一种弹翼颤振临界速度的快速计算方法  

A Convenient Method for Analysis the Critical Flutter Speed of Wings

作　　者：吴小胜[1] 黄晓鹏[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《弹箭与制导学报》2004年第3期68-70,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中提出了一种分析亚音速下弹翼颤振临界速度的工程计算方法,其中弹翼的固有振动特性用有限元方法计算,利用片条理论计算弹翼变形诱导的广义非定常气动力矩阵,从而得到单独翼的颤振模型方程。据此方法编制了相应的计算程序,以固支条件下某典型翼面为例,利用所编程序计算得到了弹翼在海平面飞行条件下的V∞-g图,给出了弹翼的颤振临界速度,对颤振特性进行了分析。An engineering method for calculating the critical flutter speed of wings in subsonic is discussed in this paper. Based on the nature vibrational characteristics of the flat wing calculated by finite element method, generalized unsteady aerodynamic forces matrix induced by the wing deformation is gotten by using strip theory, and thus the flutter model equation of the single wing is given. A program designed according to this method. And critical flutter speed of a wing supported simply is analyzed by this program. The V_∞-g figure of the flat wing under the sea level is given, too. From it the critical flutter speed of the wing is obtained.

关 键 词：颧振 固有振动 非定常气动力 片条理论 临界速度 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术]