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摘要: 现代飞行器日益呈现结构轻质化、控制系统宽通带和高权限的发展趋势. 因此, 非定常气动力、柔性结构和主动控制系统三者间的耦合力学成为重要的研究领域. 自20世纪80年代起, 航空界开始关注受控飞行器的气动弹性稳定性以及主动控制问题, 但对气动/结构的非线性效应、控制回路时滞对受控飞行器动力学行为的影响规律研究尚不充分. 研究这些影响规律不仅涉及非线性、高维数、多变参数和时滞效应等难题, 而且必须面对空气动力、飞行器结构、驱动机构、控制系统之间的强耦合问题. 其中的前沿难题是: 发展非线性气动伺服弹性动力学建模理论, 揭示上述因素诱发受控气动弹性振动的动力学机理, 开展气动伺服弹性控制风洞实验. 本文针对非线性气动伺服弹性力学所涉及的非线性非定常气动力建模、非线性结构动力学、气动伺服弹性控制律设计、气动伺服弹性实验, 总结相关研究现状和最新进展, 特别是近年来作者学术团队的研究成果, 并对进一步研究给出若干建议.Abstract: Advanced flight vehicles have been requiring lightweight structures and the expansion of bandwidth and authority of control systems. Hence, the coupled dynamics of the unsteady aerodynamics, the flexible aircraft structure, and the active control system have been an important research field in dynamics and control. The community of aeronautical technology has paid much attention to the aeroelastic stability and active control of aircraft since the 1980s, but has made less effort to study the effects of the aerodynamic and structural nonlinearities, as well as time delays in a control loop, on the aeroservoelastic behaviors of aircraft. The studies of these effects need to model the high-dimensional and parametric-varying dynamic systems with strong aerodynamic/structural nonlinearity, and hence, face with the coupling among unsteady aerodynamics, aircraft structure, and active control system. The cutting-edge problems include how to develop nonlinear aeroservoelastic modeling theory, how to reveal the dynamic mechanism behind the induced aeroelastic vibrations and how to carry out wind tunnel tests for aeroservoelasticity. This review article surveys the recent advances in reduced modeling of unsteady aerodynamics, nonlinear structural dynamics, design of aeroservoelastic control law, and experimental studies on aeroservoelastic systems, with an emphasis on the researches of the authors’ team in nonlinear aeroservoelasticity. The article also makes a number of suggestions for studies in the future.
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Key words:
- dynamics /
- active control /
- aeroservoelasticity /
- active flutter suppression
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图 3 基于非线性系统辨识的跨声速气动弹性分析. (a) 大幅值激励下的非定常广义力响应, (b) 非线性气动力诱发的极限环振荡, (c) 非线性气动力诱发的机翼“拍振”现象 (Yang et al. 2020)
图 4 机翼控制面模态的定义. (a) BACT机翼表面气动网格, (b) 控制面偏转5度后的表面气动网格 (Huang et al. 2015a)
图 5 考虑非线性气动效应的ASE系统频响曲线. (a) BACT机翼第二阶模态频响曲线 (Huang et al. 2014), (b) 三维弹性机翼气动伺服弹性频响曲线 (Huang et al. 2018)
图 9 几类变体飞行器设计方案. (a) 可变展长机翼 (Yue et al. 2017), (b) 可变弯度机翼 (Chanzy & Keane 2018), (c) 可折叠式机翼 (Friswell & Inman 2006), (d) 智能变体机翼 (Weisshaar 2013)
图 10 折叠翼模型气动伺服弹性频率响应随折叠角的变化规律. (a) 幅频响应曲面, (b) 相频响应曲面 (Huang et al. 2019)
图 18 飞翼布局飞行器的颤振研究. (a) 飞行器气动外形,(b) 鲁棒控制律设计框图 (Theis et al. 2016)
图 19 大展弦比飞翼布局飞行器的颤振研究. (a) 飞行器气动外形, (b) 开环系统颤振特性 (Zou et al. 2021)
图 23 飞翼布局飞行器气动伺服弹性模型. (a) 飞翼布局飞行器有限元模型 (Schmidt 2016), (b) 飞翼布局飞行器体自由度颤振形态
图 26 三维机翼模型颤振主动抑制风洞试验. (a) 机翼模型安装图, (b) 传感器、作动器与控制面布置, (c) 颤振主动控制系统 (Huang et al. 2015b)
图 30 计入时滞的颤振主动抑制. (a) 最优控制律执行框图, (b) 控制律施加前后的系统响应历程 (Huang et al. 2015b)
图 31 三维机翼体自由度颤振特性试验 (Li & Pak 2015)
图 32 3D打印大展弦比机翼气动弹性试验. (a) 半模飞翼布局无人机打印零件图, (b) 大展弦比机翼弯扭耦合颤振试验 (Pankonien et al. 2018)
图 33 飞翼布局无人机全机气动弹性飞行试验 (Danowsky et al. 2018)
表 1 预测非线性气动伺服弹性系统频率响应曲线的效率对比
BACT机翼 三维弹性机翼 非线性系统辨识的ASE模型 44.36 h 71.188 h 直接流固耦合的ASE模型 316 h 2990 h 
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