By Baker A.A.
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Additional info for Advances In The Bonded Composite Repair Of Metallic Aircraft Structure
12. ,,,~ in un-repaired panel for left and right hand crack tips Chapter 19. Bonded repair of acoustic fatigue cracking 543 12 - . 1 0 h E 8- a" -+-KI right outer zi 6 - A +KI right inner . -. 2- . 1 0 - 0 . . . . . . . . . . Fig. 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.
1. 2. 3. 4. 5. 6. 1. 2. 3. 4. 1. 2. Crack growth results Comparison between test results and analytical predictions Application of composite reinforcement to a full scale wing test Conclusions References Chapter 41. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. H. W. Fiebig Background Repair design Installation development Industrialization and repair Success and failures Other applications Cost savings Additional research Lessons learned Summary References Chapter 42. 1. 2. 3. 4. 5. 6. 7. 8. M. Ratwani, J. Helbling, B.
Although not shown the PSD has been computed for the two different crack lengths for both un-repaired and repaired cases. Chapter 19. 4 10g Y 5- 0 . - . 545 /I, Fig. 17. Stress intensity factor (KIII)rmsfor repaired panel. (Note change in scale compared to Fig. 16). 00000 10000 Fig. 18. PSD of displacement u (a (K&& and running integral of the PSD for repaired panel of crack length 2a = 50 mm. 18 shows the PSD for the case of a repaired panel with 2a = 50mm. 10. 18. g. 5 Hz, indicates that the crack tip is located at or near the nodal line of the corresponding mode shape.
Advances In The Bonded Composite Repair Of Metallic Aircraft Structure by Baker A.A.