根据火箭弹锁弹力的一般设计原则确定了系统火箭弹锁弹力为1470N。利用有限元法对火箭弹运输过程紧急制动进行仿真模拟,结果表明,固弹销剪切部位最大应力为155MPa,所受的最大冲击力为887N,安全系数为2.5。运输试验表明,980N的锁弹力为弹药运输要求的临界状态。发射试验表明,1470N的锁弹力满足火箭弹发射各项性能要求。因此,本系统锁弹力设定为1470N,能够满足产品运输和发射要求。

According to the general design principle of adjusting pin, the locking force in this system was confirmed as 1470N. The conveyance process of rocket was simulated by means of dynamic finite element method. The result shows that the highest stress is 155MPa and impacting force is 887N and the safety coefficient is 2.5 during the urgent brake course. The road conveyance test shows that the 980N locking force is the critical state for ammunition transport requirements. The emission test shows that the 1450N locking force can meet various performance requirements for rocket launching. Therefore, the locking force in the system is set to 1470N, which can meet the conveyance and launching requirements.