直升机尾部结构疲劳及缺陷容限试验装置研制及应用

目的 获得尾部结构的疲劳寿命和检查周期，满足民用直升机适航验证要求，保证飞机的飞行安全，开展复合材料尾部结构疲劳及缺陷容限试验技术研究。方法 介绍了尾部结构疲劳及缺陷容限试验专用试验台、气动冲击设备、柔性自动特征扫描成像无损检测系统等的设计及研制，采用研制的成套试验装置，实现尾部结构试验件连接约束和载荷边界的全面真实模拟、复杂载荷谱的精确控制、冲击损伤缺陷预制及缺陷自动识别与检测。结果 经试验验证，载荷误差小于2%，冲击能量误差小于2%，缺陷检测误差小于1 mm，各项指标都满足项目研究目标和技术指标要求。结论 研究成果在民用直升机研制中得到了成功应用，可为后续其他直升机尾部结构疲劳及缺陷容限疲劳试验提供良好的借鉴，具有重要的工程应用价值。

Development and Application of Fatigue and Flaw Tolerance Test Device on Helicopter Tail Structure

The work aims to study the fatigue and flaw tolerance test technology of composite tail structure, in order to obtain the fatigue life and check interval of tail structure, meet the airworthiness verification requirements of civil helicopters and ensure the flight safety of helicopters. The design and development of the specialized test bench, pneumatic impact equipment, flexible automatic scanning and imaging nondestructive testing system for the fatigue and flaw tolerance test of tail structure were described. With the whole set of test devices, the connecting restriction and load boundary of the tail structure specimen were simulated fully, the complex load spectrum was controlled accurately, the impact flaws were prefabricated and the flaws were detected automatically. The experimental results indicated that the load error was less than 2%, the impact energy error was less than 2% and the error of flaw detection was less than 1 mm. All indicators satisfied the research objectives and technical indicators of the project. The research results have been successfully applied in the development of civil helicopters, which can provide a good reference for other helicopter tail structure fatigue and flaw tolerance tests, and has important engineering application value.