飞行器钛合金紧固孔结构件耐久性研究

Durability of Fastener Hole Structure Parts of Titanium Alloy for Modern Aircrafts

摘要:

对TC4钛合金紧固孔结构件进行了实验和理论研究。在结构细节原始疲劳质量模型基础上，通过使用载荷谱下结构细节的裂纹扩展方程确定出给定时间下对应的裂纹尺寸分布情况，通过选择合适的参考裂纹尺寸，给出了紧固孔结构细节出现5%裂纹时的寿命，并建议为飞行器结构的经济寿命，从而为飞行器结构的经济修理提供指导和依据

Abstract:

The TC4 alloy fastener hole structure parts were researched experimentally and theoretically. Based on the mathematical model of structure detail initial fatigue quality, the corresponding crack size distribution in certain time was determined by the crack growth equation of structure detail under loading spectra. By selecting appropriate referred crack size, the life of fastener hole structure detail in which 5% crack happened was provided and the resulted life was suggested as the economical life of aircraft structure. All the work is helpful to the economic repair of the modern aircraft structure