热结构瞬态响应的耦合灵敏度分析方法与优化设计

研究结构瞬态热变形和热应力的灵敏度分析方法及其优化设计,灵敏度计算给出了直接法和伴随法两种算法.考虑了温度场的耦合作用,在直接法中需要计算温度场对设计变量的导数,在伴随法中需要计算热载荷对温度场的导数.数值算例验证了该方法的精度.伴随法在应用程序中的实现,为大型结构优化提供了高效率的灵敏度计算方法.     

热-应力耦合结构灵敏度分析方法

研究稳态／瞬态热传导灵敏度分析、以及热与机械荷载同时作用的热结构应力灵敏度分析问题。考虑了温度场随设计变量的变化及其对应力的影响,提出温度场与结构热应力耦合问题的灵敏度计算方法。特别指出了热－应力耦合灵敏度分析中温度场导数的影响, 说明了在热－应力耦合结构灵敏度分析中必须考虑耦合灵敏度。在应用软件系统JIFEX中实现了所提出的方法,数值算例验证了灵敏度算法的精度。     

频率响应位移幅值敏度分析的伴随法

频率响应位移幅值的敏度分析通常采用直接法,一次敏度分析只能计算出对一个设计变量的偏导数,这在设计变量很多的拓扑优化中因敏度分析计算量太大而显得不适用,本文推导了频率响应位移幅值敏度分析的伴随法,一次敏度分析可计算出对所有设计变量的偏导数,算例表明伴随法计算结果与直接法及差分法结果符合得很好,用伴随法分析敏度在结构拓扑优化中可以大幅提高计算效率.     

相变传热问题的灵敏度分析与优化设计方法

研究了相变传热问题的优化设计及其灵敏度分析方法. 在有限元-时间差分和等效热容 法求解相变温度场的基础上，提出了相变温度场对设计变量一阶灵敏度的计算方法，给出直 接法和伴随法两种计算格式并分析了它们的特点，建立了相变温度场优化的模型和算法，在有限元分析与优化设计软件JIFEX中实现了该方法. 数值算例表明了灵敏度计算的精度和优 化方法的有效性.     

形状设计灵敏度分析的改进的再生核质点法

基于物质导数概念和直接微分法,将再生核质点法应用于形状设计灵敏度分析（DSA）中。导出了基于无网格近似的灵敏度方程,特别强调了在考虑形状函数关于设计变量的物质导数时无网格方法与有限元法的不同。通过对RKPM形状函数及其物质导数进行矩式显式表述,提高了无网格方法的计算效率。对两个二维线弹性问题进行了位移灵敏度和应力灵敏度分析,计算结果与解析解吻合的很好;同时通过对通常的RKPM和改进的RKPM计算耗时的比较,显示了该方法不仅有效,而且可以显著地提高计算效率。     

强迫谐振动下连续体结构拓扑优化

应用结构拓扑优化ICM(独立连续映射)方法,对强迫谐振动下结构拓扑优化问题建立了以重量极小为目标,位移幅值为约束的优化模型.位移幅值采用一阶泰勒展式近似,由于拓扑优化中设计变量数目通常很多,对强迫谐振动位移幅值的敏度分析推导了伴随法公式,使得一次敏度分析可以计算出对所有设计变量的偏导数,克服了采用直接法敏度分析中一次只能计算出对一个设计变量的偏导数的不足.算例表明用伴随法分析敏度在结构拓扑优化中可以大幅提高计算效率,ICM方法采用独立于截面及形状参数的拓扑优化设计变量更清晰地反映了拓扑优化的本质.     

热传导问题灵敏度分析的伴随法

在热传导灵敏度分析的直接法的研究基础上，进一步探讨了稳态和瞬态热传导问题灵敏度分析的伴随法.推导了伴随法的计算列式，对于瞬态热传导问题，研究了瞬态约束处理的关键点方法，并提出伴随方程的精细积分解法。算例表明，稳态问题灵敏度计算，伴随法与直接法的结果是一致的；瞬态问题灵敏度计算，两种方法的精度相当。     

结构拓扑优化应力敏度分析的伴随法

针对受应力约束的连续体结构拓扑优化问题,推导了应力敏度分析的伴随法公式;并以算例形式,将伴随法计算的应力敏度结果与差分法结果进行对比,验证了所推导公式的准确性,应力敏度分析结果表明了应力对设计变量的偏导数具有局部性特点。在此基础上,以受应力约束重量极小化为目标的结构拓扑优化为例,对比分析了应力一阶Taylor近似与满应力法的优化效果。结果表明:相比满应力法,应力一阶近似能使结构应力在更多的部分达到许用应力,得到的最优结构重量更轻。对设计变量数目巨大的应力约束连续体结构拓扑优化问题,由于应力约束数目可以通过准有效约束初选及不考虑删除单元的应力约束等方式减少,通常比设计变量数目小很多,应用应力敏度分析伴随法可以显著提高计算效率。     

