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Splicing of Glass Laminate Aluminum Reinforced Epoxy (GLARE) for Large Aircraft Skin Panels

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Russian Engineering Research Aims and scope

Abstract

Splicing of glass laminate aluminum reinforced epoxy (GLARE) is considered. The selection of the optimal manufacturing configuration for large aircraft panels is analyzed. The structure and the mechanical and fatigue characteristics of large panels made using the optimal production configuration are investigated. Splicing reduces the weight of the structure by 10–15% as a result of decrease in the rivet mass and the elimination of stress concentrators (rivet holes). Airplane reliability and viability are also improved.

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ACKNOWLEDGMENTS

This research was conducted on equipment at the Climate Testing Collective Use Center at Kurchatov Institute and the Russian Research Institute of Aviation Materials (VIAM), as part of research program 6.2 (regarding high-strength crack-resistant metal–polymer laminates) within the framework of the Development Strategy for New Materials and Processing Technologies up to 2030 [19, 20].

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Authors and Affiliations

  1. All-Russian Research Institute of Aviation Materials (VIAM), National Research Center “Kurchatov Institute, Moscow, Russia

    V. V. Antipov, S. V. Samokhvalov, V. V. Sidel’nikov, Yu. N. Nefedova & A. V. Somov

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  1. V. V. Antipov
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  2. S. V. Samokhvalov
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  3. V. V. Sidel’nikov
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  4. Yu. N. Nefedova
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  5. A. V. Somov
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Correspondence to Yu. N. Nefedova.

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Translated by B. Gilbert

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Antipov, V.V., Samokhvalov, S.V., Sidel’nikov, V.V. et al. Splicing of Glass Laminate Aluminum Reinforced Epoxy (GLARE) for Large Aircraft Skin Panels. Russ. Engin. Res. 43, 41–46 (2023). https://doi.org/10.3103/S1068798X23020041

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  • DOI: https://doi.org/10.3103/S1068798X23020041

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