Improved time-marching technique for solving aeroelastic equations

科研成果: 期刊稿件文章同行评审

5 引用 (Scopus)

摘要

In the control equations of aeroelastic problem, the structural block is marched by the standard Runge-Kutta method, the generalized aerodynamic loads are computed by interpolated method and an approximate 4th order Runge-Kutta marching method in which it only needs to compute the aerodynamic loads once per each time step is developed. By solving the non-linear Bernoulli equation and computing the aeroelastic responses of a supersonic wing, the precision of the approximate method is found to be much higher than the 4th order Runge- Kutta method in which the aerodynamic loads are frozen and the computed results are very close to those by the standard Runge-Kutta method while the improved approximate method only needs quarter times of employing the aerodynamic solver comparing with the standard Runge-Kutta method. So the efficiency of the aeroelastic numerical simulation is greatly improved. For the common aeroelastic problem, only 20-30 time steps in one period is necessary to ensure a quite good time precision.

源语言英语
页(从-至)118-120
页数3
期刊Zhendong yu Chongji/Journal of Vibration and Shock
24
5
出版状态已出版 - 10月 2005

指纹

探究 'Improved time-marching technique for solving aeroelastic equations' 的科研主题。它们共同构成独一无二的指纹。

引用此