Structured Surface Mesh Generation For Aircrafts Based On Computational Conformal Geometry

CFD plays a very important role in the aerospace filed.As the pre-processing stage,mesh generation takes up almost 60% of the entire CFD numerical simulation period,which becomes a bottleneck factor affecting the design cycle of the aircraft.The surface mesh is the most consuming time phase in the structural mesh generation process.Therefore,it is very necessary to carry out research on the rapid generation algorithms for structured surface meshes in order to improve the efficiency of mesh generation and shorten the design period of aircraft.Computational conformal geometry is an emerging advanced mathematical tool.The parameterization of geometric models is realized by computer.The main algorithms include harmonic map,surface Ricci flow algorithm and Hodge decomposition algorithm.It has been found that different algorithms can be integrated for different geometric features to achieve complete geometric parameterization.Therefore,it is proposed to use the computational conformal geometry technique to achieve automatic generation of the structured surface mesh.In this paper,an automatic generation method of structured surface mesh based on computational conformal geometry is proposed.The main steps are as follows: 1)Pre-processing the initial digital model,discretizing surface and generating the spatial background mesh,and then using the computational conformal geometry technology to parameterize it into the two-dimensional parameter domain;2)Generating the mesh of the two-dimensional in the parameter domain;3)Inversely mapping the structural mesh after the two-dimensional parameter domain to the spatial background mesh,followed by the projection of structured mesh in the spatial background grid onto the CAD model surface,and finally realizing the division of the surface structure mesh.In order to verify the quality of the mesh generated by our proposed method,a structured surface mesh is generated for a rocket configuration using traditional manual method and the proposed method,and then calculated by a in-house solver.The numerical experiments show that the residual,pressure distribution and Mach number distribution of the two sets of meshes are basically identical.