Analysis of a Helicopter Blade Fatigue Fracture by Digital Fractographic Imaging Analysis

R. Mcswain, R. Gould
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Abstract

A helicopter was hovering approximately 10 ft above a ship when one spar section failed explosively. Visual inspection revealed a crack had progressed through one member of a dual spar plate assembly at a fold pin lug hole. The remaining spar plate carried the blade load until the aircraft was landed. The helicopter main rotor blade spar fracture was analyzed by conventional and advanced computerized fractographic techniques. Digital fractographic Imaging Analysis of theoretical and actual fracture surfaces was applied for automatic detection of fatigue striation spacing. The approach offered a means of quantification of fracture features, providing for objective fractography.
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直升机叶片疲劳断裂的数字断口成像分析
一架直升机在一艘船上空大约10英尺处盘旋时,一根桅杆发生爆炸。目视检查显示,裂纹已通过双梁板组件的一个成员在折叠销耳孔进展。在飞机着陆之前,剩下的翼梁板一直承受着叶片的载荷。采用传统断口分析技术和先进的计算机断口分析技术对直升机主旋翼叶片进行了断裂分析。将理论断口和实际断口的数字断口成像分析应用于疲劳条纹间距的自动检测。该方法为断口特征的量化提供了一种手段,为客观断口学提供了依据。
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