Hypersonic vehicles exhibit significantly varied dynamic characteristics across different flight regimes. These characteristics, such as model uncertainties and actuator saturation levels, have strong time-varying properties, necessitating a control strategy capable of adaptively matching robustness and responsiveness to such variability. This paper introduces an adaptive sliding mode control strategy tailored for hypersonic vehicles, which dynamically aligns controller performance with the vehicle's varying dynamic properties. Initially, a quantitative model to characterize the dynamic uncertainty of the hypersonic vehicle is constructed, and an online adaptive method to estimate the bounds of model uncertainty is proposed. This method enables real-time adaptation of controller robustness. Furthermore, the study employs artificial potential functions for online estimating control saturation and actuation rates. It adaptively modulates the control response rate coefficients based on these estimations, effectively mitigating saturation while ensuring the rapid convergence of tracking errors. Additionally, the stability of the system is scrutinized through Lyapunov theory, which verifies that the tracking error remains uniformly ultimately bounded. The simulation results corroborate the efficacy of the proposed approach, illustrating advancements in robustness, responsiveness, chattering suppression, and saturation prevention.

中文翻译：

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高超声速飞行器动态匹配自适应滑模控制

高超音速飞行器在不同的飞行状态下表现出显着不同的动态特性。这些特性，例如模型不确定性和执行器饱和水平，具有很强的时变特性，需要一种能够自适应地匹配这种变化的鲁棒性和响应性的控制策略。本文介绍了一种专为高超音速飞行器量身定制的自适应滑模控制策略，该策略可以根据飞行器不同的动态特性动态调整控制器性能。首先，构建了表征高超声速飞行器动态不确定性的定量模型，并提出了估计模型不确定性界限的在线自适应方法。该方法能够实时适应控制器的鲁棒性。此外，该研究采用人工势函数来在线估计控制饱和度和驱动率。它根据这些估计自适应地调制控制响应速率系数，有效地减轻饱和度，同时确保跟踪误差的快速收敛。此外，系统的稳定性通过李雅普诺夫理论进行了仔细检查，该理论验证了跟踪误差最终保持均匀有界。仿真结果证实了所提出方法的有效性，说明了鲁棒性、响应性、颤振抑制和饱和预防方面的进步。