Computational analysis of temperature effect in composite bolted joints for aeronautical applications

Abstract

This study focuses on the analysis of influence of temperature and bolt torque on aeronautical joint behavior. A single-lap joint, according to ASTM D5961, with a titanium bolt and composite plates was considered. A numerical model based on FEM was developed to evaluate the stress in both bolt and composite plates. Load-displacement curves, stress fields, and induced damage showed, significantly, the influence of temperature combined with torque level on the joint. It was found that in the plate, both maximum and minimum levels of torque considered produced damage above critical threshold. This fact should be accounted for, during the design process of the joint.

Drilling optimization of woven CFRP laminates under different tool wear conditions: a multi-objective design of experiments approach

“…Among different types of such materials, woven CFRPs have proven to be appealing material solutions in a broad range of applications, mainly due to their combined fatigue and corrosion resistance, light weight, high specific stiffness and strength properties, along with superior impact fracture toughness compared to unidirectional composites (Huang 2009;Santiuste et al 2011;Teti 2002). Their conformability under different manufacturing methods is also agreeable.…”

On the prediction of bolted single-lap composite joints

“…As was demon strated in [14,16] for carbon/epoxy laminates, bearing strength grows when the clamping pressure is increased. On the other hand, the negative effect is that out of plane stresses can lead to a pre mature failure of the joint [17,18]. In consequence, the maximum value of torque is limited by standards.…”

Delamination prediction in orthogonal machining of carbon long fiber-reinforced polymer composites

“…9 It is remarkable that the stacking sequence of the laminate is carefully selected for high-responsibility applications in order to optimize the material response to service loads. For instance, a sequence with external plies located at 45 is commonly selected for axial loading (direction 0 ) of composite bolted joints (see for instance Reference [3]). Joining requires previous drilling of the hole and commonly the component also needs contour milling in order to achieve dimensional specifications.…”

“…2 Surface integrity of the workpiece is critical for the subsequent assembly stage and, of course, during service life of the component. 3 Measurement of damage is costly, time consuming and sometimes needs destructive techniques to analyze the component. Despite the importance of prediction of damage mechanisms induced during machining; only few works in scientific literature deal with modeling of cutting processes in composite.…”