跨声速静气动弹性结构响应分析  

An Analysis of Structure Response for Transonic Static Aeroelasticity

作　　者：陈志敏[1] 徐敏[1] 陈士橹[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《空军工程大学学报（自然科学版）》2005年第1期1-4,共4页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(10272090)

摘　　要：采用动态网格生成和CVT数字插值技术构成了CFD/CSD耦合计算数据交换界面,结构运动方程采用有限元求解,气动载荷求解则用非定常N-S方程的双时间有限体积推进,外时间为物理时间,与结构运动方程同步迭代,松耦合求解了机翼受气动载荷作用的静气动弹性。最后得到了机翼在M∞ =0 8395,α=5 06°的CFD/CSD耦合计算的收敛值。详细分析了机翼受静气动弹性过程中结构响应和气动特性随时间变化的效应,初步研究结果表明:这种松耦合方法求解非线性气动弹性问题是可行的。A dynamic meshes and CVT interpolated technology are developed to generate interface mapping for CFD/CSD coupling procedure. Computational structural dynamics (CSD) are modeled using finite element equations. Solving aerodynamic force employs Navier-Stokes discretized based cell-centered finite volume framework with dual-time technology. An aeroelastic coupling procedure will perform with loosing coupling CFD/CSD at the same physics time step. Finally, the CFD / CSD coupling computational convergence solution is obtained for a swept wing at M_∞=0.8395,α=5.06°, using the developed nonlinear aeroelastic methodology.History of response of the structure and aerodynamic characteristic with time is analyzed. The study shows the developed CFD / CSD coupling procedure is able to compute nonlinear aeroelastic analysis.

关 键 词：动态网格 机翼 CFD/CSD 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]