针对某型导弹折叠翼,设计了一种带自锁和自解锁功能的作动筒。阐述了作动筒的工作原理,建立了弹翼展开角与作动筒工作力之间的关系,并借助动力学仿真软件ADAMS对整个系统进行了仿真分析。仿真结果表明,该种作动筒简化了折叠翼机构的设计工作,提高了系统可靠性。另外,在仿真分析中,将分离夹头作为柔性体考虑才能客观、准确地反映整个系统的运动。 For a type of missile folding wing, designed a self-locking and self-unlocking function of the actuator. The working principle of the actuator was expounded, the relation between the deployment angle of the wing and the working force of the actuator was established, and the whole system was simulated and analyzed with the aid of the dynamic simulation software ADAMS. The simulation results show that this type of actuator simplifies the design of the folding wing mechanism and improves the system reliability. In addition, in the simulation analysis, the separation chuck as a flexible body to objectively and accurately reflect the movement of the entire system.