固体火箭发动机柔性接头的结构分析  

Structural analysis on solid rocket motor flexible joint

作　　者：曹翠微[1] 陈伟民[2] 蔡体敏[1] 李敏[3] 

机构地区：[1]西北工业大学航天学院 [2]中国科学院力学研究所,北京100080 [3]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《推进技术》2006年第5期450-454,共5页Journal of Propulsion Technology

摘　　要：为了进行固体火箭发动机柔性接头结构分析,建立了三维超弹结构有限元模型,用单轴拉伸与简单剪切橡胶材料试验数据,采用三阶橡胶本构模型,载荷跟随变形的方式处理驱动载荷方向的变化,给出了典型载荷状态下的计算结果。获得了柔性接头应力应变分布,随着容压增大,弹性件径向拉应力的区域迅速减少,获得相同转角的驱动载荷将会减小,该现象与试验结果吻合较好。The 3D hyperelastic finite element model of the solid rocket motor flexible joint was set up to analyze structural characters, The experimental data of axial-tension and simple shear test were fitted to achieve the hyperelastie behavior parameters. The 3rd order deformation rubber stress-strain model was adopted and the load direction changed with the deformation was taken into account. The calculated results under the condition of typical loads and the stress and strain distributions of the flexible joint were obtained. The domain and amplitude of radial tension stress and the load achieving same angle of rotation decrease with enhancing pressure. The results agreed with the data of experiments well.

关 键 词：超弹性 弹性体 力学性能 有限元法 固体推进剂火箭发动机 

分 类 号：V435.3[航空宇航科学与技术—航空宇航推进理论与工程]