PDF下载 分享
[1]胡松启,周宴星,刘迎吉,等.固体推进剂裂纹扩展研究综述[J].火箭推进,2012,38(05):86-90.
　HU Song-qi,ZHOU Yan-xing,LIU Ying-ji,et al.Studies on crack extension in solid propellant[J].Journal of Rocket Propulsion,2012,38(05):86-90.
点击复制

固体推进剂裂纹扩展研究综述

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 38 期数: 2012年05期 页码: 86-90 栏目: 测控与试验 出版日期: 2012-10-15
Title:
Studies on crack extension in solid propellant
文章编号:
1672-9374(2012)05-0086-07
作者:
胡松启1; 周宴星2; 刘迎吉1; 陈 静1
1. 西北工业大学，陕西 西安 710072；
Author(s):
HU Song-qi1;  ZHOU Yan-xing2;  LIU Ying-ji1;  CHEN Jing1
1. Northwestern Polytechnical University, Xi’an 710072, China;
关键词:
固体推进剂; 裂纹扩展; 增压速率; 对流燃烧; 断裂韧性
Keywords:
solid propellant;  crack extension;  pressure boost rate;  convective
分类号:
V512
文献标志码:
A
摘要:
介绍国内外关于固体推进剂裂纹扩展的研究现状,总结固体推进剂裂纹扩展的试验研究和理论分析方法，归纳影响固体推进剂裂纹扩展的各种因素。分析认为：采用拉伸装置研究有裂纹推进剂力学性能和利用高速摄影系统研究裂纹燃烧和扩展情况是当前主要的研究手段；发动机燃烧室内压力、升压速率、裂纹形状尺寸和推进剂燃速是装药裂纹扩展的重要因素；必须进一步开展各因素和裂纹扩展的定量关系研究。
Abstract:
The research status of the crack extension in solid propellant at home and abroad are introduced. Experimental study and theoretical analysis of the crack extension in solid propellant are summarized. The advantages and disadvantages of such study are analyzed. The influences of various factors on crack extension in solid propellant are generalized. The results show that the tension machine and high-speed photography are main means for studying the mechanics characteristic of propellant with crack, and the combustion property of propellant and the extension of crack; the working pressure in combustion chamber, pressure boost rate, style and size of crack, and burning rate of propellant are the important factors for the crack extension in solid propellant. It is pointed out that it is necessary to research the quantitative relationship between various factors and crack extension.

参考文献/References:

[1]陈广南, 张为华. 固体火箭发动机撞击与热安全性分析[M]. 北京: 国防工业出版社, 2008.
[2]葛爱学. 固体火箭发动机点火过程与装药裂纹相互作用机理研究[D]. 长沙: 国防科学技术大学, 2004.
[3]刘著卿, 颜世东, 丁彪. 药柱裂纹对固体火箭发动机工作过程的影响[J]. 海军航空工程学院学报, 2007, 22(4): 443-446.
[4]吕光珍. 固体推进剂裂纹扩展的试验研究[J]. 推进技术, 1988 (6): 41-47.
[5]屈文忠. 国产HTPB复合推进剂裂纹扩展特性的实验研究[J]. 推进技术, 1994 (6): 88-92.
[6]成曙, 路延镇, 蔡国飙, 等. 含I型裂纹复合固体推进剂双轴拉伸实验研究[J]. 宇航材料工艺, 2007 (5): 63-66.
[7]KUO K K, CHEN A T, DAVIS T R. Convective burning in solid-propellant cracks[J]. AIAA Journal, 1978, 16(6): 600-607.
[8]KUMAR M, KUO K K. Ignition of solid propellant crack tip under rapid pressurization[J]. AIAA Journal, 1980,18(7): 825-833.
[9]KOU K K, KUMAR M, MANTZARAS J. Different modes of cracke propagation in burning solid propelants[J]. Journal of Propulsion and Power, 1987, 3(l): 22-26.
[10]LU Y C, KUO K K, WU S R. Crack propagation processs in a burning AP-based. composite solid propellant , AIAA 93-2168[R]. USA: AIAA, 1993.
[11]TODD E E. RSRMTP-H1148 main grain propellant crack initiation evaluation, AIAA 2005-3601[R]. USA: AIAA, 2005.
[12]熊华. 固体推进剂裂纹燃烧时扩展条件的实验研究和理论分析[D]. 烟台: 海军航空工程学院, 1999.
[13]沈伟. 固体推进剂裂纹燃烧与扩展的研究[D]. 烟台: 海军航空工程学院, 2000.
[14]张文普, 何国强, 刘佩进, 等. 固体推进剂装药裂纹内燃烧流动的实验研究[J]. 推进技术, 2000, 21(5): 58-60.
[15]SCHAPCRY R A. A theory of crack initiation and growth in viscoelastic media[J]. International Journal of Fracture, 1975, ll(1): 40-47.
[16]SWANSON S R. Application of schapery's theory of viscoelastic fracture of solid propellant[J]. J. Spacecraft and Rockets, 1976, 13(9): 528-535.
[17]陈光学. 固体推进剂中裂纹扩展的一条新定律[J]. 国外固体火箭技术, 1987 (4): 40-45.
[18]RICE J R, ROSENGREN G F. Plane strain deformation near crack tip in a power law hardening material[J]. Journal of Mechanics and Physics of Solids, 1968, 16(1): 1-12.
[19]SMIRNOV N N. Convective burning in channels and cracks in solid propellants[J]. Fizika Goreniyai Varyva, 1985, 21: 29-36.
[20]GRIFFITHS S K, NILSON R H. Similarity analysis of fracture growth and flame spread in deformable gas generating pryotechnics, SAND90-8472[R]. [S.L.]: SAND, 1990.
[21]DICK W A, HEALTH M T, FIEDLER R A. Integrated 3-D simulation of solid propellant rockets, AIAA 2001-3949[R]. USA: AIAA, 2001.
[22]FIELDER R A, BREITENFELD M S. Simulations of slumping propellant and flexing inhibitors in solid rocket motors, AIAA 2002-4341[R]. USA: AIAA, 2002.
[23]唐立强, 谭英杰, 蔡艳红. 刚性一粘弹性材料界面I型动态扩展裂纹的尖端场[J].力学季刊，2004, 25(2): 188-194.
[24]唐立强, 谭英杰, 蔡艳红. 刚性一粘弹性材料界面II型动态扩展裂纹的尖端场[J]. 哈尔滨工业大学学报, 2004, 36(9): 1206-1209.
[25]袁端才, 唐国金, 雷勇军. 固体发动机药柱表面裂纹分析[J]. 试验技术与试验机, 2006 (1): 9-13.
[26]李东, 黄国臣, 周长省, 等. 双基固体推进剂裂纹开裂方向的研究[J]. 弹道学报, 2008, 20(3): 24-28.
[27]KNAUSS W G. The mechanics of polymer fracture[J]. Applied Mechanics Reviews, 1973, 26: 1-17.
[28]HUFFERD W. Model of crack propagation in viscoelastic material, ADA-213907[R]. USA: ADA, 2007.
[29]GODAI T. Flame propagation into the crack of a solid propellant cracks[J]. AIAA Journal, 1970 (8): 1322-1327.
[30]JACOBS H R. An experimental study of the pressure distribution in burning flaws in a solid propellant grains [R]. [S.l.]: AFRPL-TR, 1972.
[31]李江, 何国强, 蔡体敏. 固体推进剂裂纹燃烧流场的数值模拟[J]. 推进技术, 1999, 20(3): 36-39.
[32]韩小云, 周建平. 固体推进剂裂纹对流燃烧和扩展的研究分析[J]. 推进技术, 1997, 18(6): 42-45.
[33]韩小云, 周建平. 固体推进剂燃烧断裂边界二维流场特性[J]. 推进技术, 1998, 19(6): 20-23.
[34]邢耀国, 熊华, 董可海, 等. 聚硫推进剂燃烧条件下裂纹扩展过程的研究[J]. 推进技术, 2000, 21(3): 71-74.

相似文献/References:

[1]赵峰,常新龙.某固体推进剂湿热老化模型[J].火箭推进,2008,34(01):59.
　Zhao Feng,Chang Xinlong.Hygrothermal aging life model of a composite solid propellant[J].Journal of Rocket Propulsion,2008,34(05):59.
[2]赵永俊,张兴高,张炜,等.国外固体推进剂及其粘结界面 贮存老化研究进展[J].火箭推进,2008,34(03):35.
　Zhao Yongjun,Zhang Xinggao,Zhang Wei,et al.Review on the aging property of solid propellant and bonding interface abroad[J].Journal of Rocket Propulsion,2008,34(05):35.
[3]张明,梁彦,唐庆明,等.纳米铝粉在固体推进剂中的应用[J].火箭推进,2006,32(01):35.
　Zhang Ming,Liang Yan,Tang Qingming.Progress in the application of nano aluminum powder in solid propellants[J].Journal of Rocket Propulsion,2006,32(05):35.

备注/Memo

收稿日期：2012-05-09；修回日期：2012-06-29
基金项目：总装预研基金项目（基金号9140C5203120906）
作者简介：胡松启（1976—），男，副教授，研究领域为固体推进剂及燃烧

更新日期/Last Update: 1900-01-01