三维六面体有限元网格自动划分中的一种单元转换优化算法

本文采用十节点曲边四面体转换为六面体网格,并采用非线性约束优化算法取Ｌａｐｌａｃｉａｎ光滑处理算法有效地提高六面体单元的质量,实现了对任意实体的六面体网格自动划分。     

三维有限元六面体网格几何自适应再生成方法

基于几何自适应的六面体网再生成方法,提出了一种以栅格法为基本方法,对有限元网格再划分过程中的网格再划分标准、几何形状的获取以及新旧网格之间物理量的传递等关键问题进行了研究.重点介绍了基于几何自适应的六面体网格再生成算法,首先对旧网格实体模型进行识别,根据实体模型几何特征建立加密源点信息场;然后采用栅格法生成核心网格并对...     

一种基于单元几何变形的网格修匀方法

基于单元几何变形操作提出一种高效的非结构网格质量修匀方法。其基本过程是先对每个单元独立地进行拉伸-收缩操作以优化单元的形状,然后在整个网格中通过对各单元的节点位置进行加权平均来获得改善后的网格。为进一步提高修匀方法对网格质量的优化效果,并使得该方法具备一定的网格调整能力,结合动网格技术提出了对单元进行大范围和较大幅度移动的策略;在修匀过程中还通过适当算法调整单元形心位置和单元尺寸,进一步增强了修匀方法对网格局部进行疏密调节的能力。本文方法可适用于平面和三维非结构网格的质量改善及网格调整。若干算例表明了方法的有效性。     

基于双重自适应的六面体网格再生成方法

提出了一种以栅格法为基本方法,基于几何特征和物理场量双重自适应的六面体网格再生成方法。首先,依据旧网格的表面曲率和几何特征,采用基于栅格法的几何自适应网格再生成方法,生成密度受控的基础网格;然后,将旧网格的物理场量传递到基础网格中;最后,采用有限元误差估计方法对新网格单元的计算误差进行估计,对误差较大的单元进行加密,减...     

多特征几何体的全六面体网格自动生成方法

有限元分析的精度和效率与网格划分的质量有直接关系.目前尚缺乏一种普适性的自动网格划分方法,尤其是对于具有多种几何特征的复杂模型,现有的六面体网格自动划分算法存在不同几何特征间的网格兼容性较差以及孔状特征周围网格质量不高的问题.对此本文提出一种基于映射法的六面体网格自动生成方法,在映射法的基本框架下,将物理空间中的复杂几何体映射为计算空间中的规则几何体,引入边界顶点分类,将复杂几何体边界进行简化,将子域约束进行连接,寻找贯穿边界,以使映射网格在约束特征间兼容;对圆弧特征进行等效转化,降低曲率过大对于网格过渡的影响.实例验证表明,本方法稳定可靠,生成的六面体网格质量较高,能够解决多特征复杂几何体六面体网格自动划分问题.     

薄元分解与Laplacian光顺相结合的四面体有限元网格优化方法

提出一种有效的三维实体四面体有限元网格质量优化方法以满足有限元分析对网格质量的要求。对薄元分解法进行改进,改进的薄元分解法更全面地考虑了各种劣质单元类型,能够对三维实体网格剖分中产生的各种类别的孤立劣质单元进行有效的分解;将改进的薄元分解法与Laplacian光顺优化方法相结合以解决某些网格剖分算法如推进波前法和Delaunay三角化方法产生的非孤立劣质单元问题。经过实例检验,本文提出的四面体单元网格优化算法健壮有效、易于实现,能够显著提高最差单元的质量。     

基于OPS和拓扑交换的离心泵网格质量提高算法

针对OPS算法本身固有的无法提高"全边界单元"质量的缺陷,提出了一种结合OPS和拓扑优化的网格质量提高算法。该方法通过判别"全边界单元"中边(或面)受到相邻单元共享的形式,采用不同的拓扑交换策略,且在拓扑交换过程中仅考虑网格的拓扑相关性,并不考虑网格的质量,保证将"全边界单元"转化为OPS算法提高其质量的其他类型边界单元。算例分析表明,本文算法相比Freitag的组合算法在消除极端二面角方面更具优势,相比OPS算法对提高离心泵边界网格及整体网格质量也具有较好的优势。     

