某型直升机尾桨断裂故障分析  

Fracture fault analysis of tail rotor on a helicopter

作　　者：侯波 徐冠峰 闫慧娟 楚晓阳 HOU Bo;XU Guanfeng;YAN Huijuan;CHU Xiaoyang(Army Aviation Research Institute,Army Aviation Academy,Beijing 101121,China)

机构地区：[1]陆军航空兵学院陆军航空兵研究所,北京101121

出　　处：《航空工程进展》2023年第5期144-151,共8页Advances in Aeronautical Science and Engineering

摘　　要：明确某型直升机尾桨断裂故障原因,对于该型机的使用、维护有现实意义,对于新机型的安全性提升有借鉴意义。首先通过故障树分析法对某型直升机尾桨叶断裂故障进行分析,得到底事件分析结果;然后开展宏、微观断口分析;最后对柔性梁断口损伤演化开展仿真分析。结果表明:桨叶断裂性质为低应力高周双向弯曲疲劳断裂,当柔性梁纤维压缩方向强度性能值小于700 MPa时,断口的形式与故障尾桨柔性梁断口类型相似;大载荷状态尾桨会产生较大的振动,振动的增加加剧了尾桨的载荷,导致尾桨柔性梁根部载荷增加,超出柔性梁设计承载能力,桨叶柔性梁根部疲劳断裂。Finding out the reason of the fracture fault of tail rotor on a helicopter is of practical significance for using and maintaining the helicopter and is of significant reference for improving safety of new type helicopter.The frac⁃ture fault of tail rotor blade on a helicopter is analyzed by fault tree analysis method,and the bottom event analysis results are obtained.Then,the macro and micro fractographic analysis of the tail rotor blade is carried out.Finally,the simulation analysis of the fractographic damage evolution of flexible beam is performed.The results show that the fracture property of the blade is low-stress and high-cycle bidirectional bending fatigue fracture.When the strength value of the fiber compression direction of the flexible beam is less than 700 MPa,the fractographic type is similar to that of the faulty tail rotor flexible beam.The tail rotor will produce large vibration under large fatigue load condition,and the increase of vibration can intensify the load of the tail rotor,which leads to the increase of load at the root of the flexible beam and exceeds the designed bearing capacity of the flexible beam,then fatigue fracture will occur at the root of the flexible beam of the blade.

关 键 词：尾桨 断裂 疲劳裂纹 失效分析 直升机 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]