基于遗传算法的复合推进剂粘弹性本构参数研究  

Investigation of Viscoelastic Constitutive Parameters of Composite Propellant Based on Genetic Algorithm

作　　者：郑健[1] 韩波[1] 周长省[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《弹道学报》2014年第1期22-25,共4页Journal of Ballistics

基　　金：国防重点预研基金项目;中央高校基本科研业务费专项资金资助项目(NUST2011XQTR13)

摘　　要：为了准确地获得HTPB复合固体推进剂的粘弹性本构参数,研究了基于遗传算法的全加载历程松弛模量获取方法。利用DMA实验机系统进行了HTPB复合固体推进剂试件的松弛实验,分别使用传统计算方法和遗传算法获得了HTPB推进剂的松弛模量数据。将该结果应用于真实松弛实验的加载过程中,结果表明:传统方法忽略了实验过程中的加载阶段,计算得到的松弛模量小于实验值;而基于遗传算法得到的松弛模量,精确度较高,是获取复合固体推进剂松弛模量一种较好的方法。In order to obtain viscoelastic constitutive parameters of HTPB composite solid propellant accurately,the method of acquiring relaxation modulus based on genetic algorithm was studied during the whole loading process.Relaxation experiments of HTPB composite solid propellant specimen were carried out by using the DMA experiment system.Relaxation modulus of HTPB propellant was obtained by adopting the traditional calculation method and genetic algorithm respectively,and the results were applied in the loading process of real relaxation exper-iments.The results show that due to the traditional method ignoring the loading stage in experimental process,the calculated relaxation modulus is smaller than the experimental value. The relaxation modulus based on genetic algorithm has higher precision,so it is a better method of obtaining the relaxation modulus of composite solid propellant.

关 键 词：复合推进剂 本构参数 遗传算法 松弛模量 粘弹性 

分 类 号：TJ55[兵器科学与技术—军事化学与烟火技术] V512[航空宇航科学与技术—航空宇航推进理论与工程]