北京航空航天大学学报 ›› 2009, Vol. 35 ›› Issue (12): 1511-1515.

• 论文 • 上一篇    下一篇

飞翼布局飞行器副翼性能及重构分析

柴 雪, 王钢林, 武 哲   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2009-03-12 出版日期:2009-12-31 发布日期:2010-09-14
  • 作者简介:柴 雪(1983-),女,吉林大安人,博士生,xuerch@ase.buaa.edu.cn.

Aileron control and reconfiguration of flying wing aircraft

Chai Xue, Wang Ganglin, Wu Zhe   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2009-03-12 Online:2009-12-31 Published:2010-09-14

摘要: 针对飞翼布局飞行器副翼在偏转过程中引起的纵横航向运动耦合的问题,应用升降舵、副翼和阻力舵协调偏转的方法进行控制.为提高飞翼飞行器的生存性,对舵面故障时的重构方法进行了研究.升降舵故障时,直接应用伪逆法即可应用副翼完成重构;阻力舵故障时,为解决伪逆法带来的系统不稳定及重构后系统稳态精度差的问题,将一种基于劳斯稳定判据的、加入了比例-积分控制器的改进伪逆法引入重构.仿真结果表明:该方法在保证系统稳定的基础上能够使系统性能得到最大程度的恢复.

Abstract: To decouple the longitudinal and lateral-directional coupled motion caused by the aileron deflection of the flying wing aircraft, the elevator and the split-drag-rudder (SDR) were used to cooperate with the aileron to decouple the coupled motion. In order to increase the flying wing aircraft survivability, the reconfigurable control system had been investigated. In the elevator failure reconfiguration, the pseudo-inverse method was directly used to reconstruct the control system by the aileron. In the SDR jamming failure, an improved pseudo-inverse reconfigurable method based on the routh stability was designed with the proportion-plus-integral (PI) control. The method guaranteed the stability of the reconfigured closed-loop system by using the routh stability criterion, and was capable of solving bad steady precision problems that may occur in the reconfigurable system. Simulation results are provided to show the effectiveness of the proposed method by recover the performance of original system to a maximum extent.

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