超音速弹翼非线性颤振分析与控制  

Nonlinear flutter analysis and control of supersonic missile wings

作　　者：贾尚帅[1] 丁千[1] 刘炜[2] 

机构地区：[1]天津大学机械学院力学系,天津300072 [2]中国航天科工集团公司二院二部,北京100854

出　　处：《振动与冲击》2012年第13期108-112,共5页Journal of Vibration and Shock

基　　金：国家自然科学基金项目(10972154)

摘　　要：研究超音速弹翼非线性气动弹性稳定性与主动控制问题。采用三阶活塞理论建立含间隙弹翼非线性气动弹性动力学方程,分别利用Hopf分岔理论及数值方法给出系统的线性与非线性颤振速度,应用基于微分几何法及二次型最优控制相结合的方法,设计非线性系统控制器。最后分析控制器及系统参数对控制效果的影响。仿真结果表明设计的控制器可有效地实现对非线性系统颤振的抑制。The nonlinear aeroelastic stability and active control of supersonic missile wings were investigated. In accordance with the theory of third-order piston, the nonlinear aeroelastic dynamic equations with freeplay nonlinearity were derived. Both linear and nonlinear flutter speed were obtained by using hopf bifurcation theory and numerical method respectively. The design method based on differential geometry and quadratic optimal control for nonlinear system controller was used to stabilize the flutter. The influences of the controller and the system parameters were analyzed. The simulation result shows that the method based on differential geometry and linear quadratic optimal is an effective way to control nonlinear flutter.

关 键 词：气动弹性 超音速 间隙 HOPF分岔 极限环振动 非线性控制 

分 类 号：O322[理学—一般力学与力学基础] V215.3[理学—力学]