By Baker A.A.
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Extra resources for Advances In The Bonded Composite Repair Of Metallic Aircraft Structure
This value was 12 MPa m’’’ compared to a value of 35MPam’’* for the unrepaired panel. For an aircraft component subjected to manoeuvre and gust loads this reduction in stress intensity factor would have been adequate, however crack growth corresponding to a fundamental frequency of 300 Hz will be significant. 7. Highly damped repairs for cracked panels The work carried out in this section is based on [5,15]. It is evident from the previous section that a change in direction is necessary to design an effective long Chapter 19.
Therefore, the actual structural damping is expected to be higher than that predicted in this study, hence, the results from this study are conservative. 125 mm thick aluminium applied to whole panel. 085 Patch dimensions are 75 mm ( L ) x 50 mm ( W ) Patch dimensions are 75mm ( L ) x 100mm (W) Patch dimensions are 75 mm ( L ) x 125mm ( W ) Chapter 19. Bonded repair of 549 acoustic fatigue cracking element. The modal energy, e, is calculated with Eq. 10) [a. 9) is implemented as a post-processing option in the finite element analysis package and was first validated prior to its use.
1. 2. 3. 1. 2. 4. 5. 6. 1. 2. 3. Heating methods Large area repairs in a production environment Conclusions References Chapter 40. 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.