Output Feedback Control for Lift Maximization of a Pitching Airfoil
Output Feedback Control for Lift Maximization of a Pitching Airfoil
复制标题
用于实现俯仰翼型升力最大化的输出反馈控制
DOI：
10.2514/6.2020-1836
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发表时间：
2020
期刊：
影响因子：
--
通讯作者：
D. Paley
中科院分区：
文献类型：
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作者：
Justin Lidard;Debdipta Goswami;D. B. Snyder;Girguis Sedky;Anya R. Jones;D. Paley
本文描述了实现的戈曼-赫拉罗夫模型的流动停滞附近的驱动翼型与反馈控制螺距率的目的最大化的时间平均非定常升力。设计了一种非线性状态反馈控制律来稳定非定常俯仰行为。对闭环系统进行线性化，建立了一个超临界Hopf分岔的存在性，从而得到一个稳定的极限环。产生最大时间平均升力的控制增益比最大定距升力提高了40%。输出反馈设计吸收有噪声的升力测量来估计模型状态，使用带有Perron-Frobenius算子的离散近似的递归贝叶斯滤波器来适应非线性动力学。物理系统参数的经验鉴定正在进行中。
This paper describes the implementation of theGoman-Khrabrovmodel for flow stagnation near an actuated airfoil with a feedback-controlled pitch rate for the purpose of maximizing the time-averaged unsteady lift. A nonlinear state-feedback control law is designed to stabilize unsteady pitching behavior. Linearization of the closed-loop system establishes the existence of a supercritical Hopf bifurcation, which gives rise to a stable limit cycle. Control gains that produce the greatest time-averaged lift achieve a 40% improvement from the maximum steady-pitch lift. An output feedback design assimilates noisy lift measurements to estimate the model states using a recursive Bayesian filter equipped with a discrete approximation of the Perron-Frobenius operator to accommodate the nonlinear dynamics. Empirical identification of physical system parameters is ongoing.