基于线性二次型调节器的直升机旋翼叶片振动主动控制

M. Uddin, Pratik Sarker, C. Theodore, U. Chakravarty
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引用次数: 3

摘要

主动振动控制是一种应用广泛的直升机振动控制方法。由于微电子技术的重大进步,该技术优于传统的被动控制技术,因为重量损失和缺乏对变化的飞行条件的适应性。针对直升机旋翼叶片的振动,设计了一种最优控制器。利用旋转悬臂梁三耦合振动的数学模型,建立了隔振转子叶片的状态空间模型。所需的固有频率由改进的伽辽金方法确定,并且只考虑作用在结构上的主要气动力。设计了线性二次型调节器,使其减振达到最优水平,并对控制器进行了悬停和前飞调整。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Active Vibration Control of a Helicopter Rotor Blade by Using a Linear Quadratic Regulator
Active vibration control is a widely implemented method for helicopter vibration control. Due to the significant progress in the microelectronics, this technique outperforms the traditional passive control technique due to the weight penalty and lack of adaptability for the changing flight conditions. In this paper, an optimal controller is designed to attenuate the helicopter rotor blade vibration. The mathematical model of the triply coupled vibration of the rotating cantilever beam is used to develop the state-space model of an isolated rotor blade. The required natural frequencies are determined by the modified Galerkin method and only the principal aerodynamic forces acting on the structure are considered. Linear quadratic regulator is designed to achieve the vibration reduction at the optimum level and the controller is tuned for the hovering and forward flight.
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