Modeling Multi-Layer Matrix Cracking in Thin Walled Composite Rotor Blades
Modeling Multi-Layer Matrix Cracking in Thin Walled Composite Rotor Blades
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DOI：
10.4050/1.3092872
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发表时间：
2005-10
影响因子：
1.5
通讯作者：
P. Pawar;R. Ganguli
中科院分区：
文献类型：
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作者：
P. Pawar;R. Ganguli
直升机旋翼桨叶由纤维增强复合材料制成，容易出现基体开裂。基体开裂先于更严重的损坏机制，例如分层和纤维断裂，因此是结构健康状况的有用指标。在本研究中，研究了基体裂纹对复合材料叶片刚度和挠度的影响。考虑采用具有矩形盒和具有 [0/+/-45/90] 层压板系列的两单元翼型截面的刚性平面内转子叶片。观察到刚度在基体开裂初期迅速下降，然后趋于饱和。对单层、两层和完整叶片组中基体开裂的复合材料转子叶片行为的研究表明，在基体开裂饱和点处，弯曲刚度损失为 6-12%，扭转刚度损失为 25-30%，并且开始出现更严重的损坏形式，例如脱粘/分层和纤维断裂。
Helicopter rotor blades are made of fiber-reinforced composite materials that are prone to matrix cracking. Matrix cracking precedes more serious damage mechanisms such as delamination and fiber breakage and is therefore a useful indicator of structural health. In the present study, the effect of matrix cracking on composite blade stiffness and deflections is investigated. A stiff inplane rotor blade with a rectangular box and two-cell airfoil section with [0/ +/-45/90], family of laminates is considered. It is observed that the stiffness decreases rapidly in initial phase of matrix cracking and then becomes saturated. Study of the behavior of composite rotor blade from matrix cracking in single, two and complete lamina group show a bending stiffness loss of 6-12 percent and a torsion stiffness loss of 25-30 percent at the point where matrix cracking saturates, and more severe forms of damage such as debonding/delamination and fiber breakage begin.