C/SiC复合材料是航空航天器中的耐高温材料，其服役环境存在低能量冲击源且关于此类冲击事件的研究相对较少。本文主要采用落锤冲击系统性地揭示2D叠层C/SiC复合材料平板的抗低速低能量冲击性能，通过改变冲击能量考核不同单层厚度和平板厚度的抗冲击性能变化，并利用CT技术进行冲击后无损检测，分析结构内部细观损伤。结果表明：冲击载荷下，C/SiC复合材料按冲击载荷变化可分为线性、屈服和回弹3个阶段；典型冲击损伤形式包含局部压溃、分层、纤维断裂及基体微裂纹；同等结构厚度，单层厚度越大C/SiC复合材料平板冲击变形和冲击损伤越小，冲击阻抗值越高；同等单层厚度下，结构总厚度较大的C/SiC复合材料平板冲击损伤较小，冲击阻抗较大。因此，C/SiC复合材料的预制体层数与结构厚度对低能量冲击源较为敏感，且减小单层厚度及增加结构总厚度可明显提高其抗冲击性能。
C/SiC composites as high-temperature resistant materials in the fields of aeronautics and astronautics will encounter low-energy impact sources in their service environment. This paper systematically reveals the impact resistance performance of 2D laminated C/SiC composite materials using drop-weight impact equipment. We study the impact resistance with different prefab thickness and structure thickness under different impact energy conditions. The structure damage is analyzed by the CT nondestructive testing technology, showing that the impact load can be divided into three stages: linear elasticity, yield, and rebound. Typical forms of impact damage include matrix crushes, delamination, fiber fractures and matrix microcracks. With the same structure thickness, C/SiC composites with larger ply thickness have less impact deformation, less impact damage and higher impact impedance. For the same ply thickness, C/SiC composites with larger total thickness have less impact damage and larger impact impedance. Therefore, the number of prefabricated layers and structural thickness of C/SiC composites are sensitive to low energy impact sources. Thus, we can improve the impact resistance of C/SiC composites by reducing the thickness of the prefab and increasing the total thickness of the structure.
[1] 马青松, 刘海韬, 潘余, 等.C/SiC复合材料在超燃冲压发动机中的应用研究进展[J].无机材料学报, 2013,28(3):247-255. MA Q S, LIU H T, PAN Y, et al. Research progress on the application of C/SiC composites in scramjet[J]. Journal of Inorganic Materials,2013,28(3):247-255(in Chinese).
[2] 刘丽萍, 王国林, 王一光, 等.高焓化学非平衡流条件下C/SiC复合材料的催化性能[J].航空学报, 2018,39(5):421696. LIU L P, WANG G L, WANG Y G, et al. Catalytic performance of C/SiC composites in high enthalpy chemical non-equilibrium flow[J]. Acta Aeronautica et Astronautica Sinica, 2018,39(5):421696(in Chinese).
[3] ASLAN Z, KARAKUZU R, OKUTAN B, et al. The response of laminated composite plates under low-velocity impact loading[J]. Composite Structures, 2003, 59:119-127.
[4] 张立同, 成来飞, 徐永东. 新型碳化硅陶瓷基复合材料的研究进展[J].航空制造技术,2003(1):24-32. ZHANG L T, CHENG L F, XU Y D. Progress in research work of new CMC-SiC[J]. Aeronautical Manufacturing Technology, 2003(1):24-32(in Chinese).
[5] 邹世钦, 张长瑞, 周新贵, 等. 连续纤维增强陶瓷基复合材料在航空发动机上的应用[J].航空发动机,2005,31(3):55-58. ZOU S Q, ZHANG C R, ZHOU X G, et al. Application of continuous fiber reinforced ceramic matrix composites in aeroengine[J]. Aeroengine, 2005,31(3):55-58(in Chinese).
[6] OGI K, OKABE T, TAKAHASHI M. Experimental characterization of high-speed impact damage behavior in a three-dimensionally woven SiC/SiC composite[J]. Composites Part A:Applied Science and Manufacturing, 2010,41(4):489-498.
[7] MICHAEL J P, MANSOUR R, MANIGNDAN K, et al. Characterization and simulation of foreign object damage in curved and flat SiC/SiC ceramic matrix composites[J]. Ceramics International, 2019, 45:2635-2643.
[8] TRABANDT U, FISCHER W, GUELHAN A, et al. Improvement of lifetime performance of removable TPS and hot structures[C]//9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference. Reston:AIAA, 2006:1-10.
[9] 徐红瑞, 成来飞, 梅辉. 2D C/SiC复合材料的静压痕力的损伤表征[J].航空学报,2012,33(8):1547-1553. XU H R, CHENG L F, MEI H. The characterization of indentation of 2D C/SiC composites subjected to quasi-static indentation[J]. Acta Aeronautica et Astronautica Sinica, 2012,33(8):1547-1553(in Chinese).
[10] MEI H, ZHANG L D, XU H R, et al. Damage mechanism of a carbon fiber ceramic composite during the step-loading indentation and its effect on the mechanical properties[J]. Composites:Part B, 2014, 56:142-148.
[11] HERB V, MARTIN E, COUéGNAT G. Damage analysis of thin 3D-woven SiC/SiC composite under low velocity impact loading[J]. Composites:Part A, 2012, 43:247-253.
[12] MEI H, YU C K, XU H R, et al. The effects of stitched density on low-velocity impact damage of cross-woven carbon fiber reinforced silicon carbide composites[J]. Ceramics International, 2016, 42:1762-1768.
[13] MEI H, YU C H, XU Y W, et al. Effect of impact energy on damage resistance and mechanical property of C/SiC composites under low velocity impact[J]. Materias Science & Engineering A, 2017, 687:141-147.
[14] LI B, MICHELLE S,FATT H. Impact damage and residual strength prediction of 2D woven SiC/SiC composites[J]. Finite Elements in Analysis and Design, 2016, 113:30-42.
[15] ASTM. Standard test method for measuring the damage resistance of a fiber-reinforced polymer matrix composite to a drop-weight impact event:ASTM D7136/D7136M-05[R].West Conshohocken:ASTM International,2005.
[16] ZHOU J W, LIAO B B, SHI Y Y, et al. Low-velocity impact behavior and residual tensile strength of CFRP laminates[J]. Composites Part B, 2019, 161:300-313.
[17] 孙磊, 张立同, 梅辉, 等. 2D C/SiC缺陷的无损检测与评价[J].复合材料学报,2008,25(5):85-90. SUN L, ZHANG L T, MEI H, et al. Nondestructive testing and evaluation of 2D C/SiC with defects[J]. Acta Materiae Compositae Sinica, 2008,25(5):85-90(in Chinese).
[18] 王景深. 平纹编织C/SiC复合材料低速冲击损伤的声发射表征[C]//2011中国材料研讨会论文摘要集.北京:中国材料研究学会,2011:656. WANG J S. Acoustic emission characterization of low speed impact damage of plain weave C/SiC composites[C]//Abstract Collection of Papers of 2011 China Mmaterials Seminar. Beijing:Chinese Materials Research Society, 2011:656(in Chinese).
CJA