Transmitting and Friction Behavior of a Carbon/silicon Carbide Composite Hinge in High Temperature Combustion Environment

doi:10.3724/SP.J.1077.2008.00501

Abstract

Abstract: An all-ceramic hinge based on the two dimensional carbon fiber reinforced silicon carbide matrix (C/SiC) composites was prepared by chemical vapor infiltration. The high temperature combustion wind tunnel realized simulation of the transmitting and friction behavior of the hinge at 1800℃ in an oxidizing atmosphere. Based on the coupling stress equivalent simulation system, a characterization method with the change of torque was proposed to evaluate the friction behavior. The friction and wear behavior as well as wear mechanism were studied both at high temperatures in combustion environment and at room temperature in air. The results indicate that the friction torque is stable and insensitive to the sliding time at high
temperatures, which demonstrates stable and reliable friction property and thermal load-carrying ability of the hinge. The
tribochemical reaction products on contact surface may moderate the stress distribution by providing a reaction layer for wear protection and lubrication.

Key words: carbon/silicon carbide composites, chemical vapor infiltration, friction, transmitting, high temperature combustion environment

CLC Number:

TB323

ZHANG Ya-Ni,ZHANG Li-Tong,CHENG Lai-Fei,XU Yong-Dong. Transmitting and Friction Behavior of a Carbon/silicon Carbide Composite Hinge in High Temperature Combustion Environment[J]. Journal of Inorganic Materials, DOI: 10.3724/SP.J.1077.2008.00501.

References

[1] Ortelt M, Weihs H, Fischer I, et al. Ceram. Eng. Sci. Pro., ABI/INFORM Trade & Industry, 2003, 24 (4): 281-287.
[2] Robert L. Fusaro. 2001 Annual Meeting, Society of Tribologists and Lubrication Engineers, NASA/TM-2001-210806, Orlando, Florida, 2001, May 20-24.
[3] 李思强. 载人飞船工程学概论. 北京: 科学出版社, 1985, 4: 160-162.
[4] McCleskey S F, Strasser T E, French P A, et al. AIAA-2000-5311, American Institute of Aeronautics and Astronautics, 2000.
[5] Wulz H G, Trabandt U. AIAA-97-2485, American Institute of Aeronautics and Astronautics, 1997.
[6] Kladtke R, Puttmann N, Graf E D. AIAA 1999-99-4936, American Institute of Aeronautics and Astronautics, 1999.
[7] Hald H, Weihs H. AIAA 2003-2696, International Air and Space Symposium and Exposition, 2003.
[8] Muhlratzer A, Pfeiffer H. Ceram. Eng. and Sci. Pro., ABI/INFORM Trade & Industry, 2002, 23 (3): 331-338.
[9] Ortelt M, Weihs H, Fischer I, et al. Ceram. Eng. Sci. Pro., ABI/INFORM Trade & Industry, 2003, 24 (4): 281-287.
[10] Krenkel W, Heidenreich B, Renz R. Adv. Eng. Mat., 2002, 4: 427-436.
[11] Pak Z S. Key Eng. Mat., 1999, 164-165: 820-825.
[12] 张均, 徐永东, 张立同, 等(ZHANG Jun, et al). 无机材料学报(Journal of Inorganic Materials), 2005, 20 (4): 889-893. [13] 张海军, 李文超, 姚熹, 等(ZHANG Hai-Jun, et al). 无机材料学报(Journal of Inorganic Materials), 2000, 15 (3): 480-486. [14] Vaidyaraman S, Purdy M, Walker T, et al. Key Eng. Mat., 1999, 164-165: 802-808.
[15] Paris J Y, Vincent L, Denape J. Com. Sci. Tech., 2001, 61 (3): 417-423.
[16] Zhang Y, Zhang L, Cheng L, et al. J. Am. Ceram. Soc., 2007, 90 (4): 1139-1145.
[17] Zhang Y, Zhang L, Cheng L, et al. J. Am. Ceram. Soc., 2007, 90 (8): 2630-2633.
[18] Wang Y, Hsu S M. Wear, 1996, 195 (1-2): 112-122.
[19] Zhou Y, Hirao K, Yamauchi Y, et al. J. Am. Ceram. Soc., 2003, 86 (6): 991-1002.
[20] Fischer T E, Zhu Z, Kim H, et al. Wear, 2000, 245: 53-60.
[21] Park D S, Danyluk S, McNallan M J. J. Am. Ceram. Soc., 1992, 75 (11): 3033-3039.