After first providing an overview of the status of Australian applications of bonded composite repairs to metallic aircraft structure (mainly based on boron/epoxy composites) the problems in certifying composite repairs to critical cracks in primary metallic structure are discussed. The development of acceptable generic certification procedures is essential if the use of this efficient cost-effective repair technology is to be widely employed in military and civil aircraft. One requirement for certification is the ability to predict the fatigue-crack growth behavior in patched components. An approach to developing this capability is described, based on Rose's model to estimate stress intensity in patched panels. The model is extended to allow for disbonding damage in the patch system. Experimental results are presented to demonstrate the validity of this approach for boron/epoxy-FM73 repairs to aluminum alloy 2024T3.
Bonded Composite Repair of Metallic Aircraft Components: Overview of Australian Activities
1995
14 pages
Report
No indication
English
Aircraft , Composite Materials , Engineering Materials , Aircraft maintenance , Aircraft structures , Boron-epoxy composites , Certifcation , Composite structures , Cracks , Structural analysis , Aluminum alloys , Crack propagation , Debonding (Materials) , Fatigue (Materials) , Panels , Stress intensity factors , Foreign technology
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