四面体网格质量度量准则的研究

简要回顾了度量四面体单元质量的几个常用准则。长期以来，这些准则被认为在一定意义下是相互等价的。数值试验表明，对单元形状的变化用不同的准则度量有可能产生矛盾的评判结果，从而影响到网格质量优化的进程和结果。因此在进行网格剖分或网格优化时，应对所采用的度量准则做仔细的研究和测试。     

High‐fidelity aerodynamic shape optimization of modern transport wing using efficient hierarchical parameterization

Aerodynamic shape optimization technology is presented, using an efficient domain element parameterization approach. This provides a method that allows geometries to be parameterized at various levels, ranging from gross three‐dimensional planform alterations to detailed local surface changes. Design parameters control the domain element point locations and, through efficient global interpolation functions, deform both the surface geometry and corresponding computational fluid dynamics volume mesh, in a fast, high quality, and robust fashion. This results in total independence from the mesh type (structured or unstructured), and optimization independence from the flow‐solver is achieved by obtaining gradient information for an advanced gradient‐based optimizer by finite‐differences. Hence, the optimization tool can be used in conjunction with any flow‐solver and/or mesh generator. Results have been presented recently for two‐dimensional aerofoil cases, and shown impressive results; drag reductions of up to 45% were demonstrated using only 22 active design parameters. This paper presents the extension of these methods to three dimensions, with results for highly constrained optimization of a modern aircraft wing in transonic cruise. The optimization uses combined global and local parameters, giving 388 design variables, and produces a shock‐free geometry with an 18% reduction in drag, with the added advantage of significantly reduced root moments. Copyright © 2009 John Wiley & Sons, Ltd.     

结构形状优化与智能模型化

阻碍形状优化软件广泛应用的障碍之一是依据自然设计度量描述和建立设计模型、分析模型、优化模型以及实现三个模型之间的转换.本文称这一困难为结构形状优优设计软件的适用性.本文提出了一种方法用来动态地确定平面连续体结构形状优化过程中的边界,应用基于人工智能方法的启发式规则与技术,自动生成由设计单元法表示的几何模型,也就是将一个结构自动剖分成若干个大的四边形映射单元.这些大单元对于进一步的网络生成是必要的,同时也是向全自动计算机辅助形状优化系统前进的重要一步.     

Shape optimization of a body located in incompressible flow using adjoint method and partial control algorithm

The purpose of this study is to obtain an optimal shape of a body located in an incompressible viscous flow. The optimal shape of the body is defined so as to minimize the fluid forces acting on it by determining the surface coordinates based on the finite element method and the optimal control theory. The performance function, which is used to judge the optimality of a shape, is defined as the square sum of the drag and lift forces. The minimization problem is solved using an adjoint equation method. The gradient in the adjoint equation is affected by the finite element configuration. The use of a finite element mesh whose shape is appropriate for the procedure is important in shape optimization. If the finite element mesh used is not suitable for computations, the exact gradient is not calculated. Therefore, a structured mesh is used for the adjacent area of the body and all finite element meshes are refined using the Delaunay triangulation at each iteration computation. The weighted gradient method is applied as the minimization technique. Using an algorithm in which all nodal coordinates on the surface of the body are employed and starting from a circle as an initial shape, a front‐edged and rear‐round shape is obtained because of the vortices at the back of the body. To overcome this difficulty, we introduced the partial control algorithm, in which some of the nodal coordinates on the surface of the body are updated. From four cases of computational studies, we reveal that the optimal shape has both sharp front and sharp rear edges. All computations are conducted at Reynolds number Re=250. The minimum value of the performance function is obtained. Copyright © 2010 John Wiley & Sons, Ltd.     

