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针对二元机翼颤振主动抑制问题,对二元翼段颤振控制律的设计以及风洞实验验证展开了深入研究。首先,基于Theodorsen非定常气动力理论建立了该翼段模型的运动状态方程。其次,基于鲁棒控制理论设计了H_∞控制器和μ控制器,分别与二元翼段气动弹性系统共同组成了机翼颤振主动控制系统。最后,采用数值仿真和风洞实验相结合的方式,对H_∞控制器和μ控制器的颤振控制效果进行了验证。研究结果表明:H_∞控制器和μ控制器都能有效抑制颤振的发生,可将机翼颤振临界速度由15.45 m/s提高到27 m/s以上。且μ控制器在颤振主动抑制中的颤振抑制收敛时间更短,颤振抑制风速上限更高,具有更好的鲁棒稳定性和鲁棒性能。
Aiming at the active suppression problem of the two-dimensional wing flutter, the design of the flutter control law of the two-wing segment and the wind tunnel experiment are studied in depth. First, based on the Theodorsen unsteady aerodynamic theory, the equations of motion of the wing segment model are established. Secondly, H_∞controller and μcontroller are designed based on robust control theory, which together with the dual-wing aeroelastic system constitute the wing flutter active control system. Finally, the flutter control effect of H_∞controller and μ_controller is validated by numerical simulation and wind tunnel experiment. The results show that both H_∞controller and μcontroller can effectively suppress the flutter and increase the wing flutter critical speed from 15.45 m / s to above 27 m / s. Moreover, the μ controller has shorter chatter suppression convergence time and higher upper limit of flutter suppression flutter in the active suppression of chatter, which has better robust stability and robustness.