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一、引言飞行器的结构要求轻巧、坚固、可靠。因此,要求构件的强度核算工作必须尽力准确。近十多年来发展起来的有限元素法已成为飞行器结构强度核算工作的得力工具。各国力学工作者已经发展了许多板壳元。过去,我们常用的元素是Zienkienwicz·O·C和华东水利学院提出的非协调元。这二种元素的共同缺点是元素边界上一阶法向导数不连续,因而精度较低。元素边界位移完全协调的高精度元素,虽然可以保证收敛性,应力计算效果也较好,但公式又太复杂,刚度矩阵的阶数太高。用于飞行器结构的强度校核计算,这些元素都不够理想。
I. INTRODUCTION The structure of the aircraft requires lightweight, sturdy and reliable structure. Therefore, the requirement of component strength calculation must be as accurate as possible. The finite element method developed over the past decade has become an effective tool for the structural strength calculation of aircraft. Mechanics in many countries have developed many shell elements. In the past, we commonly used element is the non-coordination element proposed by Zienkienwicz · O · C and East China Institute of Water Resources. The common disadvantage of these two elements is the discontinuity of the first-order normal at the element boundary, and hence lower accuracy. Elements with perfectly coordinated high-precision boundary-displacement can guarantee the convergence and stress calculation, but the formula is too complicated and the order of the stiffness matrix is too high. For the strength of the aircraft structure check calculation, these elements are not ideal.