纤维缠绕固体火箭发动机壳体大变形有限元分析与仿真软件介绍  

Finite Element Analysis of Large Deformation and Emulation for Filament-Wound Solid Rocket Motor Case

作　　者：戴进[1] 赫晓东[1] 杜善义[1] 

机构地区：[1]哈尔滨工业大学

出　　处：《固体火箭技术》1996年第2期21-25,共5页Journal of Solid Rocket Technology

摘　　要：将全拉格朗日（Ｔ．Ｌ）法用于轴对称大变形［１］问题，并对纤维缠绕固体火箭发动机壳体进行有限元分析，在此基础上完成了纤维缠绕复合材料壳体大变形有限元分析软件的编制，对壳体的缠绕情况、有限元网格划分、应力、应变、位移等的有限元计算进行一体化仿真。The Total Lagrange method is applied in the axisymmetric and large deformatinn problem. Meanwhile, the finite element analysis on the filament wound solid rocket motor case is carried out. Based on the above analysis, the software of axisymmetric finite element analysis for filament-wound composite case is produced, in which the winding condition, finite element grids generation, strain, stress and displacement analysis are performed and emulated.

关 键 词：固体推进剂 火箭发动机 变形 有限元 复合材料 

分 类 号：V435.22[航空宇航科学与技术—航空宇航推进理论与工程] V414.8