Dynamic Analysis of Honeycomb Sandwich Laminated Composite Plate using ANSYS

Abstract

A structural sandwich is a peculiar form of a laminated composite comprising of a combination of distinct materials which are bonded together to use effectively the properties of each separate component to the structural advantage of the whole assembly. Two thin, rigid and quite strong faces in the framework are partitioned by a thick, light and weaker core. The faces are attached adhesively to the core to ensure effective load transfer between the components. Owing to the core structure, such composites are differentiated by their stiffness. Despite the thickness of the core, sandwich composites are characterized by their light structure and a good flexural strength. These composites possess unique structure, which provides it a good thermal insulator properties. Sandwich composites finds a wide range of application in aeronautics, transportation such as road vehicles, ships, winds, marine and civil engineering. The Laminated sandwiched composite pate is preferred over simple laminated composite plate due to their great ability to essentially decrease weight while maintaining optimum mechanical performance. This weight reduction provides a large number of benefits which includes higher payloads, increased range and comparatively less fuel consumption. The Present study is done to study and investigate the Sandwich composite Panel which is formed by laminating composite sheets with Aluminium Honeycomb core and Dynamic Analysis is done to study its behaviour by computing natural frequency and corresponding deflection. Triangular, Square and Hexagonal cell for the honeycomb will be used to find the best shape under dynamic loading. Further, the effect of hexagonal cell parameter will be studied in order to find optimum parameters in ANSYS 18.1 Software.