具有侧向脉冲推力的旋转导弹建模与控制研究

Modeling and control of a spinning missile with blended aero-fin and lateral impulsive thrust

针对具有气动舵和侧向脉冲推力复合控制的自旋导弹,在准弹体坐标系中建立完整的动力学模型,由于侧向脉冲推力的离散事件特性,提出运用混杂系统理论的方法设计其复合控制自动驾驶仪。根据系统的特性将自动驾驶仪划分成两种不同的工作模式,针对不同的工作模式分别设计不同的控制方法,通过两种模式之间的切换实现导弹的快速响应和能源的合理分配。最后进行仿真检验该自动驾驶仪的有效性,并将仿真结果与气动舵单独控制时的结果作了对比。

The spinning missile with blended aero fin and lateral impulsive thrust is investigated. Mathematical models are built and an analysis of the discrete event properties of the lateral impulsive thrust is carried out. Hybrid system control theory is introduced for autopilot design. The autopilot is designed with two operating modes according to the system's behavior and different control strategies are developed with respect to different modes. Fast response and reasonable allocation of energy are achieved by means of switching between these two modes. Finally, simulations are carried out to validate the autopilot and comparison is made between the simulation results and those obtained when the aero-fins are used alone. The results show that the dynamic response characteristic of the missile can be improved by using the blended controller.