ABSTRACT
Composite material systems have become more frequent in aircraft design. A significant number of scientific studies have concentrated on understanding these composite materials and structural components in a wide range of conditions to assess their performance in the event of exposure to loads of flight. This research explores the analysis of composite laminate and sandwich systems for stress, compression, bending, impact and fatigue cracks, and analyses the styles and properties of adhesive and mechanically fastened joints. Despite the difficulty of the study of composite fractures with the analysis of metallic fracture products, the findings can be used to define subjects of potential growth in composite analysis and fracture modes, particularly in uses to analyses of material throughout aircraft structures.
