In the present study, control of a Thin Walled Beam (TWB) wing-engine system is examined applying piezoelectric actuators to enhance the performance of aeroelastic response. The composite piezoelectric governing equations of motion including the structure and electric effects are derived applying Hamilton's principle. Piezoelectric composite plate equations are added to the composite host wing-engine governing system of equations. The incompressible aerodynamic model based on Wagner's function is applied and the Ritz based solution methodology is employed. As a passive control approach, the effects of piezoelectric fiber angles are studied on the time domain response of the high-aspect-ratio wing-engine system. The linear quadratic Gaussian (LQG) control algorithm is applied as a closed-loop active control strategy to enhance the flutter response characteristics of the composite wing-engine system. Numerical results firstly, demonstrate the effectiveness of the active control strategy based on piezocomposite actuator on suppressing the flutter response of the composite wing-engine system and secondly, prove the effect of piezocomposite actuator location and fiber angle orientation on the closed-loop control performance.

在本研究中，研究了使用压电致动器来增强薄壁梁（TWB）机翼发动机系统的控制，以增强气动弹性响应的性能。应用汉密尔顿原理推导了复合压电运动控制方程，包括结构和电效应。将压电复合板方程添加到复合主翼发动机控制方程组中。应用基于瓦格纳函数的不可压缩空气动力学模型，并采用基于Ritz的求解方法。作为一种被动控制方法，研究了压电纤维角度对高纵横比机翼发动机系统时域响应的影响。将线性二次高斯（LQG）控制算法用作闭环主动控制策略，以增强复合机翼发动机系统的颤振响应特性。数值结果首先证明了基于压电复合驱动器的主动控制策略在抑制复合翼发动机系统颤动响应方面的有效性，其次，证明了压电复合驱动器的位置和纤维角度定向对闭环控制性能的影响。