带间隙非线性的机翼操纵面颤振特性研究

Flutter characteristics of wing control surface with clearance nonlinearity

针对大型民用飞机复杂机翼-副翼系统,利用双协调动态子结构法建立了缩比三维机翼-副翼带间隙操纵面颤振分析模型,得到非线性气动弹性方程,并分别在频域及时域内建立了求解方法:在频域内,利用谐波平衡法进行求解,通过引入间隙刚度的描述函数及相对舵偏振幅,建立了可利用V-g法进行颤振计算的方案;在时域内,利用有理函数拟合和时域推进法进行数值仿真,得到了与频域法结果相吻合的操纵面颤振极限环振荡特性规律。对三维矩形机翼模型开展风洞试验,揭示了间隙对操纵面颤振特性间的影响:间隙非线性使系统出现极限环振荡并使系统振荡发散风速明显降低。

Here,aiming at complex wing-aileron system of large civil aircraft,a reduced scale 3-D wing-aileron control surface flutter analysis model with clearance was established by using the double-coordinated dynamic substructure method.Nonlinear aerodynamic elastic equations were obtained,and the solving methods were established in frequency domain and time domain,respectively.In frequency domain,the harmonic balance method was used to solve the equations.By introducing the description function of clearance stiffness and relative rudder deflection amplitude,a scheme for flutter calculation with V-g method was established.In time domain,the rational function fitting and the time domain marching method were used to simulate control surface flutter limit cycle oscillation characteristics,they agree well with the results of the frequency domain method.Finally,wind tunnel tests were conducted for a 3-D rectangular wing model to reveal effects of clearance on flutter characteristics of control surface.It was shown that the nonlinearity of clearance can make the system have limit cycle oscillation,and the system oscillation divergent wind speed obviously drop.