某大型民用直升机尾段缺陷容限仿真及试验验证技术

Simulation and Test Verification Technology for Flaw Tolerance of Large Civil Helicopter Tail Section

按适航CCAR 29.571条款对民用直升机结构的缺陷容限验证要求,建立了直升机复合材料尾段结构精细化建模以及内部缺陷和冲击损伤缺陷的仿真分析方法,并完成了带制造缺陷、冲击损伤缺陷的复合材料尾段结构全尺寸缺陷容限试验验证。试验结果与仿真分析结果非常吻合,结果表明,某大型民用直升机复合材料尾段结构在安全寿命期限内,预置的初始缺陷和冲击损伤位置的缺陷不会扩展,试验结果得到适航当局的认可。

According to the requirements of airworthiness CCAR 29.571 for the verification of the flaw tolerance of civil helicopter structure,the refined analysis of the structure of the tail section of helicopter composites and the simulation analysis method of internal flaws and impact damage flaws are established,and the manufacturing flaws are completed.Verification of full-scale flaw tolerance test of composite tail section structure with impact damage defects.The test results are in good agreement with the simulation results.The results show that the flaws of the initial flaws and impact damage locations of a large civil helicopter composite tail section are not extended during the safety life,and the test results are recognized by the airworthiness authorities.