本文選題：二維三軸編織混雜層合復合材料 + 低速沖擊　； 參考：《東華大學》2015年碩士論文

【摘要】：隨著復合材料在航空航天等領域的的應用加大，克服單種纖維增強復合材料在沖擊性能方面的局限性需求增加，因此混雜復合材料具有廣闊的發(fā)展前景。目前關于編織混雜層合復合材料低速沖擊及沖擊后力學性能的研究較少，主要側(cè)重于單層編織復合材料以及單向板層合復合材料的力學性能研究，因此本課題主要對二維三軸編織混雜層合復合材料的沖擊性能和沖擊后彎曲性能進行實驗研究和理論分析，以期能為編織混雜層合復合材料的抗沖擊應用設計提供參考。 本文以兩大類共七種結構類型試樣為研究對象，第一類結構類型包含四種層合結構，分別為：3層碳纖編織片層合制得；上下兩層為碳纖編織片、中間層為玻纖編織片層合制得；上下兩層為玻纖編織片、中間層為碳纖編織片層合制得；3層玻纖編織片層合制得。第二類結構類型包含三種層合結構，分別為：3層均由碳纖為編織紗、玻纖為軸紗的編織片層合制得；3層均由玻纖為編織紗、碳纖為軸紗的編織片層合制得；3層均由編織紗和軸紗是碳纖和玻纖一隔一混雜排列的編織片層合制得。 本課題采用落錘沖擊實驗和三點彎曲實驗進行力學性能綜合測試，利用數(shù)碼相機觀察表面損傷分布、體式顯微鏡觀察橫截面和縱截面的斷面損傷特征。通過沖擊實驗所得損傷規(guī)律和數(shù)據(jù)對比初步判斷材料的抗沖擊性能，由不經(jīng)過沖擊的純彎曲實驗推出試樣的彎曲性能，進而與沖擊后的彎曲性能進行對比，分析得出剩余彎曲性能較好的復合材料試樣，從而得出具有較優(yōu)抗沖擊性能的復合材料試樣。 上下兩層為碳纖編織片、中間層為玻纖編織片制得的層合復合材料與3層均為碳纖編織片制得的層合復合材料相比，前者的沖擊表面裂紋較少、沖擊中心處橫截面裂紋較少，而單位厚度吸收能量比后者高7.61%、最大彎曲載荷值比后者高16.46%、彎曲強度高19.52%、沖擊后彎曲強度損失率低40.60%，因此可得出3層編織層合復合材料的外層為剛性材料編織片、中間層為韌性材料編織片時，可有效提高混雜材料的抗沖擊性能。 上下兩層為玻纖編織片、中間層為碳纖編織片制得的層合復合材料與3層均為玻纖編織片制得的層合復合材料相比，前者的沖擊表面裂紋較少、沖擊中心處橫截面裂紋較少，而單位厚度吸收能量比后者高2.21%，最大彎曲載荷值比后者高2.12%、彎曲強度高11.46%、但是沖擊后彎曲強度損失率僅高5.30%，因此可得出外層為韌性材料編織片、中間層為剛性材料編織片時，可在較小程度提高混雜材料的抗沖擊性能。 3層均由碳纖為編織紗、玻纖為軸紗的編織片層合制得的混雜復合材料，與3層均由玻纖為編織紗、碳纖為軸紗的編織片層合制得混雜復合材料相比，前者的沖擊正面裂紋較多、沖擊背面裂紋較少、沖擊中心處橫截面裂紋較多，單位厚度吸收能量比后者高25.80%，最大彎曲載荷值比后者高18.64%、彎曲強度高15.25%、但是沖擊后彎曲強度損失率高98.83%；而3層均由編織紗和軸紗是碳纖和玻纖一隔一混雜排列的編織片層合制得的混雜復合材料，沖擊表面和沖擊中心處橫截面裂紋損傷范圍較小，但單位厚度吸收能量最大、最大彎曲載荷值最高、彎曲強度值最低、沖擊后彎曲強度損失率接近最低，由此可知，編織片為韌性材料和剛性材料混雜編織制得時，，抗沖擊性能會下降，但編織紗為韌性材料、軸紗為剛性材料的整體性能較好。 3層編織層合復合材料的外層為剛性材料編織片、中間層為韌性材料編織片時，可有效提高材料的抗沖擊性能；外層為韌性材料編織片、中間層為剛性材料編織片時，可在較小程度提高材料的抗沖擊性能；而編織片為韌性材料和剛性材料混雜編織制得時，抗沖擊性能會下降，而編織紗為韌性材料、軸紗為剛性材料時整體性能較好。
[Abstract]:With the increasing application of composites in aerospace and other fields, the limited demand for impact properties of single fiber reinforced composites is increased. Therefore, hybrid composites have broad prospects for development. At present, there are few studies on the mechanical properties of braided hybrid composites at low velocity impact and impact. The mechanical properties of single layer braided composites and unidirectional laminates are studied. Therefore, the research and theoretical analysis of the impact and post impact bending properties of the two dimensional three axis braided hybrid composites are conducted in order to provide a reference for the impact application design of the woven hybrid laminated composites. Exam.
In this paper, two types of seven kinds of structural types are taken as the research object. The first type of structure type contains four layers of laminated structure, which are composed of 3 layers of carbon fiber braided sheets, the upper and lower two layers are carbon fiber braided pieces, the middle layer is made of glass fiber braided laminates, the upper and lower two layers are glass fiber braided pieces, and the middle layer is made of carbon fiber braided sheets. The 3 layers of glass fiber braid are made up. The second types of structural types include three kinds of laminated structures, respectively: the 3 layers are made of carbon fiber woven yarn and glass fiber for axial yarn. The 3 layers are made of glass fiber as braided yarn and carbon fiber as shaft yarn, and the 3 layers are all arranged in a mixed arrangement of woven and glass fiber. The weave sheet is laminated.
This subject uses the drop hammer impact test and the three point bending test to carry out the comprehensive test of the mechanical properties. The damage characteristics of the cross section and the longitudinal section are observed by the digital camera. The damage characteristics of the cross section and the longitudinal section are observed by the body microscope. The impact resistance of the material is preliminarily judged by the damage law and the data comparison obtained by the impact test, and the impact is not impacted by the impact test. The bending properties of the specimen are introduced by the pure bending test, and then compared with the bending properties after the impact, the composite materials with better residual bending properties are analyzed and the composite materials with better impact resistance are obtained.
The upper and lower two layers are carbon fiber braided pieces, and the interlaminating composite material made by glass fiber braided interlayer and the 3 layer are both carbon fiber woven laminated composites. The former has less impact surface crack and less crack in the cross section of the impact center, while the unit thickness absorption energy is 7.61% higher than the latter, and the maximum bending load is 16. higher than the latter. 46%, the bending strength is 19.52%, and the loss rate of bending strength is low after impact of 40.60%. Therefore, it can be concluded that the outer layer of the 3 layer woven laminated composites is a rigid material braided piece, and the middle layer is made of ductile material, which can effectively improve the impact resistance of the hybrid material.
The upper and lower two layers are glass fiber braided pieces, and the interlaminating composite material made in the middle layer is made by carbon fiber braided pieces and the 3 layers are all laminated composites made of glass fiber braided sheets. The former has less impact surface cracks and fewer cracks in the cross section of the impact center, while the absorption energy per unit thickness is 2.21% higher than that of the latter, and the maximum bending load is 2.1 higher than the latter. 2%, the bending strength is 11.46%, but the loss rate of the bending strength is only 5.30% high after the impact. Therefore, it can be found that the outer layer is a ductile material braiding piece and the middle layer is a rigid material. The impact resistance of the hybrid material can be improved to a lesser extent.
The 3 layer is a hybrid composite made of braided yarn and glass fiber as a weave yarn. Compared with the 3 layers, which are woven with glass fiber as braided yarn and the carbon fiber as the axial yarn, there are more cracks in the front face, less cracks on the back of the impact, more cracks in the cross section at the impact center and the suction unit thickness. The maximum bending load is 25.80% higher than the latter, the maximum bending load is 18.64% higher than the latter, and the flexural strength is 15.25%, but the loss rate of the bending strength is 98.83% after the impact. The 3 layer is a hybrid composite of braided yarn and shaft yarn arranged in a mixed arrangement of carbon fiber and glass fiber, and the cross section crack at the impact surface and the impact center. The damage range is small, but the unit thickness absorbs the maximum energy, the maximum bending load is the highest, the bending strength is the lowest, and the loss rate of bending strength is close to the lowest. Therefore, when the braided piece is made of ductile material and rigid material, the impact resistance will fall down, but the woven yarn is ductile and the axle yarn is rigid. The overall performance is good.
The outer layer of the 3 layer woven laminated composite material is a rigid material braiding piece and the middle layer is made of ductile material. It can effectively improve the impact resistance of the material. The outer layer is a ductile material braided piece and the middle layer is a rigid material. The impact resistance of the material can be improved in a small degree, while the braided sheet is a ductile material and a rigid material. When the material is mixed and woven, the impact resistance will decrease, while the braided yarns are tough materials, and the overall performance is better when the yarns are rigid materials.

