某电磁弹射无人机复合材料机翼结构优化设计与分析

OPTIMIZATION DESIGN AND ANALYSIS OF COMPOSITE WING STRUCTURE OF A CERTAIN ELECTROMAGNETIC-LAUNCH UNMANNED AERIAL VEHICLE

无人机已经成为航空领域重要成员之一。在无人机初步设计阶段,为减轻其结构重量,采用复合材料设计。复合材料在比强度和比刚度以及抗振和加工制造等方面优于其他传统材料,在无人机结构中得到了广泛的应用。由于复合材料层合板在生产加工过程中具有可设计性,在复合材料中已经成为使用最多的一种结构形式。以某型号电磁弹射无人机机翼为研究对象,建立了复合材料机翼结构的有限元模型,将机翼的结构重量作为优化目标,以机翼翼尖挠度和复合材料失效因子为约束条件,应用工程优化软件对复合材料翼面结构进行自由尺寸优化,整个优化过程需同时满足机翼强度及刚度要求。最终自由尺寸优化结果表明,复合材料的铺层比例和厚度分布在优化后得到了重新设计,比较之前的结构方案,优化后的铺层设计能够有效降低机翼结构质量,实现减重的优化目标。

Unmanned Aerial Vehicle has been one of the important members in the aviation industry. For lightening the weight of UAV structures in the preliminary design phase,composite material is used. Composite material has been widely used in UAV structures because of various of excellent performances,such as strength and stiffness ratio,shakeproof property as well as the performances in the process of manufacturing. Meanwhile,composite laminate has excellent designable property in the process of manufacturing,so it is widely used among all the types of composite materials. In this paper,the wing structure of a certain electromagnetic-launch unmanned aerial vehicle is selected as the research objective,and the finite element model of a composite wing structure is created. Then,the mass of the structure is chosen as the objective function,the displacement of wingtip and the failure index are chosen as constraints,and the composite wing structure is optimized by using the engineer software. The results should meet the demand of strength and stiffness during the optimization. The final optimization results show that the ratio and thickness of plies of the composite material has been redesigned. Compared with the previous designing scheme,the weight of wing structure is obviously reduced after the free-sizing optimization,which could achieve the objective of optimization.