The increasing adoption of composite materials to produce aeronautical structures has opened new horizons and research fields, both for civil and military applications. These materials offer considerable performances, regarding the strength and weight-saving, however, they require complex procedures and technologies for damage identification and repair.
The PATCHBOND II project deals with the certification strategy for bonded repairs. This type of repairs of composite structures offers many advantages compared to conventional bolted repairs, for instance, through bonded repairs, the original strength and stiffness of a structure can be restored. In addition, thin laminates of sandwich structures can be repaired instead of being replaced, something which is hardly possible using a bolted repair.
In a war or crisis situation, a fast bonded repair will be essential for the operability of the platform, however, the new bolt-free approach is also believed to be both relevant and cost-effective in peace time. Nevertheless, for an adhesively bonded repair of a critical/primary composite structure, certification is currently only possible on a case-by-case basis and not on a general basis. This is mainly due to the present adhesive bonding methods applied. Within the PATCHBOND II project, a new technology will be developed to create a damage tolerant repair method, also employing in-service structural health monitoring as part of a certified repair approach.
- The target of the project is to set the guidelines and provide analyses of bonded repairs to confirm the damage tolerant design philosophy. This includes an initial assessment of the criticality of a damaged composite structure, along with a no growth/slow growth design approach in view of new certifiable large composite repairs, involving bigger bonded repair size limits compared to current certification policy.
- Technology for in-service health monitoring of the repair will also be developed.
The PATCHBOND II project is a follow-up activity of the PATCHBOND project and it is also using the “crack stopper” technology developed within the previous EU BOPACS project.
The project involves several partners from Finland, Germany, Norway, The Netherland, and the Czech Republic, among them, the Aviation division of Czech Aerospace Research Centre is involved with doctors Roman Růžek, Radek Doubrava and Martin Kadlec. Their contribution is devoted to methodology and experimental certification of the structures, modelling of the delamination and debonding propagation using the finite element method and a structural health monitoring.
Impact simulation on sandwich panel
Patria, VTT,.Tampere University (TAU), FINLAND
Politecnico di Milano (POLIMI), ITALY
Airbus DS, WIWeB, University of Stuttgart (USTUTT), GERMANY
Norwegian Defence Research Establishment (FFI), Norwegian Defence Material Agency (NDMA), Light Structures, FiReCo, NORWAY
NLR, KVE, Fokker Services, THE NETHERLANDS
VZLU, CZECH REPUBLIC