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首页> 外文期刊>Journal of aerospace engineering >Sliding Mode Control for a Nonlinear Aeroelastic System through Backstepping
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Sliding Mode Control for a Nonlinear Aeroelastic System through Backstepping

机译：基于Backstepping的非线性气动弹性系统的滑模控制。

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摘要

This paper considers an aeroelastic two-dimensional wing-flap system with uncertainty and external disturbance. Nonlinear stiffness in pitch is expressed as the second-order polynomial form. In the uncontrolled aeroelastic model, limit cycle oscillation (LCO) appears at postflutter speed. By utilizing leading-edge and trailing-edge control surfaces as the control input, a sliding mode control scheme using varying boundary layers based on backstepping design is developed to suppress aeroelastic vibration. The proposed control strategy combines the advantages of both sliding mode control with varying boundary layers and backstepping technique. In contrast to the conventional sliding mode control design, the proposed method not only avoids chattering but also obtains stronger robustness. The results of numerical simulation clearly demonstrate the effectiveness of the proposed control strategy for aeroelastic vibration suppression under saturated controller input. (C) 2017 American Society of Civil Engineers.
机译：本文考虑具有不确定性和外部干扰的二维气动翼翼系统。音调的非线性刚度表示为二阶多项式形式。在不受控制的气动弹性模型中，极限周期振荡（LCO）以振颤后速度出现。通过利用前沿和后沿控制面作为控制输入，开发了一种基于反推设计的使用变化边界层的滑模控制方案，以抑制气动弹性振动。所提出的控制策略结合了具有变化边界层的滑模控制和后推技术的优点。与传统的滑模控制设计相比，该方法不仅避免了颤动，而且具有更强的鲁棒性。数值模拟结果清楚地证明了所提出的控制策略在饱和控制器输入下抑制气动弹性振动的有效性。 （C）2017年美国土木工程师学会。

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