By Baker A.A.
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Extra info for Advances In The Bonded Composite Repair Of Metallic Aircraft Structure
4. 5. 1. 2. 3. Birdstrike protection Repairs to EHlOl development airframe full scale fatigue test specimen Acknowledgements References Chapter 35. Case History: Repair Applications On DC-lO/MD-11 Aircraft D. 1. 2. 3. 4. 5. 6. 1. Repair design Repair analysis Repair design validation Nondestructive inspection Current status of DC-lO/MD-l 1 commercial aircraft repairs Chapter 36. Case History: CF-116 Upper Wing Skin Fatigue Enhancement Boron Doubler D. 1. 3. 4. 5. 6. 1. 1. 8. 9. 10. 11. 12. 1. 2.
Also, the behaviour of the adhesive has been modelled as a 3D element, to allow for shear deformation. 016 has been used [l]. The boundary conditions for this model are considered to be fully clamped except for the crack region which is not restrained. The patch above the crack also remains fully constrained. Clearly crack closure will occur at an increasing distance away from the crack tip, however the complexity in introducing such constraints has not been included in this preliminary study. The crack is initially 50mm long with it's centre located within the patch.
5mm [0/90] configuration. Note that the above results are highly dependent on the material loss factors used in the modelling. This loss factor is also dependent on the operating temperature. Therefore in order to design an effective highly damped repair knowledge of the temperature condition when the high SPL are generated is required. 5. Summary A methodology is proposed to enable the design highly-damped patches for cracked structures subject to intense acoustic loading. The highly-damped patch incorporates a boron/epoxy reinforcement/repair, to restore structural strength, as well as a constrained layered damping layer in order to enhance damping and thus reduce dynamic stresses.