基于自适应成长原理的板壳结构加强筋分布设计技术

将自然界分枝系统形态自适应成长机理应用于板壳结构加强筋分布设计中,深入讨论板壳结构加强筋分布设计技术.应用ANSYS APDL二次开发语言进行编程,使提出的设计原理方便地应用于实际工程设计.整个应用程序包含前处理、优化迭代及后处理三个模块.前处理模块建立设计对象的基结构,基结构由基本板壳结构和初始加强筋组成.基本板壳结构可采用ANSYS中的建模模块创建或直接导入由其他CAE软件建立的几何模型,而初始加强筋由基本板壳结构上的节点连接而成的梁单元构成.优化迭代模块包含“选种”、灵敏度分析、分歧/成长/退化等功能.采用变量扰动法,基于ANSYS有限元分析模块计算活动加强筋的近似灵敏度.根据自然界分枝系统形态形成机理进行加强筋的分歧/成长/退化.最后由后处理模块输出设计结果.以若干典型的设计案例说明所提出方法的有效性,并通过与ANSYS的结构拓扑优化设计模块的设计结果比较说明了所提出方法的可行性．     

基于拓扑优化的结构加强筋布局降噪方法研究

基于变密度拓扑优化方法,提出了通过优化加强筋布局来降低谐振结构辐射声功率的策略。优化中将加强筋单元的伪密度作为设计变量,约束为加强筋质量上限,所用寻优算法为移动渐近线(MMA)系列算法中的MMA-GC-MMA混合算法。对结构的振动响应使用有限元方法求解,对声辐射使用边界元方法求解,并在此基础上分析了目标函数对设计变量的灵敏度。以加筋箱体为例进行优化,验证了所提方法在降噪设计中的可行性和有效性,并对结果进行了讨论。     

Topology optimization of plate/shell structures with respect to eigenfrequencies using a biologically inspired algorithm

In this article, a novel approach is presented to perform topology optimization in a simple and explicit way. The method capitalizes on the use of a bio-inspired algorithm to represent topology, leading to more flexible optimization solutions along with explicit structure representation. To avoid remeshing upon design changes, a special treatment called the enhanced stiffness transformation approach (ESTA) is introduced to transform the stiffness and mass matrices of the growing stiffener into a set of equivalent stiffness and mass matrices. In this way, stiffeners are separated from the finite element mesh and can grow in an arbitrary direction to form an optimized layout solution. Notably, this approach incorporates more geometric information into topology optimization, which improves the clarity of stiffener layouts. Finally, the effectiveness of the proposed method is illustrated with two examples of maximum eigenfrequency design of plate/shell structures.     

动载荷激励下板壳结构加筋自适应成长方法

自适应成长法是基于自然界分支系统形态形成机理的一种高效结构拓扑优化设计方法。通过引入等效静态载荷法理论,运用自适应成长法解决板壳加筋结构在承受动载荷激励下的动态响应拓扑优化设计问题。根据板壳结构所受的动载荷边界条件,构建以动柔度为目标的优化数学模型,推导迭代公式,使板壳结构的加强筋从"种子"开始,沿着使结构最佳力学性能方向成长,从而形成最优加强筋分布形态。研究在简谐载荷和冲击载荷作用下的板壳结构加强筋设计例,并与静态载荷作用下的设计结果进行比较。研究结果表明,板壳结构在动态载荷作用下,其主加强筋布局形态和在静态载荷作用下相同,但在靠近载荷作用点附近出现与主加强筋平行的截面积较小的加强筋,以增加抵抗动态载荷的作用;而冲击载荷作用下的加强筋与一般简谐载荷作用下的加强筋相比,多出一层较复杂的框型筋板抵抗瞬时冲击力。     

桁架结构智能布局优化设计

结构的布局优化由于涉及尺寸、形状和拓扑三个层次的综合设计而成为优化问题中的难点,结合桁架结构提出了一个基于多个初始基结构的布局优化方法。以智能生成的、型式多样合理的基结构代替传统模型中的单一基结构,然后从不同基结构下的拓扑优化结果中找出最优设计。在克服传统基结构法有可能限制求解空间而丢失最优解这一局限性的同时,将形状和拓扑优化设计有效分离,降低了求解的难度,并且结合拓扑变化法,实现了桁架结构从选型生成、分析计算到优化设计的一体化智能设计过程。算例表明:利用该文提出的方法进行桁架结构的最优布局设计是可靠有效的。     

