[1]赵玖玲.基于全域CZM的复合推进剂细观损伤与断裂研究[J].固体火箭技术,2019,42(03):269-274.[doi:10.7673/j.issn.1006-2793.2019.03.001]
 ZHAO Jiuling.Research on microscopic damage and fracture of composite propellant based on global CZM[J].Journal of Solid Rocket Technology,2019,42(03):269-274.[doi:10.7673/j.issn.1006-2793.2019.03.001]
点击复制

基于全域CZM的复合推进剂细观损伤与断裂研究

参考文献/References:

[1]王亚平,王北海.丁羟推进剂拉伸脱湿的电子显微镜观测[J].固体火箭技术,1998,21(2):71-74.WANG-Yaping,WANG-Beihai.Electron microscopic observation of tensile dehumidification of HTPB propellant[J].Solid Rocket Technology,1998,21(2):71-74.[2]曾甲牙.丁羟推进剂拉伸断裂行为的扫描电镜研究[J].固体火箭技术,1999,22(4):69-72. ZENG Jiaya.Scanning electron microscopic study on tensile fracture behavior of HTPB propellants[J].Solid Rocket Technology,1999,22(4):69-72.[3]赵玖玲,强洪夫.复合固体推进剂宏细观损伤机理[M].北京:中国宇航出版社,2014.ZHAO Jiuling,QIANG Hongfu.Macroscopic and mesoscopic damage mechanism of composite solid propellant[M].Beijing:China Aerospace Press,2014. [4]刘著卿,李高春,邢耀国,等.复合固体推进剂细观损伤扫描电镜实验及数值模拟[J].推进技术,2011,32(3):412-16.LIU Zhuqing,LI Gaochun,XING Yaoguo,et al.Microscopic damage scanning electron microscopy experiment and numerical simulation of composite solid propellants[J].Propulsion Technology,2011,32(3):412-416.[5]李高春,邢耀国,戢治洪,等.复合固体推进剂细观界面脱粘有限元分析[J].复合材料学报,2011,28(3):229-235.LI Gaochun,XING Yaoguo,JI Zhihong,et al.Finite element analysis of microinterface debonding of composite solid propellants[J].Journal of Composite Materials,2011,28(3):229-235.[6]HAN Bo,JU Yutao,ZHOU Changsheng.Simulation of crack propagation in HTPB propellant using cohesive zone model[J].Engineering Failure Analysis,2012,26:304-317.[7]职世君,孙冰,张建伟.基于表面粘结损伤的复合固体推进剂细观损伤数值模拟[J].推进技术,2013,34(2):273-279.ZHI Shijun,SUN Bing,ZHANG Jianwei.Mesodamage numerical simulation of composite solid propellant based on surface bond damage[J].Propulsion Technology,2013,34 (2):273-279.[8]张炯,屈展,黄其青,等.基于内聚力模型的圆形夹杂与基体界面渐进脱粘分析[J].西安石油大学学报(自然科学版),2014,29(3):106-110.ZHANG Jiong,QU Zhan,HUANG Qiqing,et al.Analysis of progressive debonding between circular inclusions and matrix based on cohesion model[J].Journal of Xi’an Petroleum University(Natural Science Edition),2014,29 (3):106-110.[9]职世君,曹付齐,申志彬,等.复合固体推进剂双折线脱湿损伤模型参数影响分析[J].固体火箭技术,2017,40(2):183-188.ZHI Shijun,CAO Fuqi,SHEN Zhibin,et al.Analysis of the parameters of the doublefolded dehumidification damage model for composite solid propellants[J].Solid Rocket Technology,2017,40(2):183-188.[10]封涛,许进升,韩龙,等.含初始缺陷的复合固体推进剂力学性能[J].航空材料学报,2018,38(3):91-99.FENG Tao,XU Jinsheng,HAN Long,et al.Mechanical properties of composite solid propellants with initial defects[J].Journal of Aviation Materials,2018,38(3):91-99.[11]Bernard F ,Kamali Bernard S ,Prince W.3D multiscale modelling of mechanical behaviour of sound and leached mortar[J].Cement and Concrete Research,2008,38(4):449-458.[12]Mori T,Tanaka K.Average stress in matrix and average energy of maals with misfitting inclusion[J].Act.Metal.,1973,21(5):571-574.

相似文献/References:

[1]田四朋,唐国金,雷勇军,等.固体火箭发动机随机药柱结构分析参数的灵敏度研究[J].固体火箭技术,2008,(1):28.
[2]封锋,陈军,郑亚.基于能量特性配方设计专家系统的开发与实现[J].固体火箭技术,2009,(02):206.
[3]张伟,樊学忠,张腊莹,等.NEPE推进剂低温瞬态的粘弹特性[J].固体火箭技术,2009,(03):298.
[4]阳建红,刘朝丰,邓凯.固体推进剂的变角剪切力学试验研究[J].固体火箭技术,2009,(04):436.
[5]闫大庆,徐丹丹,师经国.固体推进剂粘合剂HTPE研究及其分子设计思想概述[J].固体火箭技术,2009,(06):644.
[6]李苗苗,汪越,郭效德,等.RDX/AMMO-BAMO推进剂燃烧模型[J].固体火箭技术,2009,(06):654.
[7]陈煜,刘云飞,夏吉东,等.键合剂对NEPE推进剂破坏趋势影响的实验定量研究[J].固体火箭技术,2010,(03):299.
[8]刘中兵,汪亮,胡春波.HTPB推进剂高压燃烧特性研究[J].固体火箭技术,2010,(03):302.
[9]段毅,刘宇,覃粒子,等.考虑两相表面反应的二硝酰胺铵点火研究[J].固体火箭技术,2010,(03):311.
[10]刘晶如,罗运军.固体推进剂用铝基复合材料的制备及性能[J].固体火箭技术,2010,(05):545.

更新日期/Last Update: 2019-07-11
PDF下载 分享