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研究含间隙超音速二元弹翼非线性颤振特性和主动控制问题.采用三阶活塞理论建立了含间隙二元弹翼非线性气动弹性动力学方程,利用Hopf分岔理论、谐波平衡法和数值方法,分析了系统的非线性颤振特性.应用基于微分几何法和二次型最优控制相结合的方法设计非线性系统控制器,推迟临界分岔速度.应用滑模变结构控制方法设计控制器,有效抑制非线性颤振,并讨论了控制参数对控制效果的影响.仿真结果表明,所设计的控制律可以有效地实现对含间隙超音速二元弹翼系统非线性颤振的控制.最后计算了在基础激励扰动下系统的动态响应,分别得到了周期运动、多周期运动、概周期运动以及混沌运动.
The nonlinear flutter characteristics and active control of two-dimensional missile with interstitial hypersonic airfoils are studied.The nonlinear aerodynamic equations of the two-component missile with interstitial airfoils are established by using the third-order piston theory. Hopf bifurcation theory, harmonic balance method And numerical methods, the nonlinear flutter characteristics of the system are analyzed.The nonlinear system controller is designed based on the combination of differential geometry and quadratic optimal control, the critical bifurcation delay is postponed.The application of sliding mode variable structure control The controller is designed to effectively suppress the nonlinear flutter and the influence of the control parameters on the control effect is discussed.The simulation results show that the proposed control law can effectively control the nonlinear flutter Finally, the dynamic response of the system under basic excitation perturbation is calculated, and periodic motion, multi-period motion, almost periodic motion and chaotic motion are obtained respectively.