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为了消除经典滑模变结构控制在导弹控制系统中产生的抖振现象,提出了一种新型的基于二阶滑模变结构控制的导弹姿态控制系统设计方法。为便于导弹姿态控制系统的设计,将复杂导弹姿态运动方程分解成三个简单的子系统,即俯仰通道子系统、偏航通道子系统和滚转通道子系统,同时将三个通道间的耦合项等效为外界干扰。当三通道间的耦合项有界时,分别给出了三个子系统的控制器。仿真结果验证了所提方法的正确性和有效性,并且有效消除了系统抖振现象。
In order to eliminate the chattering phenomenon caused by classical sliding mode variable structure control in missile control system, a new design method of missile attitude control system based on sliding mode sliding mode control is proposed. In order to facilitate the design of the missile attitude control system, the complex missile attitude motion equation is decomposed into three simple subsystems, ie, the pitch channel subsystem, the yaw channel subsystem and the roll channel subsystem, and the coupling between the three channels The equivalent of external interference. When the coupling term of three channels is bounded, the controllers of three subsystems are given respectively. The simulation results verify the correctness and effectiveness of the proposed method and effectively eliminate the chattering of the system.