|Table of Contents|

Design of angle-of-attack observer for overload control system of anti-ship missile

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2015年03期
Page:
342-
Research Field:
Publishing date:

Info

Title:
Design of angle-of-attack observer for overload control system of anti-ship missile
Author(s):
Wu Linghua1Zhao Hongchao2Jiang Xiaoming3
1.Chongqing Bureau of Naval Equipment Department,Chengdu 610100,China; 2.Faculty 703,Naval Aeronautical and Astronautical University,Yantai 264001,China; 3.The 91049th Army,Qingdao 266100,China
Keywords:
anti-ship missiles overload control system angle-of-attack observer Lyapunov stability theory output-redefinition technique overload output nonminimum phase problem sliding mode method supersonic anti-ship missiles
PACS:
TJ765.2
DOI:
-
Abstract:
In order to estimate the unknown angle-of-attack(AOA)of anti-ship missiles,an AOA observer is designed based on a nonlinear moving model of anti-ship missiles.The convergence capability of the AOA observer is analyzed according to Lyapunov stability theory.The output-redefinition technique is adopted to settle the nonminimum phase problem of overload output.The controller of missile overload control system is designed using the sliding mode method because of its strong robustness,and the tracking error of system output is ensured to converge to zero.A type of supersonic anti-ship missile is simulated and analyzed.The simulation results show that the observer output corresponds with the actual AOA basically after 0.02 s.

References:

[1] Theodoulis S,Duc G.Missile autopilot design:Gain-scheduling and the gap metric[J].Journal of Guidance Control and Dynamics,2009,32(3):986-996.
[2]Yu Jianqiao,Luo Guanchen,Mei Yuesong.Surface-to-air missile autopilot design using LQG/LTR gain scheduling method[J].Chinese Journal of Aeronautics,2011,24:279-286.
[3]Kim S H,Kim Y S,Song C.A robust adaptive nonlinear control approach to missile autopilot design[J].Control Engineering Practice,2004,12:149-154.
[4]Tsourdos A,White B A.Adaptive flight control design for nonlinear missile[J].Control Engineering Practice,2005,13:373-382.
[5]Xin Ming,Balakrishnan S N.Nonlinear H missile longitudinal autopilot design with θ-D method[J].IEEE Transactions on Aerospace and Electronic Systems,2008,44(1):41-56.
[6]Efimov D,Fridman L.Global sliding-mode observer with adjusted gains for locally Lipschitz systems[J].Automatica,2011,47(3):565-570.
[7]Daly J M,Wang D W.Output feedback sliding mode control in the presence of unknown disturbances[J].Systems and Control Letters,2009,58(3):188-193.
[8]赵红超,高晓冬,范绍里.基于抗饱和补偿器的导弹过载控制系统设计[J].南京理工大学学报,2012,36(增刊):154-159.
Zhao Hongchao,Gao Xiaodong,Fan Shaoli.Design of missile overload control system based on anti-windup compensator[J].Journal of Nanjing University of Science and Technology,2012,36(Sup):154-159.
[9]Shi Xianjun,Zhao Hongchao,Chen Jie.Terminal sliding mode control for STT missile based on RBF neural network[J].Advances in Intelligent and Soft Computing,2012,169:49-55.
[10]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2000:56-59.

Memo

Memo:
-
Last Update: 2015-06-30