摘要
基于某型导弹偏心销结构舱段连接方式,推导了连接面上偏心销的最大剪力公式,并对该结构开展了有限元分析和静力试验。有限元结果表明在给定载荷作用下,偏心销材料进入塑性,偏心销限位环发生强度破坏;连接面舱体结构局部材料进入塑形,但不会发生强度破坏;试验结果验证了上述仿真结果,并根据最大剪力公式建立单个偏心销有限元计算模型是一种比较稳妥的方法。
For cabin connection with eccentric pin based on certain missile, the formula of the maximum shear of the eccentric pin in the cabin connection was derived. And the finite element analysis and Experiment was carried out. Simulation results show that, under the given load, material of eccentric pin yield with destruction of limit ring, and local part of cabin connection yield with- out destruction of structure strength.The experimental results are in agreement with the finite element method.Moreover,the estab- lishment of a single eccentric pin finite element calculation model based on the maximum shear formula is a relatively safe method.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2017年第3期353-357,共5页
Journal of Solid Rocket Technology
基金
上海航天科技创新基金(SAST201406)
关键词
偏心销
舱段连接
强度
有限元
eccentric pin
cabin connection
strength
finite element
