固体火箭技术Issue(5)：672-677,683,7.DOI:10.7673/j.issn.1006-2793.2014.05.017
复合推进剂拉伸应变条件下燃速变化计算分析
Computational analysis on burning rate change of composite propellant under tensile strain
摘要
Abstract
Computational model on burning rate change of composite propellant under tensile strain was established,and experi-mental verification was done on the model. The results show that the model corresponds with experimental data within tensile strain increasing from 0 to 20%.Burning rate ratio and tensile strain obey the quadratic relationship,burning rate increases with strain;Burning rate ratio of composite propellant which has lower poisson ratio increases faster as tensile strain decreasing;The less binder component of composite propellants,the more significant the burning ratio changes under strain state.Loose and crack will appear on the binder under tension,and interstices appear between the binder and AP.The exposed area of AP increases,furthermore the pro-pellant burning is faster,and the burning ratio is bigger.关键词
复合推进剂/燃速/拉伸应变/粘合剂/疏松/裂纹Key words
composite propellant/burning rate/tensile strain/binder/porosity/crack分类
航空航天引用本文复制引用
胡松启,陈静,邓哲,刘迎吉..复合推进剂拉伸应变条件下燃速变化计算分析[J].固体火箭技术,2014,(5):672-677,683,7.基金项目
西北工业大学基础研究基金( JC201221) （ JC201221）
航天支撑基金( NAXA0003)。 （ NAXA0003）
