Topological Optimization Method for Aeronautical Thin-Walled Component Fixture Locating Layout

Fixture locating layout has a direct and influential impact on aeronautical thin-walled component(ATWC)manufacturing quality.The purpose is to develop a topological optimization method for ATWC fixture locating layout to minimize the manufacturing deformation.Firstly,a topological optimization model that takes the stiffness of ATWC as the objective function and the volume of the locating structure as the constraint is established.Secondly,ATWC and the locating structure are regarded as an integrated entity,and the variable-density method based topological optimization approach is adopted for the optimization of the locating structure using ABAQUS topology optimization module(ATOM).Thirdly,through a subsequent model reconstruction referring to the obtained topological structure,the optimal fixture locating layout is achieved.Finally,a case study is conducted to verify the proposed method and the comparison results with firefly algorithm(FA)coupled with finite element analysis(FEA)indicate that the number and positions of the locators for ATWC can be optimized simultaneously and successfully by the proposed topological optimization model.

Meter-Scale Thin-Walled Structure with Lattice Infill for Fuel Tank Supporting Component of Satellite:Multiscale Design and Experimental Verification

Lightweight thin-walled structures with lattice infill are widely desired in satellite for their high stiffness-to-weight ratio and superior buckling strength resulting fromthe sandwich effect.Such structures can be fabricated bymetallic additive manufacturing technique,such as selective laser melting(SLM).However,the maximum dimensions of actual structures are usually in a sub-meter scale,which results in restrictions on their appliance in aerospace and other fields.In this work,a meter-scale thin-walled structure with lattice infill is designed for the fuel tank supporting component of the satellite by integrating a self-supporting lattice into the thickness optimization of the thin-wall.The designed structure is fabricated by SLM of AlSi10Mg and cold metal transfer welding technique.Quasi-static mechanical tests and vibration tests are both conducted to verify the mechanical strength of the designed large-scale lattice thin-walled structure.The experimental results indicate that themeter-scale thin-walled structure with lattice infill could meet the dimension and lightweight requirements of most spacecrafts.

VIBRATION IN HIGH-SPEED MILLING OF THIN-WALLED COMPONENTS

To investigate the vibration principle in machining thin-walled components, a dynamic model for end milling of flexible structures is built based on considering the variations in the dynamic chip thickness and the differences between up-milling and down-milling. Two milling experiments verify the model. Experimental results show that the model can predict the milling force and displacements simultaneously in the dynamic milling process.

Fundamentals and Processes of Fluid Pressure Forming Technology for Complex Thin-Walled Components

A new generation of fluid pressure forming technology has been developed for the three typical structures of tubes,sheets,and shells,and hard-to-deform material components that are urgently needed for aerospace,aircraft,automobile,and high-speed train industries.in this paper,an over all review is introduced on the state of the art in fundamentals and processes for lower-pressure hydroforming of tubular components,double-sided pressure hydroforming of sheet components,die-less hydroforming of ellipsoidai shells,and dual hardening hot medium forming af hard-to-deform materiais Particular attention is paid to deformation behavior,stress state adjustment,defect prevention,and typical applications.In addition,future development directions of fluid pressure forming technology are discussed,including hyper lower-loading forming for ultra-large non-uniform components,precision for ming for intermetallic compound and high-entropy alloy components,intelligent process and equipment,and precise finite element simulation of inhomogeneous and strong anisotropic thin shells.

High-efficiency forming processes for complex thin-walled titanium alloys components: state-of-the-art and perspectives

Complex thin-walled titanium alloy components play a key role in the aircraft,aerospace and marine industries,offering the advantages of reduced weight and increased thermal resistance.The geometrical complexity,dimensional accuracy and in-service properties are essential to fulfill the high-performance standards required in new transportation systems,which brings new challenges to titanium alloy forming technologies.Traditional forming processes,such as superplastic forming or hot pressing,cannot meet all demands of modern applications due to their limited properties,low productivity and high cost.This has encouraged industry and research groups to develop novel high-efficiency forming processes.Hot gas pressure forming and hot stamping-quenching technologies have been developed for the manufacture of tubular and panel components,and are believed to be the cut-edge processes guaranteeing dimensional accuracy,microstructure and mechanical properties.This article intends to provide a critical review of high-efficiency titanium alloy forming processes,concentrating on latest investigations of controlling dimensional accuracy,microstructure and properties.The advantages and limitations of individual forming process are comprehensively analyzed,through which,future research trends of high-efficiency forming are identified including trends in process integration,processing window design,full cycle and multi-objective optimization.This review aims to provide a guide for researchers and process designers on the manufacture of thin-walled titanium alloy components whilst achieving high dimensional accuracy and satisfying performance properties with high efficiency and low cost.

