DAMAGE ASSESSMENT AND STRUCTURAL-TECHNOLOGICAL REPAIR SOLUTIONS FOR AIRCRAFT COMPOSITE PANELS

О. О. Васильєв, І. В. Малков, Б. А. Овчаров, С. В. Плахотников

Abstract


In this article, the research object is homogeneous composite aircraft panels with through-out holes. The study describes the typical damage common to the airplane composite structure such as scratches, punctures and delamination that can occur during operation. The aim of this article is to develop recommendations for homogeneous aircraft panels damage assessment. The damage is removed using oval or circular shapes. The finite element analysis was conducted to evaluate stress concentration factors (SCFs) influenced by defect geometry, specifically elliptical apertures, and the elastic modulus of the laminate under multiaxial loading scenarios. The analysis revealed a reduction in SCFs as elliptical defects transitioned toward crack-like geometries, with material elasticity and defect dimensions being critical parameters. These findings underscore the necessity for precise defect characterization and optimized repair strategies.

The study also evaluates several repair approaches, emphasizing the application of modern composite patches for their superior physical properties and ease of integration. Techniques such as rounded-edge and stepped patch designs are recommended to minimize stress concentration zones, enhancing structural integrity. The proposed methodology integrates computational modeling with practical repair applications, providing a robust framework for addressing damage in composite aircraft structures.

This work provides actionable insights into the mechanics of defect-induced stress distributions and presents validated repair solutions to ensure the structural reliability and operational safety of aerospace components.


Keywords


: puncture, sandwich panel, stress concentration factors, finite element Analysis, load sase, pre-impregnated fibers

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DOI: https://doi.org/10.32620/oikit.2024.102.05

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