Study on analysis and prediction of riveting assembly variation of aircraft fuselage panel

Liu, Gang; Huan, Honglun; Ke, Yinglin

doi:10.1007/s00170-014-6113-z

Cited by 33 publications

(21 citation statements)

References 30 publications

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“…Using the FEA, the variation analyses yield the useful influence coefficient method and many recent advances in the dimensional control of automotive and aircraft structures. 15,16 However, either the kinematic formulation or the influence coefficient method has difficulty in building the 3D precision calculation with rigid and compliant motions or gathering the detailed joint distortions. Hereby, the authors 3 combine a kinematic formulation with FEA, which forms a first version of 3D precision calculation that directly supports the participation of detailed joint distortions.…”

Section: Literature Reviewmentioning

confidence: 99%

Performance of reducing the dimensional error of an assembly by the rivet upsetting direction optimization

Tang

Xing

2016

Proceedings of the Institution of Mechanical Engineers, Part B:

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Reduction in the dimensional error of an assembly mostly focuses on the variation of fixtures and parts inside, in which the variation is mainly controlled by the methods relating to the fixture design and variation analysis. Recently, more researches concentrate on the dimensional analysis of the aluminum assembly where the distortion of rivet joints cannot be neglected, that is, the riveting-induced dimensional error. Hence, both the device design and the variation analysis for the riveting are drawing much attention to reduce the overall distortion. This article presents a dimensional reduction method, a rivet upsetting direction optimization based on a local-to-global dimensional calculation. The method is developed from a recent framework of assembly process optimization according to the discovered sensitivity between global dimensional error and rivet upsetting directions. A potential function that gathers the overall effect of every locating error is included. Simulations for three riveted assemblies are presented for comparison and results show that the method is efficient for the specific assignment of every rivet upsetting directions, and the effects of locating errors and rivet upsetting directions are highly coupled. The coupled effect yields the key questions in the improvement of this method. Detailed suggestions are then summarized.

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Section: Literature Reviewmentioning

confidence: 99%

Performance of reducing the dimensional error of an assembly by the rivet upsetting direction optimization

Tang

Xing

2016

Proceedings of the Institution of Mechanical Engineers, Part B:

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“…Indeed, computing contact behavior involves using a nonlinear solver, and the use of finite element software is justified for the simulation. A prediction of gap between components is a case for which a non-linear model is needed [7] [8].…”

Section: Methodsmentioning

confidence: 99%

Flexible Best Fit Assembly of Large Aircraft Components. Airbus A350 XWB Case Study

Arista

Falgarone

2017

Product Lifecycle Management and the Industry of the Future

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The need for assembly parts and structures where the perfect fitting is not guaranteed due to manufacturing/assembly tolerances and/or the influence of several physical effects, i.e. gravity, is increasing constantly in different industrial sectors and in particular in the aerospace industry. Some techniques have been developed to deal with it. In the field of large aero structures, custom-made parts using reverse engineering techniques are used to machine parts whose geometry requires to be customized for each produced aircraft. In the field of aircraft shells, a technique based on the characteristics of non-rigid components that can be slightly deformed to clear geometrical conditions by controlled forces to strain within its stress limits. FITFLEX project exploit this last technique and was carried out by Airbus Group Innovations and Airbus. The objective is supporting the Airbus A350 XWB ramp-up and the current manual positioning process of the shell by force control, defining a measurement based assembly including a flexible best-fit system. The case subject of study on FITFLEX project is the A350 XWB rear fuselage, a 14 meters by 5 meters side shell positioning process.

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“…The elastic-plastic parameters for materials used here were the same as ones used in the previous work. 19 A clearance exists between the rivet and the hole at the initial state. With the expansion of the shank, the wall of the hole was gradually bulged and complex nonlinear contact phenomena occurred.…”

Section: Finite Element Modelingmentioning

confidence: 99%

Effects of squeeze force on static behavior of riveted lap joints

Huan

Liu

2017

Advances in Mechanical Engineering

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To study the effects of the squeeze force used in the rivet installing process on structural behavior of the riveted lap joints, three-stage finite element simulation and workshop experiment of single-row countersunk riveted lap joints were implemented. Force-displacement curves and explicit configuration after various processes were obtained from both methods. Additionally, stress/strain fields were obtained from finite element analysis, and strain values at specific positions were measured by micro strain gauge during the experiment. Based on the consistency of the results, stresses on the edge of dangerous holes, load transmission, and secondary bending of joints under tensile load were analyzed. The result shows that increasing squeeze force does not have a significant influence on joint stiffness but results in a slight decrease in joint strength. Greater squeeze force introduces greater residual stress around the hole, and the maximum principal stress around the hole becomes greater tensile stress instead of initial compressive stress introduced by riveting process, thus causes weaker static strength. It is also shown that under static load, breakage occurs in the outer sheet at the end hole due to the largest load transmission and secondary bending, whereas these two aspects not only depend on the rivet installation squeeze force but also depend on the size of the exterior tensile load.

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Study on analysis and prediction of riveting assembly variation of aircraft fuselage panel

Cited by 33 publications

References 30 publications

Performance of reducing the dimensional error of an assembly by the rivet upsetting direction optimization

Performance of reducing the dimensional error of an assembly by the rivet upsetting direction optimization

Flexible Best Fit Assembly of Large Aircraft Components. Airbus A350 XWB Case Study

Effects of squeeze force on static behavior of riveted lap joints

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