Control laws for implementing active flutter suppression are generally derived from linear aeroelastic models. In this paper, families of control laws for implementing an active flutter suppression system were initially designed using linearised aeroelastic models based on the doublet lattice method after ignoring the aerodynamic loads associated with relatively faster time scales. Using these preliminary sets of control laws and the nonlinear transonic small disturbance theory, near-optimum control laws were chosen in the transonic domain to maximally increase the flutter speed of a typical aircraft wing by at least 16% or more. Thus it is shown that it is feasible to systematically design near-optimal control laws for active flutter suppression using computational models in transonic flow. The doublet lattice method coupled with the zeroth-order matrix Padé approximant provided the fastest method for synthesising a large number of preliminary control laws. The methodology was successfully demonstrated by applying it to two benchmarking examples.

中文翻译：

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使用计算模型合成跨音速域中的主动颤振抑制系统

用于实现主动颤振抑制的控制律通常来自线性气动弹性模型。在本文中，在忽略与相对较快的时间尺度相关的空气动力载荷后，最初使用基于双点格法的线性气动弹性模型设计了用于实现主动颤振抑制系统的控制律族。利用这些初步的控制律集和非线性跨音速小扰动理论，在跨音速域中选择了接近最优的控制律，以最大限度地提高典型飞机机翼的颤振速度至少 16% 或更多。因此表明，使用跨音速流中的计算模型系统地设计用于主动颤振抑制的接近最优控制律是可行的。双点格法与零阶矩阵 Padé 近似相结合，为合成大量初步控制律提供了最快的方法。通过将其应用于两个基准测试示例，该方法得到了成功的证明。