阻尼减振技术在某型飞机短舱尾罩裂纹中的应用

目的针对某型飞机短舱尾罩振动情况开展研究,制定不对结构进行颠覆性改进短舱尾罩裂纹问题的解决措施。方法对短舱尾罩处的振动情况进行测试,分析短舱尾罩裂纹形成的原因,利用阻尼减振技术的原理选择适合的阻尼材料和处理方式,通过振动测试验证改进效果。结果采用阻尼减振技术后,振动水平最大降低约83%,峰值个数明显减少,对易产生蒙皮裂纹的大于150 Hz、0.8 g以上的振动具有有效的抑制作用,能够有效提高蒙皮结构的使用寿命。结论短舱尾罩蒙皮结构采取阻尼层减振处理的方法基本解决了短舱尾罩裂纹问题,同时也给解决振动引起的类似问题提供了解决思路。

Application of Damping Vibration Absorbing Technology on the Nacelle Tail Cone of a Specific Type of Aircraft

The paper aims to study the vibration of a certain type of aircraft naco tailgate, and to develop measures to eliminate the crack of the naco tailgate without subverting the structure. The vibration condition of the nacellum stern cover was tested to analyze the cause of crack formation of the nacellum stern cover. The suitable damping material and treatment method were selected according to the principle of damping technology, and the improvement effect was verified by vibration test. After the adoption of damping vibration absorbing technology, the vibration level was reduced by about 83% to the maximum; the number of peak values was significantly reduced. It had an effective inhibitory effect on the vibration more than 150Hz and 0.8 g, which was prone to generate skin cracks, and could effectively improve the service life of skin structure. The method of damping layer is adopted to reduce the vibration of the cover skin of the nacellum.