Concurrent optimization of stacking sequence and stiffener layout of a composite stiffened panel

This article is to optimally design laminated composite stiffened panels by optimizing both stacking sequences of the panel skin and stiffeners as well as the layout of stiffeners. Starting from initial designs of stiffener layout and stacking sequences for each stiffener and the panel skin, the problem is formulated with discrete and continuous variables, where discrete 0/1 variables represent the absence/presence of each layer in initial stacking sequences, and continuous variables represent layer thicknesses. A first-level approximate problem is established to make the problem explicit. Genetic algorithm is used to determine the existence of each layer in the laminates. When the number of retained layers in stiffener becomes zero, that stiffener can be seen as unnecessary and removed. For individual fitness calculation, a second-level approximate problem is constructed to optimize continuous ply thicknesses of retained layers. Correspondingly, laminated stacking sequences and stiffener layout are concurrently optimized.     

Optimal design approach for eco-efficient machine tool bed

An optimal design approach of machine tool bed with the aim of obtaining an eco-efficient machine structure is studied. The suggested method includes three phases. The first is the layout design optimization of stiffener plates inside bed. In order to improve the design efficiency, a simplified design model called fiber model is suggested, and the layout of the stiffener plates inside bed is optimized by changing a 3-dimensional topology design optimization problem to a 2-dimensional problem. The second is the detailed sizing optimization of stiffener plates and supporting blocks under the structure based on the initial optimal model resulted from phase one. Finally, a topology design optimization process is implemented to obtain a reasonable distribution of manufacturing holes in bed structure. By considering the manufacturing requirement, an optimal bed structure is obtained. The validity of the suggested method is confirmed by a typical cylindrical grinding machine tool bed, and the result shows that the suggested method is effective, and the optimal structure has much better mechanical and economical performance by comparing with the original structures.     

基于三维几何模型的船舶扶强材自动理想化系统开发研究

目的 开发一套基于三维几何模型的船舶扶强材自动理想化系统。方法 针对船舶模型中扶强材截面形状、尺寸多变,分布密度大,进行结构规范计算时计算量大、计算条件复杂、人工计算难以涵盖全面的问题,考虑扶强材的截面变化、依附结构与相交关系,将船舶模型中的扶强材离散重组简化为单元梁,并以单元梁为基本单位进行船体梁结构相关强度校核参数的快速自动计算。结论 通过扶强材自动理想化系统,实现了对船舶扶强材间距等13项规范校核参数的快速自动计算,提高了船舶规范校核精度,缩短了船舶规范建模周期。     

机械基础结构多目标拓扑优化设计方法

机械的基础结构在保证具有足够的刚度、强度和稳定性的条件下,经济性也必须要好,因此机械基础结构常采用内部布置有加筋板的箱体结构。以某机械基础结构为例,分别用基于经验设计的内部筋板布置方法和多目标拓扑优化方法进行优化设计,得到了2 种设计方案;比较了2 种方案的动静态力学性能。结果表明,多目标拓扑优化设计的基础结构比一般经验设计的结构,刚度有所提高,而结构质量减小11. 21%,一阶固有频率提高25. 07%。     

内设加劲肋空间DKT形相贯节点轴压承载力公式

以北京大兴国际机场航站楼钢结构工程为背景，在空间DKT形相贯足尺节点试验的基础上，为进一步研究节点的受力机理，对192组不同参数的节点有限元模型进行模拟分析。研究加劲肋开口尺寸、加劲肋厚度及其设置数量对空间DKT形相贯节点受力性能的影响。对设置不同加劲肋的空间DKT形相贯节点在承受轴压下的承载力设计值和极限承载力进行多元非线性回归，得到了内设加劲肋的DKT形节点承载力设计值和极限承载力的提高系数η。在现行的钢结构设计标准基础上得到内设加劲肋相贯节点承载力设计值和极限承载力计算公式。试验和有限元分析结果表明，内设加劲肋相贯节点的承载力设计值和极限承载力公式满足精度要求，可以为工程中类似节点的设计提供可靠参考。     

