变后掠翼导弹气动特性仿真分析  

Analysis on aerodynamic characteristics of variable backswept-wing missiles

作　　者：郜阳 李彦彬[2] 王颖 吕锐 张泽 GAO Yang;LI Yan-bin;WANG Ying;LYU Rui;ZHANG Ze(Graduate College,Air Force Engineering University,Xi'an 710051;Air and Missile Defense College,Air Force Engineering University,Xi'an 710051)

机构地区：[1]空军工程大学研究生院,陕西西安710051 [2]空军工程大学防空反导学院,陕西西安710051

出　　处：《机械设计》2022年第3期68-73,共6页Journal of Machine Design

基　　金：航空基金项目(20151396013)。

摘　　要：随着世界军事技术的迅猛发展,将变体技术应用于导弹设计,使之具有更强的飞行适应能力变得尤为重要。变后掠翼是满足变体导弹飞行特点的重要手段,通过改变气动布局,使导弹具有适应低速、亚声速、跨声速和超声速飞行状态的能力。文中参考“战斧”导弹外形特点,建立了变后掠翼导弹模型,并用计算流体动力学软件对5组不同后掠角导弹模型进行了研究,对比分析了不同速度下的气动特性。通过对变后掠翼导弹的仿真计算,总结了8组马赫数对应的升阻比随后掠角的变化规律,给出了不同飞行条件下应采用的后掠角方案,为今后变体导弹的气动外形设计提供参考。With the rapid development of military technologies in the world,it is particularly important to apply the variable technology to the missile design.Thus,missiles will have stronger flight adaptability.The variable backswept wing is an important means to meet the flight characteristics of variable missiles.By changing the aerodynamic layout,the missiles can adapt to the low-speed,subsonic,transonic and supersonic flight status.In this article,referring to the shape characteristics of the“Tomahawk”missile,a model of the variable backswept-wing missile is set up.5 groups of missile models with different backswept angles are explored by means of the computational fluid dynamics software,and the aerodynamic characteristics at different speeds are compared and analyzed.Through a series of simulation and calculation of the variable backswept-wing missile,the changing law of the lift-drag ratio followed by the backswept angles corresponding to 8 groups of Mach numbers is worked out,and the suitable schemes are given when the backswept angles are adopted under different flight conditions.This study provides reference for aerodynamic shape design of variable missiles in the future.

关 键 词：变体导弹 变后掠翼 气动特性 仿真计算 升阻比 

分 类 号：TJ011.3[兵器科学与技术—兵器发射理论与技术]