A review on bistable composite laminates for aerospace applications

Lemos, Diego Magela; Marques, Flávio D.; Ferreira, António J.M.

doi:10.1016/j.compstruct.2023.117756

Cited by 11 publications

(2 citation statements)

References 124 publications

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“…However, recent explorations into bistable laminates by the research community suggest that asymmetric laminates could find utility in the aerospace industry. [74][75][76][77][78] These laminates offer stable positions without the need for a continuous power source and provide advantages such as lighter actuation systems and extended fatigue life, contributing to overall advancements in aerospace technologies. 74 Despite these considerations, the curved joint can also be employed with symmetrical laminates, albeit requiring a suitable mold with the appropriate curvature.…”

Section: Discussionmentioning

confidence: 99%

“…[74][75][76][77][78] These laminates offer stable positions without the need for a continuous power source and provide advantages such as lighter actuation systems and extended fatigue life, contributing to overall advancements in aerospace technologies. 74 Despite these considerations, the curved joint can also be employed with symmetrical laminates, albeit requiring a suitable mold with the appropriate curvature. It is imperative, however, that the chosen laminate layup induces warpage in only one direction -predominantly along the x 3 axis (normal to Figure 2)exhibiting a single principal curvature while nullifying others.…”

Section: Discussionmentioning

confidence: 99%

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Delamination prevention of composite joints with asymmetric carbon-fiber reinforced plastic adherends

Pires,

Carbas,

Marques

et al. 2024

Journal of Composite Materials

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The use of adhesive bonding in aeronautical applications has gained popularity due to its numerous advantages over traditional mechanical fastening methods. However, the issue of delamination still poses a significant challenge in fully embracing this technology in the industry. This study proposes a unique approach to optimize carbon fiber reinforced polymer (CFRP) single lap joints (SLJ) by introducing a curved joint design with varying adhesive thickness. The curvature is achieved through the intentional warpage caused by residual stresses resulting from an asymmetrical composite layup. While these residual stresses can potentially lead to cracks and distortions, this research aims to leverage their presence to enhance joint performance and mitigate delamination risks. A comprehensive analysis, involving both numerical simulations and experimental testing was conducted to compare the performance of the curved joint design with traditional configurations. The findings indicate that the curved joint design effectively prevents delamination while maintaining comparable joint strength. This demonstrates the potential benefits of employing curved joints for aeronautical components with curved geometries, affirming the feasibility and advantages of this approach. However, further optimization of the curved joint configuration is warranted to enhance its performance and expand its applicability to a broader range of applications.

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