线性常微分方程灵敏度分析的精细积分法

利用指数矩阵的导数计算来求解一类一阶线性常系数微分方程组对某一设计变量的灵敏度计算问题。对于初值问题,利用指数矩阵的导数,递推得到状态向量的灵敏度;对于线性两点边值问题,通过两点之间的状态向量的导数关系,得到全部初始条件,进而转化为初值问题计算。指数矩阵及其导数阵的高精度计算基于2N类算法,在此基础上可实施灵敏度分析的计算。本文给出了初值和两点边值常微分方程的高精度灵敏度计算方法,计算结果可认为是计算机上的精确解,算例验证了算法的有效性。     

特征向量导数计算各种模态法的比较和发展

在结构动力学修改以及结构动态设计中，灵敏度分析是十分重要的一环，往往也是主要工作量所在。如何在保证精度前提下减少灵敏度分析工作量和计算时间，具有重要意义。本文对特征向量灵敏度分析中计算特征向量导数的模态法作了综合评述，除了经典模态法和修正模态法之外，还对新近发展的迭代模态法和移位模态法进行了介绍。最后通过典型结构实例的计算仿真，对各种模态法作了比较。     

Robust design in aerodynamics using third‐order sensitivity analysis based on discrete adjoint. Application to quasi‐1D flows

In this paper, the second‐order second moment approach, coupled with an adjoint‐based steepest descent algorithm, for the solution of the so‐called robust design problem in aerodynamics is proposed. Because the objective function for the robust design problem comprises first‐order and second‐order sensitivity derivatives with respect to the environmental parameters, the application of a gradient‐based method , which requires the sensitivities of this function with respect to the design variables, calls for the computation of third‐order mixed derivatives. To compute these derivatives with the minimum CPU cost, a combination of the direct differentiation and the discrete adjoint variable method is proposed. This is presented for the first time in the relevant literature and is the most efficient among other possible schemes on condition that the design variables are much more than the environmental ones; this is definitely true in most engineering design problems. The proposed approach was used for the robust design of a duct, assuming a quasi‐1D flow model; the coordinates of the Bézier control points parameterizing the duct shape are used as design variables, whereas the outlet Mach number and the Darcy–Weisbach friction coefficient are used as environmental ones. The extension to 2D and 3D flow problems, after developing the corresponding direct differentiation and adjoint variable methods and software, is straightforward. Copyright © 2011 John Wiley & Sons, Ltd.     

特定方向"零膨胀"的最小柔顺性结构优化设计

工程中很多承载结构必须面对苛刻的温度变化工作环境,如卫星天线、太空照相机和电子器件等。剧烈的温度变化引起较大的热变形,造成仪器信号失真,精度下降;同时温度应力也会造成结构破坏甚至失效,因此零膨胀材料的研制备受关注。近年来国内外很多学者对此进行了研究,设计出具有特定等效膨胀系数的微结构,但考虑到制备工艺的限制,这类具有复杂微结构的材料制备起来比较困难,成本较高;同时这类材料一般不具备足够的刚度,难以满足承载性能的要求。本文基于结构优化设计技术,采用拓扑优化方法直接设计出具备较高的承载性能和特定方向变形较少受热载荷影响的结构。本文提出采用多目标优化的方法设计圆环结构,使其具有较高的刚度和在热载荷下圆环内表面具有较好的热几何稳定性。由于用单相材料无法同时满足高刚度和低热膨胀的要求,因此假设结构由两种不同的材料构成,用连续体拓扑优化的方法设计三相材料(两种实体材料MAT-I、MAT-II和空材料)在设计域上的最优分布,使结构满足设计要求。由对称性,设计域取为圆环的一个扇面,将设计域离散成有限元网格,每个单元具有两个设计变量:实体材料的体分比和MAT-I在实体材料中所占的体分比,采用伴随法进行灵敏度分析,用GCMMA方法求解此问题,采用体积守恒的Heaviside密度过滤函数保证获得清晰的最优拓扑构型以及避免棋盘格式的出现。通过两个数值算例,表明使用本文提出的多目标优化模型能够得到特定方向"零膨胀"同时具有一定刚度的结构设计,且这种宏观结构尺度上的两种材料组成的拓扑构型相对易于制造。     

广义变分原理的结构形状优化伴随法灵敏度分析

提出了一种利用伴随变量进行结构形状优化灵敏度分析的新方法. 基于广义变分原理， 考虑了形状优化中位移边界条件的变化对结构响应的影响. 新方法弥补了Arora 等人所提出的形状优化灵敏度分析变分原理中的缺陷，为采用伴随法进行灵敏度分析提供了 新的框架.     

