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.
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