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.