Shape morphing and topology optimization of fluid channels by explicit boundary tracking

An integrated shape morphing and topology optimization approach based on the deformable simplicial complex methodology is developed to address Stokes and Navier‐Stokes flow problems. The optimized geometry is interpreted by a set of piecewise linear curves embedded in a well‐formed triangular mesh, resulting in a physically well‐defined interface between fluid and impermeable regions. The shape evolution is realized by deforming the curves while maintaining a high‐quality mesh through adaption of the mesh near the structural boundary, rather than performing global remeshing. Topological changes are allowed through hole merging or splitting of islands. The finite element discretization used provides smooth and stable optimized boundaries for simple energy dissipation objectives. However, for more advanced problems, boundary oscillations are observed due to conflicts between the objective function and the minimum length scale imposed by the meshing algorithm. A surface regularization scheme is introduced to circumvent this issue, which is specifically tailored for the deformable simplicial complex approach. In contrast to other filter‐based regularization techniques, the scheme does not introduce additional control variables, and at the same time, it is based on a rigorous sensitivity analysis. Several numerical examples are presented to demonstrate the applicability of the approach.     

基于转换模板的三维实体全六面体网格生成方法

以四面体一六面体基本转换模板为基础,提出一系列具有伸缩性的扩展转换模板．可根据需要选择不同模板及其组合,将四面体分解为不同数量、不同密度过渡形式的六面体单元。这样,初始四面体网格不需要划分得很细,生成的六面体单元数量也可以通过采用不同规格的扩展转换模板而得到控制。提出了基于CAD几何造型的边界节点坐标修正方法．从而使边界网格更好地拟合几何模型边界。     

CFD‐based optimization of aerofoils using radial basis functions for domain element parameterization and mesh deformation

A novel domain element shape parameterization method is presented for computational fluid dynamics‐based shape optimization. The method is to achieve two aims: (1) provide a generic ‘wrap‐around’ optimization tool that is independent of both flow solver and grid generation package and (2) provide a method that allows high‐fidelity aerodynamic optimization of two‐ and three‐dimensional bodies with a low number of design variables. The parameterization technique uses radial basis functions to transfer domain element movements into deformations of the design surface and corresponding aerodynamic mesh, thus allowing total independence from the grid generation package (structured or unstructured). Independence from the flow solver (either inviscid, viscous, aeroelastic) is achieved by obtaining sensitivity information for an advanced gradient‐based optimizer (feasible sequential quadratic programming) by finite‐differences. Results are presented for two‐dimensional aerofoil inverse design and drag optimization problems. Inverse design results demonstrate that a large proportion of the design space is feasible with a relatively low number of design variables using the domain element parameterization. Heavily constrained (in lift, volume, and moment) two‐dimensional aerofoil drag optimization has shown that significant improvements over existing designs can be achieved using this method, through the use of various objective functions. Copyright © 2008 John Wiley & Sons, Ltd.     

Adaptive shape functions and internal mesh adaptation for modeling progressive failure in adhesively bonded joints

Macroscopic finite elements are elements with an embedded analytical solution that can capture detailed local fields, enabling more efficient, mesh independent finite element analysis. The shape functions are determined based on the analytical model rather than prescribed. This method was applied to adhesively bonded joints to model joint behavior with one element through the thickness. This study demonstrates two methods of maintaining the fidelity of such elements during adhesive non-linearity and cracking without increasing the mesh needed for an accurate solution. The first method uses adaptive shape functions, where the shape functions are recalculated at each load step based on the softening of the adhesive. The second method is internal mesh adaption, where cracking of the adhesive within an element is captured by further discretizing the element internally to represent the partially cracked geometry. By keeping mesh adaptations within an element, a finer mesh can be used during the analysis without affecting the global finite element model mesh. Examples are shown which highlight when each method is most effective in reducing the number of elements needed to capture adhesive nonlinearity and cracking. These methods are validated against analogous finite element models utilizing cohesive zone elements.     

