柔性梁几何非线性/后屈曲分析的改进势能列式方法研究

针对基于Updated-Lagrangian列式的能量方法存在:1) 由于位移模型的近似性而带来虚假节点力;2) 在分析节点空间转动效应上存在争议;3) 势能高阶项由于物理概念不明确给简化列式带来困难等问题,提出描述柔性梁构件有限位移过程受力状态变化的势能列式方法。根据连续介质力学极分解定理,将典型增量步内单元内力势能分解为刚体变位下初始节点力势能和自然变形中积累的初始节点力势能和应变能,推导了满足刚体运动检验和变形后节点受力平衡的空间梁单元几何刚度矩阵。建立全面反映构件非线性大位移行为的增量割线刚度矩阵显式列式。数值分析结果表明,势能列式能准确预测任意荷载作用下结构非线性平衡路径,物理概念清晰,适应工程实践对一般杆系结构非线性分析需求。     

柔性框架结构动力非线性分析的刚体准则法

大跨、高层等柔性结构,其动力响应往往表现出大位移、大转动等非线性特征。动力非线性问题的分析关键在于运动方程的高效稳定求解,以及单元大转动产生的结点力增量的有效计算。动力时程分析通常采用直接积分法,但对于强非线性动力问题,直接积分法难以兼顾计算精度与稳定性。该文基于几何非线性分析的刚体准则,针对杆件结构大转动小应变的非线性问题,提出了一种新型空间杆系结构动力非线性分析的刚体准则法。该方法采用满足刚体准则的空间非线性梁单元,结合HHT-α法求解结构运动方程,并将刚体准则植入动力增量方程的迭代求解过程以计算结点力增量。通过典型柔性框架算例结果表明,该文方法可以有效分析柔性框架结构的强动力非线性行为。与高精度单元相比,该文采用的单元刚度矩阵构造简明,计算过程简洁;与商业软件所用方法相比,单元数和迭代步少,精度高,适于工程应用。     

弹性膜结构几何非线性分析的刚体准则法

提出了一种新型弹性空间膜结构几何非线性分析方法。根据刚体准则的思想,初始受力平衡的单元在经历刚体位移后,其单元结点力方向随单元发生转动而大小不变,单元仍保持平衡。建立了新型三角形空间膜单元,该膜单元由三根空间杆件组成铰接三角形,并在中间张拉薄膜而成,杆件的材料与薄膜相同。所建立的空间膜单元的整体位形由杆单元空间铰接三角形确定,而膜单元的有限弹性变形由内部张拉的薄膜变形确定。由满足刚体准则的杆单元几何刚度矩阵推导了空间膜单元的几何刚度矩阵。根据刚体准则思想,认为膜单元在变形过程中,其刚体位移对其整体变形的贡献较大,而单元的弹性变形贡献较小。采用更新的拉格朗日格式的增量迭代法,在分析的每个阶段充分考虑刚体转动效应,利用小变形线性化理论处理自然变形的剩余效应。该方法几何刚度矩阵推导简单,无需引入对单元大变形的人为假定,可容易地退化为平面膜单元,增量迭代计算过程充分考虑刚体准则,对若干典型空间膜结构算例的分析及与已有方法的比较,验证了所建单元与方法的准确性以及计算效率。     

考虑剪切效应三维纤维梁单元的几何非线性增量有限元分析

该文以三维连续介质力学和虚功原理为基础,推导了增量U.L.有限元列式,该列式保留了大位移刚度矩阵项,并对该刚度矩阵进行修正使其成为对称矩阵。根据增量U.L.列式,推导了三维纤维梁单元的刚度矩阵。该单元采用平截面假定,以轴向节点位移表示截面上任意一点的位移,并结合Timoshenko梁理论来考虑剪切效应。以上原理编制分析程序,通过几个算例分析,证明了该方法的精确性、通用性。     

组合构件双重非线性分析模型研究与应用

以超高层建筑中当前广泛应用的杆系组合构件为研究对象,采用三维空间梁单元对其进行复杂受力状态下的双重非线性分析。为贴近实际工程同时简化计算,首先根据有限元方法和最小势能原理建立单元考虑几何非线性的弹性切线刚度矩阵;然后通过划分截面广义应变将单元截面刚度矩阵分离为弹性刚度矩阵与塑性刚度矩阵,在假定广义应变增量分布状态基础上,基于纤维模型法推导出单元塑性刚度矩阵;最后将考虑几何非线性的弹性刚度矩阵与塑性刚度矩阵集合成整体刚度矩阵,根据构件自身特性选取合理材料本构关系及数值计算方法进行构件非线性受力分析。数值分析结果表明,该文模型与方法概念清晰、计算精度高,还可应用于钢筋混凝土构件的受力性能非线性分析。     

