Stress field characteristics of eccentrically loaded aircraft spliced joints

Bedair, Osama

doi:10.1016/j.apm.2011.11.010

Cited by 6 publications

(5 citation statements)

References 15 publications

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“…Splice joint involves the joining of two members with the aid of a third structural component as shown in Figure 2. 47 The splice joint is employed to hold the surface of the wing skin and support incident stresses during loading. 48 Splice joints are employed in the wing box as skin splice joint and spar splice joint.…”

Section: Challenges In Joining For Unequal Thickness Similar Materials In Different Joint Configurationsmentioning

confidence: 99%

Challenges in joining of unequal thickness materials for aerospace applications: A review

Majeed

Mehta

Siddiquee

2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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The increasing industrial demand to reduce structural weight, optimize structural strength, and high performance has led to the increasing use of tailors welded blanks. However, the joining of tailors welded blanks is an issue of concern to researchers owing to the difference in thickness between the materials in addition to the difference in physical and chemical properties in the case of dissimilar materials. These challenges in joining of tailors welded blanks are conquered by a recent solid phase joining process known as friction stir welding. This review work covers different methods of joining unequal thickness similar/dissimilar (or tailors welded blanks) aircraft materials in different joint configurations along with the challenges and failure modes encountered in these joining processes. From this article researchers and industrialists can take advantage and conquer relative limitations in order to meet the future challenges for joining of similar/dissimilar aircraft materials with unequal thickness

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Section: Challenges In Joining For Unequal Thickness Similar Materials In Different Joint Configurationsmentioning

confidence: 99%

Challenges in joining of unequal thickness materials for aerospace applications: A review

Majeed

Mehta

Siddiquee

2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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“…It worth mentioning that limited studies were conducted to detail the micro-stress characteristics within the stiffened splice joint. Bedair (2011aBedair ( , 2012b presented finite elements modeling procedures for analysis of spliced connections used in the design of stiffened plates and shells. In the first reference by Bedair (2011a), cost-effective procedures are described that can be used by structural engineers in practice to determine the stresses in spliced members.…”

Section: Finite Element Modelling Philosophiesmentioning

confidence: 99%

“…In the second reference, Bedair (2012b), FE modeling procedure is presented to model eccentrically loaded aircraft splice joints. Description of the finite element model is shown in Figure 6.…”

Section: Finite Element Modelling Philosophiesmentioning

confidence: 99%

Recent developments in analysis of deteriorating stiffened panels subjected to static and explosive forces

Bedair¹

2013

Multi Modelg in Mat & Struct

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Purpose -The paper aims to review recent developments for analysis of deteriorating stiffened panels subjected to static and explosive forces. Design/methodology/approach -The first part reviews numerical procedures developed for stiffened panels subjected to explosive forces. The structural idealization, the theoretical basis, and the merits of these methods are discussed. The second part reviews the probabilistic procedures developed for analysis of deteriorating stiffened panels. The third part reviews recent work developed in several finite element modelling philosophies for analysis of stiffened panels. The influence of various parameters affecting the structural performance, such as geometric and material imperfections, corrosion, residual stresses, etc. is discussed. The fourth part reviews hybrid procedures developed to provide approximate solutions for the designers. Numerical procedure is presented using combination of energy formulations and mathematical programming techniques to model the interaction between the box girder components. Findings -Localized damage largely affects the performance of stiffened panels and must be accounted for in the design phase. Little emphasis was given in the published literature to developing simplified analytical models that can be used in practice to compute the residual strength of the stiffened panels under these types of loadings. Furthermore, analytical expressions are required to compute the reduction in the stiffness induced due to the structural or material defects. These expressions must be dependent on the type of damage. It must be noted that some of this damages is localized in nature and must be accounted for by using specialized functions to assess the structural defect accurately. Research work is required in this direction. Practical implications -The paper provides useful resource material for the engineers in practice regarding recent techniques developed to assess damaged stiffened panels subject to static and explosive loadings. The paper reviews work developed over the past 20 years that can be used as a baseline for future developments. Originality/value -Very limited literature dealt with the ultimate strength of damaged stiffened structure under static and explosive forces. No guidelines are available in current design codes to assess the damage in predicting the strength of deteriorating stiffened panels.

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“…Therefore, the fatigue failure of the connecting parts of aircraft structural parts has become the focus of attention of researchers from all over the world. Li et al [2,3] used a combination of finite element analysis and experiments to study the residual stress and strain of singlerivet and three-rivet countersunk head riveting parts and analyzed the influence of the maximum principal stress distribution and the residual stress on a riveted joint during the tensile load stage; Bedair et al [4] studied the circumferential stress, axial stress, and radial stress distribution close to the connecting hole of a multi-nail riveted part through the finite element method and found that the maximum tensile and compressive stress on the parts is greatly affected by the secondary bending; Skorupa et al [5] studied the influence of factors such as the type and material of rivets, the material and thickness of connecting parts, the pressure riveting force, and secondary bending on the fatigue performance of a riveted joint through experimental methods. They found that the secondary bending has the most prominent effect on the fatigue performance of the riveted joint.…”

Section: Introductionmentioning

confidence: 99%

Effect of Riveting Angle and Direction on Fatigue Performance of Riveted Lap Joints

et al. 2021

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Riveting is the most commonly used connection method in aircraft assembly, and its quality has a crucial effect on the fatigue performance of aircraft. Many factors affect the riveting quality, among which the influence of the riveting angle and direction is not clear. In this paper, a three-dimensional finite element model of single-rivet lap joints is established and verified by the driven head geometry and the riveting force data obtained from the riveting experiments. Then, by adjusting the angle and direction of the punch in the finite element model, the riveting process is simulated at the angles of 0°, 1°, 2°, and 3° and the directions of 0° and 180° to investigate the deformation of the lap joints, the stress distribution around the hole, and the stress distribution of the rivet. Finally, the fatigue tests of the single-rivet lap joints are performed and the influence of the riveting angle and direction on the connection quality and fatigue performance of the riveting joints is analyzed.

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Stress field characteristics of eccentrically loaded aircraft spliced joints

Cited by 6 publications

References 15 publications

Challenges in joining of unequal thickness materials for aerospace applications: A review

Challenges in joining of unequal thickness materials for aerospace applications: A review

Recent developments in analysis of deteriorating stiffened panels subjected to static and explosive forces

Effect of Riveting Angle and Direction on Fatigue Performance of Riveted Lap Joints

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