碳/碳复合材料的热压烧结制备工艺与力学性能
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摘要
为制备力学性能优异、致密度高的航空航天复合材料,本文采用纤维液相浸渍的致密化方法和真空热压炭化工艺,以天然鳞片石墨为碳基体、国产T300型碳纤维为增强体、中间相沥青粉为浸渍剂,通过分别改变沥青与石墨的原料质量配比(P/G)、浸渍温度等工艺参数,制备了一系列高性能碳/碳复合材料。然后,对复合材料的弯曲强度、断裂韧性、显孔率及密度等性能进行测试,再通过扫描电子显微镜对复合材料的微观形貌进行分析。研究结果表明:当P/G为1,浸渍温度为300℃时,碳/碳复合材料表现出较好的综合性能。其中,平均弯曲强度可达360 MPa,断裂韧性为6.02 MPa·m~(1/2),已达国内先进水平。同时实际密度为1.75 g·cm~(-3),显孔率为1.7%,致密度可达94.6%。
In order to obtain aerospace composite materials with excellent mechanical properties and high density,a series of carbon/carbon composites were prepared with the nature flake graphite as carbon matrix,domestic T300 carbon fiber as reinforcing body,mesophase pitch as impregnating agent by liquid impregnation-carbonization densification method and hot pressed sintering mechanism.Then the mass ratio of raw materials(P/G) and the impregnation temperature were changed respectively to investigate their relationship with flexural strength,fracture toughness,pore porosity and density of composites.And the microstructure of composites was analyzed by Scanning Electron Microscopy(SEM).The investigation results show that the average flexural strength of carbon/carbon composites reach 360 MPa when the P/G is 1 and the impregnation temperature selects 300 ℃,which achieve the international advanced level.And other mechanical properties are as follows:fracture toughness of 6.02 MPa·m~(1/2),actual density of 1.75 g·cm~(-3),pore porosity of 1.7%,densification of 94.6%.
In order to obtain aerospace composite materials with excellent mechanical properties and high density,a series of carbon/carbon composites were prepared with the nature flake graphite as carbon matrix,domestic T300 carbon fiber as reinforcing body,mesophase pitch as impregnating agent by liquid impregnation-carbonization densification method and hot pressed sintering mechanism.Then the mass ratio of raw materials(P/G) and the impregnation temperature were changed respectively to investigate their relationship with flexural strength,fracture toughness,pore porosity and density of composites.And the microstructure of composites was analyzed by Scanning Electron Microscopy(SEM).The investigation results show that the average flexural strength of carbon/carbon composites reach 360 MPa when the P/G is 1 and the impregnation temperature selects 300 ℃,which achieve the international advanced level.And other mechanical properties are as follows:fracture toughness of 6.02 MPa·m~(1/2),actual density of 1.75 g·cm~(-3),pore porosity of 1.7%,densification of 94.6%.
引文
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[2]黄荔海,李贺军,刘皓,等.碳/碳复合材料密封性能分析[J].材料科学与工程学报,2006,24(6):826-829.
[3]蒋红燕,赵丽华,杨巧勤.碳/陶复合材料研究[J].中国陶瓷,1997,33(6):41-43.
[4]MORIMOTO T,OGURA Y,KONDO M,et al.Multilayer coating for carbon/carbon composites[J].arbon,1995,33(4):351-357.
[5]Aly-Hassan M S,Hatta H,wakayama S,et al.Comparison of 2D and 3D carbon/carbon composites with respect to damage and fracture resistance[J].Carbon,2003,41:1069.
[6]SAVAGE G.Carbon-carbon composites[M].London:Chapman and Hall,1993:193-225.
[7]S S Tzeng,K H Hung,TH Ko.Growth of carbon nanofibers on activated carbon fiber fabrics[J].Carbon,2006,44:859.
[8]余鹏,朱胜利,崔振铎,等.浸渍-炭化工艺对碳/碳复合材料力学性能的影响[J].材料热处理学报,2011,10(32):33-36.
[9]周彪,王兆申,才影,等.碳纤维增韧碳化硅基复合材料制备技术的研究进展[J].中国陶瓷,2015,51(2):7-11.
[10]PARTHA P PAUL,STUART T SCHWAB.Carbon materials obtained from organometallic modification of pitch and it oxidation resistance properties[J].Carbon,1996,34(1):89-95.
[11]徐世帅,张旺玺,梁宝岩.前驱体法制备碳化硅/硅氧碳陶瓷复合材料[J].中国陶瓷,2016,52(2):62-66.
[12]G Chollon O Siron.Microstructure and mechanical properties of coal tar pitch-based 2D-C/C composites with a filler addition[J].Carbon,2001,39(13):2065-2075.
[13]李贺军,张守阳.新型碳材料[J].新型工业化,2016,6(1):15-37.
[14]W Kowbel,CH Shan.Mechanical behavior of carboncarbon composites made with cold plasma treated carbon fibers[J].Composites,1995,26(11):791-797.
[15]白瑞成,杨勇,于晓东.快速化学气相渗积制备碳/碳复合材料的工艺研究[J].材料科学与工程学报,2003,21(3):342-345.
[16]朱时珍,李贺军,李克智,等.工艺因素对C/C复合材料CVI致密化的影响[J].材料科学与工程学报,2008,26(6):829-832.
[17]黄荔海,李贺军,李克,等.复合工艺制备碳/碳密封材料弯曲断裂特性[J].稀有金属材料与工程,2006,35(2):245-248.
[18]徐林,杨文彬,冯志海,等.高性能二维碳/碳复合材料的制备与性能[J].复合材料学报,2016,33(12):2877-2883.
[19]解惠贞,崔红,李瑞珍,等.一种C/C密封材料的设计与性能表征[J].固体火箭技术,2006,29(2):139-145.
[20]航空工业部708所.三相纤维增强复合材料弯曲性能试验方法:QJ 2099-91[S].北京:中华人民共和国航空工业部,1991.