固体火箭技术2024，Vol.47Issue(2)：269-277,9.DOI:10.7673/j.issn.1006-2793.2024.02.016
固体火箭发动机复合材料壳体铝合金接头失效有限元分析
Finite element analysis of aluminum joint failure in composite case of solid rocket motor
张佳熙 1史宏斌 1丁文辉 1王立强 1徐向毅2
作者信息
- 1. 西安航天动力技术研究所,西安 710025
- 2. 中国人民解放军 93170 部队,西安 710065
- 折叠
摘要
Abstract
In order to study the fracture failure law of aluminum alloy joints in the snap connection structure of composite case,the finite element model of aft dome of case was established,and the hydroburst test was carried out with a solid motor case as the ob-ject.The applicability of the equivalent stress criterion and the maximum principal stress criterion of three kinds of aluminum alloy joints was compared through the stress and strain analysis of the simulation and experimental results.By analyzing and processing the simulation data of the previous fracture joints and the fracture joints in this paper,the relationship between the maximum principal stress and the elongation,yield limit and tensile limit of the material was studied.Combined with the empirical formula and finite ele-ment simulation,the internal pressure of the fracture of the clasp connection structure with different aluminum alloy materials and dif-ferent sizes was analyzed and compared with the experimental results.The results show that the error between the calculations of the fi-nite element model established in this article and the measured data of water pressure experiments is within 4.9%,which verifies the correctness of the finite element model.Compared to the equivalent stress criterion,the maximum principal stress criterion is more ac-curate in determining the weak position of the joint snap ring groove,and an empirical formula for the fracture coefficient of the maxi-mum principal stress when fracture occurs at the joint snap ring groove is extracted and summarized;Based on this empirical formula and combined with finite element simulation,the errors between the internal pressure of the aluminum alloy joint during fracture and the experimental burst internal pressure are 4.7%and 3.6%,respectively,which meet the needs of engineering applications.关键词
固体火箭发动机/复合材料壳体/卡环连接结构/延伸率/抗拉极限/屈服极限Key words
solid rocket motor/composite case/snap ring connection structure/elongation rates/tensile strength/yield strength分类
航空航天引用本文复制引用
张佳熙,史宏斌,丁文辉,王立强,徐向毅..固体火箭发动机复合材料壳体铝合金接头失效有限元分析[J].固体火箭技术,2024,47(2):269-277,9.
