飞翼布局飞机因具有强隐身、高气动效率等优势，收到了国内外的广泛关注。但由于其机身转动惯量小、机翼低阶弯曲模态频率低等原因，极易在飞行包线范围内发生刚-弹耦合颤振、高动态气动弹性响应等复杂气动弹性问题。本文针对柔性飞翼布局飞机的高动态气动弹性振动抑制问题，提出了一种基于鲁棒 控制器的主动气动弹性控制方法，旨在通过主动控制降低飞机结构的气动弹性振动并对外部未知扰动具有较强的鲁棒性能。首先，采用 鲁棒控制理论设计了气动弹性响应控制器，通过优化其加权参数，使闭环系统的 范数最小化，以提高系统的鲁棒性和稳定性。其次，为了验证控制方法的有效性，本文开展了风洞试验验证。风洞试验结果表明，在鲁棒控制器开启的情况下，气动弹性响应控制器在一定风速范围内均可显著降低飞机翼尖加速度响应的均方根值，最高可降低35%，进而验证了鲁棒气动弹性控制器的有效性及其鲁棒性。
Flying-wing aerial vehicles have received extensive attention at home and abroad because of their strong stealth performance and excellent aerodynamic characteristics. However, due to the small rotational inertia of the fuselage and the low frequency of the low-order bending modes of the wing, complex aeroelastic problems such as rigid-elastic coupled flutter vibration and highly dynamic aeroelastic response are very likely to occur in the flight enve-lope region. This paper presents the active aeroelastic control method based on the robust controller for high-dynamic aeroelastic vibration suppression. The control objective is to reduce the aeroelastic vibration of the aircraft structure and enhance the control robustness to external unknown disturbances simultaneously. Firstly, the aeroe-lastic response controller is designed using the robust control theory, and its weighting parameters are opti-mized to minimize the paradigm of the closed-loop system to improve its robustness and stability. Secondly, the ef
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