飞机复合材料蒙皮的优化设计  

Optimal Design of Aircraft Skin with Composition Material

作　　者：杨军[1] 张亚辉[2] 朱继宏[2] 常楠[1] 

机构地区：[1]中航工业成都飞机设计研究所,成都610091 [2]西北工业大学机电学院,西安710072

出　　处：《机械制造》2013年第11期44-47,共4页Machinery

基　　金：国家自然科学基金资助项目(编号:11002113;11172236);西北工业大学基础研究基金资助项目(编号:JC20120229)

摘　　要：从工程实际出发,提出了一种针对连续纤维增强复合材料蒙皮的三级优化设计方案,能够从铺设角、铺层比例、铺层厚度、铺层块形状及位置以及铺层次序等多个方面给出层合板的设计参数。在设计过程中,加入了一系列与实际加工制造非常吻合的制造性约束,使复合材料层合板构件的优化设计结果具有非常好的可制造性。运用该方法对某型飞机复合材料机翼前缘蒙皮进行了优化设计,取得了良好的设计结果。A three stage optimum design for continuous fiber reinforced composite laminate skin is presented based on the engineering practice that can provide laminated design parameters from multiple aspects including ply angle, ply percentage, ply thickness, shape and position of ply block and ply sequence. In the design process, a series of manufacturing constraints consistent with the practical manufacturing are added to enable the optimum design of the laminated member with composition material offering superduper manufacturability. This approach has been applied to the optimum design of the leading skin of composite wing for a certain type of aircraft and obtains a sound design results.

关 键 词：优化设计 复合材料 层合板 蒙皮 

分 类 号：TH122[机械工程—机械设计及理论] V225.3[航空宇航科学与技术—飞行器设计]