弹翼静气动弹性计算  

The Static Aeroelastic Calculation of Wings

作　　者：王华毕[1] 吴小胜[2] 姚冰[3] 

机构地区：[1]安徽军工集团,合肥230022 [2]北京理工大学宇航学院,北京100081 [3]安徽神剑科技股份有限公司,合肥230022

出　　处：《弹箭与制导学报》2010年第2期208-210,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：采用迭代法研究大展弦比弹翼的静气动弹性。弹翼的气动载荷采用涡格法进行计算,弹翼结构特性采用有限元软件(ANSYS)进行数值模拟,通过面样条插值方法将气动计算网格上的载荷插值到有限元计算模型的网格节点上进行数据交换。以布撒器弹翼为算例,在计算中对张开式弹翼翼身连接方式进行了简化。计算结果给出了计及弹性的翼面变形以及变形前后翼面的压力分布,且对不同材料特性条件下弹翼变形特性和变形前后的压力分布进行了比较。In this paper, iterative methods are used to investigate the static aeroelastic of high aspect ratio wings. The aerodynamic loads of wings are calulated by the vortex-lattice method, and the structural characteristics of wings are obtained by the Numerical simulation of the software（ANSYS）, and then interpolate the aerodynamic loads into the finite element calculation grid node to exchange data by the surface spline interpolation method. Take airborne dispenser as an illustration, wing-body connected mode is simplified during calculation, the results show wing deformation and pressure distributions before deformation and after, in which elasticity is considered, wing deformational characteristic and pressure distributions of different materials are also compared.

关 键 词：气动弹性 有限元法 气动特性 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]