一种大展弦比重叠式可折叠弹翼组件气动布局应用研究

以一种大展弦比“重叠式”可折叠弹翼组件为研究对象,采用数值模拟与风洞试验相结合的方法,分析了该弹翼组件气动布局在小型化滑翔型制导航空弹药中的应用,对弹翼组件的外形参数进行了优化设计。通过三自由度弹道仿真计算验证了该弹翼组件气动布局的气动特性及滑翔性能。研究结果表明:这种“重叠式”可折叠弹翼组件气动布局可以大幅度减小折叠弹翼在收拢状态下的外形尺寸; 在同样的弹体结构和尺寸包络限制下,弹翼弦长可达到传统面对称平直弹翼的2倍,有效增大了升力面面积,实现了在外形尺寸限制下的高升阻比气动布局; 该弹翼组件在结构上更为简洁紧凑,解决了传统的对折式弹翼形式在小型化制导弹药上应用所面临的结构效率和气动增益受限的问题。

Research on Aerodynamic Layout of a High Aspect-ratioOverlapped Foldable Wing Components

An overlapped foldable wing components with large aspect ratio were studied. The aerodynamic configuration of the wing components applied in the miniaturized gliding guided aerial ammunition was anayzed by numerical simulation and wind tunnel test,and the configuration parameters of the wing components were optimized. The aerodynamic characteristics and gliding performance of the wing components were verified by 3-DOF trajectory simulation. The results show that the aerodynamic layout of overlapped foldable wing components can greatly reduce the shape size of folded wing under the closed state. Under the restriction of the same structure and size envelope,the chord length of the wing can be twice as long as that of the symmetrica flat wing,and the area of lift surface can be effectively increased,and the high lift-drag ratio aerodynamic-configuration under size limitation was obtained. The structure of the wing components is simple and compact. The problems of structural efficiency and limited aerodynamic gain can be solved when the traditional folded wing is applied to miniaturized guided munition.