【作者】 王飞； 程小全； 汪源龙； 王军；

【Author】 Wang Fei,Cheng Xiaoquan,Wang Yuanlong,Wang Jun (School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191)

【机构】 北京航空航天大学航空科学与工程学院；

【摘要】 选取直升机复合材料桨叶的一段进行了纤维断裂和分层损伤后的振动特性理论分析,与无损伤和含相应大小穿孔损伤的翼段比较,得到了振动特性与损伤的形式和位置的关系。结果表明,各种损伤都没有改变翼段的振动模态;与含穿孔损伤不同的是含纤维断裂损伤的翼段各阶振动频率有不同程度降低,而没有升高的情况;翼段振动频率随纤维断裂展向位置的变化曲线与含穿孔损伤的有相似之处,在原来弯矩或扭矩大的地方含有纤维断裂损伤弯曲或扭转振动频率降低较多;含分层损伤翼段振动频率几乎没有改变。该研究结果对直升机复合材料桨叶结构损伤容限分析与设计具有一定的参考价值。更多还原

【Abstract】 Vibration performance theoretical analysis was carried out for a segment of composite helicopter rotor blade with fiber rupture and delamination damage in it. Comparing with the blade segment without damage and the blade segment with perforation of the same size,the effect of the damage type and location on vibration performance was obtained. The results indicate that the damage do not change the mode of blade segment,and vibration frequency of blade segment with fiber rupture decreases without any increase which is different with perforation damage. Frequency curve with change of the fiber rupture damage position along the wingspan is similar as the perforation damage. The bending or torsion vibration frequency decreases more when the fiber rupture is where bending moment or torsion is big. The vibration frequency of blade segment with delamination damage does not change. The studies and their results are of value for the damage tolerance analysis and design of the helicopter composite rotor blades.更多还原