一种基于自适应变结构的高超滑翔飞行器控制方法研究  

Study on Adaptive Variable Structure Control Law for Hypersonic Gliding Vehicle

作　　者：常莹莹[1] 王小虎[1] 何纯[1] 刘雄飞[1] 

机构地区：[1]北京控制与电子技术研究所,北京100038

出　　处：《航天控制》2015年第4期62-67,76,共7页Aerospace Control

摘　　要：针对高超声速滑翔飞行器的不确定性及强非线性耦合特性,研究了一种自适应变结构姿态控制设计方法。首先建立了高超声速飞行器在滚转通道快速将最大升力面滚转到制导机动方向时姿态控制系统的非线性数学模型,然后将结构干扰力矩、非线性耦合和气动参数摄动等不确定的输入因素视为一类有界干扰,提出了一种自适应变结构控制方法,该法在保证系统闭环稳定的前提下,在线对不确定因素的界进行估计,从而对系统中的不确定因素进行补偿,并选择适当的趋近律,通过符号函数连续化方法来解决由于变结构控制带来的抖振问题,最后进行仿真验证。仿真结果表明该方法具有良好的解耦控制效果,与传统方法相比可有效提高控制系统的控制性能和鲁棒性。A variable structure adaptive control law design approach is presented for hypersonic glide vehi- cles in the case of nonlinear, uncertainty and coupling situations. Firstly, a nonlinear simulation model is established according to the features of hypersonic glide vehicles. Secondly, structure moment and external disturbance are regarded as a class of disturbance with boundary. Thirdly, the uncertain boundary of struc- ture moment and disturbance is estimated with this method on the premise that the stabilization of close - loop system is guaranteed and chattering which is brought by the variable structure control is eliminated by choosing a suitable reaching law and a continuous analogy of sign function. At last, the numerical simula- tion results verify the feasibility of the proposed design method.

关 键 词：非线性 变结构 自适应 优化控制 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]