Buckling analysis of parallel eccentrically stiffened functionally graded annular spherical segments subjected to mechanic loads

ABSTRACT

Based on the Donnell shell theory and smeared stiffeners technique, the governing equations of functionally graded annular spherical segments with functionally graded eccentrically stiffeners are derived to investigate the buckling of these structures under compression load and radial pressure. The segment is reinforced by parallel eccentrically functionally graded stiffener system. Approximate solutions are assumed to satisfy the simply supported boundary condition and Galerkin method is applied to obtain closed-form relations of linear buckling loads. Numerical results are given to evaluate effects of stiffeners, volume fraction index and dimensional parameters to the buckling of structure.     

一类双壳结构振动特性的半解析法

以Hamilton正则方程的半解析法为基础,为一类双壳结构的振动特性提出了一种新的数学模型。基本步骤:(1)独立地建立内外壳和连接筋的线性方程组;(2)考虑到内外壳和连接筋的界面上的应力和位移的连续性,联立内外壳和连接筋的方程,从而得到全结构的方程组。主要优点是:采用了同一种Hamiltonian等参元离散壳和连接筋,结构的转动惯性、剪切变形等因素都得到了考虑,而且不限制壳的厚度和筋的高度;该方法象一般的有限元法一样适应复杂的边界条件和由多种材料构成的结构。本文的方法可推广用来研究加筋复合材料或加筋压电材料层合壳及相应的双壳结构的动力学问题。     

复合材料加筋板长桁终止端失效机制

由于设计要求或设计限制条件, 壁板的长桁常常在翼肋或机身框附近、 机翼的前后梁附近、 机翼与机身的开口附近、 机翼的油箱附近等部位终止。在面内载荷作用下, 截面形状突变和传载路径偏移在端头处会产生应力集中, 极易引起缘条/蒙皮界面脱胶分层。对三种构型的长桁终止端典型件在单向拉、 压载荷下的破坏机制进行了试验研究与数值模拟, 结果表明, 拉伸时的失效是由面外剥离应力与层间剪应力的共同作用所致, 而压缩时的失效主要是由层间剪应力所致。     

Stability design of honeycomb sandwich radome with asymmetric shape

The die radome, which is made of honeycomb sandwich structure, should be entirely refitted, for a big electronic observation facility is being fixed at the head section of an aircraft. In this work, the stability design of honeycomb sandwich radome is investigated. Initially, a local buckling failure is observed in the refitted radome during the preliminary calculation. Then design improvements are made to the existing radome, like some L-shaped stiffeners are added on the inner surface of metal faring in order to improve the stability of radome. In this way, the critical buckling load of radome increases more than 10 times. Different layout schemes for the stiffeners are studied during this work, and the best structure layout is obtained by discrete optimization method and also the relationship between stability and bar spacing is examined. Finally, the stability of radome under 45 load cases is calculated to validate the design. The result shows that the optimized design greatly improves the stability of radome. This method can be applied to structure design in preliminary assessment.     

The residual strength characteristics of stiffened panels containing fatigue cracks

In heavy structural members, where plane strain conditions prevail, linear fracture mechanics can be used for predicting residual strength. Aircraft structures consist largely of sheet structures with plane stress conditions where linear fracture mechanics do not seem to apply. Yet it is in the aircraft main structure that large fatigue cracks can develop and that has to be designed fail-safe. The present paper describes a method to predict the residual strength of a cracked sheet structure.Contrary to an unstiffened sheet, the sheet structure contains stiffening elements that can act as crack stoppers. This crack arresting action and its consequences for the residual strength are considered in the analysis.The paper proposes a method that relates the crack resistance of a stiffened panel to that of an unstiffened sheet. It takes full account of sheet-stringer interaction in the cracked region. A criterion for crack arrest is put forward. Ultimate panel failure after crack arrest is initiated either by subsequent unstable crack growth or by stiffener failure. Critical load conditions for both failure modes are presented. In case crack arrest does not occur, the residual strength of the unstiffened panel constitutes a safe lower bound.Computational results of the interacting rivet forces by both analytical and numerical (finite element) methods are presented. From these the load concentration in the stiffener and the reduction of the stress intensity at the crack tip can be determined. This enables the complete residual strength characteristics to be predicted.The results of residual strength tests on bonded and riveted panels with symmetric strip stiffeners or eccentric Z-stringers fully substantiate the method proposed for residual strength calculations.     

