纤维增强复合材料层合板振动响应分析与优化

发布时间：2018-02-09 11:34

本文关键词： 复合材料层合板界面复模量有限元振动响应 Newmark-β迭代法　出处：《南京航空航天大学》2015年硕士论文　论文类型：学位论文

【摘要】：随着航空发动机性能不断提高,越来越多的依赖于强度高、刚度大、质量轻,并具有抗疲劳、寿命长和耐高温的先进复合材料,近年来,在交通、建筑、医学和体育等领域也得到广泛的应用。本文对复合材料层合板做了以下三个方面的研究:一、建立了复合材料层合板等效振动参数(损耗因子和弹性模量)预测模型,并与文献中的其他数值方法以及实验结果进行了比较,吻合较好,验证了模型的有效性;在此基础上,分析了纤维体积分数、界面体积分数、界面材料参数以及桥联参数对复合材料层合板等效振动参数的影响。二、利用Hencky板/壳理论建立了复合材料层合板的动力学有限元模型,并与其他文献中的数值解和实验值做了对比,验证了有限元模型的有效性;在此基础上,通过模态实验,进一步验证了层合板等效振动参数预测模型的有效性;采用有限元法研究了层合板长宽比对固有频率和振型计算结果的影响情况。三、应用Newmark-β迭代法和波前法求解了动力微分方程;研究了在简谐激励和脉冲激励下,铺层顺序、铺层角度以及铺层层数对复合材料层合板振动响应、一阶固有频率和一阶比阻尼容量的影响;应用遗传算法对给定层数的复合材料层合板进行了振动参数优化,使其在固支条件下一阶共振响应幅值最小。本文的研究成果对复合材料层合板的等效振动参数的预测具有一定的参考价值;通过建立动力学有限元模型可以方便的求出任意铺层角度、任意层数的阻尼矩阵;将Newmark-β迭代法和波前法相结合,可以更方便快捷的求解复合材料层合板在不同条件下的振动响应,具有比较重要的工程意义。
[Abstract]:With the improvement of aero-engine performance, more and more advanced composite materials with high strength, high stiffness, light weight, fatigue resistance, long life and high temperature resistance have been used in recent years. Medical and physical education are also widely used. In this paper, three aspects of composite laminates are studied: first, the prediction model of equivalent vibration parameters (loss factor and elastic modulus) of composite laminates is established. The results are in good agreement with other numerical methods and experimental results, and the validity of the model is verified, and the fiber volume fraction, interface volume fraction and interface volume fraction are analyzed. The influence of interface material parameters and bridge parameters on the equivalent vibration parameters of composite laminated plates. Secondly, the dynamic finite element model of composite laminated plates is established by using Hencky plate / shell theory. The validity of the finite element model is verified by comparison with the numerical solutions and experimental results in other literatures, and the validity of the prediction model of equivalent vibration parameters of laminated plates is further verified by modal experiments. The influence of aspect ratio of laminated plates on the natural frequency and mode shape is studied by finite element method. Thirdly, the Newmark- 尾 iterative method and the wave front method are used to solve the dynamic differential equations, and the stacking sequence under harmonic and pulse excitation is studied. The effects of laying angle and layer number on the vibration response of composite laminated plate, the first order natural frequency and the first order damping capacity are studied, and the vibration parameters of composite laminated plate with given number of layers are optimized by genetic algorithm. The amplitude of the first order resonance response is minimized under the condition of clamping. The research results in this paper have a certain reference value for the prediction of equivalent vibration parameters of composite laminated plates. By establishing the dynamic finite element model, the damping matrix of any layer angle and number of layers can be obtained conveniently, and the Newmark- 尾 iterative method is combined with the wavefront method. It is more convenient to solve the vibration response of composite laminates under different conditions, which is of great engineering significance.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：TB332

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