构建面向对象的并行有限元计算集群

介绍了一种面向对象的方法来组建计算机集群进行并行有限元分析。将构成集群系统的软、硬件组件设计成不同的类层次结构,形成一个完整的集群系统类库,并以系统分析、总体设计、结点通信以及系统效率测试等过程尝试以系统化的方法来分析整个构建过程。实际结果及并行有限元分析算例表明,这样的设计策略,可以非常清晰地从整体上把握系统的实现,大大降低系统构建的复杂性,使所生成的系统具有很好的可扩展性。     

基于集群的并行有限元分析研究

利用面向对象的方法实现了基于集群的并行有限元分析.首先介绍构建高性能计算集群的系统分析新方法,并针对建成集群系统的特点,对并行消息传递库MPI进行了并行语义分析,进而对其主要的实现函数进行面向对象的重构而建立起OO消息传递库,以此为基础分别利用两种不同的策略实现了面向对象的并行有限元分析(OOParaFEA: Object-Oriented Parallel FEA),一种是通过对传统的基于域分解方法的并行PCG算法进行改造而在集群平台实现,另一种是对已有的基于子结构方法的串行有限元分析程序加以扩展,加入系统方程组并行求解器而达到有限元分析并行化的目的.多个分析算例表明,基于集群进行面向对象的并行有限元分析可以有效提高计算效率,为进一步的网络化CAD/CAE研究奠定良好基础.     

面向对象的有限元程序设计

本文按照面向对象的程序设计方法,遵循有限元分析的本质,采用Ｃ＋＋语言,建立了有关描述有限元模型的类,给出了类的描述和它的实现方法。相关的类和方法包括处理矩阵的类、节点类、单元类、材料类、形函数类等。据此编制了有限元分析的数值计算程序,并给出了一个实例。     

面向对象的钢筋混凝土有限元非线性分析程序设计

采用面向对象的程序设计方法，结合钢筋混凝土有限元非线性分析模型，利用MFC(Microsoft Foundation Class Library)建立了有关描述钢筋混凝土有限元非线性分析的类，包括混凝土单元类、钢筋单元类、粘结单元类、非线性计算类，并给出了这些类的描述和它的实现方法，并为钢筋混凝土有限元非线性分析程序采用更合理的面向对象的方法提供了思路。     

基于PVM的网络并行有限元面向对象的设计

子结构是有限元并行计算常用的一种方法,本文采用面向对象的方法,首先对子结构进行了面向对象的设计,得到了其类层次结构图;然后针对工作站网络有限元并行计算环境。提出了基于PVM消息传递平台上的Shadow—Mirror数据传输模型,该模型在有限元并行计算数据传输时,充分发挥数据面向对象的特性,采用设置数据缓冲区、短消息合并等方法以缩短数据通信时间,并据此编制了相应的程序。计算结果表明,使用文中提出的面向对象的Shadow—Mirror数据传输模型可以得到较为理想的并行加速比,而且随着问题规模增大,并行加速比增高。本文研究内容为进一步开展基于工作站网络的并行有限元研究提供了一个可参考的基础。     

面向对象有限元方法研究进展

综述了面向对象有限元方法的研究现状。基于国内外大量相关文献，首先评述了有限元方法的面向对象分析过程（OOA），包括对象的识别，对象属性，方法和关系的确定等等。其次涉及有限元方法的面向对象设计过程（OOD），具体讨论了人机交互，任务管理和数据管理等内容。再次讨论了有限元方法的面向对象编程过程（OOP），如编程语言的选择，面向对象有限元的应用和集成等问题。此外还延拓到面向对象方法增强有限元软件的表现，面向对象有限元的扩展等。最后展望该方法的发展动态。     

有限元并行分布计算研究

本文提出一种在多处理机系统上进行有限元并行分布计算的方式及称之为∑通讯的通讯方法,对实现有限元并行分布计算的若干重要问题进行了初步分析讨论。     

有限元程序的一种并行化算法

传统的以串行计算机为物质基础的有限元算法分析未能满足科学研究和工程技术发展的需要．并行处理技术的发展为解决此类问题提供了新的契机．机群式并行计算机是当今较为流行的一种并行处理方式．根据有限元法的特点，提出了一种并行有限元算法，并在多处理机分布式内存并行计算机环境下完成了面向对象并行有限元程序的编制．算例表明该算法能大大提高其分析速度，而且算法简单，实现方便．     

多波前并行处理的弹塑性子结构并行有限元

研究一种基于ＰＶＭ的弹塑性子结构并行有限元法。利用多个波前,对各子结构并行地进行静凝聚。再采用预条件共轭梯度法（ＰＣＧ）并行求解界面方程。算例表明该方法能获得较好的并行加速比,同时也能有癣地节省内存量。     

面向对象有限元分析流程自动化系统框架设计

流程自动化技术因其能够将设计人员从繁重单调的建模工作中解放出来,提高仿真效率与精度,已成为了当前CAE研究中的研究热点.传统的流程自动化系统的设计无法避免框架化程序设计的弊端,在系统功能扩充以及代码维护及复用上有极大的不足.论文运用面向对象程序设计技术,在一般的有限元软件二次开发技术的基础上,提出了一套基于面向对象技术的流程自动化系统的基本框架,说明了设计思路及意图,并给出实例验证本框架的可行性,展示了本框架的优势.     

