The repair was manufactured and the repair demonstrator is ready for testing.
As there are no standard certification methods available for adhesive bonded repairs on aerospace structures alternative certification methods have to be investigated. Finally an approach was found were the initial bond strength was substantiated by testing of traveler patches surrounding the repair patch together with an in-service monitoring of the repair patch behaviour by a dedicated SHM system.
The material properties are needed to analyse and design the repair. The properties were partly obtained by literature review and partly by performing mechanical tests.
As there are many composite materials and repair methods in use a selection of a representative demonstration platform is needed. The repair of a sandwich structure was selected to demonstrate the repair and airworthiness certification of the repair.