Structural Analysis of Aircraft Wing J Nose Panel using Mono and Multi Core Composite Materials

The sandwich construction has been recognized as a promising concept for structural design of light weight systems such as wings of aircraft; purpose to design a light-weight sandwich panel for trailers. Strength calculations, skin instability and selection of materials were carried out in order to find a new solution for this specific application. The sandwich panel consists of 2 layers of face sheets, with ply 1 has 0.3 mm thickness & ply 2 has 0.1 mm thickness and core is present between top and bottom face sheets which has 19.2 mm (Mono-core) and 9.4 mm (Multi-core) thickness. The sandwich composite panels mono core and multi core testing performed by MSC Nastran/Patran MARC software to simplify the core material selection process and to design the layers , static 4-point bending test , compression test, tensile test and shear test are executed by finite element method pre-process perform using MSC PATRAN solved in NASTRAN MARC software and engross behaviour of mono core and multi core panel , grounded on result obtained from the four point bending test, compression test and shear test of glass fibre plastic (GFRP) laminates ,preeminent sandwich structure in mono core and multi core predicted.