基于非结构网格的跨声速静气动弹性计算  

Transonic Static Aeroelastic Calculation Based on Unstructured Grid

作　　者：董军[1] 卢晓杨[1] 侯良学[1] 

机构地区：[1]中航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：《航空计算技术》2013年第1期9-12,共4页Aeronautical Computing Technique

摘　　要：基于非结构网格开发了静气动弹性计算程序,通过气动力与弹性变形的交替迭代计算实现流固耦合。气动力求解采用RANS方程,结构变形计算采用柔度系数法,通过面样条(IPS)方法进行柔度系数插值,使用改进弹簧近似法实现网格变形。通过对AGARD 445.6机翼的静气弹计算验证了方法的正确性,同时对机翼的静气动弹性特性进行了分析,计算表明,弹性变形使其升力线斜率下降、焦点前移。The static aeroelastic calculation program based on unstructured grid was developed. They fluid - structure coupling was achived by iterative calculations of aerodynamic force and structrue deformation. The aerodynamic force was solved using RANS equations and the structure deformation was calculated by flexible matrix. The flexible matrix was interpolated by IPS method, and the grid was deformed by im- proved spring method. The program was validated by calculation of AGARD 445.6 wing, and the static aeroelasticity of this wing was analysed which indicated that the elastic deformation makes lift curve slope descending and aerodynamic, focus moving ahead.

关 键 词：静气动弹性 跨声速 RANS方程 非结构网格 

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]