摘要
建立一种适用于复合材料结构的多级优化方法。第一级优化包括系统级优化和元件级优化。系统级优化以板厚度或杆横截面为设计变量，从Ｋｕｈｎ－Ｔｕｃｋｅｒ出发导出改进设计变量的迭代式；元件级优化保持最优迭层板厚度和节点位移不变，利用线性规划技术使结构应变能最大，得到最优分层厚度。第二极优化以纤维铺向角为设计变量，以降低各约束点处位移为目标进行优化，提高结构刚度。算例研究复合材料翼面盒段满足强度要求和挠曲变形规律要求时的优化设计，结果表明该方法计算方便，接口简单，收敛迅速。
This paper treats of a new multi - level. optimum design technique of the composite wing structure The optimiation prooess is divxded into two levels system level and component. In the systera level the thicknesses of laminated compsite plata represent the design variables. The optimality crterion method based on Kukn -Tucker condition is used to modify the doign variables.In the component level, to keep the thickness of the laminated composite plate and the nodal. dbplacement ,the -linear programming technique is used to obtain the optimal ply thicknesses of the laminated plated,maximizing the structural strain energy. The second level optimization uses , the fiber orientations as doign varables in order to reduce the specifieddisplaoments.As a result,the stiffness of the structure is enhanoed. The computation examples concerning the optimum design are meant to testify that a com- posite wing box structure satisfies the strength and displacement constraints . The calculation results show that this technique is highly effective and efficent .
出处
《中国民航学院学报》
1997年第1期15-21,共7页
Journal of Civil Aviation University of China
关键词
复合材料结构
优化设计
多级优化
机翼
composite structure optimum design multi - level optimization
