低速滚转弹道导弹的鲁棒滑模控制  

Robust Slip-mode Control of Ballistic Missile with Low Speed Roll

作　　者：郭景录[1] 马忠文 王志[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天科技集团六院十一所,陕西西安710100

出　　处：《火力与指挥控制》2008年第9期71-74,共4页Fire Control & Command Control

摘　　要：建立了在主动段滚转飞行的弹道导弹的非线性动力学模型。在传统反演滑模控制的基础上,考虑到导弹动力学特性依照时间尺度能够分离为快、慢变两个子系统,设计了对外干扰和参数摄动具有不变性的两级子滑模,实现递级滑模控制,同时引入一阶低通滤波器矩阵避免"膨胀项"。考虑到不确定性的界值难于事先获知,在滑模控制器中引入了自适应律实时地估计不确定性的大小,削弱抖振。最后通过数字仿真验证了这种控制器可以实现导弹稳定飞行。A nonlinear dynamics model of ballistic missile at active roll flight period is established in the paper. Based on traditional inversion slip-mode control, considering fast or slow subsystem based on dynamics characteristics of missile, two-level sub-slip-mode with invariability for external disturbance and parameter is designed to achieve graded slip-mode control, at same time, one-order low-pass filter matrix is introduced to avoid ＂expansion＂. It is considered that it is hard to know limit of uncertainty in advance, an adaptive law is introduced to estimate real-time uncertainty in the Slip-mode controller to reduce vibration and jitter. Through the digital simulation, it is shown that the controller can achieve steady flight of the missile.

关 键 词：弹道导弹 滚转 反演 低通滤波器 递级滑模 自适应律 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]