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混合网格已广泛应用于复杂外形的粘性流动模拟,能否将其推广应用于气动弹性研究,混合网格的变形方法成为主要问题。发展了一种混合网格变形方法,即生成一套非结构四面体背景网格,采用弹簧网络法进行背景网格变形,在背景网格与流场计算的CFD网格之间建立一种快速的代数插值方法,获得流场计算的混合网格变形。由于背景网格仅用于网格变形,不参与流场计算,物面网格可以与流场计算网格不一致,大大减少网格数量,提高弹簧网络法的变形能力和计算效率,进而提升流场计算混合网格的变形能力和计算效率。对于复杂外形流场网格和背景网格在物面的不一致可能造成的覆盖不完全问题,提出了同时生成覆盖流体域和固体域的多套非结构背景网格的方法,保证复杂外形计算时混合网格的高质量变形。由于背景网格采用全三维的线弹簧加扭转弹簧的动网格变形方法,大大提高了大变形的网格变形能力。首先以M 6机翼的非结构和混合网格变形为例,与已有方法比较,验证本文方法的有效性;其次运用于三维转动、平动、弯曲变形等典型工况,说明方法对大变形的实用性;最后运用于气动弹性标模和机翼带外挂导弹的复杂外形的颤振特性计算,说明其处理复杂工程问题的能力。
Hybrid mesh has been widely used in viscous flow simulation of complex shape. Whether it can be applied to the research of aeroelasticity or not, the hybrid mesh deformation method becomes the main problem. A hybrid mesh deformation method is developed, in which a set of unstructured tetrahedron background meshes is generated, the background mesh deformation is performed using the spring mesh method, and a fast Algebraic interpolation method to obtain the flow field calculated hybrid mesh deformation. Because the background mesh is only used for the deformation of the mesh and does not participate in the calculation of the flow field, the object mesh can be inconsistent with the flow field computation mesh, greatly reducing the number of meshes, increasing the deformation capacity and computational efficiency of the spring mesh method, Field computing hybrid mesh deformation capacity and computational efficiency. Aiming at the incomplete coverage problem caused by the inconsistency of the object surface between the complex shape flow field grid and the background grid, a method of simultaneously generating multiple sets of unstructured background grids covering the fluid domain and the solid domain is proposed to ensure the complex shape calculation High-quality deformation of mixed meshes. As the background grid using full three-dimensional line spring plus torsion spring moving grid deformation method, greatly improving the large deformation of the grid deformation capacity. Firstly, the unstructured and mixed mesh deformation of M 6 wing is taken as an example to verify the effectiveness of the proposed method compared with the existing methods. Secondly, the method is applied to typical working conditions such as three-dimensional rotation, translational motion and bending deformation. The practicality of deformation; and finally the calculation of the flutter properties of the complex profiles of aeroelastic modules and wing-mounted missiles, illustrating their ability to handle complex engineering problems.