本文關鍵詞： 復合材料層合板 界面 復模量 有限元 振動響應 Newmark-β迭代法　出處：《南京航空航天大學》2015年碩士論文　論文類型：學位論文

【摘要】：隨著航空發(fā)動機性能不斷提高,越來越多的依賴于強度高、剛度大、質量輕,并具有抗疲勞、壽命長和耐高溫的先進復合材料,近年來,在交通、建筑、醫(yī)學和體育等領域也得到廣泛的應用。本文對復合材料層合板做了以下三個方面的研究:一、建立了復合材料層合板等效振動參數(shù)(損耗因子和彈性模量)預測模型,并與文獻中的其他數(shù)值方法以及實驗結果進行了比較,吻合較好,驗證了模型的有效性;在此基礎上,分析了纖維體積分數(shù)、界面體積分數(shù)、界面材料參數(shù)以及橋聯(lián)參數(shù)對復合材料層合板等效振動參數(shù)的影響。二、利用Hencky板/殼理論建立了復合材料層合板的動力學有限元模型,并與其他文獻中的數(shù)值解和實驗值做了對比,驗證了有限元模型的有效性;在此基礎上,通過模態(tài)實驗,進一步驗證了層合板等效振動參數(shù)預測模型的有效性;采用有限元法研究了層合板長寬比對固有頻率和振型計算結果的影響情況。三、應用Newmark-β迭代法和波前法求解了動力微分方程;研究了在簡諧激勵和脈沖激勵下,鋪層順序、鋪層角度以及鋪層層數(shù)對復合材料層合板振動響應、一階固有頻率和一階比阻尼容量的影響;應用遺傳算法對給定層數(shù)的復合材料層合板進行了振動參數(shù)優(yōu)化,使其在固支條件下一階共振響應幅值最小。本文的研究成果對復合材料層合板的等效振動參數(shù)的預測具有一定的參考價值;通過建立動力學有限元模型可以方便的求出任意鋪層角度、任意層數(shù)的阻尼矩陣;將Newmark-β迭代法和波前法相結合,可以更方便快捷的求解復合材料層合板在不同條件下的振動響應,具有比較重要的工程意義。
[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.
【學位授予單位】：南京航空航天大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：TB332

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