Enhanced flexural and vibration behavior of interleaved CFRP composite joints with modified multiwalled carbon nanotube adhesives for aerospace and aircraft applications

Abstract

Cocured bonding and geometric modification are prominent techniques for fusing structural components in aerospace and aircraft applications. This research involved the fabrication of carbon fiber‐reinforced polymeric (CFRP) adhesive‐bonded joints utilizing novel cocuring with interleaved lamination (IL‐CC) joining techniques with multiwalled carbon nanotubes (MWCNTs) modified epoxy adhesive. Additionally, the study examined the flexural and vibration characteristics of IL‐CC CFRP composite joints. The result findings 1.0 wt% MWCNTs in epoxy adhesive had the best flexural strength and modulus, 78% and 32% higher than the pure epoxy adhesive. Additionally, the IL‐CC CFRP composite joints exhibit a 285% higher flexural strength and a 47% higher modulus than the neat CC CFRP composite joints. Nevertheless, the nanofiller with a wt% of 0.25 demonstrated the highest natural frequency across three different vibration modes, which are 14%, 21%, and 25% higher than pure epoxy adhesive. An ANOVA showed that MWCNT concentrations significantly influenced performance. Using the Levenberg–Marquardt algorithm, an artificial neural network predicted results. The overall coefficient (R) mean square error of 0.99627 is satisfactory, indicating that both outcomes are dependable and in good agreement. The results imply that IL‐CC CFRP composite joints could be used in aerospace and aircraft parts.Highlights The IL‐CC CFRP SLJs were fabricated with MWCNT‐modified adhesive. Attained the maximum flexural strength is 1.0 wt% MWCNT. Attained the maximum natural frequency is 0.25 wt% MWCNT. Statistics were analyzed using a one‐way ANOVA technique. An ANN predicts the flexural and dynamic behavior of IL‐CC CFRP SLJs.