本文關(guān)鍵詞： 復(fù)合材料層合板 界面 復(fù)模量 有限元 振動(dòng)響應(yīng) Newmark-β迭代法　出處：《南京航空航天大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：隨著航空發(fā)動(dòng)機(jī)性能不斷提高,越來越多的依賴于強(qiáng)度高、剛度大、質(zhì)量輕,并具有抗疲勞、壽命長(zhǎng)和耐高溫的先進(jìn)復(fù)合材料,近年來,在交通、建筑、醫(yī)學(xué)和體育等領(lǐng)域也得到廣泛的應(yīng)用。本文對(duì)復(fù)合材料層合板做了以下三個(gè)方面的研究:一、建立了復(fù)合材料層合板等效振動(dòng)參數(shù)(損耗因子和彈性模量)預(yù)測(cè)模型,并與文獻(xiàn)中的其他數(shù)值方法以及實(shí)驗(yàn)結(jié)果進(jìn)行了比較,吻合較好,驗(yàn)證了模型的有效性;在此基礎(chǔ)上,分析了纖維體積分?jǐn)?shù)、界面體積分?jǐn)?shù)、界面材料參數(shù)以及橋聯(lián)參數(shù)對(duì)復(fù)合材料層合板等效振動(dòng)參數(shù)的影響。二、利用Hencky板/殼理論建立了復(fù)合材料層合板的動(dòng)力學(xué)有限元模型,并與其他文獻(xiàn)中的數(shù)值解和實(shí)驗(yàn)值做了對(duì)比,驗(yàn)證了有限元模型的有效性;在此基礎(chǔ)上,通過模態(tài)實(shí)驗(yàn),進(jìn)一步驗(yàn)證了層合板等效振動(dòng)參數(shù)預(yù)測(cè)模型的有效性;采用有限元法研究了層合板長(zhǎng)寬比對(duì)固有頻率和振型計(jì)算結(jié)果的影響情況。三、應(yīng)用Newmark-β迭代法和波前法求解了動(dòng)力微分方程;研究了在簡(jiǎn)諧激勵(lì)和脈沖激勵(lì)下,鋪層順序、鋪層角度以及鋪層層數(shù)對(duì)復(fù)合材料層合板振動(dòng)響應(yīng)、一階固有頻率和一階比阻尼容量的影響;應(yīng)用遺傳算法對(duì)給定層數(shù)的復(fù)合材料層合板進(jìn)行了振動(dòng)參數(shù)優(yōu)化,使其在固支條件下一階共振響應(yīng)幅值最小。本文的研究成果對(duì)復(fù)合材料層合板的等效振動(dòng)參數(shù)的預(yù)測(cè)具有一定的參考價(jià)值;通過建立動(dòng)力學(xué)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(jié)合,可以更方便快捷的求解復(fù)合材料層合板在不同條件下的振動(dòng)響應(yīng),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(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：TB332

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