An ALE mesh movement scheme for long‐term in‐flight ice accretion

The rather irregular shapes that glaze ice may grow into while accreting over the surface of an aircraft represent a major difficulty in the numerical simulation of long periods of in‐flight icing. There is a constant need for remeshing: a wasteful procedure. In the framework of ALE formulations, a mesh movement scheme is presented, in which frame and elasticity analogies are loosely coupled. The resulting deformed mesh preserves the quality of elements, especially in the near‐wall region, where accurate prediction of heat flux and shear stresses is required. The proposed scheme handles mesh deformation in a computationally efficient manner by localizing the mesh deformation. The 2D problem of ice accretion over single and multi‐element airfoils is considered here as a numerical experiment. Experimentally measured glaze ice shapes were used to evaluate the performance of the present approach. Copyright © 2011 John Wiley & Sons, Ltd.     

汽车覆盖件工具曲面有限元网格自适应转换方法

提出一种适用于汽车覆盖件曲面有限元网格转化和在单元水平上提高模拟精度的方法,将平面下通过合并三角形单元成四边形单元的有限元网格转换方法的应用范围扩展到曲面,并且降低了对初始网格形状的要求。算法的关键在于增加了对曲面相邻单元不同夹角情况下的处理和优化规则,以使其能够更好地拟合原始CAD曲面。     

An efficient and accurate algebraic interface capturing method for unstructured grids in 2 and 3 dimensions: The THINC method with quadratic surface representation

We present in this paper an efficient and accurate volume of fluid (VOF) type scheme to compute moving interfaces on unstructured grids with arbitrary quadrilateral mesh elements in 2D and hexahedral elements in 3D. Being an extension of the multi‐dimensional tangent of hyperbola interface capturing (THINC) reconstruction proposed by the authors in Cartesian grid, an algebraic VOF scheme is devised for arbitrary quadrilateral and hexahedral elements. The interface is cell‐wisely approximated by a quadratic surface, which substantially improves the numerical accuracy. The same as the other THINC type schemes, the present method does not require the explicit geometric representation of the interface when computing numerical fluxes and thus is very computationally efficient and straightforward in implementation. The proposed scheme has been verified by benchmark tests, which reveal that this scheme is able to produce high‐quality numerical solutions of moving interfaces in unstructured grids and thus a practical method for interfacial multi‐phase flow simulations. Copyright © 2014 John Wiley & Sons, Ltd.     

四面体模型质量度量准则及其之间的关系

四面体模型质量度量准则是评价网格模型质量的标准,但长期以来,对四面体单元质量的度量和评价并没有公认的标准。因此,本文对常用的四面体网格模型质量度量准则进行总结,并从理论上证明了各质量度量准则之间的关系,同时通过实验分析各质量度量准则之间的这种关系是否成立。分析认为在优化四面体模型时,不能仅仅采用某一种度量标准来评价网格的质量,应根据不同的四面体类型,采用不同的准则或将几种准则联合起来对四面体模型质量进行度量。     

A high‐order element based adaptive mesh refinement strategy for three‐dimensional unstructured grid

Adaptive mesh refinement (AMR) shows attractive properties in automatically refining the flow region of interest, and with AMR, better prediction can be obtained with much less labor work and cost compared to manually remeshing or the global mesh refinement. Cartesian AMR is well established; however, AMR on hybrid unstructured mesh, which is heavily used in the high‐Reynolds number flow simulation, is less matured and existing methods may result in degraded mesh quality, which mostly happens in the boundary layer or near the sharp geometric features. User intervention or additional constraints, such as freezing all boundary layer elements or refining the whole boundary layer, are required to assist the refinement process. In this work, a novel AMR strategy is developed to handle existing difficulties. In the new method, high‐order unstructured elements are first generated based on the baseline mesh; then the refinement is conducted in the parametric space; at last, the mesh suitable for the solver is output. Generating refined elements in the parametric space with high‐order elements is the key of this method and this helps to guarantee both the accuracy and robustness. With the current method, 3‐dimensional hybrid unstructured mesh of huge size and complex geometry can be automatically refined, without user intervention nor additional constraints. With test cases including the 2‐dimensional airfoil and 3‐dimensional full aircraft, the current AMR method proves to be accurate, simple, and robust.