导弹复合材料立尾的动力特性分析  

Dynamic Characteristic Analyses of Composite Tail Fin of a Missile

作　　者：庞志一 

机构地区：[1]航天工业总公司三院三部

出　　处：《强度与环境》1995年第1期14-21,共8页Structure & Environment Engineering

摘　　要：对Hellinger－Reissner变分原理进行了详尽论述。依据该变分原理推导了基于折线假设的复合材料层压板元素的刚度矩阵，复合材料面板蜂窝夹芯元素的刚度矩阵。在形成元素刚度矩阵时，在子域一级求逆能节省大量机时。介绍了动力特性的分析和试验方法。运用H－R元素计算了导弹复合材料立尾的动力持性，取得了满意的结果。In this paper, the H-R varitional principle have been examined in detail. According to thatvariational principle the element stiffness matrices for composite laminated plate and sandwich plate withcomposite face and honeycomb core were deduced. Great computer time saving was achieved due to adopting first-level inversion in the subfield. Compatibility 'between plate element and beem element was solued.By using H-R element, dynamic characleristics of a composite tail fin were calculated and satisfactory results were obtained.

关 键 词：复合材料 层压板 垂直尾翼 结构动力学 导弹 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]