Buckling load analysis of grid stiffened composite cylinders

Stiffened cylindrical shells are the major components of aerospace structures. In this study global buckling load for a generally cross and horizontal grid stiffened composite cylinder was determined. This was accomplished by developing an analytical model for determination of the equivalent stiffness parameters of a grid stiffened composite cylindrical shell. This was performed by taking out a unit cell and smearing the forces and moments due to the stiffeners onto the shell. Based on this analysis the extensional, coupling and bending matrices (A, B and D matrices, respectively) associated with the stiffeners were determined. This stiffness contribution of the stiffeners was superimposed with the stiffness contribution of the shell to obtain the equivalent stiffness parameters of the whole panel. Making use of the energy method the buckling load was solved for a particular stiffener configuration. Buckling test was also performed on a stiffened composite cylinder and compared with analytical results. Finally, using the analytical model developed, parametric analysis of some of the important design variables was performed and based on these results conclusions were drawn.     

复合材料纵横加筋圆柱壳自由振动分析

使用能力法分析了两端简支复合材料纵横加筋圆柱壳的自由振动特性,从Love’s理论出发,分别计算壳体面板和纵横加筋结构的应变能和动能,在计算加筋结构应变能和动能时,将加筋结构的作用影响平均在整个壳体区域。然后代入Lagrange方程得到频率方程。通过比较,计算方法所得到的结果与文献比较吻合。采用平均法计算的结果比采用离散方法计算的结果偏小。还研究了壳体和加筋结构参数的变化对圆柱壳自由振动频率的影响。     

Numerical Analysis of Stiffener Runout Sections

The recent trend of incorporating more composite material in primary aircraft structures has highlighted the vulnerability of stiffened aerostructures to through-thickness stresses, which may lead to delamination and debonding at the skin–stiffener interface, leading to collapse. Stiffener runout regions are particularly susceptible to this problem and cannot be avoided due to the necessity to terminate stiffeners at rib intersections or at cutouts, interrupting the stiffener load path. In this paper, experimental tests relating to two different stiffener runout specimens are presented and the failure modes of both specimens are discussed in detail. A thinner-skinned specimen showed sudden and unstable crack propagation, while a thicker-skinned specimen showed initially unstable but subsequent stable crack growth. Detailed finite element models of the two specimens are developed, and it is shown how such models can explain and predict the behaviour and failure mode of stiffener runouts. The models contain continuum shell elements to model the skin and stiffener, while cohesive elements using a traction-separation law are placed at the skin–stiffener interface to effectively model the debonding which promotes structural failure.     

复合材料加筋板低速冲击损伤及剩余压缩强度试验研究

采用落锤法对复合材料加筋板进行了低速冲击损伤（LVI）试验,根据复合材料加筋板构型,设计了冲击支持支架,研究了支持支架的间距对冲击结果的影响;用相同的冲击能量对复合材料加筋板结构中3处典型位置进行冲击,得到不同位置的损伤形貌;分别对完好件和损伤试验件进行压缩试验,将试验结果进行对比,分析不同位置的冲击损伤对结构压缩性能的影响。试验结果表明：在相同的冲击能量下,支持支架间距越小,所造成的冲击损伤越严重;在50 J冲击能量下,筋条区蒙皮处的冲击所造成的损伤不易观察,筋条间蒙皮处的冲击所造成的损伤最为明显,而筋条边缘蒙皮处的冲击可以导致筋条边缘的脱粘;冲击损伤会使加筋板屈曲载荷轻微下降,筋条间蒙皮和筋条区蒙皮冲击损伤对压缩结果影响相对较小,筋条边缘处的冲击会引起损伤处蒙皮的子层屈曲,并影响结构破坏形式,使结构压缩承载能力有较为明显的下降。