Laser beam welding of aircraft fuselage structures

Brenner, Berndt; Standfuß, Jens; Dittrich, Dirk; Winderlich, B.; Liebscher, Jens; Hackius, Jens

doi:10.2351/1.5061271

Cited by 9 publications

(3 citation statements)

References 2 publications

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“…The T-joints welding is currently gaining a lot of attention as an alternative to replace riveting as the primary fabrication method of skin-stringer formation [3][4]. The disadvantages of skin-stringer joints formation using rivets include increased weight, relatively high cost, and low productivity [5][6]. The T-joints technique was first introduced in Germany [6].…”

Section: Introductionmentioning

confidence: 99%

“…The disadvantages of skin-stringer joints formation using rivets include increased weight, relatively high cost, and low productivity [5][6]. The T-joints technique was first introduced in Germany [6]. This technique was used for the manufacturing process of the Airbus A318 because it can increase the production efficiency and reduce the weight of modern aircraft [7].…”

Section: Introductionmentioning

confidence: 99%

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Simultaneous Double-Sided Metal Inert Gas Welding of AA5052 Aluminum Alloy T-Joints

Himarosa

Mudjijana

Adi

et al. 2022

MSF

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Simultaneous double-sided MIG welding as alternative method for joining the skin-stringer T-joints were investigated. The microstructure and mechanical properties of the welded joints were examined. Our study showed that a distance of 27-mm (torch to surface) results in the best weld appearance. Shorter distance produces higher heat input and causes the material stringers to melted with the filler, while longer distance increases the number of porosity and prevents the formation of a complete fusion zone.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Simultaneous Double-Sided Metal Inert Gas Welding of AA5052 Aluminum Alloy T-Joints

Himarosa

Mudjijana

Adi

et al. 2022

MSF

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“…The joints made using LBW can reduce the weight of the aircraft fuselage panels; consequently, the final transportation costs are decreased due to a lack of rivets and sealant compared with the traditional riveting technology [ 2 , 3 , 4 ]. Moreover, welding takes less manufacturing time than mechanical fastener assembly, thus reducing the manufacturing costs [ 5 , 6 ]. As an alternative to the conventional aluminum alloy, the aluminum–lithium (Al–Li) alloy with low density, high elasticity modulus, high specific stiffness, and high specific strength can be used in welding as the panel materials for the aircraft fuselage [ 7 , 8 ].…”

Section: Introductionmentioning

confidence: 99%

Experiment and Numerical Simulation for the Compressive Buckling Behavior of Double-Sided Laser-Welded Al–Li Alloy Aircraft Fuselage Panel

et al. 2020

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The aim of this work was to study the buckling behavior and failure mode of the double-sided laser-welded Al–Li alloy panel structure under the effect of axial compression via experimental and numerical simulation methods. In the test, multi-frequency fringe projection profilometry was used to monitor the out-of-plane displacement of the laser-welded panel structure during the axial compression load. In addition, the in-plane deformation was precisely monitored via strain gauge and strain rosette. The basic principles of fringe projection profilometry were introduced, and how to use fringe projection profilometry to obtain out-of-plane displacement was also presented. Numerical simulations were performed using the finite element method (FEM) to predict the failure load and buckling modes of the laser-welded panel structure under axial compression, and the obtained results were compared with those of the experiment. It was found that the fringe projection profilometry method for monitoring the buckling deformation of the laser-welded structure was verified to be effective in terms of a measurement accuracy of sub-millimeter level. The structural failure was caused by local buckling of the skin. The observed failure modes such as local buckling of the skin, bending deformation of the stringers, continuous fracture of several welds, and failure of local strength and stiffness were attributed to the deformed laser-welded panel structure under the axial compression. The predicted failure load in the numerical simulation was slightly smaller than that of the experimental test, and the error of the simulation result relative to the test result was −2.7%. The difference between them might be due to the fact that the boundary and loading conditions used in the FEM model could not be completely consistent with those used in the actual experiment.

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