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.
出处
《火力与指挥控制》
CSCD
北大核心
2008年第9期71-74,共4页
Fire Control & Command Control
关键词
弹道导弹
滚转
反演
低通滤波器
递级滑模
自适应律
ballistic missile
roll
inversion
low-pass filter
graded slip-mode
adaptive law
