螺接搭接件的力学特性试验及三维有限元分析

在考虑螺栓与孔壁间的非线性接触、摩擦、干涉配合和螺栓预紧力等因素影响的基础上,利用非线性有限元软件MSC.Marc构建螺接搭接件的三维有限元分析模型.数值模拟结果与试验结果的对比表明,文中所建三维模型能有效地模拟搭接件的表面应变、载荷传递和第三弯矩等三维力学特性,同时搭接件的三维应力、应变特性及干涉配合和螺栓预紧力对载荷传递比的影响规律也进行了讨论,计算结果和结论可作为该类结构损伤容限设计的参考依据.     

螺接搭接件的载荷传递特性试验及三维有限元分析

在考虑螺栓与孔壁间的非线性接触、摩擦、干涉配合和螺栓预紧力等因素影响的基础上,利用非线性有限元软件MSC.Marc构建了螺接搭接件的三维有限元分析模型。数值模拟结果与试验结果的对比表明:所建三维模型能有效地模拟搭接件的载荷传递特性。基于三维有限元模型,讨论了无裂纹搭接件的螺栓孔形式、干涉配合和螺栓预紧力对载荷传递比的影响规律,同时对含裂纹搭接件的载荷传递比随裂纹扩展的变化规律进行了分析,计算结果和结论可作为该类结构损伤容限设计的参考依据。     

飞机桁条-蒙皮连接结构的接触应力研究

飞机结构是由零部件通过铆接、螺接、胶接和焊接连接而组成的。连接区域应力分布情况及应力水平的研究对飞机结构的强度校核及连接区的失效破坏形式的预判有着重要的意义。基于非线性接触力学理论,利用MSC.Patran/Nastran有限元分析软件对机翼结构中复合材料桁条-蒙皮连接结构进行了研究。研究内容包括:各排钉孔的最大等效应力和钉传载荷的分布情况;对飞机桁条-蒙皮的两种连接方式,基于非线性接触理论,分别建立了桁条-蒙皮的螺接连接结构和胶-螺混合连接结构,对比了两种结构的等效应力水平大小与分布。得出以下结论:板间厚度比对孔周接触域的应力集中系数和应力分布的影响较大;处于外侧两排铆钉孔传递较大的钉传载荷,中间排的铆钉孔的钉传载荷较小;不同的连接形式对孔周应力水平影响较大。     

复合材料结构的干涉配合铆接

干涉配合能提高接头疲劳寿命 ,复合材料结构干涉配合连接的关键在于干涉量的控制。提出采用垫圈限制铆钉钉杆的膨胀 ,采用合适的钉孔间隙减小干涉量 ,并利用电磁铆接钉杆膨胀均匀的特点实现了复合材料结构的干涉配合铆接。     

铆钉铆接装配应力的分析和计算

分析了铆钉铆接时的成形过程。对铆接成形力和铆钉铆接成形后对板孔圆柱面上的径向分布压力及铆钉冒对板圆环面上的分布压力进行了计算。该分析和计算对工程实际具有一定的参考价值。同时，在对一些具有铆钉连接的板或梁进行有限元分析和计算时，解决了其力边界条件的问题。     

铆接铆钉分布压力的计算

分析计算铆接铆钉所需的压力、铆接成型后铆钉对板孔圆柱面上的径向分布压力和铆钉帽对板圆环面上的分布压力 ,对工程实际具有一定的参考价值。同时 ,在对一些具有铆钉连接的板或梁进行有限元分析和计算时 ,解决了其力边界条件的问题     

层合板多钉连接载荷分配均匀化方法

对不同钉孔配合下复合材料与金属铝板多钉双搭接的载荷分配进行计算,结果表明,通过在大载荷孔上采取间隙配合及小载荷孔上施加干涉配合的方法可显著影响多钉连接载荷分配,使得各钉载荷趋于均匀.     

含裂铆接搭接板应力强度因子分析方法

针对工程中广泛存在的铆接搭接结构断裂问题，充分考虑搭接板裂纹通过铆钉后铆钉继续传力的特点，利用位移连续条件，提出裂尖应力强度因子有限元分析模型。计算典型铆接搭接结构应力强度因子曲线，分析所提模型及其计算结果的合理性、正确性。提出的计算方法为铆接搭接结构应力强度因子提供了便捷、有效的分析手段，所得结果可供工程结构损伤容限分析时参考。     

基于手持式电磁铆接设备的无头铆钉干涉配合铆接工艺研究

根据无头钉铆接的特殊要求以及目前自动钻铆设备铆接无头铆钉存在的问题,提出采用手持式电磁铆接设备代替自动钻铆机实现无头铆钉的铆接。为准确控制铆钉两边的外伸量,在电磁铆枪前加装三爪卡盘。通过实验研究了铆钉外伸量、铆接电压等工艺参数,并分析了铆接质量,并通过工艺参数的控制达到设计的干涉量要求,实现了无头铆钉的干涉配合铆接。     

