提出一种带有锁扣,“后折前张”式的炮弹用弹翼机构设计方案。基于高压气体经小孔流动理论,通过计算程序得出气室参数最优解;利用虚拟样机技术,基于ADAMS对弹翼张开、锁定过程进行了动力学仿真分析。结果表明,在膛内和出炮口后,锁扣与弹翼座之间作用力的最大值之差取极值时,气室参数取得最优解,且膛内弹翼可靠闭锁,出炮口后弹翼能够张开并锁定。该方案可为研制弹翼机构提供参考。

In order to develop projectile wing mechanism, a kind of “back folding and front stretching” wing mechanism with a lock catch is put forward. Based on the theory of flow through small holes, the optimal solution of outlet chamber parameters is obtained by compiling MATLAB computing program of cylinder charging and discharging process and two element function for extreme value. Using virtual prototype technology, the dynamic simulation analysis of the wing opening and locking process is carried out based on ADAMS. The results are as follows: when the difference of the maximum force between the latch and the wing seat is taken as the extreme value, the optimal solution of the air chamber parameters is obtained. In addition, the wings can be locked reliably in the chamber, and can be opened and locked after the muzzle. The scheme can provide reference for the development of wing mechanism.