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高超声速飞行器纵向静不稳定、非最小相位和突出的弹性效应等特性给飞行器控制系统设计带来严峻挑战。针对该问题,文中采取鸭翼作为附加俯仰控制舵面与升降舵进行联动控制的策略,以改善高超声速飞行器的非最小相位特性和严重的弹性效应,从而达到提高控制性能的目的。首先,给出了考虑弹性模态的高超声速飞行器动力学模型;其次,研究了鸭翼对飞行器非最小相位特性以及弹性模态响应的影响,并给出合适的鸭翼布局位置和鸭翼/升降舵联动增益参数;最后,采用基于反馈线性化方法和LQR理论的非线性控制器对弹性飞行器进行控制,对比分析了鸭翼联动控制对闭环控制性能的改善作用。研究结果表明,合理的鸭翼配置可以缓解系统的非最小相位特性带来的不利影响,同时避免了控制输入对特定弹性模态的激励,从而达到提高弹性高超声速飞行器控制性能的目的。
Hypersonic vehicle longitudinal instability, non-minimum phase and prominent elastic effects and other characteristics of the aircraft control system design poses a serious challenge. In order to solve this problem, duck wing is adopted as the strategy of linkage control between additional pitch control surface and elevator, so as to improve the non-minimum phase characteristic and serious elastic effect of hypersonic vehicle so as to improve the control performance. Firstly, the dynamic model of the hypersonic vehicle considering the elastic modal is given. Secondly, the influence of the canard wing on the non-minimum phase characteristic and the elastic modal response of the aircraft is studied, and the suitable position of the canard wing and the position of the canard wing / Finally, the non-linear controller based on the feedback linearization method and the LQR theory is used to control the flexible aircraft. The improvement of the closed-loop control performance by the cantilever linkage control is analyzed and compared. The results show that the reasonable configuration of duck-wing can mitigate the adverse effects caused by the non-minimum phase of the system and avoid the stimulus of the control input to a specific elastic mode so as to improve the control performance of the elastic hypersonic vehicle.