直升机复合材料尾桨叶疲劳试验研究  

The Fatigue Testing Investigation of HelicopterComposite Tail Rotor Blade

作　　者：康浩[1] 梅卫胜[1] 

机构地区：[1]南京航空航天大学飞行器系

出　　处：《南京航空航天大学学报》1994年第1期54-58,共5页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：本文采用单点疲劳试验加载方法实现直升机复合材料尾桨叶疲劳试验挥舞、摆振、扭转方向的交变载荷协调加载，与以往多点、多向桨叶疲劳试验加载方法相比，试验设备简单，调试方便，可以达到较高的精度。复合材料桨叶在生产过程中常常在其内部带有气泡等缺陷，使得桨叶生产报废率偏高。本文主要研究这些缺陷对复合材料桨叶疲劳寿命的影响。疲劳试验结果表明，存在一定气泡缺陷的复合材料桨叶仍能满足规定的疲劳寿命。By using a method of coordinated blade displacement with loading applied at only one point, the flap, lag and torsion motions alternatively for fatigue tests on the composite tail rotor are carried out in this paper. This method only needs simpler test facilities and easier adjustment test with fair precision.This paper also presents the fatigue testing of helicopter composite tail rotor blade.This fatigue testing is to substantiate the fatigue life of tail rotor blades with leading edge voids during moulding.The fatigue life of these composite blades with leading edge voids is verified to meet the life requirement of the present standard.

关 键 词：直升机 疲劳试验 复合材料 尾桨叶 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]