發(fā)布時間：2018-01-09 19:21

  本文關(guān)鍵詞：平紋編織復(fù)合材料連接性能分析　出處：《南昌大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 平紋編織復(fù)合材料 單搭接膠接 單釘雙剪擠壓 失效準(zhǔn)則

【摘要】：目前編織復(fù)合材料層合板以其優(yōu)良的性能被廣泛用于航空航天工程設(shè)計(jì)中,而連接接頭的安全可靠問題已成為復(fù)合材料實(shí)際結(jié)構(gòu)設(shè)計(jì)的關(guān)鍵。復(fù)合材料連接主要包括:膠接、機(jī)械連接以及二者的混合連接。本文主要從試驗(yàn)角度出發(fā),針對平紋編織復(fù)合材料層合板膠接中的單搭接接頭性能和機(jī)械連接中的單釘雙剪連接擠壓性能進(jìn)行分析研究。通過試驗(yàn)方法分析了不同膠層厚度對單搭接膠接強(qiáng)度的影響,結(jié)果發(fā)現(xiàn)試件出現(xiàn)多種破壞模式,且在同種破壞形式下,單搭接膠接強(qiáng)度隨著厚度增大而減小。通過觀察發(fā)現(xiàn),試件切割凹槽深度的不同是影響破壞模式的主要因素,數(shù)值模擬也印證了這點(diǎn)。然后在本試驗(yàn)范圍內(nèi),討論了純剪理論在實(shí)際工程應(yīng)用中的誤差�；趩吾旊p剪擠壓試驗(yàn),探究了不同鋪層比例對平紋編織復(fù)合材料單釘雙剪擠壓強(qiáng)度的影響。結(jié)果表明:在本試驗(yàn)范圍內(nèi),試件破壞應(yīng)力隨著0?45鋪層所占比例的增加而非線性提高;單釘雙剪擠壓破壞過程是逐層失效的過程,在試驗(yàn)過程中會出現(xiàn)初始損傷點(diǎn),且隨著0?45鋪層所占比例的增加,破壞的逐層失效特征會越來越不明顯。通過在ABAQUS中對平紋編織復(fù)合材料層合板單釘雙剪擠壓進(jìn)行模擬,基于二維Hashin失效準(zhǔn)則,對單釘雙剪擠壓初始失效層及失效位置進(jìn)行了判定。模擬結(jié)果表明在相同擠壓位移作用下,越靠近層合板內(nèi)部的單層越容易首先發(fā)生破壞且首先發(fā)生失效的位置是孔周0??0處。通過對平紋編織復(fù)合材料層合板單釘雙剪擠壓逐層孔周徑向應(yīng)力分布數(shù)值模擬結(jié)果分析,假設(shè)了孔周逐層失效區(qū)域,并將上限理論應(yīng)用到平紋編織復(fù)合材料單釘雙剪連接強(qiáng)度計(jì)算中去,基于二維Hashin失效準(zhǔn)則,探究了一種能有效預(yù)測本文所用平紋編織復(fù)合材料層合板的單釘雙剪擠壓強(qiáng)度的方法。
[Abstract]:At present, braided composite laminates are widely used in aerospace engineering design for their excellent properties. The safety and reliability of the connection joint has become the key to the practical structural design of composite materials. The composite joints mainly include: bonding, mechanical connection and the hybrid connection. This paper mainly from the point of view of the test. The properties of single lap joint in plain braided composite laminate bonding and extrusion performance of single nail double shear joint in mechanical connection were studied. The strength of single lap joint with different thickness of adhesive layer was analyzed by experimental method. The effect of degree. The results show that there are many failure modes in the specimen, and under the same failure mode, the strength of single lap bonding decreases with the increase of thickness. The cutting depth of the specimen is the main factor that affects the failure mode, and the numerical simulation also confirms this point. Then in the scope of this test. The error of pure shear theory in practical engineering application is discussed. The effects of different layering ratios on the extrusion strength of plain braided composites with single nail and double shear are investigated. The results show that the failure stress of the specimens increases with 0? The failure process of single nail and double shear extrusion is the process of failure layer by layer, and the initial damage point will appear in the process of test, and with 0? With the increase of the proportion of 45 layers, the failure characteristics of failure layer by layer will be less and less obvious. The single nail double shear extrusion of plain braided composite laminates is simulated in ABAQUS. Based on the two dimensional Hashin failure criterion, the initial failure layer and the failure position of single nail and double shear extrusion are determined. The simulation results show that under the same extrusion displacement. The closer the laminated plate is to the inner layer, the easier it is for the first failure to occur and the first failure is at the hole circumference 0? ? Through the numerical simulation results of radial stress distribution around holes in plain braided composite laminates with single nail and double shear extrusion, the failure zone of each layer of holes is assumed. The upper bound theory is applied to the strength calculation of single nail and double shear joint of plain braided composites based on two-dimensional Hashin failure criterion. An effective method for predicting the extrusion strength of flat braided composite laminates with single nail and double shear is studied.
【學(xué)位授予單位】：南昌大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB33

【參考文獻(xiàn)】

相關(guān)碩士學(xué)位論文 前1條

1 顧亦磊;復(fù)合材料機(jī)械連接強(qiáng)度分析及影響因素研究[D];西北工業(yè)大學(xué);2006年

，

本文編號：1402327