CHINESE JOURNAL OF ENERGETIC MATERIALS
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固体火箭发动机粘接界面参数识别与损伤破坏数值模拟
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1.海军航空大学, 山东 烟台 264000;2.海军装备部驻北京地区军事代表局, 北京 100071;3.火箭军工程大学, 陕西 西安 710025

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山东省高等学校“青年科创计划”(2019KJB017)


Parameter Inverse Identification and Damage Failure Process Simulation of Adhesive Interface of Solid Rocket Motor
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Affiliation:

1.Naval Aeronautical University, Yantai 264000, China;2.Military Representative Bureau of Naval Armament Department in Beijing Region, Beijing 100071, China;3.Xi′an Hi-Tech Institute, Xi′an 710025, China

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    摘要:

    为了研究固体火箭发动机粘接界面的损伤破坏过程,按照QJ2038.1A-2004制作了固体火箭发动机矩形粘接试件,对粘接试件进行了单向拉伸试验,获得了粘接试件的损伤破坏模式。根据粘接试件损伤破坏特点,建立了粘接试件的有限元数值模型,采用基于分步反演与Hooke-Jevees优化算法结合的反演方法,准确地获取了推进剂/衬层/绝热层界面混合模式下双线型内聚力模型的相关参数,将其应用于粘接试件拉伸试验损伤破坏过程的数值模拟中。研究结果表明:粘接试件主要的破坏形式为推进剂/衬层/绝热层界面处的脱粘;提出的反演识别方法能够较好地获取固体火箭发动机的界面相关参数,拉伸速度为2 mm·min-1时,固体火箭发动机粘接界面的初始模量、最大粘接强度、断裂能分别为0.86 MPa、0.63 MPa、3.13 kJ·m-2;推进剂/衬层/绝热层界面的损伤导致粘接试件的应力随应变增加的速率减慢,人工脱粘层尖端处界面的起裂,并且沿试件中央扩展,最终贯穿粘接试件是粘接试件主要损伤破坏模式。

    Abstract:

    In order to study the damage and failure process of adhesive interface of solid rocket motor, rectangular adhesive specimen of solid rocket motor was made based on QJ2038.1A-2004 regulation standard and tensile tests was carried out. The damage and failure mode of the adhesive interface specimen was obtained. The parameter inverse identification method which is based on step inverse and Hooke-Jevees optimization algorithm was adopted. The relevant parameters of the bilinear cohesive model of mix mode at the propellant/liner/insulator interface were obtained and were applied into the numerical simulation of the damage and failure process of adhesive specimen in tensile tests. Results show that the main failure form of adhesive interface specimen is the debonding at the interface of the propellant/liner/insulator layer; the proposed parameter inverse identification method can obtain the interface parameters of solid rocket motors well. The initial modulus, maximum bonding strength and fracture energy of the propellant/liner/insulator layer of solid rocket motors are 0.86 MPa, 0.63 MPa and 3.13 kJ·m-2 at tension speed of 2 mm·min-1, respectively. The damage of the propellant/liner/insulation layer interface makes the increase rate of stress decrease with the tensile strain. The initiation interface crack at the tip of the artificial debonding layer and the expansion along the center of the specimen, and finally penetration of the bonded specimen is the main damage and failure mode of the adhesive specimen.

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引用本文

伍鹏,李高春,韩永恒,等.固体火箭发动机粘接界面参数识别与损伤破坏数值模拟[J].含能材料,2021,29(3):211-219. DOI:10.11943/CJEM2020096.
WU Peng, LI Gao-chun, HAN Yong-heng, et al. Parameter Inverse Identification and Damage Failure Process Simulation of Adhesive Interface of Solid Rocket Motor[J]. Chinese Journal of Energetic Materials, 2021, 29(3):211-219. DOI:10.11943/CJEM2020096.

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  • 收稿日期: 2020-04-16
  • 最后修改日期: 2021-01-10
  • 录用日期: 2020-09-28
  • 在线发布日期: 2020-12-25
  • 出版日期: 2021-03-25