By Baker A.A.

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6. 7. 8. M. Ratwani, J. Helbling, B. M. Ratwani Case History: Bonded Composite Reinforcement of Ship Structures I. 9. J. C. 1. Introduction Acoustic fatigue is due to a very high intensity excitation as a result of pressure waves caused by either engine or aerodynamic effects. 1. In the former region, overall sound pressure levels greater than 170dB have been measured in flight [l]. These high sound pressure levels appear to be a result of an aerodynamic disturbance at the inlet lip [l]. 1. Cracking generally occurs along the longer side of the panel where the bending stresses due to out-of-plane vibrations are a maximum.

5. 6. Load cases Design and stress analysis Static testing and repair validation Certification and implementation to aircraft Conclusions References xxvii 898 899 903 905 906 906 Chapter 34. UK Applications P. 1. 2. 3. 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.

13. Stress intensity factor ( K I ) ~ , in , , ~repaired panel. (Note the change in scale compared to Fig. ) - 35 - 30 25- ga 1 K,, left crack h 20- v . 2 h 15- y 10- 5. . . . . . . . . . Fig. 14. 15, (KrI),s has been substantially reduced. Note that when the right hand crack tip grows out from under the repair, the value for (KII)rmsfor the right hand outer crack tip exceeds the value for the right hand inner crack tip. 11. Also it would be expected that the right hand inner and outer values would converge approaching the right hand boundary.

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