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[1]史震,何晨迪.高超声速飞行器姿态跟踪鲁棒自适应控制[J].电机与控制学报,2018,22(07):118-124.[doi:10.15938/j.emc.2018.07.015]
 SHI Zhen,HE Chen-di. Robust adaptive attitude control for hypersonic reentry vehicle[J].,2018,22(07):118-124.[doi:10.15938/j.emc.2018.07.015]
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《电机与控制学报》[ISSN:1007-449X/CN:23-1 408/TM]

卷:
22
期数:
2018年07
页码:
118-124
栏目:
出版日期:
2018-10-31

文章信息/Info

Title:
 Robust adaptive attitude control for hypersonic reentry vehicle
作者:
 史震 何晨迪
 ( 哈尔滨工程大学 自动化学院,黑龙江 哈尔滨 150001)
Author(s):
 SHI Zhen HE Chen-di
  ( College of Automation,Harbin Engineering University,Harbin 150001,China)
关键词:
姿态跟踪控制 参数不确定性 外界干扰 反步法 鲁棒自适应
Keywords:
attitude tracking control uncertain parameters external disturbances backstepping methodrobust adaptive method
分类号:
V 448. 2
DOI:
10.15938/j.emc.2018.07.015
文献标志码:
A
摘要:
 针对高超声速飞行器再入姿态跟踪问题提出一种新的控制策略,该控制律同时考虑气动参数摄动和外界干扰。首先,研究面向控制对象的仿射非线性模型; 然后,基于反步法设计一种鲁棒自适应控制律。该控制律采用自适应策略在线估计不确定参数,利用鲁棒控制策略对外界干扰进行补偿,并且引入一阶低通滤波器避免了反步法中虚拟变量求导计算复杂的问题。最后,基于 Lya-punov 稳定性理论证明了姿态角跟踪误差一致最终有界。仿真结果证明该鲁棒自适应控制律能够有效抑制外界干扰,对不确定参数有良好自适应性,具有良好的跟踪性能和强鲁棒性。
Abstract:
An attitude tracking controller is proposed for hypersonic reentry vehicle ( HRV) system withuncertain parameters and external disturbances being simultaneously addressed. Firstly,the nonlinear af-fine model of HRV was researched. Then a robust adaptive controller was designed based on the back-stepping method. In the proposed controller,
adaptive strategies were used to estimate the uncertain aero-dynamic parameters online. A robust strategy was applied to eliminate the external disturbances. Mean-while,
a first-order low-pass filter was used to avoid the virtual variable derivative in the backsteppingmethod. The tracking errors were proved uniformly and ultimately bounded by the Lyapunov stability the-orem. Simulation results show that the proposed robust adaptive controller,in the presence of aerodynamicparameters perturbations and external disturbances,has good tracking performance and strong robustness.

参考文献/References:

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[2]袁国平,史小平.带有特殊不确定性的导弹非线性自适应控制[J].电机与控制学报,2010,(05):104.
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备注/Memo

备注/Memo:
收稿日期:2016-05-31
作者简介:史 震(1961-),男,教,博士生导师,研究方向为飞行器制导与控制棋术、飞行器捷联惯性导航技术
何晨迪(1987-),女,博士研究生,研完方向为飞行器制导与控制
更新日期/Last Update: 2018-09-28