Sheet Bulk Forming of Thin-Walled Components with External Gearing through Upsetting Using Controllable Deformation Zone Method

Sheet-bulk metal forming(SBMF)is a promising process for manufacturing complex sheet components with functional elements.In this study,the entire forming process for a typical thin-walled component with external gearing is investigated,including sheet forming and bulk forming processes.Deep drawn cups are prepared during sheet forming;subsequently,upsetting is performed on the sidewall to form external gearing.The upsetting method performed is known as upsetting with a controllable deformation zone(U-CDZ).Compared with the conventional upsetting method,a floating counter punch with a counter force is used in the U-CDZ method such that the forming mechanism is changed into the accumulation of the deformation zone instead of deformation throughout the entire sidewall.The effects of the counter force and material flow are investigated to understand the mechanism.The forming quality,i.e.,the formfilling and effective strain distribution,improved,whereas a high forming load is avoided.In addition,a punch with a lock bead is used to prevent folding at the inner corner during the experiment.

Vibrations in High Speed Milling of Thin-walled Components

Thin-walled structures have been widely used in the aerospace industry.The dynamic interaction between the milling cutter and thin-walled workpiece can easily lead to vibration.This paper investigates the vibration caused during milling the thin-walled workpiece on the NC machining center,presents a theoretical milling vibration model of thin-walled beam.The model was verified by using milling experiments and numerical simulations.Some valuable conclusions are derived,this will be references to scientific research and guides to the vibration-free milling of thin-walled structures at different cutting speeds.

Recent Developments on Damage and Fracture of Thin-Walled Complex Components Produced by Spinning

The spinning technique has been widely used in the manufacture of aerospace thin-walled axisymmetric components because of its excellent formability. Damage and fracture,as the important defects that often occur and must be avoided in the forming and service stages of components,have attracted much attention of researchers. In this paper,the fracture behavior and laws of spinning components such as conical parts,tubular parts,and components with inner ribs are summarized,the typical coupled and uncoupled ductile fracture models are introduced,and their applications in spinning are analyzed. Meanwhile,the recent developments on the modified ductile fracture model in analyzing damage and fracture mechanisms of spinning are emphatically introduced. The results could provide guidance for the selection and establishment of appropriate ductile fracture models in the finite element simulation for the accurate prediction and analysis of fracture moment,location,form,damage mechanism,and evolution law,and help the development of precision spinning techniques for high-performance thin-walled complex components.

Collaborative manufacturing technologies of structure shape and surface integrity for complex thin-walled components of aero-engine:Status,challenge and tendency

Presently,the service performance of new-generation high-tech equipment is directly affected by the manufacturing quality of complex thin-walled components.A high-efficiency and quality manufacturing of these complex thin-walled components creates a bottleneck that needs to be solved urgently in machinery manufacturing.To address this problem,the collaborative manufacturing of structure shape and surface integrity has emerged as a new process that can shorten processing cycles,improve machining qualities,and reduce costs.This paper summarises the research status on the material removal mechanism,precision control of structure shape,machined surface integrity control and intelligent process control technology of complex thin-walled components.Numerous solutions and technical approaches are then put forward to solve the critical problems in the high-performance manufacturing of complex thin-wall components.The development status,challenge and tendency of collaborative manufacturing technologies in the high-efficiency and quality manufacturing of complex thin-wall components is also discussed.

