推进剂/包覆层界面脱粘率相关特性研究

doi:10.7527/S1000-6893.2015.0089

固体力学与飞行器总体设计

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推进剂/包覆层界面脱粘率相关特性研究

余家泉¹, 许进升¹, 陈雄¹, 周长省¹, 贾登¹, 李宏文²

1. 南京理工大学机械工程学院, 南京 210094;
2. 晋西工业集团有限责任公司, 太原 030027

收稿日期:2015-01-08 修回日期:2015-03-26 出版日期:2015-12-15 发布日期:2015-04-27
通讯作者: 许进升,Tel.:025-84315452,E-mail:xujinsheng@njust.edu.cn E-mail:xujinsheng@njust.edu.cn
作者简介:余家泉,男,硕士研究生。主要研究方向:固体火箭发动机装药结构完整性分析。Tel:025-84315452,E-mail:njustyjq@126.com;许进升,男,博士,讲师。主要研究方向:固体火箭发动机装药结构完整性分析。Tel:025-84315452,E-mail:xujinsheng@njust.edu.cn
基金资助:
江苏省自然科学基金(BK20140772)

Rate-dependent property of propellant and inhibitor interface debonding

YU Jiaquan¹, XU Jinsheng¹, CHEN Xiong¹, ZHOU Changsheng¹, JIA Deng¹, LI Hongwen²

1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;
2. Jinxi Industries Group Co. Ltd., Taiyuan 030027, China

Received:2015-01-08 Revised:2015-03-26 Online:2015-12-15 Published:2015-04-27
Supported by:
Natural Science Foundation of Jiangsu Province (BK20140772)

摘要/Abstract

摘要：

固体火箭发动机(SRM)装药包覆界面性能对发动机安全工作意义重大。为研究改性双基(CMDB)推进剂/三元乙丙(EPDM)包覆层界面在不同受载速率下的脱粘情况,采用双悬臂梁(DCB)试件对包覆粘接界面进行了界面脱粘性能试验研究,获取了脱粘界面扩展过程中的加载点载荷-位移曲线。同时,构建了界面率相关内聚力模型(CZM),并采用Hooke_Jeeves优化算法反演识别出相关模型参数。通过对比多阶段加载实验及仿真结果曲线验证了模型的可靠性,结果表明,二者变化趋势基本一致,最大误差小于15%,所得结论对固体火箭发动机装药界面脱粘研究具有一定参考价值。

关键词: 固体火箭发动机, 界面脱粘, 率相关内聚力模型, 有限元方法, 参数反演识别

Abstract:

The interfacial property between propellant and inhibitor has a significant impact on the working stability of the solid rocket motor (SRM). In order to investigate the debonding property of the interface between the composite modified double-base (CMDB) propellant and the ethylene-propylene-diene monomer (EPDM) inhibitor at different loading rates, an test research is conducted using double cantilever beam (DCB) specimen and the load-displacement curves are obtained. Meanwhile, an interface model is proposed based on the rate-dependent cohesive zone model (CZM) and the relevant parameters are inversed by the Hooke-Jeeves optimization algorithm. The model's accuracy is verified by comparing the multistage loading experiment curve with the simulation curve. The result shows that the change trend is consistent and the tolerance is less than 15%, which certificates that the interface model has some reference values for the debonding research in the solid rocket motor.

Key words: solid rocket motor, interface debonding, rate-dependent cohesive zone model, finite element method, parametric inversing identification

中图分类号:

V512

余家泉, 许进升, 陈雄, 周长省, 贾登, 李宏文. 推进剂/包覆层界面脱粘率相关特性研究[J]. 航空学报, 2015, 36(12): 3861-3867.

YU Jiaquan, XU Jinsheng, CHEN Xiong, ZHOU Changsheng, JIA Deng, LI Hongwen. Rate-dependent property of propellant and inhibitor interface debonding[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(12): 3861-3867.

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推进剂/包覆层界面脱粘率相关特性研究

Rate-dependent property of propellant and inhibitor interface debonding

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