飞行器空气舵系统的高效刚度分配优化方法研究

空气舵系统是飞行器典型操纵部件,其伺服作动器、连杆、摇臂、舵轴和舵面等子结构对空气舵系统的整体刚度有着不同程度的贡献,合理分配各子结构的刚度,可使空气舵系统的整体刚度得到进一步优化.本文提出了一种基于多体系统传递矩阵法和遗传算法相结合的空气舵系统高效刚度分配优化方法.首先,基于多体系统传递矩阵法建立了以结构尺寸和材料属性为参数的高效结构动力学计算模型,仿真结果表明,基于该计算模型所预测的空气舵第一阶俯仰模态固有频率与商业软件计算结果的误差仅为1.06%.其次,基于本文建立的高效结构动力学计算模型对各子结构刚度对空气舵系统动力学特性的贡献进行了灵敏度分析,给出了各部件对系统固有频率贡献的规律.最后,采取将遗传算法和多体系统传递矩阵法相结合的思路,以所建立的空气舵高效结构动力学模型为适应度函数,各子部件尺寸作为待优化变量,空气舵系统整体质量为约束条件,对空气舵系统各个子结构的刚度分配进行了优化.优化结果表明,在保持空气舵系统整体重量不变的条件下,可将空气舵系统第一阶俯仰模态固有频率提高约15.8%.     

考虑几何非线性和热效应的刚柔耦合系统的频域特性研究

研究温度场中旋转刚体-梁系统的刚-柔耦合动力学特性.考虑几何非线性和热效应,从精确的应变-位移关系式出发,用虚功原理和有限单元法建立了旋转刚体-梁系统的刚-柔耦合动力学方程.由于非线性刚度阵与变形的高次项有关,将非线性刚度阵的各元素表示为广义坐标阵和常值阵的乘积.数值计算表明,该方法可避免重复积分,提高计算效率.在此基础上研究了在温度递增的情况下几何非线性对系统的刚-柔耦合动力学特性的影响,用频谱分析方法研究了系统的固有频率随中心刚体转动惯量和温度的变化.     

组合结构等效阻尼比的确定及 在有限元计算中的应用

针对组合结构动力响应计算中,一般根据工程经验确定结构阻尼比,往往导致结构动力响应计算结果偏小,不利于结构安全评估的问题,首先根据复阻尼理论与结构动力学方法,推导出组合结构的等效阻尼比计算公式;然后,以某体育场组合结构为工程背景,在有限元法基础上使用ANSYS软件建立该结构的有限元模型.根据计算出的自振特性以及利用ANSYS二次开发功能所形成的阻尼刚度矩阵,实现等效阻尼比的有限元法求解.计算结果表明,等效阻尼比能够正确反映组合结构的动力特性,从而可以科学地计算其动态响应.     

大展弦比板弯扭耦合受迫振动分析

对于工程广泛存在的大展弦比结构,首次研究了大展弦比板弯扭耦合受迫振动响应.考虑弦向相对弯曲刚度远大于展向弯曲刚度,将弦向截面等效为刚体,考虑其绕展向轴线的扭转,应用Hamilton原理分别计算大展弦比板的势能与动能,建立两端简支的大展弦比板弯扭耦合受迫振动的动力学控制方程.将动力学控制方程进行Galerkin截断后,通过谐波平衡法和微分求积法/微分求积单元法,计算得到了大展弦比模型弯扭耦合受迫振动稳态响应的解析解及数值解,同时验证了解的截断收敛性及谐波收敛性.最后研究了外激励幅值对结构受迫振动响应的影响.结果将为工程中广泛存在的大展弦比结构设计提供指导.     

基于多体动力学的车辆道岔通过性能研究

道岔复杂的轮轨关系及其变截面特性是车辆通过道岔时引起振动甚至脱轨的关键因素.根据60kg/m钢轨18号可动心轨道岔设计布置图,在多体动力学软件中建立车辆—道岔耦合系统模型,在此基础上对车辆—道岔系统模型进行验证,仿真计算车辆侧向和直向通过道岔的动力学响应.结果表明转辙器区、辙叉区轨道截面变化和轮轨型面匹配是影响车辆动力学性能的主要因素.最后,对车辆侧向通过离散轨道模型工况下的动力学响应进行仿真计算,讨论道岔轨下整体刚度和阻尼对模型动力学性能的影响,为改善车辆通过道岔时的动力学性能、道岔轨下刚度与阻尼参数匹配提供理论基础.     

多管火箭炮两种定向管的比较分析

为了分析比较玻璃钢定向管和金属定向管的性能,以某多管火箭武器定向管为研究对象,基于结构有限元方法建立了火箭武器的结构动力学模型,计算得到发射过程中的动力学响应.数值计算结果表明:两种定向管均满足强度要求,能正常发射,玻璃钢定向管的质量为金属定向管的23%,有利于武器系统的轻量化.玻璃钢定向管的刚度小于金属定向管的刚度,发射时方位和俯仰的摆动幅度大于金属定向管,应采取措施增强刚度.     

