基于Mori-Tanaka有限元法的粘弹复合推进剂非线性界面脱粘  

Nonlinear interface debonding of viscoelastic composite propellant using Mori-Tanaka finite element method

作　　者：刘承武[1] 阳建红[1] 邓凯[1] 陈飞[1] 张晖[1] 

机构地区：[1]第二炮兵工程学院,陕西西安710025

出　　处：《推进技术》2011年第2期225-229,共5页Journal of Propulsion Technology

摘　　要：为了研究复合推进剂基体的大应变粘弹性和界面的非线性脱粘,将Mori-Tanaka法和有限元数值求解相结合,提出了一种Mori-Tanaka有限元法。同时,为验证该方法的有效性,针对推进剂夹杂随机填充的特点,提出了一种含非线性界面脱粘的数值仿真法。最后以某推进剂配方为算例,对两种方法的计算结果了进行比较。结果表明,两种方法结果接近,从而验证了Mori-Tanaka有限元法的有效性,且该方法计算量小,极大的提高了计算效率。两种方法的提出,可以有效的用来分析界面对推进剂力学性能的影响。To investigate the composite solid propellant with large strain viscoelasticity in the matrix and interface nonlinear debonding around the filled particles,the Mori-Tanaka finite element method（MTFEM） was presented combing the Mori-Tanaka method and finite element method.At the same time,in order to verify its effectiveness,a simulation method for the interface debonding of the composite solid propellant consisting of random filled particles was also presented.Finally,a computational case of one kind of composite solid propellant was investigated.It is demonstrated that the results got from these two methods are close and the MTFEM is effective.The computational time can be reduced dramatically and computational effectiveness can be increased greatly by using MTFEM.The debonding of the composite solid propellant can be analyzed effectively through these two micromechanical methods.

关 键 词：复合推进剂 Mori-Tanaka法 数值仿真 界面脱粘 

分 类 号：V512.3[航空宇航科学与技术—航空宇航推进理论与工程]