<abstract xmlns="http://www.w3.org/1999/xhtml">The paper proposes a method of calculating the maximum displacement in the aircraft metal structure repaired by CPBR (bonded composite patch repair).The calculations were made based on specimens. The specimens were prepared according to the current requirements used in aviation. The 2024-T3 alloy metal sheet was a structure. To repair the structure used the boron-epoxy composite patch in prepreg technology was used.The metal structure was modeled as an isotropic elastic body. The metal structure coated with the composite patch was modeled as an orthotropic structure. Based on this, the stress was determined in the metal structure.The size opening displacement in the metal structure was determined based on the model of linear elastic fracture mechanics for the plane stress state.The calculation results were verified by measuring the displacement in laboratory conditions.The laboratory tests made it possible to demonstrate the accuracy of the proposed approach.</abstract>

The paper proposes a method of calculating the maximum displacement in the aircraft metal structure repaired by CPBR (bonded composite patch repair).The calculations were made based on specimens. The specimens were prepared according to the current requirements used in aviation. The 2024-T3 alloy metal sheet was a structure. To repair the structure used the boron-epoxy composite patch in prepreg technology was used.The metal structure was modeled as an isotropic elastic body. The metal structure coated with the composite patch was modeled as an orthotropic structure. Based on this, the stress was determined in the metal structure.The size opening displacement in the metal structure was determined based on the model of linear elastic fracture mechanics for the plane stress state.The calculation results were verified by measuring the displacement in laboratory conditions.The laboratory tests made it possible to demonstrate the accuracy of the proposed approach.

Approach to Critical Crack Opening Displacement Modeling of Damage in Metal Sheets after Composite Patch Bonded Repair

Fatigue of Aircraft Structures

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

The paper proposes a method of calculating the maximum displacement in the aircraft metal structure repaired by CPBR (bonded composite patch repair).The...

Approach to Critical Crack Opening Displacement Modeling of Damage in Metal Sheets after Composite Patch Bonded Repair

Online veröffentlicht: 22. Juli 2017

Seitenbereich: 104 - 110

DOI: https://doi.org/10.1515/fas-2016-0009

Schlüsselwörter
composites, aerospace, composite patch bonded repair

© 2016 Michał Sałacinski et al., published by De Gruyter Open

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Approach to Critical Crack Opening Displacement Modeling of Damage in Metal Sheets after Composite Patch Bonded Repair

Online veröffentlicht: 22. Juli 2017

Seitenbereich: 104 - 110

DOI: https://doi.org/10.1515/fas-2016-0009

Schlüsselwörtercomposites, aerospace, composite patch bonded repair

© 2016 Michał Sałacinski et al., published by De Gruyter Open

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Schlüsselwörter
composites, aerospace, composite patch bonded repair