钛合金沉头铆钉干涉配合的工艺研究

随着航空工业的发展和对飞机高性能、长寿命的要求,针对某型号飞机钛合金沉头铆钉采用普通铆接干涉配合工艺,通过ANSYS有限元分析软件计算和试验两种途径来研究铆钉钉杆尺寸与铆接结构件间干涉量的关系,即在不同外伸量的工艺参数下所形成的干涉量。结果表明,在满足相同的墩头和外观尺寸的要求下,外伸量为(1.1~1.2)d和(0.5~0.6)l时铆接的干涉量分布均匀且铆接的质量较高,疲劳寿命最大。为铆接的干涉配合和工艺优化提供了重要的参考价值。     

Study of the impact of riveting sequence, rivet pitch, and gap between sheets on the quality of riveted lap joints using finite element method

Sheet metal parts are widely used in the assembly of aircraft. The most common method of joining sheet metal parts is through riveting. There are many parameters associated with a riveting process that affect the quality of rivets and the integrity of the final assembled product. This paper presents a study on the effect of some controllable process parameters in riveting (i.e., the sequence of riveting, distance between rivets (pitch), and gap between sheets) on the quality of riveted lap joints and the formed rivets. The study is performed on a one eight-inch nominal diameter flat head Tinner rivet and 0.064-in.-thick aluminum sheet. Finite element simulation is used as a means of modeling and analysis of the riveting process. Statistical design of experiment is employed to analyze the simulation data. A good combination of riveting process parameters is found which minimizes the residual stress in sheets and rivets, bulging and material growth in sheets, and which reduces the chances of postriveting clearance in a riveted lap joint.     

整体壁板结构纵向连接接头的应力分布研究

纵向连接接头是影响机身整体壁板结构的安全疲劳寿命的关键部位,因此本文设计了一种适用于机身整体壁板纵向连接的阶梯状两台阶铆接接头结构。文中应用ANSYS软件建立阶梯状两台阶铆接接头结构的三维非线性有限元模型,进行静强度有限元分析,得到接头结构上的精确应力分布,确定各铆钉孔边危险点处的应力集中系数,对接头结构的疲劳性能分析有着重要的参考基础,为纵向连接接头的设计及综合验证提供科学依据。     

Experimental and numerical studies of stress/strain characteristics in riveted aircraft lap joints

The fatigue property of riveted lap joint is greatly related to the riveting-induced residual stress, especially the stress distribution on the faying surface. However, an accurate study of the residual stress characteristics in the riveted sheet could be very difficult. In this paper, both numerical and experimental investigations were carried out on the stress/strain characteristics in riveted aircraft lap joints. A special specimen was designed for the test of strain variations on the faying surface of the sheet by microstrain gages. For the numerical simulation, the rivet squeezing process was analyzed using the explicit dynamic finite element (FE) method, whilst a general static FE analysis was employed for the elastic springback after the squeeze force was removed. A comparison of the strain variations between the experimental results and FE simulations shows a general good agreement, although there may be some difference for points measured near the hole surface. The FE analysis reveals that both compressive and tensile residual stresses could be introduced in the riveted sheet. Massive compressive residual stress can be created in the near-surface layer of the hole. However, the stress level is not always increased with increasing the squeeze force, and so is the improvement of fatigue life observed. Further study is still necessary to account for the fatigue life decreasing effect caused by a high squeeze force.

     

基于ANSYS/FE-SAFE的单搭自冲铆接头的疲劳分析

采用有限元分析软件ANSYS建立单搭自冲铆接头模型,对接头进行静力分析,在此基础上结合ANSYS/FE-SAFE,基于正弦激励载荷,对单搭自冲铆接头的疲劳寿命和安全系数进行了分析,得出自冲铆接头的最大应力位置与疲劳破坏位置一致,均为上板与铆钉头接触的部位。从安全系数云图中可得到工作安全系数大于许用安全系数,满足条件要求。用ANSYS/FE-SAFE软件来进行疲劳分析可以为下一步研究提供一定的参考。     

飞机结构紧固件柔度影响因素分析

紧固件柔度是飞机连接部位的疲劳寿命重要影响因素,常常作为考虑飞机结构疲劳寿命模拟和分析的主要参数。本文在验证弹塑性有限元法计算紧固件柔度有效性的基础上,利用弹塑性有限元法对不同紧固件连接的单搭接结构进行仿真分析,并由仿真分析得出的紧固件细节的载荷位移曲线计算紧固件柔度。分析表明:扁圆头铆钉铆钉头越小柔度值越大;埋头铆钉柔度值相对于扁圆头铆钉有所增大,十字槽埋头螺栓柔度值相对于埋头铆钉稍有增大;过盈配合使紧固件柔度值大幅减小。     

