有限元法在机翼整体壁板成形中的应用

The Application of Finite Element Method in the Forming of Aircraft Wing Skin Panels

喷丸是现代飞机机翼整体壁板成形的首选方法 ,但喷丸成形参数的选择在很大程度上依赖于实验数据和操作经验 ,耗时费资。有限元方法的应用可部分解决这一难题。分析了喷丸成形的变形特点 ,介绍了Homer的有限元设计方法、Levers的比拟法及笔者使用的变形等效模拟法 ,并对

Shot peening has become a successful method for the forming of aircraft wing skin panels for several years, but the determination of peening parameters is still relied heavily on the empirical data and the experience of technicians. The application of peen forming to a new skin design must be determined experimentally and hence it is expensive, time consuming and tedious. The application of finite element method can partially solve this troublesome problem. In this paper, the main idea of a finite element design method and a finite simulation method proposed by S.E. Homer and A. Levers respectively are outlined. The deformation equivalence method presented by author is introduced in detail. The properties of these methods are listed.