改进共旋坐标法的Timoshenko梁单元非线性分析

为提高空间Timoshenko梁单元非线性问题的计算精度,在共旋坐标法的基础上,提出了一种改进的Timoshenko梁单元几何非线性分析方法。利用虚功原理得到改进空间梁单元的刚度矩阵;使用有限质点法中的逆向运动思路计算单元局部坐标系下的刚体旋转矩阵;根据整体坐标系与局部坐标系之间旋转角度的转化以及微分关系,求得空间梁单元的切线刚度矩阵;编制了相应的有限元程序,对多个经典的大变形结构进行几何非线性分析。计算结果印证了该文所提出改进方法的正确性,同时与传统共旋坐标法相比,具有更高的精度。     

基于场一致性的可带铰空间梁元几何非线性分析

虽然关于几何非线性分析的空间梁单元研究成果较多,但这些单元均是基于几何一致性得到的单元刚度矩阵,而基于场一致性的单元研究则较少,该文基于局部坐标系(随转坐标系)下扣除结构位移中的刚体位移得到的结构变形与结构坐标系下的总位移的关系,直接利用微分方法导出两者增量位移之间的关系,再基于场一致性原则,最终获得空间梁单元在大转动、小应变条件下的几何非线性单元切线刚度矩阵,在此基础上根据带铰梁端受力特征,导出了能考虑梁端带铰的单元切线刚度矩阵表达式,利用该文的研究成果编制了程序,对多个梁端带铰和不带铰的算例进行了空间几何非线性分析,计算结果表明这种非线性单元列式的正确性,实用价值较强。     

GSQ24壳体单元用于板壳结构的几何非线性分析

在考虑剪切变形的Von Karman大变形小应变假设下,基于全Lagrange描述方法,将平面内带有旋转自由度的GSQ24壳体单元用于板壳结构的几何非线性分析,给出了板壳结构大变形下的小位移刚度矩阵、初应力刚度矩阵、初位移刚度矩阵有限元列式。同时,文中也给出了既考虑材料非线性,又考虑几何非线性的强非线性问题的板壳结构分析时的有限元列式。数值算例与变分法和级数解结果比较,表明本文方法的可行性。     

三维杆系结构的几何非线性有限元分析

为了更准确地描述杆系结构的几何非线性性能,建立了一种基于三维梁单元有限元分析的计算方法。引入了考虑两方向曲率和扭转角变化的坐标转换矩阵来描述任意增量下的单元平移和转动;采用了包括轴向变形和扭转的非线性项的刚度矩阵来考虑高阶非线性项的影响。应用广义位移控制法进行增量迭代,编制了相应的三维梁单元非线性计算程序NL_Beam3D。通过对几个例子进行的分析,验证了该方法可较好地考虑结构几何非线性。     

平面杆系结构几何非线性数值分析

本文基于Ｔ．Ｌ坐标，导出了梁单元的几何非线性的割线刚度矩阵和切线刚度矩阵显式，算例表明，本文的两个刚度矩阵可有效的分析平面杆系结构的几何非线性问题。     

On the derivation and possibilities of the secant stiffness matrix for non linear finite element analysis

In this paper the general non symmetric parametric form of the incremental secant stiffness matrix for non linear analysis of solids using the finite element metod is derived. A convenient symmetric expression for a particular value of the parameters is obtained. The geometrically non linear formulation is based on a Generalized Lagrangian approach. Detailed expressions of all the relevant matrices involved in the analysis of 3D solids are obtained. The possibilities of application of the secant stiffness matrix for non linear structural problems including stability, bifurcation and limit load analysis are also discussed. Examples of application are given for the non linear analysis of pin joined frames.     

求解非线性链式结构瞬态响应的传递矩阵方法

基于传统的传递矩阵方法与数值积分和ＮｅｗｔｏｎＲａｐｈｓｏｎ迭代法,提出了可迭代增量传递矩阵,用于求解具有大运动、非线性特征的链式多体系统瞬态响应;它包括增量传递矩阵和ＮＲ迭代传递矩阵;由增量传递矩阵得到时程积分每一瞬时状态量;由ＮＲ迭代传递矩阵得到该瞬时提高精度的解。该文以一链式多体系统为例说明该方法的建模、计算过程。最后,以一个平面四杆机械臂为算例将本文方法与逐步积分法所得结果作了比较,验证了该方法的可行性。     

空间桁架大位移问题的有限元分析

本文在Ｔ．Ｌ．坐标下，利用能量原理，同时导出了空间杆元精确的割线刚度矩阵和切线刚度矩阵显式。文中采用几种方法实现了空间桁架大位移分析的几何非线性有限元解法。算例表明，本文导出的两个刚度矩阵可极为有效的分析各类空间桁架的几何非线性问题，且使程序具有极好的调试性     

复合材料加筋板的大变形有限元分析

本文将考虑横向剪切变形的Mindlin's理论应用于复合材料加筋板的大变形分析,在Total-Lagrange坐标系下推导了八结点等参弯曲板单元和三结点等参梁单元的增量平衡方程和切线刚度矩阵,非线性问题采用增量法和Newton-Raphson迭代法相结合的方法求解.本文通过一些算例,证明了所采用单元具有良好的收敛性和足够的精度,并讨论了边界条件、纤维铺设角和加筋疏密等因素对复合材加料筋板非线性解的影响.     

