亚音速飞行的某型导弹舵面颤振特性研究

Research on Flutter Characteristic of Some Type Missile′s Control Surface in Subsonic Flight

颤振特性研究已广泛应用于飞行器设计中。在导弹飞行中,容易发生颤振的部位是舵面与舵机的结合处。使用ANSYS有限元分析软件建立了某型导弹舵面的动力学有限元模型,并应用Block Lanczons求解器对其进行固有模态分析。在导弹亚音速飞行条件下,采用片条理论计算模拟舵面变形诱导的气动力,再将颤振方程转换到以各阶模态振型为基的模态空间上,得到在模态空间下简化的舵面颤振方程。最后应用MATLAB软件编制程序,用V-g法求解舵面颤振方程。对其他战术导弹舵翼面的设计分析具有一定的参考意义。

The flutter characteristic has been widely used in the design of vehicles.In the missile flight,the flutter is prone to happen at the part of the combination of control surface and steering gear.We used finite element analysis（ANSYS） to establish the dynamic finite element model of some type missile,and applied Block Lanczons solver to analyze the intrinsic model of some type missile.We calculated analog control surface deformation induced aerodynamic force using strip theory on the subsonic flight condition,and then transformed the flutter equation to the modal space based on the order components of mode shapes,then got the simplified flutter control surface equation in the modal space.Finally,we applied the Matlab software to program to solve the flutter control surface equation using the V-g method.