具有结构非线性的超音速翼面气动弹性分析

Aeroelastic Analysis of Supersonic Wing with Structural Nonlinearity

为分析超音速流中全动操纵面的非线性气动弹性特性,采用描述函数法计入操纵间隙引起的结构刚度非线性,用修正的活塞理论计算非定常气动力,并以龙格-库塔法按时间步推进运动方程,求解非线性系统的响应特性。某超音速小展弦比全动翼面的气动弹性响应分析结果表明,由于结构非线性的影响,在一定的速度范围内,系统响应出现极限环运动;且极限环幅值随来流速度的增大而增大;操纵间隙增大,极限环振荡的频率、幅值均增大。分析结果为飞行器的结构设计提供了参考。

To investigate the nonlinear aeroelastic characteristics of wing in supersonic flow,describing function method was used in dealing with structural nonlinearity by control clearance,aerodynamic loads were calculated based on the modify piston theory,and flutter equation was solved by Runge-Kutta method to obtain the motion response in time-space. Nonlinear aeroelastic analysis of a supersonic low aspect ratio all-movable wing show that the limit cycle response occurs in certain flow velocity range due to structural nonlinearity,and amplitude of limit cycle increase with increasing of flow velocity. Frequency and amplitude of limit cycle motion also increase with increasing of the rotary clearance. Investigate results provide theoretical basis for the structural design of crafts.