某型飞机翼梁振动时效参数化工艺测试分析

Testing Analysis of Vibratory Stress Relief Parametric Technologic for Some Airplane's Swing Spar

为了测量飞机翼梁振动时效处理时残余应力的量值,提出了用相应结构动态参数的变化来进行监测的方法。本文介绍了翼梁振动时效处理的工艺流程,并对测试激振频率、激振时间、激振力和试件固有频率、振后频率等动态参数进行了取样测试分析,试验表明动态参数的变化规律与残余应力的下降规律相对应。

In order to measure the value of residual stress, which is produced in the progress of wing spar vibration stress relief, we take the supervising method to solve the problems with corresponding structure dynamic parametric changing. It has introduced the technologic flow, analyzing the testing vibratory frequency, vibratory time, vibratory power and the sample＇s dynamic parameter, in the end, the experiment indicate the changing rules are correspond between dynamic parametric and residual stress descend.