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
王颖 1李裕 1刘力 1李彦彬1
作者信息
- 1. 空军工程大学防空反导学院,陕西 西安 710051
- 折叠
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.
Abstract
In order to increase the internal space of the missile and reduce the air resistance,the missile shape in-creasingly 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 theoreti-cal 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Key words
Large aspect ratio missile/Aerodynamic characteristics/Flutter/Variable swept wing引用本文复制引用
出版年
2024
NETL
NSTL
万方数据