北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (7): 827-832.

• 论文 • 上一篇    下一篇

高超声速飞行器迎角观测器及控制器设计

陈洁, 周绍磊, 宋召青   

  1. 海军航空工程学院 控制工程系, 烟台264001
  • 收稿日期:2010-08-10 出版日期:2011-07-30 发布日期:2011-08-04
  • 作者简介:陈 洁(1978-),女,山东龙口人,讲师,hjhychenjie@tom.com.
  • 基金资助:

    国家自然科学基金资助项目(61004002;90716021)

Nonlinear modelling and open-loop dynamatics characteristics for one hypersonic aircraft

Chen Jie, Zhou Shaolei, Song Zhaoqing   

  1. Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai 264001, China
  • Received:2010-08-10 Online:2011-07-30 Published:2011-08-04

摘要: 针对高超声速飞行器非线性动力学系统中所特有的输出非线性、状态向量强耦合等特性,综合考虑了飞行中的不确定性、具有复杂非线性输出、状态向量不完全可测量等因素,提出一种基于Lyapunov法的滑模观测器和控制器设计方法,用于解决高超声速飞行器迎角观测器不能精确测量的问题.首先在观测器设计过程中,利用过载输出滑模面构造了Lyapunov函数,确定出观测器收敛的条件,并基于线性化理论求出观测器增益矩阵.然后在控制器设计过程中,采用基于动态面的自适应反演方法设计出控制律,用多层神经网络调节函数逼近系统中的高频未建模动态,设计鲁棒项函数解决了逼近误差的影响问题,并进行了稳定性分析和仿真验证.

Abstract: Considering that the hypersonic aircraft nonlinear dynamatic system owns the characteristics of nonlinear output, highly coupled of state vector, a novel sliding surface observer and controller design based on Lyapunov function was presented. During the course of observer design, overload output sliding surface was adopted to consrtruct Lyapunov function to guarantee the astringency of observer, and observer plus matrix could be gotten. Then, dynamic surface adaptive backstepping was adopted to design control law, multi-layers nerual network adjust function was introduced to compensate the influence from the uncertain, and the robust terms were designed to solve the problem from approach error. The stability analysis and simulations demonstrate the good performance of the controller.

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