Effect of assisted transverse magnetic field on distortion behavior of thin-walled components in WEDM process

Machining performance of thin-walled components made by aeronautical difficult-toprocess materials is a significant issue in the aviation manufacturing industry.Although wire electric discharge machining-low speed(WEDM-LS)is one of typical non-contact machining processes without macro cutting force,which does well in removing hardness and brittleness materials via pulsed discharge at high temperature,but few researchers have studied the thermal distortion behavior leading to a considerable geometric error in the WEDM-LS of thin-walled components.In this paper,a transverse magnetic field assisted method is applied for affecting the uniformity of discharge point distribution so as to reduce the distortion in WEDM-LS processing thin-wall component.First,the generation mechanism of this new distortion behavior and the impact mechanism of transverse magnetic field(TMF)on distortion are demonstrated by theoretical analysis.In order to further figure out the distortion behavior in the TMF-WEDM process,a new thermophysical model considering the discharge point distribution is established to simulate temperature field,residual stress field and distortion profiles.Then a large number of Taguchi experiments are carried out to investigate the influences of process parameters including pulse discharge energy(pulse on time,pulse off time,and current)and magnetic field strength on distortion in WEDM-LS.To comparatively analyze simulated and experimental results,the accuracy of established thermophysical model is verified within a relative error of 18.38%in distortion.Moreover,it can be revealed that transverse magnetic field contribute to significantly improve the longitudinal distribution uniformity with maximum increase of 12.32%at magnetic field strength:0.15 T,leading to significant reductions of 32.77%in distortion and 22.68%in recast layer.Eventually,we also presented the variation of residual stress and recast layer along thickness direction under different distortion behavior,which are in good agreement with that of distortion behavior.

先进航空材料和复杂构件的焊接技术

概述了一航材料院在十五期间对先进航空材料和复杂构件的焊接技术研究的主要结果与进展,其中包括已经获得实际应用的焊接技术以及相关有价值的探索性研究结果。

航空整体结构件加工变形校正技术研究

针对航空结构件的变形问题,提出了包含有加工残余应力的变形整体结构件三维质量模型的重构技术,建立加工变形—校正过程的协同仿真环境,将2个过程有机地结合起来;利用改进的二分法进行校正参数的计算,分析了校正支点位置的确定及不同校正载荷作用方式对于校正效果影响,揭示出加工后工件残余应力与校正残余应力的耦合作用规律;通过大量有限元仿真计算,获得了典型框类工件变形校正的规律性曲线,建立了适用于反弯校正的有限元数学模型,设计了变形校正试验,验证了有限元仿真结果的可行性和有效性。

移动机器人铣削制孔系统基准检测

结合航空大部件的数字化对接装配需求,设计了一套用于对接面铣削制孔的移动机器人加工系统,并提出具体的加工工艺流程。研究了基于激光轮廓扫描仪的大量散乱点云数据的预处理算法,提出基于栅格法和迭代拟合法的对接面特征提取算法。针对移动机器人加工系统在大场景下的高精度定位问题,提出基于扫描线法和最小二乘法原理的对接基准孔坐标找正算法。通过产品的加工实验验证,对接面铣削和制孔精度满足系统要求的各项技术指标,证明了本文提出的移动机器人铣削制孔系统的装配对接面加工方法能够精确地完成大部件数字化装配任务,对提高装配质量和效率具有重要意义。

基于残余应力释放的航空结构件加工变形模型与结构优化方法

在毛坯成形过程中,材料力学性能的非均匀性导致铝合金厚板内产生残余应力,以致在后续切削加工过程中,随着材料的去除,残余应力的释放使得整体结构件发生变形,严重影响着整体结构件的尺寸稳定性。因此,定量化研究切削过程中残余应力释放的加工变形分析与预测是进行加工质量控制的核心环节,对于实现加工过程的高效化和精密化至关重要。通过铝厚板的材料去除转化为残余应力的释放,利用静力平衡条件将作用于整体结构件的残余应力等效为外力后,综合考虑铝厚板横向方向和轧制方向的残余应力,依据弯曲变形理论创新性地建立铝厚板内初始残余应力释放模型。残余应力释放模型不仅能够准确地计算整体结构件的加工变形,而且还能够方便地优化工艺参数完成加工变形的有效控制。根据模型计算值与有限元仿真值、实验测量值的相互比较,分析结果表明:无论是幅值还是变形曲线,计算值都与仿真值具有高度一致性,而与测量值相比,尽管在变形曲线上具有很好的吻合性,但由于残余应力的测量误差使得两者在幅值上亦存在一定误差。

基于子结构法的航空结构件动态特性快速分析

为实现航空整体结构件不同加工阶段的动态特性快速分析,将工件按等效原则简化为若干标准特征子结构,进行参数化建模,采用子结构模态综合法进行航空整体结构件的动态特性研究,讨论了其基本原理并介绍了工程实现方法。选取典型航空结构件,实现其动态特性的快速分析。结果表明,工件子结构划分原则准确有效,利用模态综合法可提高计算效率,并保证良好的精度。

