ABSTRAK Nguyen Anh Tuan
PUBLIC Irwan Sofiyan COVER Nguyen Anh Tuan
PUBLIC Irwan Sofiyan BAB 1 Nguyen Anh Tuan
PUBLIC Irwan Sofiyan BAB 2 Nguyen Anh Tuan
PUBLIC Irwan Sofiyan BAB 3 Nguyen Anh Tuan
PUBLIC Irwan Sofiyan BAB 4 Nguyen Anh Tuan
PUBLIC Irwan Sofiyan BAB 5 Nguyen Anh Tuan
PUBLIC Irwan Sofiyan PUSTAKA Nguyen Anh Tuan
PUBLIC Irwan Sofiyan
The unrelenting passion of aerospace and automotive industry to enhance the
performance of aircraft and automotive are constantly driving the development of
improved high-performance structural material. Composites material are one such
class of material that play a significant role in current and future aerospace and
automotive component. One of the main attractions to composite materials is that
they’re extremely lightweight, 30% lighter than aluminum and 25% the weight of
steel. Carbon-Fiber-Reinforced plastic (CFRP) and Glass-Fiber-Reinforced
plastic (GFRP) are usually used to make a component. Both of which are stiff and
strong. Bolted joints are common mechanical fastened joint use for joining the
composite part. It is unavoidable in complex structures because of their low cost,
simplicity and facilitation of disassembly for repair. Bolted joints require holes in
the composite structure. These holes cause large stress concentrations, decrease
the load holding capacity and increase the complexity of the numerical analysis
In this study, the composite CFRP woven fabric single-lap bolted joint is taken into
account to analyze the failure mechanisms and failure load of composite structures.
Experiments of single-lap bolted joints is conducted to study the progressive failure
behavior of bolted joint structure. To validate experiment results, a traction –
separation law is used as a constitutive model and is implemented within Extended
Finite Element Method (XFEM) approach to predict bearing stress at failure and
track the propagation of the crack. The approach is based on an assumption that
damage in composite hole structure initiates and propagates from the hole in a selfsimilar
fashion. To analyze the influence of parameters of composite plate on the
failure, the three parameters to be considered are: width, thickness and stacking
sequence. Effect of clamp-up torque in bolted joint also conduct to study the
influence of this value to the strength of joint structure. Good agreement of bearing
strength prediction of single-lap bolted joints can be seen at most of geometric
configuration between experimental and simulation results (below 20 percent) and
the bearing failure observed in experiments could not be treated in current study.