导弹翼面组件开锁装置失效分析

Failure Analysis on Unlocking Equipment in Missile Wing Plane Unit

某型导弹翼面组件例行试验中,多次出现开锁装置失效现象。对开锁装置的工作原理、摩擦情况和结构尺寸进行了分析。结果表明:开锁装置失效原因为陀螺舵轴的接触部位发生粘着磨损及疲劳点蚀,使开锁装置在随机振动载荷作用下摩擦阻力增大而导致失效。在此基础上,通过清除润滑脂中的磨损碎屑,合理选配零件尺寸,保证零件过渡面光滑等改进措施,解决了翼面组件振动后开锁力超差问题,有效地避免了开锁装置的失效。

The unlocking equipment in a missile wing plane unit failed during routine testing.In order to find out the failure cause,the working principle,friction state and physical dimension of the unlocking equipment were analyzed.It was found that the failure resulted from the increase of the friction resistance caused by the adhesion wear and fatigue point erosion at the contact region of the gyro rudder shaft under the effect of random vibration loading.Based on the analysis above,the wear debris in the grease was cleaned out,the dimension of the parts was improved,and the transition surfaces of the parts were smoothed.As a result,the decline of the unlocking force after the vibration of the missile wing plane unit was prevented,and the failure problem of the unlocking equipment was solved.