Selection of the method for joining composite structural elements in the tail fuselage of a light aircraft
Published: 02.12.2024
Authors: Tun Lin Htet, Prosuntsov P.V.
Published in issue: #12(156)/2024
DOI: 10.18698/2308-6033-2024-12-2411
Category: Aviation and Rocket-Space Engineering | Chapter: Strength and Thermal Conditions of Aircraft
The paper examines various methods for connecting components made of polymer composite materials, focusing on adhesive and combined adhesive-mechanical joints. The primary focus is on the comparative analysis of these connection types in terms of their effectiveness, manufacturability, and impact on the structural strength and overall weight of the assembly. Aerodynamic and mass-inertial forces acting on the aircraft in various design load cases were considered. The stress-strain state of the structural elements (ribs) was analyzed using the ANSYS Workbench. Based on this analysis, a rational method for connection of composite structural components is proposed, which provides weight reduction of the structure while maintaining sufficient strength and reliability of the assembled elements. The strength evaluation of structural elements was conducted with consideration of their safety factor according to the failure criterion for composite materials.
EDN AIZQCC
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