Abstract
Glass fiber composite laminates have competitive properties than monotonic material for their superior mechanical strength. Lab joints in composite structure are of great importance in aerospace and aircraft industry. Therefore, lab joints’ strength and failure of composite laminates structure are experimentally investigated. Composites laminates of four different stacking sequences and layup are manufactured using hand layup technique and curing at room temperature. Specimens of unidirectional laminates of [0]8 stacking sequence are used to test lamina mechanical properties while [0/90]2s, [0/60/90]s and woven are used to test the mechanical properties of lab joints. Lab joints of single row and double row are produced and tested in bearing using simple mode I test (tension test). The results illustrate that bearing strength of quasi-brittle laminates of [0/60/90]s has more stability and strength than that of woven glass fiber, then the cross ply laminates of [0/90]2s; this can be attributed to increase of anisotropy of cross ply laminates than other composite laminate structure.
Highlights
Structure of Composite laminates is nowadays having a competitive availability in a lot of applications especially in aerospace, aircraft and Marian industry
The results illustrate that bearing strength of quasi-brittle laminates of [0/60/90]s has more stability and strength than that of woven glass fiber, the cross ply laminates of [0/90]2s; this can be attributed to increase of anisotropy of cross ply laminates than other composite laminate structure
Mohammed et al [8] used X-FEM procedures to simulate the nominal strength of size effect glass fiber composite laminates; these results were in a good agreement with the experimental results
Summary
Structure of Composite laminates is nowadays having a competitive availability in a lot of applications especially in aerospace, aircraft and Marian industry. Xiao and Ishikawa [5] studied mechanical and fracture properties of fastened composite joints They investigate the polymer matrix cracking of the bearing strength performance. They summarized that failure due to compressive damage involved four stages; damage initiation; damage growth and structural fracture. Xiao and Ishikawa [6] analytically and numerically studied the bearing failure and performance of bolted composite joints. They used the finite element progressive damage model. Mohammed et al [8] used X-FEM procedures to simulate the nominal strength of size effect glass fiber composite laminates; these results were in a good agreement with the experimental results. It is aimed to find the bearing strength of lab joint manufactured from those types of this material with single and double rows bolts
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