.1001-5965.2015.0486

基于高阶奇异值分解的LPV鲁棒控制器设计

doi: 10.13700/j.bh.1001-5965.2015.0486

北京航空航天大学自动化科学与电气工程学院, 北京 100083

基金项目: 国家自然科学基金（61273099）；航空科学基金（20135851041）

详细信息

作者简介:
孙斌男,硕士研究生。主要研究方向:先进飞行器控制。E-mail: sun1990bin@qq.com Tel.: 010-82316873;杨凌宇男,博士,副教授,硕士生导师。主要研究方向:先进飞行器控制,容错控制,先进布局飞机多操纵控制方法。E-mail: yanglingyu@buaa.edu.cn Tel.: 010-82316873

通讯作者:
杨凌宇,Tel.: 010-82316873 E-mail: yanglingyu@buaa.edu.cn

中图分类号: V249.12
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出版历程
- 收稿日期: 2015-07-20
- 网络出版日期: 2016-07-20

Robust LPV control design based on HOSVD

School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 针对高超声速飞行器线性变参数（LPV）模型建模中准确度与复杂度之间的矛盾性，提出了一种基于网格化张量及高阶奇异值分解（HOSVD）的凸多胞LPV模型建模及控制方法。首先基于雅可比线性化给出了大包线网格化模型的张量描述形式，然后提出了一种基于HOSVD的多胞LPV模型生成算法，将网格化模型表述为有限个线性时不变（LTI）顶点及权重函数的组合，并基于舍弃的奇异值给出了建模误差的指标，最后结合某航天飞机再入段六自由度非线性模型进行了大包线鲁棒LPV控制器设计与仿真验证，结果表明该方法可获得计算复杂度低且保证建模精度的LPV模型，设计的鲁棒变增益控制器能够使系统快速跟踪姿态角指令信号，并能够保证系统的稳定性和鲁棒性。
- 高超声速飞行器 /
- 飞行包线 /
- 多胞线性变参数(LPV)系统 /
- 鲁棒变增益控制 /
- 高阶奇异值分解(HOSVD)
Abstract: Considering the trade-off between the accuracy and complexity of the linear parameter varying (LPV) modeling of hypersonic vehicles, a novel polytopic LPV modelling technique based on grid tensors and higher-order singular value decomposition (HOSVD) was developed. Firstly, through Jacobian linearization, the grid tensor description of a hypersonic vehicle with large flight envelopes was introduced, and a polytopic LPV model was constructed using HOSVD. The resulting model was described by a linear combination of vertices of linear time invariant (LTI) models and corresponding weighting functions. The discarded singular values were treated as a modeling error index. A robust variable gain controller which combines a robust controller and gain scheduling technique was then designed for the 6 degree-of-freedom nonlinear model of the hypersonic vehicle. Simulation results demonstrate that the proposed method not only reduces the computational complexity, but also guarantees the modeling accuracy. Furthermore, under the proposed controller, the closed loop system can track the attitude commands rapidly, and good stability and robustness are achieved.
- hypersonic vehicle /
- flight envelope /
- polytopic linear parameter varying (LPV) system /
- robust variable gain control /
- higher-order singular value decomposition (HOSVD)

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参考文献(15)

[1]	白辰,任章,樊垚,等.基于模糊神经网络扰动观测器的RLV动态逆再入姿态控制[J].中南大学学报(自然科学版),2013,7(1):58-62.BAI C,REN Z,FAN Y,et al.Dynamic inversion control for RLV reentry attitude based on fuzzy-neural disturbance observer[J].Journal of Central South University(Natural Scicence),2013,7(1):58-62(in Chinese).
[2]	HALL C E,SHTESSEL Y B.Sliding mode disturbance observer-based control for a reusable launch vehicle[J].Journal of Guidance Control and Dynamics,2006,29(6):1315-1328.
[3]	LIND R.Linear parameter-varying modeling and control of structural dynamics with aerothermoelastic effects[J].Journal of Guidance Control and Dynamics,2002,25(4):733-739.
[4]	YUSUKE Y,TAKASHI S.Attitude control of spacecraft with VSCMGs using LPV modeling technique[C]//SICE Annual Conference.Tokyo:Waseda University,2011:2678-2683.
[5]	KUMAR A.Convex modeling techniques for aircraft control[D].Virginia:Virginia Polytechnic Institute and State University,2000:1-5.
[6]	PETRES Z.Polytopic decomposition of linear parameter-varying models by tensor-product model transformation[D].Budapest:Budapest University of Technology and Economics,2006:25-89.
[7]	秦伟伟,郑志强,刘刚,等.高超声速飞行器的LPV鲁棒变增益控制[J].系统工程与电子技术,2011,33(6):1327-1331.QIN W W,ZHENG Z Q,LIU G,et al.Robust variable gain control for hypersonic vehicles based on LPV[J].Systems Engineering and Electronics,2011,33(6):1327-1331(in Chinese).
[8]	王明昊,刘刚,杨述华.高超声速飞行器的多胞LPV系统控制器设计[J].空间控制技术与应用,2013,39(1):15-22.WANG M H,LIU G,YANG S H.Polytopic-LPV-system-based control design for hypersonic vehicle[J].Aerospace Control and Application,2013,39(1):15-22(in Chinese).
[9]	HE C F,YANG L Y,WANG Z C,et al.Linear parameter-varying attitude controller design for a reusable launch vehicle during reentry[C]//Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference.Piscataway,NJ:IEEE Press,2014:2723-2728.
[10]	RAJWADE A,RANGARAJAN A,BANERJEE A.Image denoising using the higher order singular value decomposition[J].IEEE Transactions on Pattern Analysis and Machine Intelligence,2013,35(4):849-862.
[11]	OHARA A,YAMAGUCHI Y,MORITO T.LPV modeling and gain scheduled control of reentry vehicle in approach and landing phase[C]//AIAA Guidance,Navigation, Control and Conference and Exhibit.Reston:AIAA,2001:1-11.
[12]	Aerodynamic design data book,Volume 1M:Orbiter vehicle STS-1: SD72-SH-0060 [R].[S.l.]:Rockwell International,1980.
[13]	王振超,杨凌宇,张晶,等.面向大包线导弹的分回路LPV姿态控制器设计[J].航空兵器,2015,1(2):14-20.WANG Z C,YANG L Y,ZHANG J,et al.Loop separate LPV attitude controller design for large envelope missile[J].Aero Weaponry,2015,1(2):14-20(in Chinese).
[14]	夏文艳,高嵩,王洁,等.基于H_∞混合灵敏度的导弹解耦控制器设计方法[J].电子设计工程,2009,17(11):43-45.XIA W Y,GAO S,WANG J,et al.Decoupling based on the H_∞ mixed sensitivity controller for missile design method[J].Electronic and Engineering,2009,17(11):43-45(in Chinese).
[15]	傅彩芬,谭文,刘吉臻.基于回路成形的鲁棒增益调度控制器设计[J].信息与控制,2005,34(2):152-156.FU C F,TAN W,LIU J Z.Robust gain scheduling controller based on loop shaping[J].Information and Control,2005,34(2):152-156(in Chinese).