固体火箭发动机接头组合件三维弹塑性有限元分析  

Three-dimensional elastoplastic finite element analysis of the back-joint subassembly of SRM

作　　者：杜建科[1] 乐发仁[2] 沈亚鹏[1] 何景轩[2] 

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室,西安710049 [2]中国航天科技集团公司第四研究院,西安710025

出　　处：《固体火箭技术》2003年第3期14-17,共4页Journal of Solid Rocket Technology

摘　　要：对固体发动机复合材料壳体接头组合件在内压作用下的应力变形进行了三维有限元分析。分析了两种不同厚度的水压堵益对结构变形的影响,考虑了螺栓、堵盖、接头等金属材料的塑性性质,复合材料按正交各向异性体处理。结果说明,在内压作用下,较厚的堵盖(40mm)和接头在外缘发生分离,使得接头肩部变形略大;而较薄的堵盖(28mm)与接头内缘发生分离,对密封结构不利。在内压作用下,复合材料和接头侧面也发生分离。该分析方法和结果可供接头及其密封设计提供参考。The back-joint subassembly of a SRM shell is analyzed based on the three-dimensional finite element method. The effect on the deformation of the configuration due to the closure thickness, plastic properties of the metal materials and orthogonal anisotropy of the composite materials are considered. The results show that under the inner pressure, the thicker closure (40mm) is separated from the joint at the outside fringe of the closure and results in a larger deformation of the joint shoulder; and the thinner one (28mm) is separated from the joint at the inside fringe of the closure, so it is harmful to the airproof structure. These factors should be taken into account when a joint and a closure are designed. The composite materials are severed from the joint flank, too. The processing method and the calculated results would be help to the design of the joint and the airproof structure.

关 键 词：固体火箭发动机 复合材料壳体 接头 弹性变形 塑性变形 有限元分析 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]