谱元法计算结果的可视化问题

谱元法是计算流体力学中一类特殊的方法,它集成了有限元法处理复杂区域的灵活性和谱方法的高精度。谱元法产生的数据具有特殊的结构。其可视化也要求特殊的算法。本文讨论谱元法数值模拟结果的等值线产生方法及实现过程。     

SEM30齿轮箱振动噪声分析及优化设计

针对SEM30齿轮箱在运行过程中出现异响的问题,基于多体动力学理论,利用ADAMS建立齿轮副虚拟样机,计算齿轮啮合力。基于有限元法,利用ANSYS计算齿轮箱体的动态响应。响应结果作为边界元法的边界条件,计算齿轮箱体的声学特性。基于声学传递向量(ATV)法,利用VIRTUAL.LAB计算齿轮箱振动噪声的板块贡献量。仿真结果表明,齿轮箱的振动噪声在齿轮箱固有频率与齿轮啮合频率重合或接近时达到最大值,为今后齿轮箱体结构优化设计提供了依据。     

LabVIEW下货车平顺性仿真分析

首先建立了货车整车动力学模型,针对该模型给出了计算频域内的四轮随机输入下加速度功率谱密度响应的算法和程序流程,并在LabVIEW中利用其提供的线性代数矩阵节点编写了计算程序.以CA-141货车为例,利用LabVIEW编写的程序计算车身质心垂向加速度功率谱密度,并与实测结果进行了比较.     

空间杆系结构回传波射分析及程序实现

为有效地进行杆系结构应力波响应分析,基于传统的空间杆系结构回传波射矩阵法,考虑黏滞阻尼、复刚度阻尼及节点集中质量的影响,采用VC+ +编制通用回传波射矩阵法分析程序. 该程序可以计算空间杆系结构在任意动力集中载荷作用下任意位置的动力瞬态响应. 针对某刚架结构,比较运用该程序与运用有限元法得到的结果,验证该方法的精确度.     

Static, dynamic and stability analysis of structures composed of tapered beams

A new numerical method is proposed for the static, dynamic and stability analysis of linear elastic plane structures consisting of beams with constant width and variable depth. It is a finite element method based on an exact flexural and axial stiffness matrix and approximate consistent mass and geometric stiffness matrices for a linearly tapered beam element with constant width. Use of this method provides the exact solution of the static problem with just one element per member of a structure with linearly tapered beams and excellent approximate solutions of the dynamic and stability problems with very few elements per member of the structure in a computationally very efficient way. Very detailed comparison studies of the proposed method against a number of other known finite element methods with respect to accuracy and computational efficiency for cantilever tapered beams of rectangular and I cross section clearly favor the proposed method. A continuous beam, a gable frame and a portal frame consisting of tapered members are analyzed by the proposed method as well as by other known methods to illustrate the use of the method to structures composed of tapered beams.     

基于MSC Nastran的前副车架动刚度分析

设计某A级乘用车的前副车架,并用HyperMesh建立其有限元模型,用MSC Nastran的模态频率响应方法对该前副车架进行动刚度分析,得到相关频率的动刚度值.对该前副车架悬置点的动刚度分析可以为车辆NVH性能提供理论参考.     

Structural damage identification using system dynamic properties

A damage detection method is presented for the identification and quantification of damage that leads to a change in the structure’s mass and/or stiffness properties. The proposed method requires the use of finite element to model the structure in its undamaged state as well as information on the dynamic properties such as frequencies and mode shapes of the structure in its damaged state. The technique is applicable to any structure that can be accurately modeled using the finite element method and whose frequencies and mode shapes can be reliably measured. A structure pseudo force vector derived from the residual force method is described to locate the damaged regions in the structure. A matrix condensation approach in conjunction with a proportional damage model is then employed to quantify the damage by calculating the change in stiffness and mass properties of the damaged elements in the structure. The validity of the method is demonstrated by applying it to three structures: a beam, a frame and a plate. It is shown that if the amount of damage is not excessively large, the proposed method can be used to detect damage in these structures even when the measured system dynamic properties are slightly erroneous.     

Modal spectral element formulation for axially moving plates subjected to in-plane axial tension

The use of frequency-dependent spectral element matrix (or dynamic stiffness matrix) in structural dynamics is known to provide very accurate solutions, while reducing the number of degrees-of-freedom to resolve the computational and cost problems. Thus, in the present paper, the modal spectral element is formulated for thin plates moving with constant speed under a uniform in-plane axial tension. The concept of the Kantorovich method is used to formulate the modal spectral element matrix in the frequency-domain. The present modal spectral element is then evaluated by comparing its solutions with exact analytical solutions as well as with FEM solutions. The effects of the moving speed and the in-plane tension on the dynamic characteristics of a moving plate are investigated numerically.     

