直升机尾梁内蒙皮裂纹修理方案研究

Study on repairing of crack of helicopter tailboom inner skin

尾梁是直升机的主要结构件。建立直升机尾段结构总体/局部有限元模型,根据有限元分析结果确认其内蒙皮天线开孔位置有较高的应力水平,且裂纹是在疲劳载荷作用下产生并扩展的。对分别采用薄铝板和玻璃布对尾梁内蒙皮天线开孔位置裂纹进行修理的两种修理方案进行评估,发现修理后应力水平相对原结构分别降低了72%和81%。结合修理工艺参数,最终选择采用玻璃布对多架次某型直升机尾梁内蒙皮裂纹进行修理,然后进行了超过半年和五百飞行小时的检验,结果内蒙皮裂纹修理位置未出现故障,验证了利用玻璃布修理尾梁夹层结构内蒙皮裂纹的可靠性。

Tailboom is the principal structure of the helicopter,and the helicopter rear structure global/local fi⁃nite element mode is built.Based on the finite element analysis result,it is confirmed that there is a high stress level in the tailboom inner skin antenna opening hole area,the crack is produced and propagated under fatigue load.The crack is repaired by using two methods of thin aluminum sheet and glass fabric.From the result of finite element a⁃nalysis results of different repair schemes,the stress leve decreased 72%and 81%respectively compared with the o⁃riginal structure.Combined with the repair process and parameters,the glass fiber fabric is chosen to repair the crack,it is confirmed by several helicopters over half a year and 500 flight hours,the tailboom inner skin has no more failure.The reliability of repairing tailboom skin crack was verified.