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首页> 外文期刊>Journal of Fluids and Structures >State-space model identification and feedback control of unsteady aerodynamic forces
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State-space model identification and feedback control of unsteady aerodynamic forces

机译：非定常空气动力的状态空间模型辨识与反馈控制

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摘要

Unsteady aerodynamic models are necessary to accurately simulate forces and develop feedback controllers for wings in agile motion; however, these models are often high dimensional or incompatible with modern control techniques. Recently, reduced-order unsteady aerodynamic models have been developed for a pitching and plunging airfoil by linearizing the discretized Navier-Stokes equation with lift-force output. In this work, we extend these reduced-order models to include multiple inputs (pitch, plunge, and surge) and explicit parameterization by the pitch-axis location, inspired by Theodorsen's model. Next, we investigate the naive application of system identification techniques to input-output data and the resulting pitfalls, such as unstable or inaccurate models. Finally, robust feedback controllers are constructed based on these low-dimensional state-space models for simulations of a rigid flat plate at Reynolds number 100. Various controllers are implemented for models linearized at base angles of attack α_0 = 0°, α_0 = 10°, and α_0 = 20°. The resulting control laws are able to track an aggressive reference lift trajectory while attenuating sensor noise and compensating for strong nonlinearities.
机译：非稳定的空气动力学模型对于精确地模拟力并开发敏捷机翼的反馈控制器是必要的。但是，这些模型通常是高维的，或者与现代控制技术不兼容。最近，通过将离散化的Navier-Stokes方程与升力输出线性化，已经针对俯仰和俯冲翼型开发了降阶非定常空气动力学模型。在这项工作中，我们扩展了这些降阶模型，以包括多个输入（音高，突降和波动），并根据西奥多森模型的启发通过音高轴位置进行显式参数化。接下来，我们研究系统识别技术在输入输出数据上的天真应用以及由此产生的陷阱，例如不稳定或不准确的模型。最后，基于这些低维状态空间模型构造鲁棒的反馈控制器，以仿真雷诺数为100的刚性平板。针对在基本攻角α_0= 0°，α_0= 10°时线性化的模型实现了各种控制器，并且α_0= 20°。由此产生的控制律能够跟踪激进的参考升程轨迹，同时衰减传感器噪声并补偿强烈的非线性。

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