PARALLEL ANALYSIS OF COMBINED FINITE／DISCRETE ELEMENT SYSTEMS ON PC CLUSTER

A computational strategy is presented for the nonlinear dynamic analysis of largescale combined finite/discrete element systems on a PC cluster. In this strategy, a dual-level domain decomposition scheme is adopted to implement the dynamic domain decomposition. The domain decomposition approach perfectly matches the requirement of reducing the memory size per processor of the calculation. To treat the contact between boundary elements in neighbouring subdomains, the elements in a subdomain are classified into internal, nterfacial and external elements. In this way, all the contact detect algorithms developed for a sequential computation could be adopted directly in the parallel computation. Numerical examples show that this implementation is suitable for simulating large-scale problems. Two typical numerical examples are given to demonstrate the parallel efficiency and scalability on a PC cluster. The project supported by the National Natural Science Foundation of China (10372114) and the Engineering and Physical Sciences Research Council (EPSRC) of UK (GR/R21219)     

并行冲击/侵彻有限元数值模拟技术

探讨了冲击/侵彻问题涉及到的非线性材料模型、接触搜索算法、接触力计算公式、破坏模式等理论和算法,介绍了基于集群并行计算机的有限元法并行化基本思路和方法。应用实例表明本文中提出的有限元计算格式和并行化方法能够有效求解冲击/侵彻问题。     

Parallel finite element computation of missile aerodynamics

A flow simulation tool, developed by the authors at the Army HPC Research Center, for compressible flows governed by the Navier–Stokes equations is used to study missile aerodynamics at supersonic speeds, high angles of attack and for large Reynolds numbers. The goal of this study is the evaluation of this Navier–Stokes computational technique for the prediction of separated flow fields around high-length-to-diameter (L/D) bodies. In particular, this paper addresses two issues: (i) turbulence modelling with a finite element computational technique and (ii) efficient performance of the computational technique on two different multiprocessor mainframes, the Thinking Machines CM-5 and CRAY T3D. The paper first provides a discussion of the Navier–Stokes computational technique and the algorithm issues for achieving efficient performance on the CM-5 and T3D. Next, comparisons are shown between the computation and experiment for supersonic ramp flow to evaluate the suitability of the turbulence model. Following that, results of the computations for missile flow fields are shown for laminar and turbulent viscous effects. © 1997 John Wiley & Sons, Ltd.     

Parallel finite element simulation of large ram-air parachutes

In the near future, large ram-air parachutes are expected to provide the capability of delivering 21 ton payloads from altitudes as high as 25,000 ft. In development and test and evaluation of these parachutes the size of the parachute needed and the deployment stages involved make high-performance computing (HPC) simulations a desirable alternative to costly airdrop tests. Although computational simulations based on realistic, 3D, time-dependent models will continue to be a major computational challenge, advanced finite element simulation techniques recently developed for this purpose and the execution of these techniques on HPC platforms are significant steps in the direction to meet this challenge. In this paper, two approaches for analysis of the inflation and gliding of ram-air parachutes are presented. In one of the approaches the point mass flight mechanics equations are solved with the time-varying drag and lift areas obtained from empirical data. This approach is limited to parachutes with similar configurations to those for which data are available. The other approach is 3D finite element computations based on the Navier–Stokes equations governing the airflow around the parachute canopy and Newton’s law of motion governing the 3D dynamics of the canopy, with the forces acting on the canopy calculated from the simulated flow field. At the earlier stages of canopy inflation the parachute is modelled as an expanding box, whereas at the later stages, as it expands, the box transforms to a parafoil and glides. These finite element computations are carried out on the massively parallel supercomputers CRAY T3D and Thinking Machines CM-5, typically with millions of coupled, non-linear finite element equations solved simultaneously at every time step or pseudo-time step of the simulation. © 1997 John Wiley & Sons, Ltd.     

OBJECT-ORIENTED FINITE ELEMENT ANALYSIS AND PROGRAMMING IN VC++

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一种新型并行化有限元结构模态分析集成系统

以成熟有限元软件的模态分析流程和大型稀疏矩阵特征值的并行求解为基础,开发出一种基于大规模并行机的新型有限元结构模态分析系统。通过对串行CAE软件的二次开发,将模态分析过程中计算量最大的特征值求解部分代之以并行计算。针对并行机特性以隐式重启动Lanczos算法为基础,编写了基于MPI的特征值并行求解程序,并通过实际算例验证了并行程序的加速比和扩展性;同时实现并行程序与其它串行分析步骤的无缝集成,使集成系统的界面友好,操作方便。本系统使结构模态分析的规模和速度大幅度提高,以大型CAE软件MSC／NASTRAN为并行化求解器开发平台,在“神威Ⅰ”超级计算机上验证了其可行性和高效性。     

Parallel finite element computation of unsteady incompressible flows

A parallel semi-explicit iterative finite element computational procedure for modelling unsteady incompressible fluid flows is presented. During the procedure, element flux vectors are calculated in parallel and then assembled into global flux vectors. Equilibrium iterations which introduce some ‘local implicitness’ are performed at each time step. The number of equilibrium iterations is governed by an implicitness parameter. The present technique retains the advantages of purely explicit schemes, namely (i) the parallel speed-up is equal to the number of parallel processors if the small communication overhead associated with purely explicit schemes is ignored and (ii) the computation time as well as the core memory required is linearly proportional to the number of elements. The incompressibility condition is imposed by using the artificial compressibility technique. A pressure-averaging technique which allows the use of equal-order interpolations for both velocity and pressure, this simplifying the formulation, is employed. Using a standard Galerkin approximation, three benchmark steady and unsteady problems are solved to demonstrate the accuracy of the procedure. In all calculations the Reynolds number is less than 500. At these Reynolds numbers it was found that the physical dissipation is sufficient to stabilize the convective term with no need for additional upwind-type dissipation. © 1998 John Wiley & Sons, Ltd.