摘要
针对高性能飞航导弹过载控制系统,考虑舵机的一阶动态特性,设计了一种滑模变结构控制律,其中滑模面由导弹的过载及其一、二阶导数组成。为便于工程实现,进一步采用角速度和角加速度信号来近似代替过载的一、二阶导数。仿真结果验证了该方法的正确性和有效性。
For an agile winged missile control system, taking the dynamics of a first-order actuator into consideration, a variable structure control（VSC） law is designed, where the sliding model surface consists of overload signals and its first-order and second-order derivatives. For convenience in engineering, the first-order and second-order derivatives of the overload are further replaced hy pitch rate and pitch acceleration respectively. Simulation results confirm the correctness and validity of this design.
出处
《飞行力学》
CSCD
北大核心
2006年第3期45-48,共4页
Flight Dynamics
关键词
过载控制
滑模控制
舵动态
鲁棒性
overload control
sliding model control
actuator dynamics
robustness
