【摘要】：碳纖維增韌環(huán)氧樹脂基復(fù)合材料具有輕質(zhì)、高強(qiáng)、可設(shè)計(jì)性優(yōu)良的特點(diǎn),因此一直備受各界研究者們的青睞。近年來,漸進(jìn)損傷分析方法(CDM)被廣泛地應(yīng)用于航空航天復(fù)合材料結(jié)構(gòu)。然而,層合板的漸進(jìn)損傷和連續(xù)剛度退化通常表現(xiàn)出高度的非線性。如何理解能量耗散后的損傷演化機(jī)理至關(guān)重要。復(fù)合材料層合板在低速?zèng)_擊載荷下的失效破壞機(jī)理尤為復(fù)雜,通常伴隨著應(yīng)變局部化現(xiàn)象的產(chǎn)生。本文旨在針對(duì)復(fù)合材料層合板的面內(nèi)損傷,引入由Ba?ant等人發(fā)展起來的非局部積分理論,通過在漸進(jìn)失效模型中嵌入VUMAT子程序來解決低速?zèng)_擊載荷下復(fù)合材料的局部化問題。仿真結(jié)果表明,非局部漸進(jìn)失效模型能夠很好地模擬復(fù)合材料試樣在不同載荷條件下的失效演化和動(dòng)力學(xué)響應(yīng),有效地改善了復(fù)合材料分析模型的網(wǎng)格敏感性問題。為進(jìn)一步驗(yàn)證非局部漸進(jìn)失效沖擊模型的有效性,通過試驗(yàn)與有限元仿真相結(jié)合的方法,圍繞民機(jī)復(fù)合材料結(jié)構(gòu)沖擊后剩余壓縮、剩余剪切強(qiáng)度問題展開了研究。首先,針對(duì)T700/QY8911和T700/3234復(fù)合材料層合板的在低速?zèng)_擊下的損傷演化及沖擊響應(yīng)進(jìn)行非局部有限元模擬,將改進(jìn)的Hashin準(zhǔn)則、雙線性及指數(shù)型損傷演化規(guī)律引入子程序中,驗(yàn)證了非局部算法在解決沖擊損傷模擬問題中的準(zhǔn)確性。然后,通過ABAQUS重啟動(dòng)分析,將沖擊損傷以預(yù)定義場(形式賦予復(fù)合材料無損結(jié)構(gòu),分別完成了低速?zèng)_擊-壓縮/剪切模擬的全過程,仿真結(jié)果與試驗(yàn)吻合良好,大大提高了剩余強(qiáng)度模型的分析精度。最后,研究了引入沖擊損傷后的復(fù)合材料梁腹板結(jié)構(gòu)在剪切載荷下的失效機(jī)理和承載特性,發(fā)現(xiàn)在子層屈曲和纖維斷裂的共同作用下,試驗(yàn)件最終失去承載能力,發(fā)生沿45?方向的失效破壞。結(jié)合非局部漸進(jìn)失效模擬,完成了對(duì)復(fù)合材料梁腹板結(jié)構(gòu)損傷容限的初步評(píng)估。
[Abstract]:Carbon fiber toughened epoxy matrix composites have been favored by researchers for their advantages of light weight, high strength and good designability. In recent years, the progressive damage analysis method (CDM) has been widely used in aerospace composite structures. However, progressive damage and continuous stiffness degradation of laminated plates usually show high nonlinearity. How to understand the mechanism of damage evolution after energy dissipation is very important. The failure mechanism of composite laminated plates under low speed impact loads is particularly complicated and usually accompanied by strain localization. Aiming at the in-plane damage of composite laminates, the nonlocal integral theory developed by Ba?ant et al is introduced to solve the localization problem of composites under low speed impact by embedding VUMAT subroutine in the progressive failure model. The simulation results show that the nonlocal progressive failure model can well simulate the failure evolution and dynamic response of composite specimens under different loading conditions and effectively improve the mesh sensitivity of composite analysis model. In order to further verify the effectiveness of the non-local progressive failure impact model, the residual compression and residual shear strength of civil aircraft composite structures after impact were studied by means of the combination of test and finite element simulation. Firstly, the damage evolution and impact response of T700/QY8911 and T700 / 3234 composite laminates under low speed impact are simulated by non-local finite element method. The improved Hashin criterion, bilinear and exponential damage evolution rules are introduced into the subroutine. The accuracy of the nonlocal algorithm in solving the impact damage simulation problem is verified. Then, through the ABAQUS restarting analysis, the impact damage is predefined in the form of the composite structure, and the whole process of the low-speed impact-compression / shear simulation is completed, respectively. The simulation results are in good agreement with the test results. The precision of residual strength model is greatly improved. Finally, the failure mechanism and load-bearing characteristics of composite beam web structure with impact damage under shear load are studied. It is found that under the joint action of sub-layer buckling and fiber fracture, the ultimate bearing capacity of the specimen is lost and the bearing capacity is 45? Directional failure. Combined with nonlocal progressive failure simulation, the damage tolerance of composite beam web structure was evaluated.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TB33

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 曲勰;黃茂松;呂璽琳;;基于非局部Mohr-Coulomb模型的土體漸進(jìn)破壞分析[J];巖土工程學(xué)報(bào);2013年03期

2 歐建華;韓強(qiáng);;懸臂碳納米管純彎問題的非局部彈性解[J];科學(xué)技術(shù)與工程;2011年24期

3 程小全;王飛;胡仁偉;江善元;;含穿孔損傷復(fù)合材料槳葉結(jié)構(gòu)的振動(dòng)特性[J];復(fù)合材料學(xué)報(bào);2010年02期

4 益小蘇;張明;安學(xué)鋒;劉立朋;;先進(jìn)航空樹脂基復(fù)合材料研究與應(yīng)用進(jìn)展[J];工程塑料應(yīng)用;2009年10期

5 付麗;杜星文;;基于非局部理論的一維損傷模型的有限元算法[J];航空學(xué)報(bào);2009年05期

6 易大可;王自強(qiáng);;能量非局部模型和新的應(yīng)變梯度理論[J];力學(xué)學(xué)報(bào);2009年01期

7 林智育;許希武;;復(fù)合材料層板低速?zèng)_擊后剩余壓縮強(qiáng)度[J];復(fù)合材料學(xué)報(bào);2008年01期

8 崔海坡;溫衛(wèi)東;崔海濤;;復(fù)合材料層合板沖擊損傷及剩余強(qiáng)度分析方法[J];固體力學(xué)學(xué)報(bào);2006年03期

9 沈新普,沈國曉,陳立新,楊璐;梯度增強(qiáng)的彈塑性損傷非局部本構(gòu)模型研究[J];應(yīng)用數(shù)學(xué)和力學(xué);2005年02期

10 黃再興;關(guān)于非局部場論的幾個(gè)新觀點(diǎn)及其在斷裂力學(xué)中的應(yīng)用(Ⅲ)——重論線性非局部彈性理論[J];應(yīng)用數(shù)學(xué)和力學(xué);1999年11期

相關(guān)博士學(xué)位論文 前3條

1 何艷斌;航空復(fù)合材料典型結(jié)構(gòu)低能量沖擊損傷及動(dòng)力響應(yīng)研究[D];華南理工大學(xué);2016年

2 趙士洋;復(fù)合材料層合板損傷模型的建構(gòu)方法及其應(yīng)用[D];西北工業(yè)大學(xué);2014年

3 朱煒W，

本文編號(hào)：2262093