Abstract
Use of composite structures in various sectors is rapidly increasing. The composite materials are becoming very popular due to high strength to weight ratio, high stiffness to weight ratio, low coefficient of friction, improved appearance etc. Extensive literature is available for the behavior of composite bolted joints subjected to tensile loading for the aerospace structures. The work reported in this paper is an attempt to extend the analytical model for studying the behaviour of composite bolted joint under compressive loading. The model is capable of conducting the parametric study on the joint stiffness variation with respect to parameters such as plate width, bolt diameter and stacking sequence for compressive loading. The model is verified experimentally. The experiments were designed to study the effect of variation in the parameters on the joint stiffness. Unidirectional and bidirectional carbon fibre epoxy composite laminates were tested as per ASTM D5961. The parameters viz. stacking sequence, bolt diameter, plate width of the joint stiffness are identified as significant.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
