基于滑模变结构控制的机翼颤振主动抑制方法研究

Active flutter suppression, an active research subject in field of aeroelasticity which represents an advanced aerospace design concept and technology, has an inherently multidisciplinary feature. It plays an important role for the theory development and engineering application to the present structure and control system design of modern flight vehicles. Recently, there is no suffient nonlinear control techniques, which derive from the area of aeroelasticity, can be used in active flutter suppression, especially for the ones that could be realized. Moreover, the modern control theory has some critical disadvantages in control law realization and parameter robustness, which withdraws its application to the active flutter suppression. For this consideration, sliding mode variable structure control method is adopted to introduce this study for the active flutter suppression of a wing, in order to find a novel idea of nonlinear consideration for active flutter suppression. It has some attractive features in application, such as that physical realization can be performed conveniently, and the features of low order, robust as well as quick response of control. 2D wing is selected as the beginning of technology research for theory and mechanism discussion. Then, some typical sliding mode observer will be selected as the joint, which connect the sliding mode control method and common control methods. In the end, the applications will be extended to the 3D real wing by the efforts of this project. A series of design procedures on active flutter suppression based on the sliding mode variable structure control strategy will be generated in this progress. Then a new approach will be provided for the future active control of nonlinear aeroelastic systems.

颤振主动抑制是气动弹性领域的活跃研究分支。它代表了航空技术的先进理念，具有多学科融合的特点，对现代飞行器结构和控制系统设计具有理论和工程意义。当前气动弹性领域发展出的非线性颤振主动抑制控制律设计方法数量有限，而基于最优控制的方法体系因物理实现难度大、鲁棒性差等严重缺陷，制约了其在颤振主动抑制中的应用。本项目申请拟采用滑模变结构控制策略，以机翼的颤振主动抑制设计为切入点，探求一种满足气动弹性物理背景需求，易于物理实现，具备低阶次、鲁棒、快速响应等特点，并且能够考虑非线性因素的颤振主动抑制控制律设计新思路。技术途径拟以2D机翼模型作为突破口，开展理论论证和机理研究；然后以滑模观测器为桥梁，通过将滑模控制与常规控制律设计方法杂交、融合，使技术应用拓展至3D真实机翼对象。最终形成一套基于滑模变结构控制策略的机翼颤振主动抑制方法体系，为非线性的气动弹性主动控制开辟一条新的技术途径。

本项目围绕颤振主动抑制问题研究滑模控制方法在气动弹性主动控制中的应用。主要内容包括：1）二维机翼模型的滑模控制机理研究；2）二维、三维机翼模型的滑模观测器研究；以及3）带有间隙非线性因素的二维机翼滑模控制极限环抑制研究。研究结果表明，滑模控制方法适用于颤振主动抑制设计，并且具有独特的设计和使用效果；滑模观测器结合气动弹性物理背景，可将控制系统转化为全输出反馈形式，在二维对象推广至三维真实机翼模型方面具有重要意义；滑模控制方法用于间隙非线性气动弹性系统的极限环主动抑制，极限环发生的速度范围可以得到显著提高，振荡的幅值有所降低。本项目研究的科学意义在于开辟了一条通往非线性气动弹性主动控制的新技术途径。