超音速条件下复杂带翼外形的强迫振动分析

Forced Vibration Analysis of Complex Configurations with Fins in Supersonic Environment

基于三维非定常N-S (Navier Stokes)方程开展超音速条件下“十”字翼导弹动态特性数值研究。空间方向的离散采用二阶精度的Roe格式,非定常流动求解采用“双时间步”(Dual-time-step)方法的隐式LU-SGS格式。在Etkin非定常气动力模型基础上,通过强迫简谐运动过程辨识动态稳定性参数(动导数),分析了减缩频率、子迭代步数和网格规模对动导数辨识结果的影响,并通过与实验结果的比较,验证了计算结果的可靠性。

A numerical simulation investigation based on the Navier Stokes equations of dynamic characteristics of missile geometries with fins in Supersonic Environment was presented.The 2-order Roe scheme and the dual-time-step method are respectively applied to discrete of the spatial and time derivative of the unsteady fluency.Based on the unsteady Etkin pneumatics model,dynamic stability derivatives were calculated from load history of the unsteady flow.The influence of frequency of force-oscillation,inner-iteration steps and mesh dimension to aerodynamic force/moment was investigated.The dynamic stability derivatives predicted by the present methods quite agree with the experiment results.