大长径比变后掠翼导弹的颤振特性分析  

Flutter Characteristics Analysis of Variable Swept Wing Missile with Large Aspect Ratio

作　　者：王颖 李裕 刘力[1] 李彦彬[1] WANG Ying;LI Yu;LIU Li;LI Yan-bin(Air and Missile Defense College,Air Force Engineering University,Xi’an Shaanxi 710051,China)

机构地区：[1]空军工程大学防空反导学院,陕西西安710051

出　　处：《计算机仿真》2024年第4期55-58,493,共5页Computer Simulation

基　　金：基于集员估计框架预测滤波的高超飞行器精确导航技术研究(61703424)。

摘　　要：为了增大导弹的内部空间,同时减小空气阻力,导弹外形日益趋于大长径比机构,而这样的设计易造成导弹低频颤振等明显的气动弹性问题。为解决上述问题,可通过调节导弹的气动外形,改变系统气动特性,达到抑制颤振的作用。针对变体飞行器技术之一的变后掠翼展开研究,围绕大长径比导弹的颤振问题,揭示飞行速度对导弹飞行时颤振特性的影响规律,而后验证通过改变导弹后掠角主动抑制导弹颤振方法的可行性,为解决导弹的颤振问题提供理论支撑。In order to increase the internal space of the missile and reduce the air resistance,the missile shape increasingly tends to a large aspect ratio mechanism,and such a design is easy to cause obvious aeroelastic problems such as low-frequency flutter of the missile.This problem can be solved by adjusting the aerodynamic shape of the missile and changing the aerodynamic characteristics of the system to suppress flutter.In this paper,the variable swept wing,one of the variant aircraft technologies,is studied.Around the flutter problem of missiles with large aspect ratio,the influence law of flight speed on the flutter characteristics of missiles in flight is revealed,and then the feasibility of actively suppressing the flutter of missiles by changing the sweep angle of missiles is verified,which provides theoretical support for solving the flutter problem of missiles.

关 键 词：大长径比导弹 气动特性 颤振 变后掠翼 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]