摘要
以二维非定常Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程为模型方程，采用Ｊａｍｅｓｏｎ有限体积法并引入变系数隐式残值光顺及固接网格计算了直升机旋翼不同展向位置处翼剖面的非定常气动力。进而采用插值的方法模拟直升机在悬停及前飞状态下，旋翼的桨叶所受的非定常气动力载荷，并将之与桨叶的结构振动方程相耦合，求解其时域内的结构响应。非定常气动力计算结果与实验结果做了对比，两者比较吻合，旋翼结构响应计算结果合理。
Using Jameson's finite volume method,two dimensional unsteady Navier Stokes equations are solved to calculate the unsteady aerodynamic on the airfoil of different position of the helicopter rotor.In the calculation,residual average with variable coefficients are also used and the grid are fixed to the airfoil.Fairly good agreement between calculation results and experimental results is shown in the paper.Then interpolation method,based on the upper calculation,are employed to simulate the aerodynamic load on the rotor in hover and forward flight.At the same time,the structural vibration equations of rotor are calculated with finite element method.At last,the aerodynamic load is coupled with the vibration equations of helicopter rotor,and the reasonable results for structural response of rotor are obtained.
出处
《飞行力学》
CSCD
北大核心
1998年第1期31-36,共6页
Flight Dynamics
关键词
旋翼
非定常
结构响应
气动力
直升机
N-S方程
Rotor Unsteady Navier Stokes equations Finite volume method Structural response
