巡飞弹扇式折叠翼结构优化研究  

Structural Optimization of Fan Style Folding Wing of Cruise Missile

作　　者：许兆庆[1] 吴军基[1] 薛晓中[1] 

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《南京理工大学学报》2011年第4期494-497,共4页Journal of Nanjing University of Science and Technology

基　　金：国家部委预先研究项目(102080403)

摘　　要：对某巡飞弹的新型扇式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,取中翼、后翼长度及其与前翼连结点做为设计变量;采用FLUENT软件计算了相关的气动升力,将前、中、后翼近似简化为受均布线载荷作用的三根铰链悬臂梁,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,采用复形调优法进行迭代计算,代入约束条件,得出了最优结果。结果表明:采用扇式弹翼既能有效地提高升力,也能大幅减小弹翼的结构变形。The structural optimization of the new fan style wing of a certain cruise missile is investigated here.The optimum object is to minimize the wing tip deformation of the front wing;the design variables are length of the middle and rear wings and their joined points.The aerodynamic forces are calculated using the software FLUENT.All the wings are simplified to three joined cantilever beams which undergo the distributed static loads.The function of the object and the design variables are established through the statics mechanics analysis and the optimal mathematic model is conducted.The complex optimal method is adopted for iterative calculation after the constraint conditions are input.The optimization results indicate that the fan style wing can not only increase the lift force effectively,but also reduce the structure deformation of the wing obviously.

关 键 词：巡飞弹 扇式弹翼 优化 结构变形 

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]