固体火箭技术2012，Vol.35Issue(1)：108-113,6.
固体火箭发动机复合材料壳体裙连接区结构数值分析
Numerical analysis on lap structure between skirt and composite SRM case
王立强 1任全彬 1尤军峰1
作者信息
- 1. 中国航天科技集团公司四院四十一所,燃烧、流动和热结构国家级重点实验室,西安710025
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摘要
Abstract
The FEM structural analysis of the lap structure between skirt and composite case of SRM (LBSCC) when bearing the thrust load was carried out based on the ANSYS FEM software. The simplified 3D analysis model was built referring to the case structure and loading distribution characteristic. The rationalization of the simplified model and validity of the FEM results were confirmed according to the comparing study of simulation results with experiment data of a APMOC fiber wound composite case. Finally, the numerical analysis and structural improvement design of a carbon filament winding cases was implemented. Analysis results show that increasing the thickness or the material stiffness of the reinforced layers can decrease the strain extreme significantly and improve the strains distribution of the case. The load bearing capability of the improved structural design can be increased by about 20%.关键词
发动机壳体裙连接区/纤维缠绕复合材料壳体/有限元结构分析Key words
lap between skirt and case/filament winding composite material case/finite element structural analysis分类
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王立强,任全彬,尤军峰..固体火箭发动机复合材料壳体裙连接区结构数值分析[J].固体火箭技术,2012,35(1):108-113,6.
