某型飞机副翼抖动故障分析

Analysis of Aileron Vibration Failure of a Certain Aircraft

某型飞机副翼操纵系统采用不可逆助力操纵来驱动副翼偏转,驾驶盘到助力器输入端之间通过拉杆摇臂传动的简单机械系统,助力器到副翼段为机械传动系统,不同的是助力器-副翼段为闭环控制系统。飞机在进行地面调试及试飞过程中出现副翼抖动的情况,在副翼空载情况下尤为严重,且出现抖动不收敛现象。针对该故障,对副翼操纵系统的传动环节和液压系统进行了检查,根据助力器闭环系统的工作原理对副翼助力器-操纵面进行了仿真建模,对副翼操纵系统进行实物测量来修正仿真模型。通过对模型的时域、频域分析,其仿真结果与抖动情况吻合良好,确定了副翼抖动的根本原因,为后续改进提供了重要的依据。文中所使用的建模仿真方法也可用于其他飞机不可逆助力操纵系统设计,在设计过程中就确保系统闭环稳定,从系统动态性能指标出发对零部件的设计提出明确的设计指标。

A certain aircraft aileron control system uses irreversible booster to drive the aileron deflection.A simple mechanical system is driven from the cockpit control wheel to the input of the irreversible booster through a series of rods and arms,and the transmission from the irreversible booster to the aileron is also a mechanical system.The difference is that the irreversible booster-aileron section is a closed-loop control system.Aileron vibration occurs during ground adjustment and flight test of the aircraft,especially in the no load condition,and sometimes the vibration does not converge.Aiming at this failure,the transmission linkages and hydraulic system of aileron control system are checked,and the simulation model of irreversible booster-control surface is carried out according to the working principle of the irreversible booster closed-loop system.In addition,the simulation model is modified by physical measurement of aileron control system.Both the time and frequency domain analysis of the model are conducted,and the simulation results are in good agreement with the vibration situation.Finally,the fundamental reason of aileron vibration is determined,which provides an important reference for the subsequent improvement.The modeling and simulation method used in this paper can also be used in the design of irreversible booster of other aircraft.In the design process,the closed-loop stability of the system is ensured,and specific design indexes are pro-posed for the design of spare parts based on the dynamic performance of the system.