身-翼-舵组合体高超声速变攻角颤振计算  

Flutter Analysis of Body-Wing-Rudder Configurations at Hypersonic Velocities and Variable Attack-Angles

作　　者：刘超峰[1] 李海东[1] 杨炳渊[1] 

机构地区：[1]上海航天技术研究院第八设计部,上海200233

出　　处：《宇航学报》2011年第8期1663-1669,共7页Journal of Astronautics

摘　　要：推广和发展了原来只能用于二维升力面的当地流活塞理论,形成可解决包括弹身、弹翼、舵面、身-翼组合体、身-翼-舵组合体大攻角颤振计算的新方法。其中气动力计算采用CFD数值仿真与工程算法相结合的方法,求解结构运动方程时则利用状态空间法进行时域仿真。对某身-翼-舵组合体型号的计算表明该型号颤振动压随马赫数和攻角都呈现先增加后下降的变化趋势;在大马赫数和大攻角作用时,颤振动压有明显的下降;在较小攻角状态下颤振动压不降反升,与传统文献报导单独分枝颤振动压随攻角增大而单调下降不同,表明复杂外形组合体的气动弹性稳定性受到多种因素的共同作用,颤振特性更加复杂。计算结果表明弹体稳定性与飞行姿态相关,同时也证明了本文方法在高超声速复杂外形飞行器提气动弹性分析中的有效性。The local piston theory of two-dimensional lifting surface is developed and a new method of flutter analysis is proposed for the configurations of body-wing-rudder at hypersonic velocity.In this method the aerodynamic force is calculated by the combined method of CFD（Computational Fluid Dynamics） simulation and engineering algorithm.The structural motion equation is solved by the state space method in time domain.The computational result of a missile in body-wing-ruder configuration shows that the critical dynamic pressure firstly increases then decreases as the Mach number and the attack-angle increase.The phenomenon of the increasing critical dynamic pressure at a small attack-angle is different from the monotonously decreasing in the traditional literatures,which indicates that the aeroelasticity stability of a configuration at high velocity is affected by multiple factors and the flutter characteristic becomes more complicated.The computational result also demonstrates that the above method is effective and efficient for aerocrafts in complicated shape at hypersonic velocity.

关 键 词：气动弹性 颤振 高超声速飞行器 当地流活塞理论 

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]