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[1]李高春,姜爱民,黄卫东,等.固体火箭发动机粘接界面变形破坏的细观试验与数值模拟[J].火炸药学报,2018,41(3):314-318.[doi:10.14077/j.issn.1007-7812.2018.03.018]
 LI Gao-chun,JIANG Ai-min,HUANG Wei-dong,et al.Meso-experiment and Numerical Simulation of Deformation and Failure Adhesive Interface for Solid Rocket Motor[J].,2018,41(3):314-318.[doi:10.14077/j.issn.1007-7812.2018.03.018]
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固体火箭发动机粘接界面变形破坏的细观试验与数值模拟()
     
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《火炸药学报》[ISSN:1007-7812/CN:61-1310/TJ]

卷:
41卷
期数:
2018年第3期
页码:
314-318
栏目:
出版日期:
2018-06-29

文章信息/Info

Title:
Meso-experiment and Numerical Simulation of Deformation and Failure Adhesive Interface for Solid Rocket Motor
作者:
李高春 姜爱民 黄卫东 王朝轰 王玉峰 刘铁
1. 海军航空大学岸防兵学院, 山东 烟台 264001;
2. 海军航空大学航空基础学院, 山东 烟台 264001;
3. 91115部队, 浙江 舟山 316000
Author(s):
LI Gao-chun JIANG Ai-min HUANG Wei-dong WANG Chao-hong WANG Yu-feng LIU Tie
1. Coast Defense College, Naval Aviation University, Yantai Shandong 264001, China;
2. Aeronautical Base College, Naval Aviation University, Yantai Shandong 264001, China;
3. The 91115 th Unit of PLA, Zhoushan Zhejiang 316000, China
关键词:
固体火箭发动机粘接界面变形破坏数值模拟脱粘
Keywords:
solid rocket motoradhesive interfacedeformation and failurenumerical simulationdebonding
分类号:
TJ55;V435
DOI:
10.14077/j.issn.1007-7812.2018.03.018
文献标志码:
-
摘要:
采用扫描电镜原位拉伸试验观察固体火箭发动机粘接界面试件在拉伸过程的变形和破坏过程,分析了载荷作用下界面失效模式和机理;依据粘接界面细观结构,建立了界面的细观数值模型,考虑了其细观损伤特点,在推进剂内部颗粒与基体之间以及推进剂/衬层之间引入界面元,对界面细观变形和破坏过程进行了数值模拟。结果表明, 在外界应变5%时,表现为非均质材料内部应力分布不均,随应变的增加,推进剂内部脱湿形成的微孔洞不断扩展,最终导致界面破坏,界面拉伸失效过程表现为损伤的起裂和扩展,是推进剂内部脱湿和粘接界面脱粘共同作用的结果;界面元能有效地模拟粘接界面的脱粘过程,细观数值计算结果与试验结果吻合,正确反映了粘接界面在拉伸过程中细观损伤萌生与扩展的规律。
Abstract:
The scanning electron microscope in-situ tensile test was used to observe the deformation and failure process of the adhesive interface specimens of solid rocket motor in the tensile process. The failure mode and mechanism of interface under loading action were analyzed. The mesoscopic numerical model of the interface was established according to the meso structure of the adhesive interface, and the characteristics of its meso damage were considered. The interface element between propellant particles and matrix and propellant/liner was introduced to simulate the meso deformation and failure process of the interface. The results show that when the external strain is 5%, the internal stress distribution in the heterogeneous material is uneven. With the increase of the strain, the microporous holes formed in the internal dehumidification of propellant continuously expand and eventually lead to the destruction of the interface. The failure process of the interfacial tension is manifested by the initiation and expansion of the damage, which is the results of combined action of internal dehumidification of the propellant and debonding of the adhesion interface. The interface element can effectively simulate the debonding process of the adhesive interface, and the mesoscopic numerical results agree with the experimental ones, which correctly reflects the law of mesoscopic damage initiation and expansion during the tensile process.

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备注/Memo

备注/Memo:
收稿日期:2018-02-02;改回日期:2018-04-27。
基金项目:预研共性技术基金(No.9140A28)
作者简介:李高春(1978-),男,副教授,从事固体火箭发动机的教学和科研工作。E-mail:leespringhjhy@sina.com
更新日期/Last Update: 1900-01-01