A numerical approach to define the rotational stiffness of a prefabricated connection and experimental study

A numerical approach is proposed to define the elastic rotational stiffness of a typical joint on the top beam of a prefabricated reinforced concrete gable frame structure. The 12 degrees of freedom triangular plane stress finite element is used to examine the connection region. Using this joint rotational stiffness value, realistic results are obtained in the frame analysis. The experimental verification is performed by means of the photoelastic method. Following the proposed method, an effective joint length with reduced moment of inertia is defined and using this concept the frame solution is simply achieved, including the existence of joint.     

SPAR analysis of LDEF vibration characteristics

This paper presents a structural dynamic modeling of the Long Duration Exposure Facility (LDEF), which is a Space Shuttle payload of passive scientific experiments contained in trays mounted on a large cylindrically shaped structure. Special detailed finite element modeling, using the SPAR system of computer programs was required to obtain good agreement between analytical and test vibrations modes. Experimental trays contributed significantly to overall LDEF stiffnesses, and these contributions were realistically represented for each tray by the stiffness matrix of an equivalent orthotropic panel in the overall LDEF SPAR model. Orthotropic stiffnesses for this panel were obtained from finely detailed statically loaded tray SPAR models in which stiffness coupling was accounted for along with partial relative sliding allowed by the tray clamping attachments. Joint boundary conditions were also significant in the structural dynamic modeling of LDEF, and static data proved valuable in assessing modeling of local end fittings.     

基于动力学仿真的系留气球鼻锥有限元分析

针对系留气球进行了动力学仿真分析,在此基础上对一种用于固定球体的新型鼻锥结构进行了结构有限元分析,以确定其强度与刚度.首先采用计算流体力学CFD求得特定风速下系留气球所受的气动力,随后通过多体动力学软件Adams进行动力学仿真分析,确定作用在鼻锥上载荷的大小,并以此作为有限元分析的载荷边界条件;然后采用有限元分析的方法对鼻锥结构进行静力学和动力学分析;最后确定极限风速下艇首与鼻锥连接处的变形、载荷及应力情况.通过分析,为新型鼻锥结构进一步的设计改进与优化提供了参考依据.     

基于多模型拓扑优化方法的车身结构概念设计

为获得最优的初始设计方案,在车身概念设计阶段对车身结构进行拓扑优化。车身结构性能指标综合考虑整体刚度、局部动态刚度和碰撞性能,采用多模型优化(multi-model optimization,MMO)方法解决此类复杂工况的拓扑优化问题,通过调节设计空间和设置参数,获得车身最优载荷路径。根据拓扑优化结果初步形成车身框架结构,可为后期详细设计提供参考。     

Geometric nonlinear effects on the planar dynamics of a pivoted flexible beam encountering a point-surface impact

Flexible-body modeling with geometric nonlinearities remains a hot topic of research by applications in multibody system dynamics undergoing large overall motions. However, the geometric nonlinear effects on the impact dynamics of flexible multibody systems have attracted significantly less attention. In this paper, a point-surface impact problem between a rigid ball and a pivoted flexible beam is investigated. The Hertzian contact law is used to describe the impact process, and the dynamic equations are formulated in the floating frame of reference using the assumed mode method. The two important geometric nonlinear effects of the flexible beam are taken into account, i.e., the longitudinal foreshortening effect due to the transverse deformation, and the stress stiffness effect due to the axial force. The simulation results show that good consistency can be obtained with the nonlinear finite element program ABAQUS/Explicit if proper geometric nonlinearities are included in the floating frame formulation. Specifically, only the foreshortening effect should be considered in a pure transverse impact for efficiency, while the stress stiffness effect should be further considered in an oblique case with much more computational effort. It also implies that the geometric nonlinear effects should be considered properly in the impact dynamic analysis of more general flexible multibody systems.     

某SUV车架多目标拓扑优化设计

为得到同时满足刚度和动态要求的SUV车架,基于SIMP材料插值方法,分别以刚度最大和低阶模态固有频率最大作为优化目标建立拓扑优化模型,利用折中规划法建立多工况下刚度和低阶固有频率多目标优化模型,通过拓扑优化迭代得到新的SUV车架;对新车架进行仿真分析,得到其位移和应力分布及前4阶固有频率.其静态特性满足材料要求且有很大提高,第1阶固有频率提高到30.3 Hz,新车架质量减轻到193.3 kg.计算结果表明该方法能够很好地解决多目标下的结构优化问题。