航空兵器Issue(6)：32-35,44,5.
含裂纹 HTPB 推进剂断裂准则研究
Study of Fracture Criterion for HTPB Propellant with Crack
李晔鑫 1韩波 1李记威1
作者信息
- 1. 中国空空导弹研究院，河南洛阳 471009
- 折叠
摘要
Abstract
The surface crack of the solid propellant influences the security of SRM ( SolidR-ocket Motor) seriously.The stress intensity factor and J-integral used for fracture toughness at present can not be applied to solid propellant directly.In order to obtain the fracture criterion of model-Ⅰcrack for HTPB propellant at medium and low strain rate, a fracture criterion based on strain is established through experi-ment and numerical simulation.The uniaxial tensile tests of standard and unilateral notched HTPB propel-lant samples are conducted to get material tensile strength, and the finite element method is employed to calculate the strain intensity factor.The results indicate that the fracture criterion based on strain in this study is more practical than that based on stress for HTPB propellant at medium and low strain rate.关键词
固体推进剂/断裂/有限元方法Key words
solid propellant/fracture/finite element method分类
航空航天引用本文复制引用
李晔鑫,韩波,李记威..含裂纹 HTPB 推进剂断裂准则研究[J].航空兵器,2014,(6):32-35,44,5.
