基于TLC的高超声速飞行器自抗扰姿态控制  

ADRC Attitude Control Based on TLC for Hypersonic Aircraft

作　　者：裴云峰[1] 王宏伦[1] 张惠平[2] 邵星灵[1] 苏子康[1] 

机构地区：[1]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191 [2]北京航天自动控制研究所,北京100854

出　　处：《战术导弹技术》2013年第6期79-84,共6页Tactical Missile Technology

基　　金：中国高校基本科研业务费专项资金资助(YWF-10-01-B015)

摘　　要：针对高超声速飞行器控制指令受噪声干扰、气动参数不精确、各通道强耦合以及舵面偏角有限等特点,设计了基于轨迹线性化(TLC)的自抗扰姿态控制器。针对姿态角指令信号受噪声干扰、姿态回路受加速度限制的特点,应用最速二阶跟踪微分器对姿态指令进行预处理;应用轨迹线性化方法分别对姿态角回路、角速率回路设计解耦控制器;为了提高控制器的鲁棒性,在角速率回路以综合干扰为扩张状态设计扩张状态观测器(ESO),并对综合干扰进行补偿。仿真结果表明,该方法可以有效滤除指令信号中噪声、减小舵面偏角,并提高控制系统的鲁棒性。Hypersonic aircraft has the characters of noise jamming to control command, inaccuracy of aerodynamic parameters, coupling between channels, limited rudder angle etc. The design of attitude controller was presented by trajectory linearization method combined with ADRC. According to noise jam- ming to control command and limited rudder angle, attitude command was processed by two-order track- ing differentiator （TD）. The controller of angle loop and angular rate loop were designed by trajectory linearization. In order to improve the robustness of the controller, extended state observer （ESO） was de- signed in angular rate loop to observe and compensate the synthetic interference. The simulation results show that this method could filter out noise, reduce the rudder angle effectively, and improve the robust- ness of the control system.

关 键 词：跟踪微分器 扩张状态观测器 自抗扰控制 轨迹线性化 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]