利用时滞反馈对飞机起落架半主动控制系统进行等峰优化

Equal-peak Optimization of Semi-active Control for Aircraft Landing Gear System by Using Delayed Feedback Control

文章提出了一种利用时滞反馈对飞机起落架扭转摆振系统进行等峰优化的方法.首先,建立了考虑支柱扭转角、侧向位移、轮胎变形的振动微分方程,并得到了振动系统的解析解.其次,设计了一种等峰优化方法,根据优化准则,对不同当量轮胎侧偏刚度系数,通过调节反馈增益系数和时滞量实现了对支柱扭转角幅频响应曲线的等峰优化.同时,为了保证系统在稳定的前提下工作,采用CTCR方法有效的判定了时滞动力系统的稳定性.研究表明,对任意的当量轮胎侧偏刚度系数,都存在一对最优的反馈增益系数和时滞的最优值,能够实现对支柱扭转角振幅的最大抑制.最后,通过频域分析证明了时滞反馈控制等峰优化结果的有效性,通过时域分析证明了数据的可靠性.

In the present paper,the equal-peak optimization method of delayed feedback control for torsional shimmy oscillations of aircraft landing gear system is proposed.Firstly,the oscillations of differential equations considering the yaw angle and lateral displacement of the strut as well as the tire deformation are established,and the analytical solution of the oscillation system is obtained.Secondly,an equalpeak optimization method is designed.For different equivalent tire cornering stiffness coefficients,the amplitude-frequency response curve of the strut yaw angle is optimized by adjusting the gain and time delay based on the optimization criteria.In order to ensure that the system works under the conditions of stability,the cluster treatment of characteristic roots(CTCR)is used to effectively determine the stability of dynamic system with time delays.The results show that for any equivalent tire cornering stiffness coefficient,there exists a pair of optimal gain and time delay,and the yaw angle amplitude of the strut can be suppressed to a minimum value.Finally,the validity of the equal-peak optimization results of delayed feedback control is proven by the frequency-domain analysis,and the reliability of the data is proven by the time-domain analysis.