直升机主桨毂复合材料星形件疲劳研究

直11型机主桨毂星形件是典型的复合材料层合板结构,在复杂的疲劳载荷环境下,有可能出现几种不同形式破坏模式,如:分层破坏和纤维断裂,忽略任何一种可能出现的破坏模式都将可能给飞行带来安全隐患。理想的试验是有限的试验件能得到所有的破坏模式的结果。本文较完整地总结和介绍了直11型机和“海豚”的复合材料星形件疲劳试验及试验结果,较详细地分析了各种破坏模式的形成机理和挥摆载荷比对破坏模式出现率的影响,认为疲劳试验载荷的挥摆载荷比不应仅仅根据实际飞行时载荷状况,主要应根据星形件结构性能来确定。

THE FATIGUE RESEARCH FOR THE COMPOSITE STAR OF HELICOPTER MAIN HUB

The star of Z- 11 helicopter main hub is a typical composite material laminated structure. Under the complicate fatigue loads.it is probable to occur different failure models,such as the delamination and the fiber crack.To ignore any one of these failure models would bring about the hidden trouble for the safe flight of helicopter.It is perfect that the test can be able to appear all failure models and get all test data with finite several samples. This paper integrally summarizes the fatigue test and the test result of composite star of Z- 11 and "Dolphin" helicopter, analyzes in detail the forming mechanism of all failure models and the effect of the ratio of flap load to lag load on the occurence probability of each failure model. And in this paper it is reckoned that this ratio in the fatigue test should depend on the structure character of the star rather the than real load in flight.