Third‐order sensitivity analysis for robust aerodynamic design using continuous adjoint

Robust design problems in aerodynamics are associated with the design variables, which control the shape of an aerodynamic body, and also with the so‐called environmental variables, which account for uncertainties. In this kind of problems, the set of design variables, which leads to optimal performance, taking into account possible variations in the environmental variables, is sought. One of the possible ways to solve this problem is by means of the second‐order second‐moment approach, which requires first‐order and second‐order derivatives of the objective function with respect to the environmental variables. Should the minimization problem be solved using a gradient‐based method, algorithms for the computation of up to third‐order sensitivity derivatives (twice with respect to the environmental variables and once with respect to the shape controlling design variables) must be devised. In this paper, a combination of the continuous adjoint variable method and direct differentiation to compute the third‐order sensitivities is proposed. This is shown to be the most efficient among all alternative methods provided that the environmental variables are much less than the design ones. Apart from presenting the method formulation, this paper focuses on the assessment of the so‐computed up‐to third‐order mixed derivatives through comparison with costly finite‐difference schemes. To this end, the robust design of a two‐dimensional duct is performed. Then, using the validated method, the robust design of a two‐dimensional cascade airfoil is demonstrated. Although both cases are handled as inverse design problems, the method can be extended to other objective functions or three‐dimensional problems in a straightforward manner. Copyright © 2012 John Wiley & Sons, Ltd.     

A numerical method of calculating first and second derivatives of dynamic response based on Gauss precise time step integration method

This paper describes an accurate and efficient method for calculating the first and second derivatives of dynamic response with respect to design variables for linear structural systems subjected to transient loads. An efficient algorithm to calculate the dynamic responses and their first and second derivatives is formulated based on Gauss precise time step integration method. The algorithm is achieved by direct differentiation and only a single dynamic analysis is required. Several numerical examples are comparatively demonstrated using the new developed method, analytical method, and central difference method. The results show that the new method is highly accurate compared with the analytical approach and is more efficient than the central difference method.     

Stochastic sensitivity analysis of coupled acoustic-structural systems under non-stationary random excitations

This paper presents a new sensitivity analysis method for coupled acoustic–structural systems subjected to non-stationary random excitations. The integral of the response power spectrum density (PSD) of the coupled system is taken as the objective function. The thickness of each structural element is used as a design variable. A time-domain algorithm integrating the pseudo excitation method (PEM), direct differentiation method (DDM) and high precision direct (HPD) integration method is proposed for the sensitivity analysis of the objective function with respect to design variables. Firstly, the PEM is adopted to transform the sensitivity analysis under non-stationary random excitations into the sensitivity analysis under pseudo transient excitations. Then, the sensitivity analysis equation of the coupled system under pseudo transient excitations is derived based on the DDM. Moreover, the HPD integration method is used to efficiently solve the sensitivity analysis equation under pseudo transient excitations in a reduced-order modal space. Numerical examples are presented to demonstrate the validity of the proposed method.     

Aerodynamic design using the truncated Newton algorithm and the continuous adjoint approach

In this paper, the so‐called ‘continuous adjoint‐direct approach’ is used within the truncated Newton algorithm for the optimization of aerodynamic shapes, using the Euler equations. It is known that the direct differentiation (DD) of the flow equations with respect to the design variables, followed by the adjoint approach, is the best way to compute the exact matrix, for use along with the Newton optimization method. In contrast to this, in this paper, the adjoint approach followed by the DD of both the flow and adjoint equations (i.e. the other way round) is proved to be the most efficient way to compute the product of the Hessian matrix with any vector required by the truncated Newton algorithm, in which the Newton equations are solved iteratively by means of the conjugate gradient (CG) method. Using numerical experiments, it is demonstrated that just a few CG steps per Newton iteration are enough. Considering that the cost of solving either the adjoint or the DD equations is approximately equal to that of solving the flow equations, the cost per Newton iteration scales linearly with the (small) number of CG steps, rather than the (much higher, in large‐scale problems) number of design variables. By doing so, the curse of dimensionality is alleviated, as shown in a number of applications related to the inverse design of ducts or cascade airfoils for inviscid flows. Copyright © 2011 John Wiley & Sons, Ltd.