Ablation Characteristic of 3D C/SiC Composite Nozzle in a Small Solid Rocket Motor

doi:10.3724/SP.J.1077.2008.00938

Abstract

Abstract: Ablation properties of a 3D C/SiC composite nozzle were investigated by using hot-firing test in a small solid propellant
rocket motor. Ablation mechanisms of the C/SiC composites and effects of the combustion gases parameters were discussed. The results show that the linear ablation rate at the throat of the composite nozzle is 0.128±0.088mm/s, and the mass ablation rate is 0.166kg/(m²·s). Ablation behavior for the 3D C/SiC composite shows a nonuniform process, which is directly affected by the compositions, temperature, pressure and the velocity of combustion gases. The ablation in the divergent section, convergent section and the regions near the throat grows severe by degrees. Ablation mechanisms of C/SiC composite are the cooperation of thermo-physical ablation, thermo-chemical ablation and thermo-mechanical erosion, which involve the decomposition of the SiC, oxidation of the SiC and carbon fiber, as well as chemical and mechanical erosion by Al₂O₃ slags and particles, respectively.

Key words: ablation, C/SiC composites, solid rocket motor, ablation mechanisms

CLC Number:

TB332

CHEN Bo,ZHANG Li-Tong,CHENG Lai-Fei,LUAN Xin-Gang. Ablation Characteristic of 3D C/SiC Composite Nozzle in a Small Solid Rocket Motor[J]. Journal of Inorganic Materials, DOI: 10.3724/SP.J.1077.2008.00938.

References

[1] Hlratzer A, Pfeiffer H. SAMPE, 2002, 38 (4): 22--29.
[2] Papenburg U, Beyer S, Laube H. Advanced ceramic matrix composites for space propulsion systems. AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 33rd, Seattle, WA, USA. AIAA- 1997-3391.
[3] Beyer S, Knabe H. Development and testing of C/SiC components for liquid rocket propulsion applications. AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 35th, Los Angeles, CA, USA, 1999. AIAA-1999-2896.
[4] Felix F, William F, Nancy R. An innovative thermal management system for a mach 4 to mach 8 hypersonic scramjet engine. AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 34th, Cleveland, OH, USA, 1998. AIAA-1998-3734.
[5] Siebenhaar A, Johnson R W. Aero jet storable fuel scramjet flow path concepts: phase I program overview. AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 9th, Norfolk, VA, USA, 1999. AIAA-1999-4923.
[6] 何洪庆, 王思民, 牛嵩高, 等. 固体火箭技术, 1993, (3): 31--36.
[7] Xu Y D, Zhang L T. J. Am. Ceram. Soc., 1997, 80 (7): 1897--1900.
[8] Xu Y D, Zhang L T, Cheng L F, et al. Carbon, 1998, 36 (7-8): 1051--1056.
[9] 潘育松, 徐永东, 陈照峰, 等. 兵器材料科学与工程, 2006, 29 (1): 17--21.
[10] Sanford Gordon, Bonnie J McBride. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications I. Analysis, NASA RP-1311. Cleveland, Ohio, USA. National Aeronautics and Space Administration, Lewis Research Center, 1994. 1--61.
[11] Sanford Gordon, Bonnie J McBride. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications II. User’s Manual and Program Description, NASA RP-1311-P2. Cleveland, Ohio, USA. National Aeronautics and Space Administration, Lewis Research Center, 1996. 1--178.
[12] 李宜敏, 张中钦, 张远君. 固体火箭发动机原理, 第一版. 北京: 北京航空航天大学出版社, 1991. 109--123.
[13] 郑亚, 陈军, 鞠玉涛, 等. 固体火箭发动机传热学, 第一版. 北京: 北京航空航天大学出版社, 2006. 111, 204.
[14] Yu Daimon, Akiko Matsuo. Heat Flux Estimation on the Nozzle Wall of Solid Rocket Motor Nozzle, 23rd International Symposium on Space Technology and Science. Yokohama, JAPAN, 2002. ISTS 2002-e-05.
[15] (俄)A.A.希什科夫, c.л.帕宁, B.B.鲁缅采夫, 著; 关正西, 赵克熙, 译. 固体火箭发动机工作过程, 第一版. 北京: 中国宇航出版社, 2006, 170, 220--223.
[16] 殷小玮. 西北工业大学博士学位论文, 2001.
[17] Nathan S. Jacobson. J. Am. Ceram. Soc., 1993, 76 (1): 3--28.
[18] René C J Schiepers, van Frans J J Loo, de Gijsbertus With. J. Am. Ceram. Soc., 1988, 71 (6): C284--C287.