高超声速飞行器气动伺服弹性的自适应抑制

针对弹性高超声速飞行器的气动伺服弹性问题，提出一种结合线性自抗扰和自适应陷波器的综合控制方案。针对强耦合和强不确定性问题，采用线性自抗扰控制对总扰动进行快速估计和补偿。为了在最小化对刚体控制性能影响的同时实现对频率未知且时变的弹性模态的抑制，采用能够在线估计弹性频率的自适应陷波器。根据气动伺服弹性抑制问题的特点提炼出对自适应陷波器的性能需求。针对这些需求设计了两种基于递推最大似然法的多频率直接辨识方案——参数单独自适应和同时自适应方案。为了提高辨识算法在各种随机扰动下的鲁棒性，在此基础上提出一种在线有效性监督机制，并通过大量的数字仿真对两种方案进行了性能对比。最后，在弹性高超声速飞行器模型上进行仿真，仿真结果验证了所提控制方案的有效性。

Adaptive aeroservoelasticity suppression of hypersonic vehicles

A comprehensive control scheme combining active disturbance rejection control and an adaptive notch filter is proposed in this paper for the aeroservoelasticity suppression of hypersonic vehicles. For the strong coupling effects and uncertainties, active disturbance rejection control is employed to estimate and compensate the total disturbance in a fast manner. An adaptive notch filter is designed to suppress the flexible modes with unknown and time-varying frequencies and minimize the effect on the performance of the rigid-body control. Based on the characteristics of the aeroservoelasticity suppression problem, the performance requirements for the adaptive notch filter are proposed first. To meet these requirements, two schemes based on the recursive maximum likelihood algorithm, the individual and simultaneous adaptation schemes, respectively, are proposed to achieve direct estimation of multiple frequencies. An online supervision strategy is designed to improve the robustness of the adaptive algorithm under multiple perturbations. Extensive numerical simulations are conducted to compare the performance of these two schemes. Finally, simulations are performed on the flexible hypersonic vehicle model to validate the effectiveness of the proposed method.