用于机器人自动钻铆的自动供钉系统试验研究

为了解决飞机数字化装配中自动钻铆机铆钉输送困难的问题,介绍了一套可以为机器人自动钻铆终端执行器输送铆钉的自动供钉系统。铆钉从供钉装置输送到插钉机构采用气管输送,在输送过程铆钉由于气压、弯曲半径等原因容易卡在输钉管中,为此运用结构分析、受力分析以及运动状态分析的方法,并结合流体力学知识对管中的铆钉进行了分析计算,得出了满足铆钉顺利输送的最小弯曲半径和最小输送气压等必要条件。实验计算结果验证了自动供钉系统铆钉管道气动输送的可行性。     

应力与腐蚀因素对连接件腐蚀疲劳寿命交互作用的研究

在应力控制下分别研究了不同应力,预腐蚀时间对3．5％NaCl溶液中有涂层的LY12CZ铝合金铆接连接件的腐蚀疲劳性能影响的规律。试样结构是根据飞机蒙皮的真实结构设计制成的单剪切连接件,按实际工艺过程进行表面处理。试验结果表明,提高应力和延长预腐蚀时间均会缩短连接件的腐蚀疲劳寿命。应力与环境腐蚀因素对连接件的腐蚀疲劳寿命的影响作用不是简单的叠加关系,而是相互影响的,结果还表明,在无预腐蚀的条件下有涂层连接件在pH值为6的NaCl溶液中的腐蚀疲劳寿命比空气中的寿命要高,并且在高低应力范围内均有此现象,在30MPa下预腐蚀对连接件的疲劳寿命的影响作用比50MPa下预腐蚀对连接件疲劳寿命的作用要明显。     

Microstructure investigation and mechanical property analysis in electromagnetic riveting

Electromagnetic riveting (EMR) is a new joining technology based on high-speed magnetic impulse forming and conventional riveting. EMR experiments were conducted on dual-layered 2A12 aluminum alloy sheets with one 2A10 aluminum alloy rivet. Observation of the microstructure and mechanical properties of rivet heading verified the forming quality of the heading. And, mechanical property tests were performed to evaluate the durability of riveted specimens through shear and pull-out loading. Microstructure observation indicated that adiabatic shear bands, where the deformation was highly concentrated, were an important characteristic of deformed structures in rivet headings under electromagnetic riveting. The distribution law of hardness in rivet headings was obtained. The compressive yield strength of rivet headings increased 70 % over that of the original rivets. Riveted specimens were capable of withstanding shear loads of 23.2 kN and pull-out loads of 35 kN. Ruptures characterized by a scanning electron microscope were found to be due to shear failure.     

铝钢电阻单元焊冲裁过程建模

针对铝钢异种材料电阻单元焊工艺的铆钉冲裁过程,建立了冲裁过程二维轴对称有限元仿真模型,对冲裁过程中接头的几何形貌演化以及应力分布特征进行了分析,并利用该模型研究了铆钉头部形貌、铆钉腿部形貌、落料模凸台宽度、落料模凸台高度和铆钉与落料模间隙等五个几何特征对冲裁过程及冲裁接头质量的影响规律,提出了铆钉和模具几何形貌的优化建议。     

Numerical analysis of static performance comparison of friction stir welded versus riveted 2024-T3 aluminum alloy stiffened panels

Most researches on the static performance of stiffened panel joined by friction stir welding（FSW） mainly focus on the compression stability rather than shear stability. To evaluate the potential of FSW as a replacement for traditional rivet fastening for stiffened panel assembly in aviation application, finite element method（FEM） is applied to compare compression and shear stability performances of FSW stiffened panels with stability performances of riveted stiffened panels. FEMs of 2024-T3 aluminum alloy FSW and riveted stiffened panels are developed and nonlinear static analysis method is applied to obtain buckling pattern, buckling load and load carrying capability of each panel model. The accuracy of each FEM of FSW stiffened panel is evaluated by stability experiment of FSW stiffened panel specimens with identical geometry and boundary condition and the accuracy of each FEM of riveted stiffened panel is evaluated by semi-empirical calculation formulas. It is found that FEMs without considering weld-induced initial imperfections notably overestimate the static strengths of FSW stiffened panels. FEM results show that, buckling patterns of both FSW and riveted compression stiffened panels represent local buckling of plate between stiffeners. The initial buckling waves of FSW stiffened panel emerge uniformly in each plate between stiffeners while those of riveted panel mainly emerge in the mid-plate. Buckling patterns of both FSW and riveted shear stiffened panels represent local buckling of plate close to the loading corner. FEM results indicate that, shear buckling of FSW stiffened panel is less sensitive to the initial imperfections than compression buckling. Load carrying capability of FSW stiffened panel is less sensitive to the initial imperfections than initial buckling. It can be concluded that buckling loads of FSW panels are a bit lower than those of riveted panels whereas carrying capabilities of FSW panels are almost equivalent to those of riveted panels with identical geometries. Finite elem