飞行器操纵面嗡鸣的非结构网格并行计算方法  

Parallel Numerical Simulations of Aircraft Control Surface Buzz on Unstructured Grids

作　　者：幺虹 郭承鹏[1] 张颖[1] 

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《华侨大学学报（自然科学版）》2016年第6期676-680,共5页Journal of Huaqiao University(Natural Science)

基　　金：航空科学基金资助项目(2014ZA27003)

摘　　要：为了数值模拟飞行器操纵面的嗡鸣现象,在集群计算机MPI并行计算环境下建立基于三维非定常欧拉方程耦合结构运动方程的嗡鸣计算方法.气动流场求解采用基于非结构网格的中心有限体积法进行空间离散,时间推进采用双时间方法,结构运动方程采用Adams预估校正方法求解.针对翼面与操纵面缝隙间存在的网格运动问题,在非结构网格系统上采用Delaunay图映射方法实现网格的运动变形.最后,使用飞行器操纵面标准嗡鸣计算模型对计算方法进行验证,结果表明:所建立的并行计算方法正确,程序具有很好的计算效率,能够对飞行器操纵面嗡鸣进行高效的数值分析.In order to perform the numerical simulation of the buzz of aircraft control surface,a MPI parallel computation based on 3Dunsteady Euler equations coupling with structural motion equations was established for cluster computers.In the solution process of pneumatic flow field,the spatial discretization was carried out using the centered finite volume method based on the unstructured grids.In addition,the time stepping was solved with the dual time method,and the structural motion equations were solved with the Adams predictor correction method.Aiming at the grid motion problem existing in the gap between the airfoil and control surface,the motion and deformation of grids were realized with Delaunay image mapping method in the unstructured grid system.Finally,the computation method was verified with the standard buzz computation model for the aircraft control surface.The results validated the established parallel computation method and indicated the excellent computation efficiency of the proposed model.

关 键 词：嗡鸣 飞行器 操纵面 并行计算 动网格 Adams预估校正 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]