火箭炮交流位置伺服系统滑模变结构控制策略

Sliding Mode Variable Structure Control Strategy of AC Position Servo System of MLRS

对多管火箭炮负载特性,转动惯量变化规律及其燃气流冲击力矩作用规律进行了定量分析,基于此设计了多管火箭炮交流位置伺服系统结构并提出了滑模变结构控制策略,对其具体控制结构的形式进行了分析,提出了统一滑模变结构控制和串级滑模变结构控制两种方案。最后给出了两种滑模变结构控制结构的计算机仿真结果,结果表明该控制策略具有较强的抗负载扰动能力和参数鲁棒性,可以适应多管火箭炮的负载干扰力矩以及转动惯量的变化。

Load characteristics, transformation law of moment of inertia and action rule of exhausted flow shock moment of multiple launch rocket system （MLRS） are quantitatively analyzed. Based on this, structure of AC position servo system of MLRS is designed, and sliding mode variable structure control theory and strategy are proposed. Two solutions such as uniform sliding mode variable structure control and cascade sliding mode variable structure control are presented. Finally, computer simulating results of two kinds of sliding mode variable structure control are given. The results showed that this control strategy has stronger robustness and parameter stability, and it can be suitable for load dis turbing moment and transformation of moment of inertia of MLRS.