High-order free vibration analysis of sandwich beams with a flexible core using dynamic stiffness method

In this paper, high-order free vibration of three-layered symmetric sandwich beam is investigated using dynamic stiffness method. The governing partial differential equations of motion for one element are derived using Hamilton’s principle. This formulation leads to seven partial differential equations which are coupled in axial and bending deformations. For the harmonic motion, these equations are divided into two ordinary differential equations by considering the symmetrical sandwich beam. Closed form analytical solutions of these equations are determined. By applying the boundary conditions, the element dynamic stiffness matrix is developed. The element dynamic stiffness matrices are assembled and the boundary conditions of the beam are applied, so that the dynamic stiffness matrix of the beam is derived. Natural frequencies and mode shapes are computed by use of numerical techniques and the known Wittrick–Williams algorithm. Finally, some numerical examples are discussed using dynamic stiffness method.     

Axisymmetric response of nonlinearly elastic cylindrical shells to dynamic axial loads

The axisymmetric response of nonlinearly elastic cylindrical shells subjected to dynamic axial loads is analysed by using an incremental formulation. The material elastic nonlinearity is modeled by the generalized Ramberg—Osgood representation. The time-dependent displacements of the shell are assumed to be governed by nonlinear equations of motion based on the von Karman—Donnell kinematic relations; moreover, both in-surface and out-of-surface inertia terms are included. The finite difference method with respect to the spatial coordinate and the Runge—Kutta method with respect to time are employed to derive a solution. Numerical results demonstrate the effect of the material nonlinearity on the deflections, stiffness matrices and dynamic buckling behavior of cylindrical shells.     

Finite element analysis of non-linear static and dynamic response

The paper presents the theoretical and computational procedures which have been applied in the design of a general purpose computer code for static and dynamic response analysis of non-linear structures. A general formulation of the incremental equations of motion for structures undergoing large displacement finite strain deformation is first presented. These equations are based on the Lagrangian frame of reference, in which constitutive models of a variety of types may be introduced. The incremental equations are linearized for computational purposes, and the linearized equations are discretized using isoparametric finite element formulation. Computational techniques, including step-by-step and iterative procedures, for the solution of non-linear equations are discussed, and an acceleration scheme for improving convergence in constant stiffness iteration is reviewed. The equations of motion are integrated using Newmark's generalized operator, and an algorithm with optional iteration is described. A solution strategy defined in terms of a number of solution parameters is implemented in the computer program so that several solution schemes can be obtained by assigning appropriate values to the parameters. The results of analysis of a few non-linear structures are briefly discussed.     

On a numerical solution of the supersonic panel flutter eigenproblem

An automated digital computer procedure is presented in this paper which enables efficient solution of the eigenvalue problem associated with the supersonic panel flutter phenomena. The step-by-step incremental solution procedure is based on an inverse iteration technique which effectively utilizes solution results from the previous step in determining such results during the current solution step. Also, the computations are limited to the determination of a few specific roots only, which are expected to contain the flutter mode, and this is achieved at each step without having to compute any other root. The structural discretization achieved by the finite element method yields highly banded stiffness, mass, and aerodynamic matrices; the aerodynamic matrix evaluated by the linearized piston theory is real but unsymmetric in nature. The solution algorithm presented in this paper fully exploits the banded form of the associated matrices, and the resulting computer program written in FORTRAN V for the JPL UNIVAC 1108 computer proves to be most efficient and economical when compared to existing procedures of such analysis. Numerical results are presented for a two-dimensional panel flutter problem.     

Eigensolution for large structural systems with substructures

A method for calculating natural frequencies and mode shapes of large structural systems with substructures and the subspace iteration is developed. The method uses only substructural stiffness matrices and the mass matrix for each finite element of the system. The mass matrix for the entire structure or any of its substructures need not be computed. However, efficiency of the method is improved when mass matrix for the entire structure is computed and saved in the computer core. No approximating assumptions are made. Thus, natural frequencies and mode shapes for the finite element model employed are the same with or without the substructuring algorithm. This is demonstrated by computing first ten natural frequencies and the corresponding mode shapes for an open truss helicopter tail-boom structure.