Experimental and Numerical Study on Bolted/Bonded Composite Joints for Aircraft

Bolted and bonded joining technologies in composite structures have been widely studied since the 1970s. Although every technology has advantages and disadvantages, bonded joint technology has the potential to reduce the weight and manufacturing cost of advanced aircraft structures. However, bolted joining is still generally required for certification and regulatory compliance. An alternative to these technologies is the use of hybrid bolted/bonded joints combining elements from both technologies. When compared with bolted and bonded technology in composite structures, hybrid joining technology is at an early stage of development, very few journal papers have been written on this topic as of the time of this writing. Previously reported research efforts have been focused on the load sharing and strength improvement. The load sharing has been analyzed experimentally using instrumented bolts and numerically using finite element modelling. The strength analysis has been studied experimentally. The present research was proposed to study hybrid bolted/bonded joints experimentally using a “design of experiments” approach. The aim was to investigate the effect of several factors on the joint strength and load sharing in bolted/bonded hybrid joints. In addition to this, finite element modelling was successfully applied to predict the load sharing and strength, and the results were compared with the experiments with good agreement. The instrumented bolt technique is limited due to the bolt size. To surpass this limitation with the proposed design of experiments, a different approach was needed. Along with the design of experiments and numerical analysis, a novel technique using digital image correlation to measure the shear strains at the adhesive edge was applied to measure the load sharing. Also, the load sharing was computed in all the joint configurations, not only a single sample joint configuration, as was typically reported in other studies. The numerical results in terms load sharing showed a very good agreement with the experiments. On the other hand, using cohesive zone modelling, the strength was predicted with a good agreement compared with the experimental results. Finally, the analysis of variance from the design of experiments quantified the effect of the proposed factors in the joint strength.

Name thesis:degree_name

Doctor of Philosophy (Ph.D.)

Level thesis:degree_level

Doctoral

Discipline thesis:degree_discipline

Engineering, Aerospace

Grantor dc:publisher

Carleton University

Year dc:date.issued

2016

Author dc:creator

• Lopez Cruz, Pedro

Statement dc:rights

• Copyright © 2016 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.

Language dc:language.iso

en

DOI

10.22215/etd/2016-11608

OAI identifier oai:identifier

oai:carleton.scholaris.ca:20.500.14718/38623