【學位授予單位】：東華大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：TB332

【參考文獻】

相關期刊論文 前10條

1 劉德博;關志東;陳建華;黎增山;;復合材料低速沖擊損傷分析方法[J];北京航空航天大學學報;2012年03期

2 王亮亮,孫志杰,張大興,張佐光;混雜纖維絲束沖擊拉伸性能實驗研究[J];玻璃鋼/復合材料;2004年03期

3 鄧宗才;李建輝;;混雜FRP復合材料混雜效應的研究與進展[J];玻璃鋼/復合材料;2008年01期

4 李家駒,李延紅,曾漢民;論復合材料彎曲實驗[J];玻璃鋼/復合材料;1996年04期

5 陳利,梁子青,馬振杰,劉景艷,李嘉祿;三維五向編織復合材料縱向性能的實驗研究[J];材料工程;2005年08期

6 徐穎;溫衛(wèi)東;崔海坡;;復合材料層合板低速沖擊逐漸累積損傷預測方法[J];材料科學與工程學報;2006年01期

7 張彥;朱平;來新民;梁新華;;低速沖擊作用下碳纖維復合材料鋪層板的損傷分析[J];復合材料學報;2006年02期

8 張超;許希武;郭樹祥;;二維二軸1×1編織復合材料細觀結構模型及力學性能有限元分析[J];復合材料學報;2011年06期

9 楊靈敏;焦亞男;高華斌;;三維編織復合材料低速沖擊試驗與分析[J];紡織學報;2009年05期

10 張平;桂良進;范子杰;;三向編織復合材料彈性性能研究[J];工程力學;2009年01期

本文編號：1803045