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Adaptive Feedback Linearisation and Control of a Flexible Aircraft Wing

机译：自适应反馈线性和控制柔性飞机翼

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Active control systems are used on aircraft to reduce loads due to gusts and manoeuvres, reduce the effect of noise, and could also increase the speed at which flutter occurs. Unfortunately most aeroservoelastic systems include some form of nonlinearity, and this increases the complexity of the feedback system and also facilitates the likelihood of Limit Cycle Oscillations occurring. Previous work on the application of Adaptive Feedback Linearisation to aeroelastic systems has demonstrated the promising potential of this method when applying control in the presence of substantial nonlinearity. In this work, Adaptive Feedback Linearisation is applied to an aeroelastic model of a cantilevered flexible wing with a cubic hardening structural nonlinearity in an engine pylon. Using assumed vibration modes, a suitable model of the wing is developed, into which structural nonlinearity is incorporated. Closed-loop control is implemented on the aeroservoelastic system via linearising feedback computed through the Adaptive Feedback Linearisation algorithm. The advantage of the latter is the guaranteed stability of the closed-loop aeroelastic system, despite lack of knowledge of the exact description of the nonlinearity. It is shown how such an approach can be used to delay the onset of flutter or limit cycle oscillations.
机译：在飞机上使用有源控制系统，以减少由于阵风和机动而导致的负载，降低噪音的效果，并且还可以增加颤动的速度。遗憾的是，大多数空气氛围系统包括某种形式的非线性，这增加了反馈系统的复杂性，并且还促进了发生限制循环振荡的可能性。以前关于应用自适应反馈线性化的适应性到空气弹性系统的工作已经证明了这种方法在存在大致非线性存在下施加控制时的有希望的潜力。在这项工作中，自适应反馈线性化应用于悬臂柔性翼的空气弹性模型，在发动机塔中具有立方体硬化结构非线性。使用假定的振动模式，开发了合适​​的机翼模型，结合了结构非线性。通过通过自适应反馈线性化算法计算的线性化反馈在Aeroservoelastic系统上实现闭环控制。尽管缺乏对非线性的确切描述，但后者的优点是闭环空气弹性系统的保证稳定性。示出了如何使用这种方法来延迟颤动或极限循环振荡的开始。

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