巡飞弹钻石背折叠翼结构优化设计  

Structural Optimization of the Diamond Back Wing of Cruise Missile

作　　者：许兆庆[1] 吴军基[1] 薛晓中[1] 李培林[2] 

机构地区：[1]南京理工大学动力工程学院,南京210094 [2]中国航天科技七院七部,成都610100

出　　处：《机械设计与研究》2011年第1期87-90,共4页Machine Design And Research

基　　金：国家部委预先研究基金资助项目(102080403)

摘　　要：对某型巡飞弹的钻石背弹翼进行了结构优化,将前翼的翼尖变形最小做为优化目标,取后翼长度及其与前翼连结点做为设计变量;将前、后翼近似简化为受均布线载荷作用的两根铰链悬臂梁,通过对此超静定结构的受力分析,建立了优化目标与设计变量之间的函数表达式,导出其优化数学模型,分别采用复形调优法与遗传算法进行迭代计算,代入约束条件,得出了最优结果;结果表明,最优时后翼的前掠角非常小,采用钻石背弹翼既能有效的提高升力,也能大幅减小弹簧的结构变形,是非常优良的结构布局形式。The structural optimization of the diamond back wing of certain cruise missile is presented in this paper, the optimum object is to minimize wing tip deformation of the front wing. The design variables are length of the rear wing and the joined point of two wings. The aerodynamic forces are calculated by the software FLUENT. The front and rear wingsare simplified as two joined cantilever beams which undergone the distributed static loads. The function of the object and the design variables is established through the dynamic analysis and the optimal mathematic model is deduced. The complex optimal method and the genetic algorithms method are adopted respectively for iterative calculation after the constraint conditions being input. The optimization results indicate that the sweepforward angle of the rear wing will be very small, and the diamond back wing can not only increase the lift effectively, but also reduce the structure deformation of the wing obviously.

关 键 词：巡飞弹 钻石背弹翼 结构优化 

分 类 号：V214.19[航空宇航科学与技术—航空宇航推进理论与工程]