飞行器非线性气动伺服弹性力学

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. 

Nonlinear aeroservoelasticity of aircraft

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.