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Active aeroelastic output feedback control with partial measurements by the method of receptances

机译：主动气弹输出反馈控制，采用接受方法进行部分测量

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The method of receptances allows the design of active aeroelastic control for suppressing the flutter instabilities and for augmenting the flutter boundaries by pole placement. This method is purely based on available receptance transfer functions, which can be available for controller design from the embedded sensors and actuators on the aircraft. In recent years, receptance based single-input and multiple-input full state feedback control has been developed, which requires the displacement and velocity measurements associated with each degree of freedom, which may not be available in practice. The design of a controller using partially available measurements in these scenarios is related to the static output feedback design, which leads to the solution of associated nonlinear problems and/or the design of complimentary state estimators or observers. In order to overcome such restrictions, in this paper a method for feedback control design using the receptance method is presented which can utilize the available partial measurements for control gain computation. This is achieved by introducing redundancy of acceleration measurement and adding associated acceleration feedback in the controller loop. This leads to a linear constrained least-square problem for the design of the controller. The working of this approach is shown with numerical examples associated with various wing models. It is demonstrated that prescribed aeroelastic modes can be controlled to achieve flutter suppression and flutter boundary extension, by designing a feedback controller using partial measurements from the available sensors. Parametric studies are presented to demonstrate that such output feedback control allows the optimal selection of measurements and the corresponding sensor location to minimize the controller norm. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：接收方法允许设计主动气动弹性控制，以抑制颤振不稳定性并通过极点放置来增大颤振边界。该方法仅基于可用的接收传递函数，可以从飞机上的嵌入式传感器和执行器进行控制器设计。近年来，已经开发了基于接收的单输入和多输入全状态反馈控制，这需要与每个自由度相关的位移和速度测量，这在实践中可能不可用。在这些情况下使用部分可用的测量值的控制器的设计与静态输出反馈设计有关，这将导致相关的非线性问题的解决和/或互补状态估计器或观察器的设计。为了克服这些限制，本文提出了一种使用接受方法的反馈控制设计方法，该方法可以利用可用的部分测量值进行控制增益计算。这可以通过引入加速度测量的冗余并在控制器回路中添加相关的加速度反馈来实现。这导致控制器设计的线性约束最小二乘问题。通过与各种机翼模型相关的数值示例显示了该方法的工作。结果表明，通过使用来自可用传感器的部分测量值来设计反馈控制器，可以控制规定的空气弹性模式以实现颤动抑制和颤动边界扩展。提出了参数研究，以证明这种输出反馈控制可以最佳地选择测量值和相应的传感器位置，从而最大程度地减少控制器规范。 （C）2019 Elsevier Masson SAS。版权所有。

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