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This study aims to investigate the effect of countersunk rivet head dimensions on the fatigue performance of the riveted specimens of 2024-T3 alloy.

The relationship between rivet head dimensions and fatigue behavior was investigated by finite element method and fatigue test. The fatigue fracture of the specimens was analyzed by scanning electron microscopy.

A change of the rivet head dimensions will cause a change in the stress concentration and residual normal stress, the stress concentration near the rivet hole causes the fatigue crack source to be located on the straight section of the countersunk rivet hole and the residual normal stress can effectively restrain the initiation and expansion of fatigue cracks. The fatigue cycle will cause the rivet holes to produce different degrees of surface wear.

The fatigue life of the specimens with the height of the rivet head of 2.28 mm and 2.00 mm are similar, but the specimens with the height of the rivet head of 1.72 mm were far higher than the other specimens.

The riveting process is a metal forming process involving complex elastic-plastic deformation, which will induce a compressive residual stress field and cause local distortions in the connecting areas. Regarding to the aircraft panel assemblies with plenty of rivets, the global deformation is inevitable and undesired, leading difficulties to downstream assembly processes. This paper aims to present a new method for the local distortion calculation and the global deformation prediction of sheet panel assemblies during the automated riveting process.

In this paper, a simplified algebraic study is presented to analyze the local distortion of single countersunk rivet joint with the consideration of the barrel-like shape of the driven head and the through-thickness variations along the rivet shank. Then, an equivalent rivet unit is proposed based on the result of the algebraic study and embedded into the global-level model for the prediction of the overall distortions of riveted panels.

The algebraic study is able to reach a more precise contour of the deformed rivet than the traditional assumption of cylindrical deformations and rapidly determine the equivalent coefficients of the riveting unit. The result also shows an industrial acceptable accuracy of the prediction for the global deformations of the double-layered panel assemblies widely used in the aircraft panel structures.

A new local-global method for predicting the deformations of the riveted panel assembly based on the algebraic study of the local distortions is proposed to help the engineers in the early design stages or in the assembly process planning stage.

In order to improve the rationality of the design of carbon fiber composite riveting structures in engineering products and reduce physical tests, the stress changes of various parts during the carbon fiber-reinforced polymer (CFRP) riveting process, the influence area of hole edge stress and the damage of CFRP plates were studied from the perspective of numerical simulation. The reasonable arrangement requirements of composite riveted structures, installation speed and damage characteristics of CFRP plates in engineering applications are obtained. The research results provide technical references for the design and installation of composite riveting structures in engineering products.

Taking the forming process of the riveted structure between countersunk blind rivets and CFRP plates as the research object, the forming principle of countersunk blind rivets and the damage characteristics of CFRP plates were analyzed. Using contact nonlinearity theory, the anisotropic material modeling method and the Hashin failure criterion, the stress changes in various parts during the riveted joint forming process, the influence area of stress at the hole edge of the rivet holes and the damage of the CFRP plates were analyzed.

Reasonable rivet layout spacing was obtained; the peak stress of the rivet assembly increases with the increase of the rivet installation speed, and the influence area of the hole edge on the CFRP plate is a circular area with an outward extension radius of 0∼6 mm. Therefore, the arrangement distance between rivets is greater than the ring area, the damage law and installation speed of CFRP plates are given, the damage extends inward from the first layer of the laminates and the installation speed of 15 mm/s can satisfy the requirement of riveting installation better.

The riveting and forming process under different speeds is analyzed from the perspective of numerical simulation, and the stress variation rule of each part of the rivet and the damage of the CFRP plate under each speed are obtained. Reasonable rivet arrangement requirements and installation speed were given. This study provides technical support for the rivet arrangement method and mechanical property analysis of CFRP riveted structures in complex engineering products.

The purpose of this paper is to investigate the strain concentration factor in a central countersunk hole riveted in rectangular plates under uniaxial tension using finite element and response surface methods.

In this work, ANSYS software was elected to create the finite element model of the present structure, execute the analysis and generate strain concentration factor (,) data. Response surface method was implemented to formulate a second order equation to precisely compute (,) based on the geometric and material parameters of the present problem.

The computations of this formula are accurate and in a great agreement with finite element analysis (FEA) data. This equation was further used for obtaining optimum hole and plate designs.

An optimum design of the countersunk hole and the plate that minimizes the (,) value was achieved and hence validated with FEA findings.

IN the design of aircraft structures for fatigue strength, it is as well to bear in mind that those parts most likely to give trouble fatigue‐wise are those wherein rivets or bolts have to react a load. The term ‘react’ is used here to distinguish this from the case where rivets or bolts arc used to hold the skin on the frame, etc., where the worst possible concentration of stress in terms of the nominal gross area will approach that of a hole in an infinitely wide sheet, or about 3·0. The riveted joint is more likely to approach that of a lug, which, for conventional rivet spacing and edge distance would be about 5½ in terms of gross stress. In other words, our working stress for a joint would be about one‐half the axial stress in a plain sheet with holes for the same life. Other things, such as normal loads and buckling, may alter this ratio somewhat.

The purpose of this paper is to present a dual-robot pneumatic riveting system for fuselage panel assembly, including the system design, dynamic analysis and sensitivity analysis. The dual-robot pneumatic riveting system is designed to improve riveting efficiency and quality, thus finally replace the traditional two-man riveting mode where possible.

The dual-robot pneumatic riveting system has been designed by considering vibration reduction for the tools and isolation for robots. Nonlinear multi-body dynamic model including clearance and collision is established for investigating the dynamic performance and analyzing the systemic sensitivities with respect to the key variations. Semi-implicit Runge–Kuta algorithm is used for solving the dynamic equations and shop experiments are implemented to verify the effectiveness of the numerical simulations.

The simulation results show the tools can be held stably enough for riveting operation and the system sensitivity with respect to robot gesture can achieve the expected level. The experiment validates the proposed system with a good performance, and the riveting quality could adequately meet the requirements. The system is capable of installing an aluminum alloy countersunk 5 mm diameter rivet in 5 s.

The dual robot pneumatic riveting system is successfully developed and test. It has been applied in a project of fuselage panel assembly in the aircraft manufacturing industry in China.

To replace the traditional manual rivet installation, this paper presents a dual robot pneumatic riveting system and includes both the system design and dynamic analysis.

WHEN a new aeroplane is produced, every effort is made to ensure that it will be free from the “bugs”, to use that expressive word of the aircraft industry, experienced on previous types. This goal is usually attained, but unfortunately the sum total of defects does not decrease, mainly because new and comparatively untried ideas will have been incorporated to improve the new aircraft. Defects arising from these will most probably outweigh those obviated by experience, and so, until finality in design is reached, there will continue to be design defects. Another factor is that the other aircraft with which the comparison is being made will usually have been in service for some time and their teething ailments largely eliminated and thus forgotten.

Contrary to the general conception of adding weight for fatigue resistance it is sometimes possible to reduce the fatigue hazard by removing weight. The theory of having bearing area, tear‐out area, and tension area sufficient to develop the full shear strength of a rivet is not necessarily sound when fatigue life is considered. Accordingly, marked improvements in fatigue resistance can be achieved by reducing the underlying areas to such an extent that they are incapable of inducing loads causing fatigue failures of the main structure. Results of tests involving fatigue failure are given, and seven basic considerations in the design of fatigue resistant structures are listed.

THIS paper deals with semi shear‐resistant panels (incomplete tension fields) subjected to pure shear—as well as combined shear and tension loads. It establishes the stresses in the midplane of the sheet and the loads acting on panel joints.

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States National Advisory Committee for Aeronautics and publications of other similar Research Bodies as issued