超音速弹翼非线性颤振分析与控制

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振动与冲击 ›› 2012, Vol. 31 ›› Issue (13) : 108-112.

论文

超音速弹翼非线性颤振分析与控制

贾尚帅 1 ，丁千 1 ，刘炜 2

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Nonlinear Flutter Analysis and Control of the Supersonic Missile Wings

Jia Shang-shuai1 Ding Qian2 Liu Wei 2

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摘要

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。

Abstract

Abstract: The nonlinear aeroelastic stability and active control of the supersonic missile wings are investigated. Adopting the third-order piston, the nonlinear aeroelastic dynamic equations with freeplay nonlinearity are derived, both linear and nonlinear flutter speed are obtained through hopf bifurcation theory and numerical method respectively. The design method based on differential geometry and quadratic optimal control for nonlinear system controller is used to stabilize the flutter. At last, the influence of the controller and the system parameters are analyzed. The simulation result shows that the method based on differential geometry and linear quadratic optimal is an effective way in control of nonlinear flutter.

导出引用

贾尚帅 ;丁千 ;刘炜 . 超音速弹翼非线性颤振分析与控制[J]. 振动与冲击, 2012, 31(13): 108-112

Jia Shang-shuai Ding Qian Liu Wei . Nonlinear Flutter Analysis and Control of the Supersonic Missile Wings[J]. Journal of Vibration and Shock, 2012, 31(13): 108-112