毛坯开槽方式中零件加工变形的演变机理与控制方法

广泛用作飞机薄壁整体结构件毛坯的铝合金厚板,在制造过程中出现的塑性变形不均匀性将导致残余应力的产生。高速铣削过程中残余应力的释放将引起飞机薄壁整体结构件的加工变形,这严重影响加工质量。因此,建立了毛坯释放变形后零件铣削的有限元仿真方法,挠度解析法的计算结果和实验测量的数据均验证了有限元仿真值无论是在趋势上还是变形量上均高度吻合。利用有限元方法揭示了开槽方式对毛坯释放变形的影响规律,分析了零件加工变形与毛坯释放变形之间的关系。结果表明:毛坯释放多大变形量,零件就能减小多大的变形量。在建立毛坯释放变形预测模型的基础上,提出了开槽方式的遗传算法优化方法,随机测试集表明神经网络的预测精度高达95%左右,而三框件在最佳开槽方式下能减小34.5%的变形。

T型航空铝合金结构件淬火残余应力数值模拟分析

运用ABAQUS有限元软件建立了T型航空7050铝合金构件淬火残余应力模型,得到了构件在淬火过程中的冷却曲线和不同部位的残余应力分布规律。结果表明:T型构件无论是肋部位还是腹板部位在淬火过程中均呈现出表面压应力,芯部拉应力的整体分布规律。但由于零件的复杂性,肋部位的塑性应变相对集中,导致其无论是表面还是芯部,产生的淬火残余应力均大于腹板部位的残余应力,且在整个淬火过程中分布规律相对复杂。

基于FTA与LS-SVM的航空部件危险性分级方法

针对目前危险性分级方法的不足,提出了基于故障树分析(fault tree analysis,FTA)与最小支持向量机(least square support vector machine,LS-SVM)的航空部件危险性定量分级方法。首先通过布尔代数法对FTA进行逻辑描述,采用概率重要度表示部件失效的后果严重程度,在此基础上通过LS-SVM对航空部件的危险性进行分级。实例证明,该方法能够准确地反映航空部件对飞行安全的影响。

面向航空结构件的自动化测量技术研究及应用

为实现检测过程自动化从而提升检测效率,针对航空结构件,提出一种坐标测量机检测轨迹的自动规划方法,开发了一套检测轨迹自动规划系统。依据测量点的法矢及测量机的摆角分度特性计算测头对应的位姿;以航空结构件的几何特征为驱动,对检测轨迹进行规划;基于VERICUT对检测轨迹进行仿真,避免测量过程的干涉碰撞;构建检测轨迹与DMIS语句的映射关系模型,实现测量程序的自动生成。应用验证表明,该系统能直接依据三维模型进行检测轨迹的规划,减少了测量过程的人工干预,检测效率较传统检测模式提升22%-34.6%。

飞机整体结构件的“加工变形-疲劳寿命”多目标结构优化方法

在毛坯制造过程中,材料力学性能的非均匀性导致铝合金厚板内产生残余应力,以致在后续的高速切削加工过程中,随着材料的大量去除,残余应力的释放使得整体结构件发生变形,严重影响着整体结构件的尺寸稳定性。因此,研究零件结构与零件变形之间的关系对于实现加工过程的高效化和精密化至关重要。首先,将铝厚板内残余应力的释放合理地等效为外载荷的施加,利用材料力学弯曲变形公式建立铝厚板在厚度方向上加工变形的挠度模型。由实际加工测量可知:加工变形的公式解析值、有限元仿真值与实际测量值吻合得很好。为了进一步分析零件结构与疲劳寿命之间的关系,通过名义应力法对零件的最小疲劳寿命与疲劳载荷下零件的最大应力进行等效以简化分析,对部分具有代表性的结构进行静力分析后将其作为样本进行神经网络拟合,得到了以3个腹板位置为输入、零件最大加工变形及最大疲劳应力为输出的神经网络模型。最后利用神经网络模型构建了一个使得最大加工变形和最大疲劳应力都尽可能小的多目标优化问题,使用遗传算法求解该多目标问题后取得的最优解为:3个腹板与零件底部距离分别为8.868 mm、27.992 mm、28.000 mm,此时零件的最大加工变形为0.088 mm,最小的随机疲劳载荷寿命为4.432×10^(7)次。