无纬布/网胎叠层针刺C/C材料的制备及性能  

Fabrication and performance of a C/C composite using a needled non-woven carbon fiber felt as a preform

作　　者：李艳[1,2] 崔红[1,2] 郑蕊[2] 嵇阿琳[2] 周绍建[2] 

机构地区：[1]西北工业大学材料学院,陕西西安710072 [2]西安航天复合材料研究所,陕西西安710025

出　　处：《新型炭材料》2017年第1期56-62,共7页New Carbon Materials

基　　金：国防基础科研项目(C0320110006)~~

摘　　要：以无纬布/炭纤维网胎叠层针刺预制体为增强体,经化学气相渗透(CVI)联合沥青浸渍/高压炭化(HPIC)方法制备了针刺C/C材料,研究了该材料的热力学性能,并与整体毡C/C材料进行了对比。结果表明:针刺C/C材料室温及2 800℃下轴向拉伸强度分别为24.50 MPa和52.88 MPa,较整体毡C/C材料分别提高了138%和170%,且拉伸破坏模式为假塑性。针刺C/C材料热物理性能优于整体毡C/C材料,1 000℃轴向热膨胀系数仅为1.409×10-6/℃,相比降低了64%。针刺C/C材料优异的机械强度和良好的热物理性能为其在固体火箭发动机中的应用奠定了基础。A C/ C composite was prepared by chemical vapor infiltration followed by repeated pitch impregnation and high pres-sure carbonization to a final density of 1. 9 g/cm^3 using a needled non-woven carbon fiber felt preform. Its mechanical properties were compared with a 3D woven C/C composite. Results indicated that the axial tensile strength of the needled C/C composite was 24.5 and 52. 88 MPa at room temperature and 2 800 益,respectively,correspondingly 138 and 170% higher than that of the 3D woven C/C composite. The failure mode of the needled composite was pseudoplastic. The axial thermal expansion coefficient of the needled composite at 1 000℃ was only 1.409×10^-6/℃, 64% lower than that of the 3D woven composite. The needled C /C com-posite exhibits excellent mechanical strength and thermal physical properties which make it potentially useful for a solid rocket mo-tor.

关 键 词：无纬布/网胎预制体、针刺C/C材料 拉伸强度 热物理性能 

分 类 号：TB332[一般工业技术—材料科学与工程]