摘要
为提高飞机平尾的结构计算精度,利用HyperMesh同时建立结构网格与流场网格,在翼面结构与流场中物面节点坐标位置完全相同的情况下,分别采用偶极子格网法(Double-Lattice Method,DLM)与计算流体力学(Computational Fluid Dynamics,CFD)法计算飞机平尾负攻角变化时的升力变化情况.在HyperMesh中建立平尾有限元模型和流体模型,用FLUENT计算气动升力,用MSC Nastran进行静力分析.计算结果与实验结果的对比表明DLM更快,CFD法更精确,所以可以在翼面设计初期用DLM计算翼面载荷,在翼面设计后期用CFD法计算翼面载荷.
To improve the computational accuracy of horizontal tail structure of aircraft, the grids of structural and flow field are simultaneously established by HyperMesh, the nodal coordinates of wing surface structure and wall in the fluid field are fully equal, and the lift force is calculated by Double- Lattice Method（DLM） and Computational Fluid Dynamics（CFD） method respectively while the minus attack angle of horizontal tail is changing. The structural finite element model and fluid model are built by HyperMesh, the aerodynamic Lift force is calculated by FLUENT, and the static force analysis is performed by MSC Nastran. The comparison of the results of DLM and CFD method and the experimental data indicates that DLM is faster, CFD method is more accurate. Therefore, DLM can be used to calculate air load in the initial design phase of wing surface while CFD method can be used to calculate air load in the detailed design phase.
出处
《计算机辅助工程》
2009年第2期21-24,共4页
Computer Aided Engineering
