文中针对某型发射装置振动后产生卸弹困难的问题,深入研究了该型发射装置采用的楔形防振机构的原理,并在此基础上,通过控制防振机构零件的尺寸偏差来控制防振片的最大下压量,将原有的单一防振片减振变为防振片减振与间隙减振相结合的综合减振形式,通过理论分析、有限元仿真和试验验证,证明了改进方案的有效性和可行性,彻底解决了该型防振机构卸弹困难问题,为发射装置的防振机构设计提供参考。

In view of difficult unloading missile after vibration test of launcher, the vibration control principle of wedge self-locking vibration proof mechanism in this launcher was researched deeply in this paper. On this basis, by controlling dimension deviation of parts in vibration proof mechanism to control the maximum pressing number of the anti-vibration piece, the original single vibration control by antivibration piece was changed to comprehensive anti-vibration form containing anti-vibration piece and damping clearance. The improvement program to solve the difficult issues of unloading the missile was effective and feasible which proved by theoretical analysis, finite element simulation and experimental validation, which can provide reference design for anti-vibration mechanism of new launchers.